STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility for a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station are (left to right) Mission Specialists Valery Tokarev, Julie Payette (holding a lithium hydroxide canister) and Dan Barry. Other crew members at KSC for the IVT are Commander Kent Rominger, Pilot Rick Husband and Mission Specialists Ellen Ochoa and Tamara Jernigan. Mission STS-96 carries the SPACEHAB Logistics Double Module, which has equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility, the STS-96 crew looks over equipment during a payload Interface Verification Test for the upcoming mission to the International Space Station. From left are Commander Kent Rominger, Mission Specialists Tamara Jernigan and Valery Tokarev of Russia, Pilot Rick Husband, and Mission Specialists Ellen Ochoa and Julie Payette (backs to the camera). They are listening to Chris Jaskolka of Boeing talk about the equipment. Mission STS-96 carries the SPACEHAB Logistics Double Module, which will have equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. It carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m. EDT.

A Shuttle Derived Vehicle launch system

NASA Technical Reports Server (NTRS)

Tewell, J. R.; Buell, D. N.; Ewing, E. S.

1982-01-01

This paper describes a Shuttle Derived Vehicle (SDV) launch system presently being studied for the NASA by Martin Marietta Aerospace which capitalizes on existing Shuttle hardware elements to provide increased accommodations for payload weight, payload volume, or both. The SDV configuration utilizes the existing solid rocket boosters, external tank and the Space Shuttle main engines but replaces the manned orbiter with an unmanned, remotely controlled cargo carrier. This cargo carrier substitution more than doubles the performance capability of the orbiter system and is realistically achievable for minimal cost. The advantages of the SDV are presented in terms of performance and economics. Based on these considerations, it is concluded that an unmanned SDV offers a most attractive complement to the present Space Transportation System.

EXPRESS Rack: The Extension of International Space Station Resources for Multi-Discipline Subrack Payloads

NASA Technical Reports Server (NTRS)

Sledd, Annette; Danford, Mike; Key, Brian

2002-01-01

The EXpedite the PRocessing of Experiments to Space Station or EXPRESS Rack System was developed to provide Space Station accommodations for subrack payloads. The EXPRESS Rack accepts Space Shuttle middeck locker type payloads and International Subrack Interface Standard (ISIS) Drawer payloads, allowing previously flown payloads an opportunity to transition to the International Space Station. The EXPRESS Rack provides power, data command and control, video, water cooling, air cooling, vacuum exhaust, and Nitrogen supply to payloads. The EXPRESS Rack system also includes transportation racks to transport payloads to and from the Space Station, Suitcase Simulators to allow a payload developer to verify data interfaces at the development site, Functional Checkout Units to allow payload checkout at KSC prior to launch, and trainer racks for the astronauts to learn how to operate the EXPRESS Racks prior to flight. Standard hardware and software interfaces provided by the EXPRESS Rack simplify the integration processes, and facilitate simpler ISS payload development. Whereas most ISS Payload facilities are designed to accommodate one specific type of science, the EXPRESS Rack is designed to accommodate multi-discipline research within the same rack allowing for the independent operation of each subrack payload. On-orbit operations began with the EXPRESS Rack Project on April 24, 2001, with one rack operating continuously to support long-running payloads. The other on-orbit EXPRESS Racks operate based on payload need and resource availability. Sustaining Engineering and Logistics and Maintenance functions are in place to maintain operations and to provide software upgrades.

The Extension of ISS Resources for Multi-Discipline Subrack Payloads

NASA Technical Reports Server (NTRS)

Sledd, Annette M.; Gilbert, Paul A. (Technical Monitor)

2002-01-01

The EXpedite the processing of Experiments to Space Station or EXPRESS Rack System was developed to provide Space Station accommodations for subrack payloads. The EXPRESS Rack accepts Space Shuttle middeck locker type payloads and International Subrack Interface Standard (ISIS) Drawer payloads, allowing previously flown payloads an opportunity to transition to the International Space Station. The EXPRESS Rack provides power, data command and control, video, water cooling, air cooling, vacuum exhaust, and Nitrogen supply to payloads. The EXPRESS Rack system also includes transportation racks to transport payloads to and from the Space Station, Suitcase Simulators to allow a payload developer to verify data interfaces at the development site, Functional Checkout Units to allow payload checkout at KSC prior to launch, and trainer racks for the astronauts to learn how to operate the EXPRESS Racks prior to flight. Standard hardware and software interfaces provided by the EXPRESS Rack simplify the integration processes, and facilitate simpler ISS payload development. Whereas most ISS Payload facilities are designed to accommodate one specific type of science, the EXPRESS Rack is designed to accommodate multi-discipline research within the same rack allowing for the independent operation of each subrack payload. On-orbit operations began with the EXPRESS Rack Project on April 24, 2001, with one rack operating continuously to support long-running payloads. The other on-orbit EXPRESS Racks operate based on payload need and resource availability. Sustaining Engineering and Logistics and Maintenance functions are in place to maintain operations and to provide software upgrades.

Payload transportation system study

NASA Technical Reports Server (NTRS)

1976-01-01

A standard size set of shuttle payload transportation equipment was defined that will substantially reduce the cost of payload transportation and accommodate a wide range of payloads with minimum impact on payload design. The system was designed to accommodate payload shipments between the level 4 payload integration sites and the launch site during the calendar years 1979-1982. In addition to defining transportation multi-use mission support equipment (T-MMSE) the mode of travel, prime movers, and ancillary equipment required in the transportation process were also considered. Consistent with the STS goals of low cost and the use of standardized interfaces, the transportation system was designed to commercial grade standards and uses the payload flight mounting interfaces for transportation. The technical, cost, and programmatic data required to permit selection of a baseline system of MMSE for intersite movement of shuttle payloads were developed.

ISS Payload Operations: The Need for and Benefit of Responsive Planning

NASA Technical Reports Server (NTRS)

Nahay, Ed; Boster, Mandee

2000-01-01

International Space Station (ISS) payload operations are controlled through implementation of a payload operations plan. This plan, which represents the defined approach to payload operations in general, can vary in terms of level of definition. The detailed plan provides the specific sequence and timing of each component of a payload's operations. Such an approach to planning was implemented in the Spacelab program. The responsive plan provides a flexible approach to payload operations through generalization. A responsive approach to planning was implemented in the NASA/Mir Phase 1 program, and was identified as a need during the Skylab program. The current approach to ISS payload operations planning and control tends toward detailed planning, rather than responsive planning. The use of detailed plans provides for the efficient use of limited resources onboard the ISS. It restricts flexibility in payload operations, which is inconsistent with the dynamic nature of the ISS science program, and it restricts crew desires for flexibility and autonomy. Also, detailed planning is manpower intensive. The development and implementation of a responsive plan provides for a more dynamic, more accommodating, and less manpower intensive approach to planning. The science program becomes more dynamic and responsive as the plan provides flexibility to accommodate real-time science accomplishments. Communications limitations and the crew desire for flexibility and autonomy in plan implementation are readily accommodated with responsive planning. Manpower efficiencies are accomplished through a reduction in requirements collection and coordination, plan development, and maintenance. Through examples and assessments, this paper identifies the need to transition from detailed to responsive plans for ISS payload operations. Examples depict specific characteristics of the plans. Assessments identify the following: the means by which responsive plans accommodate the dynamic nature of science programs and the crew desire for flexibility; the means by which responsive plans readily accommodate ISS communications constraints; manpower efficiencies to be achieved through use of responsive plans; and the implications of responsive planning relative to resource utilization efficiency.

Mission Peculiar Equipment (MPE) For Spacelab Mission 1 Payload

NASA Astrophysics Data System (ADS)

Sims, John H.; Dodeck, Hauke

1982-02-01

Spacelab interfaces and services for payloads are advertised in the Spacelab Payload Accommodations Handbook (SPAH). These accommodations are available to the total payload and must be managed and apportioned by a payload integrator. A major part of the integration task is satisfying all instruments/facilities servicing requirements which vary with each item of payload equipment and, when totalled, sometimes exceed the capabilities as defined in SPAH. Such a determination is an output of the integrated payload design and integration effort which consists of analytical assessments based on individual payload equipment requirements inputs, STS and Spacelab available accommodations and constraints, and programmatic considerations. This systems engineering activity spans all engineering disciplines, assesses the module and pallet layouts and simultaneous operation of instrument/facility combinations, and requires a detailed knowledge of the Spacelab design. Introduction of a broad range of payload integrator-provided Mission Peculiar Equipment (MPE) into the Spacelab Mission 1 payload complement was necessary to be added to the Spacelab provisions in order to satisfy the interface and service requirements for each payload developer. This paper provides insight into various aspects of this MPE; including why it is needed, driving design considerations, design and development problems, and conclusions and recommendations for the future. MPE identified for Spacelab Mission 1 begins an inventory that will continue to expand as other mission requirements are identified and the Spacelab flight frequency increases.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility, the STS-96 crew looks at equipment as part of a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station . From left are Mission Specialist Ellen Ochoa (behind the opened storage cover ), Commander Kent Rominger, Pilot Rick Husband (holding a lithium hydroxide canister) and Mission Specialists Dan Barry, Valery Tokarev of Russia and Julie Payette. In the background is TTI interpreter Valentina Maydell. The other crew member at KSC for the IVT is Mission Specialist Tamara Jernigan. Mission STS-96 carries the SPACEHAB Logistics Double Module, which has equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility, STS-96 crew members look over equipment during a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station. From left are Khristal Parker, with Boeing; Mission Specialist Dan Barry, Pilot Rick Husband, Mission Specialist Tamara Jernigan, and at the far right, Mission Specialist Julie Payette. An unidentified worker is in the background. Also at KSC for the IVT are Commander Kent Rominger and Mission Specialists Ellen Ochoa and Valery Tokarev of Russia. Mission STS-96 carries the SPACEHAB Logistics Double Module, which will have equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. It carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility, (left to right) STS-96 Pilot Rick Husband and Mission Specialists Julie Payette and Ellen Ochoa work the straps on the Sequential Shunt Unit (SSU) in front of them. The STS-96 crew is at KSC for a payload Interface Verification Test (IVT) for its upcoming mission to the International Space Station . Other crew members at KSC for the IVT are Commander Kent Rominger and Mission Specialists Tamara Jernigan, Dan Barry and Valery Tokarev of Russia. The SSU is part of the cargo on Mission STS-96, which carries the SPACEHAB Logistics Double Module, with equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility, STS-96 Mission Specialist Valery Tokarev of Russia (left) and Commander Kent Rominger (second from right) listen to Lynn Ashby (far right), with JSC, talking about the SPACEHAB equipment in front of them during a payload Interface Verification Test (IVT). In the background behind Tokarev is TTI interpreter Valentina Maydell. Other STS-96 crew members at KSC for the IVT are Pilot Rick Husband and Mission Specialists Dan Barry, Ellen Ochoa, Tamara Jernigan and Julie Payette. Mission STS-96 carries the SPACEHAB Logistics Double Module, which will have equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. It carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

During a payload Interface Verification Test (IVT) in the SPACEHAB Facility, STS-96 Mission Specialist Valery Tokarev of Russia (second from left) and Commander Kent Rominger learn about the Sequential Shunt Unit (SSU) in front of them from Lynn Ashby (far right), with Johnson Space Center. At the far left looking on is TTI interpreter Valentina Maydell. Other crew members at KSC for the IVT are Pilot Rick Husband and Mission Specialists Ellen Ochoa, Tamara Jernigan, Dan Barry and Julie Payette. The SSU is part of the cargo on Mission STS-96, which carries the SPACEHAB Logistics Double Module, with equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility, STS-96 Mission Specialist Valery Tokarev (in foreground) of the Russian Space Agency closes a container, part of the equipment that will be in the SPACEHAB module on mission STS-96. Behind Tokarev are Pilot Rick Husband (left) and Mission Specialist Dan Barry (right). Other crew members at KSC for a payload Interface Verification Test for the upcoming mission to the International Space Station are Commander Kent Rominger and Mission Specialists Ellen Ochoa, Tamara Jernigan and Julie Payette. Mission STS-96 carries the SPACEHAB Logistics Double Module, which has equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

During a payload Interface Verification Test (IVT) in the SPACEHAB Facility, STS-96 Mission Specialist Tamara Jernigan checks over instructions while Mission Specialist Dan Barry looks up from the Sequential Shunt Unit (SSU) in front of him to other equipment Lynn Ashby (right), with Johnson Space Center, is pointing at. Other crew members at KSC for the IVT are Commander Kent Rominger, Pilot Rick Husband, and Mission Specialists Ellen Ochoa, Julie Payette and Valery Tokarev of Russia. The SSU is part of the cargo on Mission STS-96, which carries the SPACEHAB Logistics Double Module, with equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

During a payload Interface Verification Test (IVT) in the SPACEHAB Facility, STS-96 Pilot Rick Husband and Mission Specialist Ellen Ochoa (on the left) and Mission Specialist Julie Payette (on the far right) listen to Khristal Parker (second from right), with Boeing, explain about the equipment in front of them. Other crew members at KSC for the IVT are Commander Kent Rominger and Mission Specialists Tamara Jernigan, Dan Barry and Valery Tokarev of Russia. The SSU is part of the cargo on Mission STS-96, which carries the SPACEHAB Logistics Double Module, with equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility for a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station are (kneeling) STS-96 Mission Specialists Julie Payette and Ellen Ochoa, Pilot Rick Husband, and (standing at right) Mission Specialist Dan Barry. At the left is James Behling, with Boeing, explaining some of the equipment that will be on board STS-96. Other STS-96 crew members at KSC for the IVT are Commander Kent Rominger and Mission Specialists Tamara Jernigan and Valery Tokarev of Russia. Mission STS-96 carries the SPACEHAB Logistics Double Module, which will have equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. It carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

The LEAN Payload Integration Process

NASA Technical Reports Server (NTRS)

Jordan, Lee P.; Young, Yancy; Rice, Amanda

2011-01-01

It is recognized that payload development and integration with the International Space Station (ISS) can be complex. This streamlined integration approach is a first step toward simplifying payload integration; making it easier to fly payloads on ISS, thereby increasing feasibility and interest for more research and commercial organizations to sponsor ISS payloads and take advantage of the ISS as a National Laboratory asset. The streamlined integration approach was addressed from the perspective of highly likely initial payload types to evolve from the National Lab Pathfinder program. Payloads to be accommodated by the Expedite the Processing of Experiments for Space Station (EXPRESS) Racks and Microgravity Sciences Glovebox (MSG) pressurized facilities have been addressed. It is hoped that the streamlined principles applied to these types of payloads will be analyzed and implemented in the future for other host facilities as well as unpressurized payloads to be accommodated by the EXPRESS Logistics Carrier (ELC). Further, a payload does not have to be classified as a National Lab payload in order to be processed according to the lean payload integration process; any payload that meets certain criteria can follow the lean payload integration process.

Space Station Freedom Central Thermal Control System Evolution

NASA Technical Reports Server (NTRS)

Bullock, Richard; Olsson, Eric

1990-01-01

The objective of the evolution study is to review the proposed growth scenarios for Space Station Freedom and identify the major CTCS hardware scars and software hooks required to facilitate planned growth and technology obsolescence. The Station's two leading evolutionary configurations are: (1) the Research and Development node, where the fundamental mission is scientific research and commercial endeavors, and (2) the Transportation node, where the emphasis is on supporting Lunar and Mars human exploration. These two nodes evolve from the from the assembly complete configuration by the addition of manned modules, pocket labs, resource nodes, attached payloads, customer servicing facility, and an upper and lower keel and boom truss structure. In the case of the R & D node, the role of the dual keel will be to support external payloads for scientific research. In the case of the Transportation node, the keel will support the Lunar (LTV) and Mars (MTV) transportation vehicle service facilities In addition to external payloads. The transverse boom is extended outboard of the alpha gimbal to accommodate the new solar dynamic arrays for power generation, which will supplement the photovoltaic system. The design, development, deployment, and operation of SSF will take place over a 30 year time period and new Innovations and maturation in technologies can be expected. Evolutionary planning must include the obsolescence and insertion of the new technologies over the life of the program, and the technology growth issues must be addressed in parallel with the development of the baseline thermal control system. Technologies that mature and are available within the next 10 years are best suited for evolutionary consideration as the growth phase begins in the year 2000. To increase TCS capability to accommodate growth using baseline technology would require some penalty in mass, volume, EVA time, manifesting, and operational support. To be cost effective the capabilities of the heat acquisition, transport, and rejection subsystems must be increased.

Payload Documentation Enhancement Project

NASA Technical Reports Server (NTRS)

Brown, Betty G.

1999-01-01

In late 1998, the Space Shuttle Program recognized a need to revitalize its payload accommodations documentation. As a result a payload documentation enhancement project was initiated to review and update payload documentation and improve the accessibility to that documentation by the Space Shuttle user community.

Acceleration ground test program to verify GAS payload No. 559 structure/support avionics and experiment structural integrity

NASA Technical Reports Server (NTRS)

Cassanto, John M.; Cassanto, Valerie A.

1988-01-01

Acceleration ground tests were conducted on the Get Away Special (GAS) payload 559 to verify the structural integrity of the structure/support avionics and two of the planned three flight experiments. The ITA (Integrated Test Area) Standardized Experiment Module (ISEM) structure was modified to accommodate the experiments for payload 559. The ISEM avionics consisted of a heavy duty sliver zinc power supply, three orthogonal-mounted low range microgravity accelerometers, a tri-axis high range accelerometer, a solid state recorder/programmer sequencer, and pressure and temperature sensors. The tests were conducted using the Gravitational Plant Physiology Laboratory Centrifuge of the University City Science Center in Philadelphia, PA. The launch-powered flight steady state acceleration profile of the shuttle was simulated from lift-off through jettison of the External Tank (3.0 g's). Additional tests were conducted at twice the nominal powered flight acceleration levels (6 g's) and an over-test condition of four times the powered flight loads to 12.6 g's. The present test program has demonstrated the value of conducting ground tests to verify GAS payload experiment integrity and operation before flying on the shuttle.

Design of the deformable mirror demonstration CubeSat (DeMi)

NASA Astrophysics Data System (ADS)

Douglas, Ewan S.; Allan, Gregory; Barnes, Derek; Figura, Joseph S.; Haughwout, Christian A.; Gubner, Jennifer N.; Knoedler, Alex A.; LeClair, Sarah; Murphy, Thomas J.; Skouloudis, Nikolaos; Merck, John; Opperman, Roedolph A.; Cahoy, Kerri L.

2017-09-01

The Deformable Mirror Demonstration Mission (DeMi) was recently selected by DARPA to demonstrate in-space operation of a wavefront sensor and Microelectromechanical system (MEMS) deformable mirror (DM) payload on a 6U CubeSat. Space telescopes designed to make high-contrast observations using internal coronagraphs for direct characterization of exoplanets require the use of high-actuator density deformable mirrors. These DMs can correct image plane aberrations and speckles caused by imperfections, thermal distortions, and diffraction in the telescope and optics that would otherwise corrupt the wavefront and allow leaking starlight to contaminate coronagraphic images. DeMi is provide on-orbit demonstration and performance characterization of a MEMS deformable mirror and closed loop wavefront sensing. The DeMi payload has two operational modes, one mode that images an internal light source and another mode which uses an external aperture to images stars. Both the internal and external modes include image plane and pupil plane wavefront sensing. The objectives of the internal measurement of the 140-actuator MEMS DM actuator displacement are characterization of the mirror performance and demonstration of closed-loop correction of aberrations in the optical path. Using the external aperture to observe stars of magnitude 2 or brighter, assuming 3-axis stability with less than 0.1 degree of attitude knowledge and jitter below 10 arcsec RMSE, per observation, DeMi will also demonstrate closed loop wavefront control on an astrophysical target. We present an updated payload design, results from simulations and laboratory optical prototyping, as well as present our design for accommodating high-voltage multichannel drive electronics for the DM on a CubeSat.

Space Station program status and research capabilities

NASA Technical Reports Server (NTRS)

Holt, Alan C.

1995-01-01

Space Station will be a permanent orbiting laboratory in space which will provide researchers with unprecedented opportunities for access to the space environment. Space Station is designed to provide essential resources of volume, crew, power, data handling and communications to accommodate experiments for long-duration studies in technology, materials and the life sciences. Materials and coatings for exposure research will be supported by Space Station, providing new knowledge for applications in Earthbased technology and future space missions. Space Station has been redesigned at the direction of the President. The redesign was performed to significantly reduce development, operations and utilization costs while achieving many of the original goals for long duration scientific research. An overview of the Space Station Program and capabilities for research following the redesign is presented below. Accommodations for pressurized and external payloads are described.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility, (from left) STS-96 Mission Specialist Julie Payette, Pilot Rick Husband and Mission Specialist Ellen Ochoa learn about the Sequential Shunt Unit (SSU) in front of them from Lynn Ashby (far right), with Johnson Space Center. The STS-96 crew is at KSC for a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station . Other crew members at KSC for the IVT are Commander Kent Rominger and Mission Specialists Tamara Jernigan, Dan Barry and Valery Tokarev of Russia. The SSU is part of the cargo on Mission STS-96, which carries the SPACEHAB Logistics Double Module, with equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

Life science payloads planning study. [for space shuttle orbiters and spacelab

NASA Technical Reports Server (NTRS)

Nelson, W. G.; Wells, G. W.

1977-01-01

Preferred approaches and procedures were defined for integrating the space shuttle life sciences payload from experiment solicitation through final data dissemination at mission completion. The payloads operations plan was refined and expended to include current information. The NASA-JSC facility accommodations were assessed, and modifications recommended to improve payload processing capability. Standard format worksheets were developed to permit rapid location of experiment requirements and a Spacelab mission handbook was developed to assist potential life sciences investigators at academic, industrial, health research, and NASA centers. Practical, cost effective methods were determined for accommodating various categories of live specimens during all mission phases.

Space Station needs, attributes and architectural options, volume 2, book 2, part 4: International reports

NASA Technical Reports Server (NTRS)

1983-01-01

The capabilities of the European Space Agency's SPAS and EURECA platforms for reference payload accommodation are considered. The instrument pointing subsystem, the position and hold mount, and the antenna pointing mechanism developed by Dornier are described. Relevant payloads for the space station are summarized and space station accommodation aspects are discussed.

Development of an Environmental Monitoring Package for the International Space Station

NASA Technical Reports Server (NTRS)

Carruth, Ralph M., Jr.; Clifton, Kenneth S.; Vanhooser, Michael T.

1999-01-01

The first elements of the International Space Station (ISS) will soon be launched into space and over the next few years ISS will be assembled on orbit into its final configuration. Experiments will be performed on a continuous basis both inside and outside the station. External experiments will be mounted on attached payload locations specifically designed to accommodate experiments and provide data and power from ISS. From the beginning of the space station program it has been recognized that external experiments will require knowledge of the external environment because it can affect the science being performed and may impact lifetime and operations of the experiments. Recently an effort was initiated to design and develop an Environment Monitoring Package (EMP) was started. This paper describes the derivation of the requirements for the EMP package, the type of measurements that the EMP will make and types of instruments which will be employed to make these measurements.

KSC-04PD-1133

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Technicians in the Orbiter Processing Facility attach a crane to Discoverys airlock before lifting it for installation. The airlock is located inside the orbiters payload bay and is sized to accommodate two fully suited flight crew members simultaneously. Support functions include airlock depressurization and repressurization, extravehicular activity equipment recharge, liquid-cooled garment water cooling, EVA equipment checkout, and communications. Discovery is designated as the Return to Flight vehicle for mission STS-114, no earlier than March 2005. STS-114 mission is Logistics Flight 1, which is scheduled to deliver supplies and equipment plus the external stowage platform to the International Space Station.

STS payload data collection and accommodations analysis study. Volume 2: Payload data collection

NASA Technical Reports Server (NTRS)

1978-01-01

A format developed for Space Transportation System payload data collection and a process for collecting the data are described along with payload volumes and a data deck to be used as input for the Marshall Interactive Planning System. Summary matrices of the data generated are included.

KSC-99pp0208

NASA Image and Video Library

1999-02-11

KENNEDY SPACE CENTER, FLA. -- In the SPACEHAB Facility for a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station are (left to right) Mission Specialists Valery Tokarev, Julie Payette (holding a lithium hydroxide canister) and Dan Barry. Other crew members at KSC for the IVT are Commander Kent Rominger, Pilot Rick Husband and Mission Specialists Ellen Ochoa and Tamara Jernigan. Mission STS-96 carries the SPACEHAB Logistics Double Module, which has equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m

14 CFR 1214.812 - Payload specialists.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 5 2010-01-01 2010-01-01 false Payload specialists. 1214.812 Section 1214.812 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION SPACE FLIGHT Reimbursement for...-furnished mission specialists. Accommodations for, and mission-independent training of, any payload...

14 CFR 1214.812 - Payload specialists.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 5 2012-01-01 2012-01-01 false Payload specialists. 1214.812 Section 1214.812 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION SPACE FLIGHT Reimbursement for...-furnished mission specialists. Accommodations for, and mission-independent training of, any payload...

14 CFR 1214.812 - Payload specialists.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 5 2013-01-01 2013-01-01 false Payload specialists. 1214.812 Section 1214.812 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION SPACE FLIGHT Reimbursement for...-furnished mission specialists. Accommodations for, and mission-independent training of, any payload...

14 CFR 1214.812 - Payload specialists.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 5 2011-01-01 2010-01-01 true Payload specialists. 1214.812 Section 1214.812 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION SPACE FLIGHT Reimbursement for...-furnished mission specialists. Accommodations for, and mission-independent training of, any payload...

14 CFR § 1214.812 - Payload specialists.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 5 2014-01-01 2014-01-01 false Payload specialists. § 1214.812 Section § 1214.812 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION SPACE FLIGHT Reimbursement...-furnished mission specialists. Accommodations for, and mission-independent training of, any payload...

Science and Applications Space Platform (SASP) End-to-End Data System Study

NASA Technical Reports Server (NTRS)

Crawford, P. R.; Kasulka, L. H.

1981-01-01

The capability of present technology and the Tracking and Data Relay Satellite System (TDRSS) to accommodate Science and Applications Space Platforms (SASP) payload user's requirements, maximum service to the user through optimization of the SASP Onboard Command and Data Management System, and the ability and availability of new technology to accommodate the evolution of SASP payloads were assessed. Key technology items identified to accommodate payloads on a SASP were onboard storage devices, multiplexers, and onboard data processors. The primary driver is the limited access to TDRSS for single access channels due to sharing with all the low Earth orbit spacecraft plus shuttle. Advantages of onboard data processing include long term storage of processed data until TRDSS is accessible, thus reducing the loss of data, eliminating large data processing tasks at the ground stations, and providing a more timely access to the data.

Stacked Buoyant Payload Launcher

DTIC Science & Technology

2013-05-14

unit, the signal ejector , or through the escape hatch lockout trunk. Each of these deployment methods has disadvantages. [0005] Torpedo tubes are... ejector tube can accommodate payloads approximately three inches in diameter. Thus, payload size is extremely limited. The escape hatch lockout trunk...signal ejector tube. Additionally, the system 10 can launch multiple payloads during one launch sequence, or can provide multiple launches at

Shuttle payload interface verification equipment study. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1976-01-01

A preliminary design analysis of a stand alone payload integration device (IVE) is provided that is capable of verifying payload compatibility in form, fit and function with the shuttle orbiter prior to on-line payload/orbiter operations. The IVE is a high fidelity replica of the orbiter payload accommodations capable of supporting payload functional checkout and mission simulation. A top level payload integration analysis developed detailed functional flow block diagrams of the payload integration process for the broad spectrum of P/L's and identified degree of orbiter data required by the payload user and potential applications of the IVE.

A simultaneous spin/eject mechanism for aerospace payloads

NASA Technical Reports Server (NTRS)

Palmer, G. D.; Banks, T. N.

1976-01-01

A simultaneous spin/eject mechanism was developed for aerospace applications requiring a compact, passive device which would accommodate payload support and controlled-release functions, and which would provide a highly accurate spin-ejection motion to the payload. The mechanism satisfied the requirements and is adaptable to other deployment applications.

Space science/space station attached payload pointing accommodation study: Technology assessment white paper

NASA Technical Reports Server (NTRS)

Lin, Richard Y.; Mann, Kenneth E.; Laskin, Robert A.; Sirlin, Samuel W.

1987-01-01

Technology assessment is performed for pointing systems that accommodate payloads of large mass and large dimensions. Related technology areas are also examined. These related areas include active thermal lines or power cables across gimbals, new materials for increased passive damping, tethered pointing, and inertially reacting pointing systems. Conclusions, issues and concerns, and recommendations regarding the status and development of large pointing systems for space applications are made based on the performed assessments.

Spacelab payload accommodation handbook. Appendix B: Structure interface definition module

NASA Technical Reports Server (NTRS)

1978-01-01

The mechanical interfaces between Spacelab and its payload are defined. The envelopes available for mounting payload hardware are specified together with the standard structural attachment interfaces. Overall load capabilities and the local load capabilities for individual attachment interfaces are defined for the standard mounting locations. The mechanical environment is defined and the mechanical interfaces between the payload and the EPDS, CDMS and ECS are included.

KSC-99pd0209

NASA Image and Video Library

1999-02-11

KENNEDY SPACE CENTER, FLA. -- In the SPACEHAB Facility, the STS-96 crew looks at equipment as part of a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station . From left are Mission Specialist Ellen Ochoa (behind the opened storage cover ), Commander Kent Rominger, Pilot Rick Husband (holding a lithium hydroxide canister) and Mission Specialists Dan Barry, Valery Tokarev of Russia and Julie Payette. In the background is TTI interpreter Valentina Maydell. The other crew member at KSC for the IVT is Mission Specialist Tamara Jernigan. Mission STS-96 carries the SPACEHAB Logistics Double Module, which has equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m

KSC-99pp0201

NASA Image and Video Library

1999-02-11

KENNEDY SPACE CENTER, FLA. -- In the SPACEHAB Facility, STS-96 Mission Specialist Valery Tokarev of Russia (left) and Commander Kent Rominger (second from right) listen to Lynn Ashby (far right), with JSC, talking about the SPACEHAB equipment in front of them during a payload Interface Verification Test (IVT). In the background behind Tokarev is TTI interpreter Valentina Maydell. Other STS-96 crew members at KSC for the IVT are Pilot Rick Husband and Mission Specialists Dan Barry, Ellen Ochoa, Tamara Jernigan and Julie Payette. Mission STS-96 carries the SPACEHAB Logistics Double Module, which will have equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. It carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m

KSC-99pd0214

NASA Image and Video Library

1999-02-11

KENNEDY SPACE CENTER, FLA. -- During a payload Interface Verification Test (IVT) in the SPACEHAB Facility, STS-96 Mission Specialist Valery Tokarev of Russia (second from left) and Commander Kent Rominger learn about the Sequential Shunt Unit (SSU) in front of them from Lynn Ashby (far right), with Johnson Space Center. At the far left looking on is TTI interpreter Valentina Maydell. Other crew members at KSC for the IVT are Pilot Rick Husband and Mission Specialists Ellen Ochoa, Tamara Jernigan, Dan Barry and Julie Payette. The SSU is part of the cargo on Mission STS-96, which carries the SPACEHAB Logistics Double Module, with equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m

Payload IVA training and simulation

NASA Technical Reports Server (NTRS)

Monsees, J. H.

1982-01-01

The development of a training program for the intravehicular operation of space shuttle payloads is discussed. The priorities for the program are compliance with established training standards, and accommodating changes. Simulation devices are also reviewed.

Planning for Space Station Freedom laboratory payload integration

NASA Technical Reports Server (NTRS)

Willenberg, Harvey J.; Torre, Larry P.

1989-01-01

Space Station Freedom is being developed to support extensive missions involving microgravity research and applications. Requirements for on-orbit payload integration and the simultaneous payload integration of multiple mission increments will provide the stimulus to develop new streamlined integration procedures in order to take advantage of the increased capabilities offered by Freedom. The United States Laboratory and its user accommodations are described. The process of integrating users' experiments and equipment into the United States Laboratory and the Pressurized Logistics Modules is described. This process includes the strategic and tactical phases of Space Station utilization planning. The support that the Work Package 01 Utilization office will provide to the users and hardware developers, in the form of Experiment Integration Engineers, early accommodation assessments, and physical integration of experiment equipment, is described. Plans for integrated payload analytical integration are also described.

Space processing applications payload equipment study. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

Hammel, R. L.

1974-01-01

A study was conducted to derive and collect payload information on the anticipated space processing payload requirements for the Spacelab and space shuttle orbiter planning activities. The six objectives generated by the study are defined. Concepts and requirements for space processing payloads to accommodate the performance of the shuttle-supported research phase are analyzed. Diagrams and tables of data are developed to show the experiments involved, the power requirements, and the payloads for shared missions.

Integration Process for Payloads in the Fluids and Combustion Facility

NASA Technical Reports Server (NTRS)

Free, James M.; Nall, Marsha M.

2001-01-01

The Fluids and Combustion Facility (FCF) is an ISS research facility located in the United States Laboratory (US Lab), Destiny. The FCF is a multi-discipline facility that performs microgravity research primarily in fluids physics science and combustion science. This facility remains on-orbit and provides accommodations to multi-user and Principal investigator (PI) unique hardware. The FCF is designed to accommodate 15 PI's per year. In order to allow for this number of payloads per year, the FCF has developed an end-to-end analytical and physical integration process. The process includes provision of integration tools, products and interface management throughout the life of the payload. The payload is provided with a single point of contact from the facility and works with that interface from PI selection through post flight processing. The process utilizes electronic tools for creation of interface documents/agreements, storage of payload data and rollup for facility submittals to ISS. Additionally, the process provides integration to and testing with flight-like simulators prior to payload delivery to KSC. These simulators allow the payload to test in the flight configuration and perform final facility interface and science verifications. The process also provides for support to the payload from the FCF through the Payload Safety Review Panel (PSRP). Finally, the process includes support in the development of operational products and the operation of the payload on-orbit.

Low energy stage study. Volume 4: Cost benefits analysis and recommendations. [orbital launching of space shuttle payloads

NASA Technical Reports Server (NTRS)

1978-01-01

The costs and benefits of existing/planned systems, new propulsion concepts, and adaptations of existing/planned systems (as supported by Orbiter interface requirements and operations requirements) were quantified. Scenarios of these propulsion approaches were established which accommodate the low energy regime as defined by the new low energy payload mission model. These scenarios were screened on a cost and then a benefits basis. A propulsion approach comprising existing/planned systems and a new propulsion concept were selected as the most cost effective approach to accommodate the model payloads and the low energy regime they represent. Key cost drivers and sensitivity trends were identified. All costs were derived in 1977 dollars.

An Environment Monitoring Package for the International Space Station

NASA Technical Reports Server (NTRS)

Carruth, M. Ralph; Clifton, Kenneth S.

1998-01-01

The first elements of the International Space Station (ISS) will soon be launched into space and over the next few years ISS will be assembled on orbit into its final configuration. Experiments will be performed on a continuous basis both inside and outside the station. External experiments will be mounted on attached payload locations specifically designed to accommodate experiments, provide data and supply power from ISS. From the beginning of the space station program it has been recognized that experiments will require knowledge of the external local environment which can affect the science being performed and may impact lifetime and operations of the experiment hardware. Recently an effort was initiated to design and develop an Environment Monitoring Package (EMP). This paper describes the derivation of the requirements for the EMP package, the type of measurements that the EMP will make and types of instruments which will be employed to make these measurements.

External Contamination Control of Attached Payloads on the International Space Station

NASA Technical Reports Server (NTRS)

Soares, Carlos E.; Mikatarian, Ronald R.; Olsen, Randy L.; Huang, Alvin Y.; Steagall, Courtney A.; Schmidl, William D.; Wright, Bruce D.; Koontz, Steven

2012-01-01

The International Space Station (ISS) is an on-orbit platform for science utilization in low Earth orbit with multiple sites for external payloads with exposure to the natural and induced environments. Contamination is one of the induced environments that can impact performance, mission success and science utilization on the vehicle. This paper describes the external contamination control requirements and integration process for externally mounted payloads on the ISS. The external contamination control requirements are summarized and a description of the integration and verification process is detailed to guide payload developers in the certification process of attached payloads on the vehicle. A description of the required data certification deliverables covers the characterization of contamination sources. Such characterization includes identification, usage and operational data for each class of contamination source. Classes of external contamination sources covered are vacuum exposed materials, sources of leakage, vacuum venting and thrusters. ISS system level analyses are conducted by the ISS Space Environments Team to certify compliance with external contamination control requirements. This paper also addresses the ISS induced contamination environment at attached payload sites, both at the requirements level as well as measurements made on ISS.

Atmosphere, Magnetosphere and Plasmas in Space (AMPS). Spacelab payload definition study. Volume 2: Mission support requirements document. Addendum: Flight 2

NASA Technical Reports Server (NTRS)

1976-01-01

The AMPS Flight 2 payload, its operation, and the support required from the Space Transportation System (STS) are described. The definition of the payload includes the flight objectives and requirements, the experiment operations, and the payload configuration. The support required from the STS includes the accommodation of the payload by the orbiter/Spacelab, use of the flight operations network and ground facilities, and the use of the launch site facilities.

NASA's Space Launch System: Deep-Space Deployment for SmallSats

NASA Technical Reports Server (NTRS)

Schorr, Andy

2017-01-01

From its upcoming first flight, NASA's new Space Launch System (SLS) will represent a game-changing opportunity for smallsats. On that launch, which will propel the Orion crew vehicle around the moon, the new exploration-class launch vehicle will deploy 13 6U CubeSats into deep-space, where they will continue to a variety of destinations to perform diverse research and demonstrations. Following that first flight, SLS will undergo the first of a series of performance upgrades, increasing its payload capability to low Earth orbit from 70 to 105 metric tons via the addition of a powerful upper stage. With that change to the vehicle's architecture, so too will its secondary payload accommodation for smallsats evolve, with current plans calling for a change from the first-flight limit of 6U to accommodating a range of sizes up to 27U and potentially ESPA-class payloads. This presentation will provide an overview and update on the first launch of SLS and the secondary payloads it will deploy. Currently, flight hardware has been produced for every element of the vehicle, testing of the vehicle's propulsion elements has been ongoing for years, and structural testing of its stages has begun. Major assembly and testing of the Orion Stage Adapter, including the secondary payload accommodations, will be completed this year, and the structure will then be shipped to Kennedy Space Center for integration of the payloads. Progress is being made on those CubeSats, which will include studies of asteroids, Earth, the sun, the moon, and the impacts of radiation on organisms in deep space. They will feature revolutionary innovations for smallsats, including demonstrations of use of a solar sail as propulsion for a rendezvous with an asteroid, and the landing of a CubeSat on the lunar surface. The presentation will also provide an update on progress of the SLS Block 1B configuration that will be used on the rocket's second flight, a discussion of planned secondary payload accommodations on that configuration of the vehicle, and a look at the current state of planning of upcoming missions and what that could mean for deep-space smallsat flight opportunities.

Atmosphere, Magnetosphere and Plasmas in Space (AMPS). Space payload definition study. Volume 2: Mission support requirements document

NASA Technical Reports Server (NTRS)

1976-01-01

The flight payload, its operation, and the support required from the Space Transporatation System (STS) is defined including the flight objectives and requirements, the experiment operations, and the payload configurations. The support required from the STS includes the accommodation of the payload by the orbiter/Spacelab, use of the flight operations network and ground facilities, and the use of the launch site facilities.

EVAL system concept definition. Partial spacelab payload

NASA Technical Reports Server (NTRS)

1976-01-01

The preliminary design of an earth-viewing spacelab payload, with accommodations shared by both NASA and ESA is addressed. Mission parameters for this flight include a launch date of September 1981, an inclination of 57 deg, and an orbital altitude of 325 km. A seven-day mission is planned. The NASA portion of this payload is assigned to the EVAL (Earth Viewing Applications Laboratory) program. The ESA complement is designed as a multiuser payload.

Earth Viewing Applications Laboratory (EVAL). Dedicated payload, standard test rack payload, sensor modifications

NASA Technical Reports Server (NTRS)

1976-01-01

The preliminary analysis of strawman earth-viewing shuttle sortie payloads begun with the partial spacelab payload was analyzed. The payloads analyzed represent the two extremes of shuttle sortie application payloads: a full shuttle sortie payload dedicated to earth-viewing applications, and a small structure payload which can fly on a space available basis with another primary shuttle payload such as a free flying satellite. The intent of the dedicated mission analysis was to configure an ambitious, but feasible, payload; which, while rich in scientific return, would also stress the system and reveal any deficiences or problem areas in mission planning, support equipment, and operations. Conversely, the intent of the small structure payload was to demonstrate the ease with which a small, simple, flexible payload can be accommodated on shuttle flights.

Space Shuttle Payload Information Source

NASA Technical Reports Server (NTRS)

Griswold, Tom

2000-01-01

The Space Shuttle Payload Information Source Compact Disk (CD) is a joint NASA and USA project to introduce Space Shuttle capabilities, payload services and accommodations, and the payload integration process. The CD will be given to new payload customers or to organizations outside of NASA considering using the Space Shuttle as a launch vehicle. The information is high-level in a visually attractive format with a voice over. The format is in a presentation style plus 360 degree views, videos, and animation. Hyperlinks are provided to connect to the Internet for updates and more detailed information on how payloads are integrated into the Space Shuttle.

Pucksat Payload Carrier

NASA Technical Reports Server (NTRS)

Milam, M. Bruce; Young, Joseph P.

1999-01-01

There is an ever-expanding need to provide economical space launch opportunities for relatively small science payloads. To address this need, a team at NASA's Goddard Space Flight Center has designed the Pucksat. The Pucksat is a highly versatile payload carrier structure compatible for launching on a Delta II two-stage vehicle as a system co-manifested with a primary payload. It is also compatible for launch on the Air Force Medium Class EELV. Pucksat's basic structural architecture consists of six honeycomb panels attached to six longerons in a hexagonal manner and closed off at the top and bottom with circular rings. Users may configure a co-manifested Pucksat in a number of ways. As examples, co-manifested configurations can be designed to accommodate dedicated missions, multiple experiments, multiple small deployable satellites, or a hybrid of the preceding examples. The Pucksat has fixed lateral dimensions and a downward scaleable height. The dimension across the panel hexagonal flats is 62 in. and the maximum height configuration dimension is 38.5 in. Pucksat has been designed to support a 5000 lbm primary payload, with the center of gravity located no greater than 60 in. from its separation plane, and to accommodate a total co-manifested payload mass of 1275 lbm.

KENNEDY SPACE CENTER, FLA. - Seen in the photo is one end of the airlock that is installed in the payload bay of orbiter Discovery. The airlock is normally located inside the middeck of the spacecraft’s pressurized crew cabin. The airlock is sized to accommodate two fully suited flight crew members simultaneously. Support functions include airlock depressurization and repressurization, extravehicular activity equipment recharge, liquid-cooled garment water cooling, EVA equipment checkout, donning and communications. The outer hatch isolates the airlock from the unpressurized payload bay when closed and permits the EVA crew members to exit from the airlock to the payload bay when open.

NASA Image and Video Library

2004-01-22

KENNEDY SPACE CENTER, FLA. - Seen in the photo is one end of the airlock that is installed in the payload bay of orbiter Discovery. The airlock is normally located inside the middeck of the spacecraft’s pressurized crew cabin. The airlock is sized to accommodate two fully suited flight crew members simultaneously. Support functions include airlock depressurization and repressurization, extravehicular activity equipment recharge, liquid-cooled garment water cooling, EVA equipment checkout, donning and communications. The outer hatch isolates the airlock from the unpressurized payload bay when closed and permits the EVA crew members to exit from the airlock to the payload bay when open.

KENNEDY SPACE CENTER, FLA. - A worker in the Orbiter Processing Facility checks the open hatch of the airlock in Discovery’s payload bay. The airlock is normally located inside the middeck of the spacecraft’s pressurized crew cabin. The airlock is sized to accommodate two fully suited flight crew members simultaneously. Support functions include airlock depressurization and repressurization, extravehicular activity equipment recharge, liquid-cooled garment water cooling, EVA equipment checkout, donning and communications. The outer hatch isolates the airlock from the unpressurized payload bay when closed and permits the EVA crew members to exit from the airlock to the payload bay when open.

NASA Image and Video Library

2004-01-22

KENNEDY SPACE CENTER, FLA. - A worker in the Orbiter Processing Facility checks the open hatch of the airlock in Discovery’s payload bay. The airlock is normally located inside the middeck of the spacecraft’s pressurized crew cabin. The airlock is sized to accommodate two fully suited flight crew members simultaneously. Support functions include airlock depressurization and repressurization, extravehicular activity equipment recharge, liquid-cooled garment water cooling, EVA equipment checkout, donning and communications. The outer hatch isolates the airlock from the unpressurized payload bay when closed and permits the EVA crew members to exit from the airlock to the payload bay when open.

Role of man in flight experiment payloads, phase 1, appendices 1 and 2. [Spacelab project planning

NASA Technical Reports Server (NTRS)

Malone, T. B.; Kirkpatrick, M.

1974-01-01

The individual task durations are calculated in a series of time line realization problems, and a functional requirements data collection technique, designed to accommodate the data requirements for Spacelab payloads, is presented.

Geostationary Platforms Mission and Payload Requirements Study. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1979-01-01

Time-phased missions and payloads for potential accommodation on geostationary platforms and the engineering requirements placed upon the platform housekeeping elements by selected payloads are identified. Optimum locations for geostationary platforms, potential missions and their characteristics, and potential user requirements were determined as well as the interface requirements between the missions and h the geostationary platform. A payload data book was prepared and antenna tradeoff studies were conducted. Payload missions are defined in terms of frequencies, power, beam patterns, interconnections, support requirements, and other characteristics.

Payload accommodations. Avionics payload support architecture

NASA Technical Reports Server (NTRS)

Creasy, Susan L.; Levy, C. D.

1990-01-01

Concepts for vehicle and payload avionics architectures for future NASA programs, including the Assured Shuttle Access program, Space Station Freedom (SSF), Shuttle-C, Advanced Manned Launch System (AMLS), and the Lunar/Mars programs are discussed. Emphasis is on the potential available to increase payload services which will be required in the future, while decreasing the operational cost/complexity by utilizing state of the art advanced avionics systems and a distributed processing architecture. Also addressed are the trade studies required to determine the optimal degree of vehicle (NASA) to payload (customer) separation and the ramifications of these decisions.

Centaur operations at the space station

NASA Technical Reports Server (NTRS)

Porter, J.; Thompson, W.; Bennett, F.; Holdridge, J.

1987-01-01

A study was conducted on the feasibility of using a Centaur vehicle as a testbed to demonstrate critical OTV technologies at the Space Station. Two Technology Demonstration Missions (TDMs) were identified: (1) Accommodations, and (2) Operations. The Accommodations TDM contained: (1) berthing, (2) checkout, maintenance and safing, and (3) payload integration missions. The Operations TDM contained: (1) a cryogenic propellant resupply mission, and (2) Centaur deployment activities. A modified Space Station Co-Orbiting Platform (COP) was selected as the optimum refueling and launch node due to safety and operational considerations. After completion of the TDMs, the fueled Centaur would carry out a mission to actually test deployment and help offset TDM costs. From the Station, the Centaur could carry a single payload in excess of 20,000 pounds to geosynchronous orbit or multiple payloads.

Maximizing Launch Vehicle and Payload Design Via Early Communications

NASA Technical Reports Server (NTRS)

Morris, Bruce

2010-01-01

The United States? current fleet of launch vehicles is largely derived from decades-old designs originally made for payloads that no longer exist. They were built primarily for national security or human exploration missions. Today that fleet can be divided roughly into small-, medium-, and large-payload classes based on mass and volume capability. But no vehicle in the U.S. fleet is designed to accommodate modern payloads. It is usually the payloads that must accommodate the capabilities of the launch vehicles. This is perhaps most true of science payloads. It was this paradigm that the organizers of two weekend workshops in 2008 at NASA's Ames Research Center sought to alter. The workshops brought together designers of NASA's Ares V cargo launch vehicle (CLV) with scientists and payload designers in the astronomy and planetary sciences communities. Ares V was still in a pre-concept development phase as part of NASA?s Constellation Program for exploration beyond low Earth orbit (LEO). The space science community was early in a Decadal Survey that would determine future priorities for research areas, observations, and notional missions to make those observations. The primary purpose of the meetings in April and August of 2008, including the novel format, was to bring vehicle designers together with space scientists to discuss the feasibility of using a heavy lift capability to launch large observatories and explore the Solar System. A key question put to the science community was whether this heavy lift capability enabled or enhanced breakthrough science. The meetings also raised the question of whether some trade-off between mass/volume and technical complexity existed that could reduce technical and programmatic risk. By engaging the scientific community early in the vehicle design process, vehicle engineers sought to better understand potential limitations and requirements that could be added to the Ares V from the mission planning community. From the vehicle standpoint, while the human exploration mission could not be compromised to accommodate other payloads, the design might otherwise be tailored to not exclude other payload requirements. This paper summarizes the findings of the workshops and discusses the benefits of bringing together the vehicle design and science communities early in their concept phases

ARM Aerial Facility ArcticShark Unmanned Aerial System

NASA Astrophysics Data System (ADS)

Schmid, B.; Hubbell, M.; Mei, F.; Carroll, P.; Mendoza, A.; Ireland, C.; Lewko, K.

2017-12-01

The TigerShark Block 3 XP-AR "ArcticShark" Unmanned Aerial System (UAS), developed and manufactured by Navmar Applied Sciences Corporation (NASC), is a single-prop, 60 hp rotary-engine platform with a wingspan of 6.5 m and Maximum Gross Takeoff Weight of 295 Kg. The ArcticShark is owned by the U.S. Department of Energy (DOE) and has been operated by Pacific Northwest National Laboratory (PNNL) since March 2017. The UAS will serve as an airborne atmospheric research observatory for DOE ARM, and, once fully operational, can be requested through ARM's annual call for proposals. The Arctic Shark is anticipated to measure a wide range of radiative, aerosol, and cloud properties using a variable instrument payload weighing up to 46 Kg. SATCOM-equipped, it is capable of taking measurements up to altitudes of 5.5 Km over ranges of up to 500 Km. The ArcticShark operates at airspeeds of 30 to 40 m/s, making it capable of slow sampling. With a full fuel load, its endurance exceeds 8 hours. The aircraft and its Mobile Operations Center (MOC) have been hardened specifically for operations in colder temperatures.ArcticShark's design facilitates rapid integration of various types of payloads. 2500 W of its 4000 W electrical systems is dedicated to payload servicing. It has an interior payload volume of almost 85 L and four wing-mounted pylons capable of carrying external probes. Its payload bay volume, electrical power, payload capacity, and flight characteristics enable the ArcticShark to accommodate multiple combinations of payloads in numerous configurations. Many instruments will be provided by the ARM Aerial Facility (AAF), but other organizations may eventually propose instrumentation for specific campaigns. AAF-provided measurement capabilities will include the following atmospheric state and thermodynamics: temperature, pressure, winds; gases: H2O and CO2; up- and down-welling broadband infrared and visible radiation; surface temperature; aerosol number concentration, size distribution, absorption composition (filter samples), and cloud-droplet size distribution.

Small, Low Cost, Launch Capability Development

NASA Technical Reports Server (NTRS)

Brown, Thomas

2014-01-01

A recent explosion in nano-sat, small-sat, and university class payloads has been driven by low cost electronics and sensors, wide component availability, as well as low cost, miniature computational capability and open source code. Increasing numbers of these very small spacecraft are being launched as secondary payloads, dramatically decreasing costs, and allowing greater access to operations and experimentation using actual space flight systems. While manifesting as a secondary payload provides inexpensive rides to orbit, these arrangements also have certain limitations. Small, secondary payloads are typically included with very limited payload accommodations, supported on a non interference basis (to the prime payload), and are delivered to orbital conditions driven by the primary launch customer. Integration of propulsion systems or other hazardous capabilities will further complicate secondary launch arrangements, and accommodation requirements. The National Aeronautics and Space Administration's Marshall Space Flight Center has begun work on the development of small, low cost launch system concepts that could provide dedicated, affordable launch alternatives to small, high risk university type payloads and spacecraft. These efforts include development of small propulsion systems and highly optimized structural efficiency, utilizing modern advanced manufacturing techniques. This paper outlines the plans and accomplishments of these efforts and investigates opportunities for truly revolutionary reductions in launch and operations costs. Both evolution of existing sounding rocket systems to orbital delivery, and the development of clean sheet, optimized small launch systems are addressed.

Space Shuttle payload accommodation and trends in customer demands

NASA Technical Reports Server (NTRS)

Hedin, Daniel L.; Wilson, James R.

1992-01-01

This paper will review payload demands for Shuttle resources and services in the pre-Space Station Freedom time frame. Requests for flight in both the Orbiter cargo bay and middeck will be considered. Factors limiting more efficient use of the Shuttle will also be discussed.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, a cameraman films part of Discovery’s payload bay for a special feature on the KSC Web. In the background is the open hatch of the airlock, located inside the middeck of the spacecraft’s pressurized crew cabin. The airlock is sized to accommodate two fully suited flight crew members simultaneously. Support functions include airlock depressurization and repressurization, extravehicular activity equipment recharge, liquid-cooled garment water cooling, EVA equipment checkout, donning and communications. The outer hatch isolates the airlock from the unpressurized payload bay when closed and permits the EVA crew members to exit from the airlock to the payload bay when open.

NASA Image and Video Library

2004-01-22

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, a cameraman films part of Discovery’s payload bay for a special feature on the KSC Web. In the background is the open hatch of the airlock, located inside the middeck of the spacecraft’s pressurized crew cabin. The airlock is sized to accommodate two fully suited flight crew members simultaneously. Support functions include airlock depressurization and repressurization, extravehicular activity equipment recharge, liquid-cooled garment water cooling, EVA equipment checkout, donning and communications. The outer hatch isolates the airlock from the unpressurized payload bay when closed and permits the EVA crew members to exit from the airlock to the payload bay when open.

The Space Shuttle orbiter payload retention systems

NASA Technical Reports Server (NTRS)

Hardee, J. H.

1982-01-01

Payloads are secured in the orbiter payload bay by the payload retention system or are equipped with their own unique retention systems. The orbiter payload retention mechanisms provide structural attachments for each payload by using four or five attachment points to secure the payload within the orbiter payload bay during all phases of the orbiter mission. The payload retention system (PRS) is an electromechanical system that provides standarized payload carrier attachment fittings to accommodate up to five payloads for each orbiter flight. The mechanisms are able to function under either l-g or zero-g conditions. Payload berthing or deberthing on orbit is accomplished by utilizing the remote manipulator system (RMS). The retention mechanisms provide the capability for either vertical or horizontal payload installation or removal. The payload support points are selected to minimize point torsional, bending, and radial loads imparted to the payloads. In addition to the remotely controlled latching system, the passive system used for nondeployable payloads performs the same function as the RMS except it provides fixed attachments to the orbiter.

International Space Station External Contamination Environment for Space Science Utilization

NASA Technical Reports Server (NTRS)

Soares, Carlos E.; Mikatarian, Ronald R.; Steagall, Courtney A.; Huang, Alvin Y.; Koontz, Steven; Worthy, Erica

2014-01-01

The International Space Station (ISS) is the largest and most complex on-orbit platform for space science utilization in low Earth orbit. Multiple sites for external payloads, with exposure to the associated natural and induced environments, are available to support a variety of space science utilization objectives. Contamination is one of the induced environments that can impact performance, mission success and science utilization on the vehicle. The ISS has been designed, built and integrated with strict contamination requirements to provide low levels of induced contamination on external payload assets. This paper addresses the ISS induced contamination environment at attached payload sites, both at the requirements level as well as measurements made on returned hardware, and contamination forecasting maps being generated to support external payload topology studies and science utilization.

Coupled loads analysis for Space Shuttle payloads

NASA Technical Reports Server (NTRS)

Eldridge, J.

1992-01-01

Described here is a method for determining the transient response of, and the resultant loads in, a system exposed to predicted external forces. In this case, the system consists of four racks mounted on the inside of a space station resource node module (SSRNMO) which is mounted in the payload bay of the space shuttle. The predicted external forces are forcing functions which envelope worst case forces applied to the shuttle during liftoff and landing. This analysis, called a coupled loads analysis, is used to couple the payload and shuttle models together, determine the transient response of the system, and then recover payload loads, payload accelerations, and payload to shuttle interface forces.

Remote Advanced Payload Test Rig (RAPTR) Portable Payload Test System for the International Space Station (ISS)

NASA Technical Reports Server (NTRS)

Calvert, John; Freas, George, II

2017-01-01

The RAPTR was developed to test ISS payloads for NASA. RAPTR is a simulation of the Command and Data Handling (C&DH) interfaces of the ISS (MIL-STD 1553B, Ethernet and TAXI) and is designed to facilitate rapid testing and deployment of payload experiments to the ISS. The ISS Program's goal is to reduce the amount of time it takes a payload developer to build, test and fly a payload, including payload software. The RAPTR meets this need with its user oriented, visually rich interface. Additionally, the Analog and Discrete (A&D) signals of the following payload types may be tested with RAPTR: (1) EXPRESS Sub Rack Payloads; (2) ELC payloads; (3) External Columbus payloads; (4) External Japanese Experiment Module (JEM) payloads. The automated payload configuration setup and payload data inspection infrastructure is found nowhere else in ISS payload test systems. Testing can be done with minimal human intervention and setup, as the RAPTR automatically monitors parameters in the data headers that are sent to, and come from the experiment under test.

The International Space Station as a Research Laboratory: A View to 2010 and Beyond

NASA Technical Reports Server (NTRS)

Uri, John J.; Sotomayor, Jorge L.

2007-01-01

Assembly of International Space Station (ISS) is expected to be complete in 2010, with operations planned to continue through at least 2016. As we move nearer to assembly complete, replanning activities by NASA and ISS International Partners have been completed and the final complement of research facilities on ISS is becoming more certain. This paper will review pans for facilities in the US On-orbit Segment of ISS, including contributions from International Partners, to provide a vision of the research capabilities that will be available starting in 2010. At present, in addition to research capabilities in the Russian segment, the United States Destiny research module houses nine research facilities or racks. These facilities include five multi-purpose EXPRESS racks, two Human Research Facility (HRF) racks, the Microgravity Science Glovebox (MSG), and the Minus Eighty-degree Laboratory Freezer for ISS (MELFI), enabling a wide range of exploration-related applied as well as basic research. In the coming years, additional racks will be launched to augment this robust capability: Combustion Integrated Rack (CIR), Fluids Integrated Rack (FIR), Window Observation Rack Facility (WORF), Microgravity Science Research Rack (MSRR), Muscle Atrophy Research Exercise System (MARES), additional EXPRESS racks and possibly a second MELFI. In addition, EXPRESS Logistics Carriers (ELC) will provide attach points for external payloads. The European Space Agency s Columbus module will contain five research racks and provide four external attach sites. The research racks are Biolab, European Physiology Module (EPM), Fluid Science Lab (FSL), European Drawer System (EDS) and European Transport Carrier (ETC). The Japanese Kibo elements will initially support three research racks, Ryutai for fluid science, Saibo for cell science, and Kobairo for materials research, as well as 10 attachment sites for external payloads. As we look ahead to assembly complete, these new facilities represent a threefold increase from the current research laboratory infrastructure on ISS. In addition, the increase in resident crew size will increase from three to six in 2009, will provide the long-term capacity for completing research on board ISS. Transportation to and from ISS for crew and cargo will be provided by a fleet of vehicles from the United States, Russia, ESA and Japan, including accommodations for thermally-conditioned cargo. The completed ISS will have robust research accommodations to support the multidisciplinary research objective of scientists worldwide.

Enabling Science and Deep Space Exploration through Space Launch System (LSL) Secondary Payload Opportunities

NASA Technical Reports Server (NTRS)

Singer, Jody; Pelfrey, Joseph; Norris, George

2016-01-01

For the first time in almost 40 years, a NASA human-rated launch vehicle has completed its Critical Design Review (CDR). By reaching this milestone, NASA's Space Launch System (SLS) and Orion spacecraft are on the path to launch a new era of deep space exploration. NASA is making investments to expand science and exploration capability of the SLS by developing the capability to deploy small satellites during the trans-lunar phase of the mission trajectory. Exploration Mission 1 (EM-1), currently planned for launch no earlier than July 2018, will be the first mission to carry such payloads on the SLS. The EM-1 launch will include thirteen 6U Cubesat small satellites that will be deployed beyond low earth orbit. By providing an earth-escape trajectory, opportunities are created for advancement of small satellite subsystems, including deep space communications and in-space propulsion. This SLS capability also creates low-cost options for addressing existing Agency strategic knowledge gaps and affordable science missions. A new approach to payload integration and mission assurance is needed to ensure safety of the vehicle, while also maintaining reasonable costs for the small payload developer teams. SLS EM-1 will provide the framework and serve as a test flight, not only for vehicle systems, but also payload accommodations, ground processing, and on-orbit operations. Through developing the requirements and integration processes for EM-1, NASA is outlining the framework for the evolved configuration of secondary payloads on SLS Block upgrades. The lessons learned from the EM-1 mission will be applied to processes and products developed for future block upgrades. In the heavy-lift configuration of SLS, payload accommodations will increase for secondary opportunities including small satellites larger than the traditional Cubesat class payload. The payload mission concept of operations, proposed payload capacity of SLS, and the payload requirements for launch and deployment will be described to provide potential payload users an understanding of this unique exploration capability.

TOPEX satellite option study

NASA Technical Reports Server (NTRS)

1982-01-01

The basic design of the fleet satellite communication spacecraft (FLTSATCOM) can easily accommodate any of the three payload options for the ocean dynamic topography experiment (TOPEX). The principal mission requirements as well as the payload accommodations and communications systems needed for launching this payload are reviewed. The existing FLTSATCOM satellite design is identified and the approaches for the proposed propulsion system are described in addition to subsystems for mechanical; power; attitude and velocity control; and telemetry, tracking and control are described. The compatability of FLTSATCOM with the launch vehicle is examined and its capabilities vs TOPEX requirements are summarized. Undetermined changes needed to meet data storage, thermal control, and area to mass ratio requirements are discussed. Cost estimates are included for budgetary and planning purposes. The availability of the described design is assessed based on the continuing production of FLTSATCOM spacecraft during the schedule span planned for TOPEX.

International utilization and operations

NASA Technical Reports Server (NTRS)

Goldberg, Stanley R.

1989-01-01

The international framework of the Space Station Freedom Program is described. The discussion covers the U.S. space policy, international agreements, international Station elements, overall program management structure, and utilization and operations management. Consideration is also given to Freedom's user community, Freedom's crew, pressurized payload and attached payload accommodations, utilization and operations planning, user integration, and user operations.

External Contamination Environment at ISS Included: Selected Results from Payloads Contamination Mapping Delivery 3 Package

NASA Technical Reports Server (NTRS)

Olsen, Randy; Huang, Alvin; Steagall, Courtney; Kohl, Nathaniel; Koontz, Steve; Worthy, Erica

2017-01-01

The International Space Station is the largest and most complex on-orbit platform for space science utilization in low Earth orbit. Multiple sites for external payloads, with exposure to the associated natural and induced environments, are available to support a variety of space science utilization objectives. Contamination is one of the induced environments that can impact performance, mission success and science utilization on the vehicle. The ISS has been designed, built and integrated with strict contamination requirements to provide low levels of induced contamination on external payload assets.

International Space Station (ISS) Accommodation of a Single US Assured Crew Return Vehicle (ACRV)

NASA Technical Reports Server (NTRS)

Mazanek, Daniel D.; Garn, Michelle A.; Troutman, Patrick A.; Wang, Yuan; Kumar, Renjith; Heck, Michael L.

1997-01-01

The following report was generated to give the International Space Station (ISS) Program some additional insight into the operations and issues associated with accommodating a single U.S. developed Assured Crew Return Vehicle (ACRV). During the generation of this report, changes in both the ISS and ACRV programs were factored into the analysis with the realization that most of the work performed will eventually need to be repeated once the two programs become more integrated. No significant issues associated with the ISS accommodating the ACRV were uncovered. Kinematic analysis of ACRV installation showed that there are viable methods of using Shuttle and Station robotic manipulators. Separation analysis demonstrated that the ACRV departure path clears the Station structure for all likely contingency scenarios. The payload bay packaging analysis identified trades that can be made between payload bay location, Shuttle Remote Manipulator System (SRMS) reach and eventual designs of de-orbit stages and docking adapters.

Economy of middeck payloads

NASA Technical Reports Server (NTRS)

Michel, E. L.; Huffstetler, W. J.

1986-01-01

The utilization of the middeck, designed as the crew quarters, for experiments is examined. The dimensions of the middeck's standard lockers, double lockers, adapter plates, and the galley, which are applicable for experiments, are described. The utilities available for middeck payloads include ac and dc electrical power supply, active and passive cooling, vacuum/vent line connections, and data handling, and four basic payload configurations are possible. The development of a middeck accommodations rack to make payload space more flexible and to enable an optimum number and variety of experiments to be flown is proposed. Diagrams of the orbiter's middeck and experimental designs are provided.

Space Launch System (SLS) Mission Planner's Guide

NASA Technical Reports Server (NTRS)

Smith, David Alan

2017-01-01

The purpose of this Space Launch System (SLS) Mission Planner's Guide (MPG) is to provide future payload developers/users with sufficient insight to support preliminary SLS mission planning. Consequently, this SLS MPG is not intended to be a payload requirements document; rather, it organizes and details SLS interfaces/accommodations in a manner similar to that of current Expendable Launch Vehicle (ELV) user guides to support early feasibility assessment. Like ELV Programs, once approved to fly on SLS, specific payload requirements will be defined in unique documentation.

First Spacelab flight - A status report of the joint ESA/NASA mission

NASA Technical Reports Server (NTRS)

Craft, H. G., Jr.; Sanfourche, J.-P.

1978-01-01

A general overview of the first Spacelab flight is presented and a table is given listing the payload composition. An accommodation study is presented with emphasis on the configuration, mass status, timeline, and experiment interface specifications. Also considered are flight and ground operations, safety factors, and payload specialists training for the first flight.

An EXPRESS Rack Overview and Support for Microgravity Research on the International Space Station (ISS)

NASA Technical Reports Server (NTRS)

Pelfrey, Joseph J.; Jordan, Lee P.

2008-01-01

The EXpedite the PRocessing of Experiments to Space Station or EXPRESS Rack System has provided accommodations and facilitated operations for microgravity-based research payloads for over 6 years on the International Space Station (ISS). The EXPRESS Rack accepts Space Shuttle middeck type lockers and International Subrack Interface Standard (ISIS) drawers, providing a modular-type interface on the ISS. The EXPRESS Rack provides 28Vdc power, Ethernet and RS-422 data interfaces, thermal conditioning, vacuum exhaust, and Nitrogen supply for payload use. The EXPRESS Rack system also includes payload checkout capability with a flight rack or flight rack emulator prior to launch, providing a high degree of confidence in successful operations once an-orbit. In addition, EXPRESS trainer racks are provided to support crew training of both rack systems and subrack operations. Standard hardware and software interfaces provided by the EXPRESS Rack simplify the integration processes for ISS payload development. The EXPRESS Rack is designed to accommodate multidiscipline research, allowing for the independent operation of each subrack payload within a single rack. On-orbit operations began for the EXPRESS Rack Project on April 24, 2001, with one rack operating continuously to support high-priority payloads. The other on-orbit EXPRESS Racks operate based on payload need and resource availability. Over 50 multi-discipline payloads have now been supported on-orbit by the EXPRESS Rack Program. Sustaining engineering, logistics, and maintenance functions are in place to maintain hardware, operations and provide software upgrades. Additional EXPRESS Racks are planned for launch prior to ISS completion in support of long-term operations and the planned transition of the U.S. Segment to a National Laboratory.

Spacelab payload accommodation handbook. Preliminary issue

NASA Technical Reports Server (NTRS)

1976-01-01

The main characteristics of the Spacelab system are described. Sufficient information on Spacelab capabilities is provided to enable individual experimenters or payload planning groups to determine how their payload equipment can be accomodated by Spacelab topics discussed include major spacelab/experiment interfaces; Spacelab payload support systems and requirements the experiments must comply with to allow experiment design; and development and integration up to a level where a group of individual experiments are integrated into a complete Spacelab payload using Spacelab racks/floors and pallet segments. Integration of a complete Spacelab payload with Spacelab subsystems, primary module structure etc., integration of Spacelab with the Orbiter and basic operational aspects are also covered in this preliminary edition of the handbook which reflects the current Spacelab baseline design and is for information only.

Life science payloads planning study integration facility survey results

NASA Technical Reports Server (NTRS)

Wells, G. W.; Brown, N. E.; Nelson, W. G.

1976-01-01

The integration facility survey effort described is structured to examine the facility resources needed to conduct life science payload (LSP) integration checkout activities at NASA-JSC. The LSP integration facility operations and functions are defined along with the LSP requirements for facility design. A description of available JSC life science facilities is presented and a comparison of accommodations versus requirements is reported.

Materials experiment carrier concepts definition study. Volume 1: Executive summary, part 2

NASA Technical Reports Server (NTRS)

1981-01-01

The materials experiment carrier (MEC) is an optimized carrier for near term and advanced materials processing in space (MPS) research and commercial payloads. When coupled with the space platform (SP), the MEC can provide the extended duration, high power and low acceleration environment the MPS payload typically requires. The lowest cost, technically reasonable first step MEC that meets the MPS program missions objectives with minimum programmatic risks is defined. The effectiveness of the initial MEC/space platform idea for accommodating high priority, multidiscipline, R&D and commercial MPS payloads, and conducting MPS payload oprations at affordable funding and acceptable productivity levels is demonstrated.

A Definition of STS Accommodations for Attached Payloads

NASA Technical Reports Server (NTRS)

Echols, F. L.; Broome, P. A.

1983-01-01

An input to a study conducted to define a set of carrier avionics for supporting large structures experiments attached to the Space Shuttle Orbiter is reported. The "baseline" Orbier interface used in developing the avionics concept for the Space Technology Experiments Platform, STEP, which Langley Research Center has proposed for supporting experiments of this sort is defined. Primarily, flight operations capabilities and considerations and the avionics systems capabilities that are available to a payload as a "mixed cargo" user of the Space Transportation System are addressed. Ground operations for payload integration at Kennedy Space Center, and ground operations for payload support during the mission are also discussed.

Standard payload computer for the international space station

NASA Astrophysics Data System (ADS)

Knott, Karl; Taylor, Chris; Koenig, Horst; Schlosstein, Uwe

1999-01-01

This paper describes the development and application of a Standard PayLoad Computer (SPLC) which is being applied by the majority of ESA payloads accommodated on the International Space Station (ISS). The strategy of adopting of a standard computer leads to a radical rethink in the payload data handling procurement process. Traditionally, this has been based on a proprietary development with repeating costs for qualification, spares, expertise and maintenance for each new payload. Implementations have also tended to be unique with very little opportunity for reuse or utilisation of previous developments. While this may to some extent have been justified for short duration one-off missions, the availability of a standard, long term space infrastructure calls for a quite different approach. To support a large number of concurrent payloads, the ISS implementation relies heavily on standardisation, and this is particularly true in the area of payloads. Physical accommodation, data interfaces, protocols, component quality, operational requirements and maintenance including spares provisioning must all conform to a common set of standards. The data handling system and associated computer used by each payload must also comply with these common requirements, and thus it makes little sense to instigate multiple developments for the same task. The opportunity exists to provide a single computer suitable for all payloads, but with only a one-off development and qualification cost. If this is combined with the benefits of multiple procurement, centralised spares and maintenance, there is potential for great savings to be made by all those concerned in the payload development process. In response to the above drivers, the SPLC is based on the following concepts: • A one-off development and qualification process • A modular computer, configurable according to the payload developer's needs from a list of space-qualified items • An `open system' which may be added to by payload developers • Core software providing a suite of common communications services including a verified protocol implementation required to communicate with the ISS • A standardized ground support equipment and accompanying software development environment • The use of commercial hardware and software standards and products.

Expert systems applications for space shuttle payload integration automation

NASA Technical Reports Server (NTRS)

Morris, Keith

1988-01-01

Expert systems technologies have been and are continuing to be applied to NASA's Space Shuttle orbiter payload integration problems to provide a level of automation previously unrealizable. NASA's Space Shuttle orbiter was designed to be extremely flexible in its ability to accommodate many different types and combinations of satellites and experiments (payloads) within its payload bay. This flexibility results in differnet and unique engineering resource requirements for each of its payloads, creating recurring payload and cargo integration problems. Expert systems provide a successful solution for these recurring problems. The Orbiter Payload Bay Cabling Expert (EXCABL) was the first expert system, developed to solve the electrical services provisioning problem. A second expert system, EXMATCH, was developed to generate a list of the reusable installation drawings available for each EXCABL solution. These successes have proved the applicability of expert systems technologies to payload integration problems and consequently a third expert system is currently in work. These three expert systems, the manner in which they resolve payload problems and how they will be integrated are described.

Preliminary Surface Thermal Design of the Mars 2020 Rover

NASA Technical Reports Server (NTRS)

Novak, Keith S.; Kempenaar, Jason G.; Redmond, Matthew J.; Bhandari, Pradeep

2015-01-01

The Mars 2020 rover, scheduled for launch in July 2020, is currently being designed at NASA's Jet Propulsion Laboratory. The Mars 2020 rover design is derived from the Mars Science Laboratory (MSL) rover, Curiosity, which has been exploring the surface of Mars in Gale Crater for over 2.5 years. The Mars 2020 rover will carry a new science payload made up of 7 instruments. In addition, the Mars 2020 rover is responsible for collecting a sample cache of Mars regolith and rock core samples that could be returned to Earth in a future mission. Accommodation of the new payload and the Sampling Caching System (SCS) has driven significant thermal design changes from the original MSL rover design. This paper describes the similarities and differences between the heritage MSL rover thermal design and the new Mars 2020 thermal design. Modifications to the MSL rover thermal design that were made to accommodate the new payload and SCS are discussed. Conclusions about thermal design flexibility are derived from the Mars 2020 preliminary thermal design experience.

The October 1973 NASA mission model analysis and economic assessment

NASA Technical Reports Server (NTRS)

1974-01-01

Results are presented of the 1973 NASA Mission Model Analysis. The purpose was to obtain an economic assessment of using the Shuttle to accommodate the payloads and requirements as identified by the NASA Program Offices and the DoD. The 1973 Payload Model represents a baseline candidate set of future payloads which can be used as a reference base for planning purposes. The cost of implementing these payload programs utilizing the capabilities of the shuttle system is analyzed and compared with the cost of conducting the same payload effort using expendable launch vehicles. There is a net benefit of 14.1 billion dollars as a result of using the shuttle during the 12-year period as compared to using an expendable launch vehicle fleet.

An initial study of family accommodation in children and adolescents with chronic tic disorders.

PubMed

Storch, Eric A; Johnco, Carly; McGuire, Joseph F; Wu, Monica S; McBride, Nicole M; Lewin, Adam B; Murphy, Tanya K

2017-01-01

This initial study examined the nature, incidence, and clinical correlates of family accommodation in youth with tic disorders, and validated a brief self-report measure of tic-related family accommodation, the Tic Family Accommodation Scale (TFAS). Seventy-five youth aged 6-18 who were diagnosed with a tic disorder and their parent completed a diagnostic clinical interview, and clinician and parent-report measures of tic severity, depressive symptoms, anxiety symptoms, behavioral problems, family accommodation and impairment. An exploratory factor analysis of the TFAS showed a two-factor structure, with good internal consistency for the Total score, Modification of Child Environment and Modification of Parent Environment subscales (α = 0.88, 0.86, and 0.81, respectively). Family accommodation was not associated with tic severity. Family accommodation was associated with increased anxiety and depressive symptoms, higher externalizing, rule breaking, aggressive behaviors and social problems, and with greater tic-related functional impairment. Anxiety and externalizing problems (but not depressive symptoms) predicted family accommodation when controlling for tic severity. Family accommodation predicted high levels of functional impairment over and above the effect of tic severity, anxiety, depression and externalizing problems. Family accommodation is a common phenomenon for youth with tic disorders, with modifications typically encompassing changes to the child and/or parent environments. Accommodation was not associated with tic severity, but was related to higher levels of anxiety, depressive symptoms, externalizing symptoms, aggression, and rule breaking behaviors. Results suggest that other emotional symptoms are more likely to drive accommodation practices than the tic symptoms per se.

The Space Shuttle - A future space transportation system

NASA Technical Reports Server (NTRS)

Thompson, R. F.

1974-01-01

The objective of the Space Shuttle Program is to achieve an economical space transportation system. This paper provides an introductory review of the considerations which led to the Government decisions to develop the Space Shuttle. The role of a space transportation system is then considered within the context of historical developments in the general field of transportation, followed by a review of the Shuttle system, mission profile, payload categories, and payload accommodations which the Shuttle system will provide, and concludes with a forecast of the systems utilization for space science research and payload planning activity.

Secondary Payload Opportunities on NASA's Space Launch System (SLS) Enable Science and Deep Space Exploration

NASA Technical Reports Server (NTRS)

Singer, Jody; Pelfrey, Joseph; Norris, George

2016-01-01

For the first time in almost 40 years, a NASA human-rated launch vehicle has completed its Critical Design Review (CDR). With this milestone, NASA's Space Launch System (SLS) and Orion spacecraft are on the path to launch a new era of deep space exploration. This first launch of SLS and the Orion Spacecraft is planned no later than November 2018 and will fly along a trans-lunar trajectory, testing the performance of the SLS and Orion systems for future missions. NASA is making investments to expand the science and exploration capability of the SLS by developing the capability to deploy small satellites during the trans-lunar phase of the mission trajectory. Exploration Mission 1 (EM-1) will include thirteen 6U Cubesat small satellites to be deployed beyond low earth orbit. By providing an earth-escape trajectory, opportunities are created for the advancement of small satellite subsystems, including deep space communications and in-space propulsion. This SLS capability also creates low-cost options for addressing existing Agency strategic knowledge gaps and affordable science missions. A new approach to payload integration and mission assurance is needed to ensure safety of the vehicle, while also maintaining reasonable costs for the small payload developer teams. SLS EM-1 will provide the framework and serve as a test flight, not only for vehicle systems, but also payload accommodations, ground processing, and on-orbit operations. Through developing the requirements and integration processes for EM-1, NASA is outlining the framework for the evolved configuration of secondary payloads on SLS Block upgrades. The lessons learned from the EM-1 mission will be applied to processes and products developed for future block upgrades. In the heavy-lift configuration of SLS, payload accommodations will increase for secondary opportunities including small satellites larger than the traditional Cubesat class payload. The payload mission concept of operations, proposed payload capacity of SLS, and the payload requirements for launch and deployment will be described to provide potential payload users an understanding of this unique exploration capability.

EXPRESS Rack Overview

NASA Technical Reports Server (NTRS)

Sledd, Annette M.; Mueller, Charles W.

1999-01-01

The EXpedite the PRocessing of Experiments to Space Station or EXPRESS Rack System, was developed to provide Space Station accommodations for small, subrack payloads. The EXPRESS Rack accepts Space Shuttle middeck locker type payloads and International Subrack Interface Standard (ISIS) Drawer payloads, allowing previously flown payloads an opportunity to transition to the International Space Station. The EXPRESS Rack provides power, data, command and control, video, water cooling, air cooling, vacuum exhaust, and Nitrogen supply to payloads. The EXPRESS Rack system also includes transportation racks to transport payloads to and from the Space Station, Suitcase Simulators to allow a payload developer to verify power and data interfaces at the development site, Functional Checkout Units to allow Payload checkout at KSC prior to launch, and trainer racks for the astronauts to learn how to operate the EXPRESS Racks prior to flight. Standard hardware and software interfaces provided by the EXPRESS Rack simplify the analytical and physical integration processes, and facilitates simpler ISS payload development. The EXPRESS Rack has also formed the basis for the U.S. Life Sciences payload racks on Space Station.

The ISS EXPRESS Rack: An Innovative Approach of Rapid Integration

NASA Technical Reports Server (NTRS)

Sledd, Annette M.

2000-01-01

The EXpedite the PRocessing of Experiments to Space Station or EXPRESS Rack System, was developed to provide Space Station accommodations for small, subrack payloads. The EXPRESS Rack accepts Space Shuttle middeck locker type payloads and International Subrack Interface Standard (ISIS) Drawer payloads, allowing previously flown payloads an opportunity to transition to the International Space Station. The EXPRESS Rack provides power, data, command and control, video, water cooling, air cooling, vacuum exhaust, and Nitrogen supply to payloads. The EXPRESS Rack system also includes transportation racks to transport payloads to and from the Space Station, Suitcase Simulators to allow a payload developer to verify power and data interfaces at the development site, Functional Checkout Units to allow Payload checkout at KSC prior to launch, and trainer racks for the astronauts to learn how to operate the EXPRESS Racks prior to flight. Standard hardware and software interfaces provided by the EXPRESS Rack simplify the analytical and physical integration processes, and facilitates simpler ISS payload development. The EXPRESS Rack has also formed the basis for the U.S. Life Sciences payload racks and the Window Observational Research Facility on Space Station.

ILLUMA-T (Integrated LCRD LEO User Modem and Amplifier Terminal) Payload

NASA Technical Reports Server (NTRS)

Seas, Antonios; Gonnsen, Zachary; Yarnall, Timothy

2018-01-01

Presentation on ILLUMA-T (Integrated LCRD LEO User Modem and Amplifier Terminal) Payload at the Japanese Experiment Module (JEM) External Payload Interface Coordination Meeting on May 9, 2018 at the Japan Aerospace Exploration Agency (JAXA) in Tsukuba, Japan. Meeting to discuss details of installing payload on JEM.

STS-98 crew checks out the U.S. Lab Destiny in Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- In the payload bay of the orbiter Atlantis, STS-98 Commander Ken Cockrell (center) and Mission Specialist Marsha Ivins (right) look over the mission payload, the U.S. Lab Destiny (in the background). The crew is at KSC for Terminal Countdown Demonstration Test activities, which also include a simulated launch countdown. A key element in the construction of the International Space Station, Destiny is a pressurized module designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 13 locations especially designed to support experiments. The module already has five system racks installed inside. Launch of STS-98 on its 11-day mission is scheduled for Jan. 19 at 2:11 a.m. EST.

STS-98 crew checks out the U.S. Lab Destiny in Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- In the payload bay of Atlantis, two workers (background and right) watch STS-98 Robert Curbeam practice work he will do on the U.S. Lab Destiny in space. The mission payload, Destiny is a key element in the construction of the International Space Station. The lab is a pressurized module designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 13 locations especially designed to support experiments. The module already has five system racks installed inside. The STS-98 crew is at KSC for Terminal Countdown Demonstration Test activities, which also include a simulated launch countdown. Launch of STS-98 on its 11-day mission is scheduled for Jan. 19 at 2:11 a.m. EST.

Hitchhiker-G: A new carrier system for attached shuttle payloads

NASA Technical Reports Server (NTRS)

Goldsmith, T. C.

1987-01-01

A new carrier system has been developed for economical and quick response flight of small attached payloads on the space shuttle. Hitchhiker-G can accommodate up to 750 lb. of customer payloads in canisters or mounted to an exposed plate. The carrier connects to the orbiter's electrical systems and provides up to six customers with standard electrical services including power, real time telemetry, and commands. A transparent data and command system concept is employed to allow the customer to easily use his own ground support equipment and personnel to control his payload during integration and flight operations. The first Hitchhiker-G was successfully flown in January 1986 on STS 61C.

Space Transportation System/Spacelab accommodations

NASA Technical Reports Server (NTRS)

De Sanctis, C. E.

1978-01-01

A description is provided of the capabilities offered by the Spacelab design for doing research in space. The Spacelab flight vehicle consists of two basic elements including the habitable pressurized compartments and the unpressurized equipment mounting platforms. Spacelab services to payloads are considered, taking into account payload mass, electrical power and energy, heat rejection for Spacelab and payload, aspects of Spacelab data handling, and the extended flight capability. Attention is also given to the Spacelab structure, crew station and habitability, the electrical power distribution subsystem, the command and data management subsystem, the experiment computer operating system, the environmental control subsystem, the experiment vent assembly, the common payload support equipment, the instrument pointing subsystem, and details concerning the utilization of Spacelab.

Servicing capability for the evolutionary Space Station

NASA Technical Reports Server (NTRS)

Thomas, Edward F.; Grems, Edward G., III; Corbo, James E.

1990-01-01

Since the beginning of the Space Station Freedom (SSF) program the concept of on-orbit servicing of user hardware has been an integral part of the program implementation. The user servicing system architecture has been divided into a baseline and a growth phase. The baseline system consists of the following hardware elements that will support user servicing - flight telerobotic servicer, crew and equipment translation aid, crew intravehicular and extravehicular servicing support, logistics supply system, mobile servicing center, and the special purpose dextrous manipulator. The growth phase incorporates a customer servicing facility (CSF), a station-based orbital maneuvering vehicle and an orbital spacecraft consumables resupply system. The requirements for user servicing were derived from the necessity to service attached payloads, free flyers and coorbiting platforms. These requirements include: orbital replacement units (ORU) and instrument changeout, National Space Transportation System cargo bay loading and unloading, contamination control and monitoring, thermal protection, payload berthing, storage, access to SSF distributed systems, functional checkout, and fluid replenishment. The baseline user servicing capabilities accommodate ORU and instrument changeout. However, this service is limited to attached payloads, either in situ or at a locally adjacent site. The growth phase satisfies all identified user servicing requirements by expanding servicing capabilities to include complex servicing tasks for attached payloads, free-flyers and coorbiting platforms at a dedicated, protected Servicing site. To provide a smooth evolution of user servicing the SSF interfaces that are necessary to accommodate the growth phase have been identified. The interface requirements on SSF have been greatly simplified by accommodating the growth servicing support elements within the CSF. This results in a single SSF interface: SSF to the CSF.

Science and payload options for animal and plant research accommodations aboard the early Space Station

NASA Technical Reports Server (NTRS)

Hilchey, John D.; Arno, Roger D.; Gustan, Edith; Rudiger, C. E.

1986-01-01

The resources to be allocated for the development of the Initial Operational Capability (IOC) Space Station Animal and Plant Research Facility and the Growth Station Animal and Plant Vivarium and Laboratory may be limited; also, IOC accommodations for animal and plant research may be limited. An approach is presented for the development of Initial Research Capability Minilabs for animal and plant studies, which in appropriate combination and sequence can meet requirements for an evolving program of research within available accommodations and anticipated budget constraints.

Small Payload Integration and Testing Project Development

NASA Technical Reports Server (NTRS)

Sorenson, Tait R.

2014-01-01

The National Aeronautics and Space Administration's (NASA) Kennedy Space Center (KSC) has mainly focused on large payloads for space flight beginning with the Apollo program to the assembly and resupply of the International Space Station using the Space Shuttle. NASA KSC is currently working on contracting manned Low Earth Orbit (LEO) to commercial providers, developing Space Launch System, the Orion program, deep space manned programs which could reach Mars, and providing technical expertise for the Launch Services Program for science mission payloads/satellites. KSC has always supported secondary payloads and smaller satellites as the launch provider; however, they are beginning to take a more active role in integrating and testing secondary payloads into future flight opportunities. A new line of business, the Small Payload Integration and Testing Services (SPLITS), has been established to provide a one stop shop that can integrate and test payloads. SPLITS will assist high schools, universities, companies and consortiums interested in testing or launching small payloads. The goal of SPLITS is to simplify and facilitate access to KSC's expertise and capabilities for small payloads integration and testing and to help grow the space industry. An effort exists at Kennedy Space Center to improve the external KSC website. External services has partnered with SPLITS as a content test bed for attracting prospective customers. SPLITS is an emerging effort that coincides with the relaunch of the website and has a goal of attracting external partnerships. This website will be a "front door" access point for all potential partners as it will contain an overview of KSC's services, expertise and includes the pertinent contact information.

Space tug/shuttle interface compatibility study. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1975-01-01

Shuttle interfaces required for space tug accommodation are primarily involved with supporting and servicing the tug during launch countdown, flight, and postlanding; deploying and retrieving the tug on orbit; and maintaining control over the tug when it is in or near the orbiter. Each of these interface areas was investigated to determine the best physical and operational method of accomplishing the required functions, with an overriding goal of establishing simple and flexible orbiter interface requirements suitable for tug, tug payloads, IUS and other cargo. It is concluded the orbiter payload accommodations and the MSFC baseline tug are generally interface compatible. Specific minor changes to tug and orbiter interfaces were identified to provide full compatibility. A system concept for supporting and deploying tug from orbiter is described.

Innovative approach for low-cost quick-access small payload missions

NASA Astrophysics Data System (ADS)

Friis, Jan W., Jr.

2000-11-01

A significant part of the burgeoning commercial space industry is placing an unprecedented number of satellites into low earth orbit for a variety of new applications and services. By some estimates the commercial space industry now exceeds that of government space activities. Yet the two markets remain largely separate, with each deploying dedicated satellites and infrastructure for their respective missions. One commercial space firm, Final Analysis, has created a new program wherein either government, scientific or new technology payloads can be integrated on a commercial spacecraft on commercial satellites for a variety of mission scenarios at a fraction of the cost of a dedicated mission. NASA has recognized the advantage of this approach, and has awarded the Quick Ride program to provide frequent, low cost flight opportunities for small independent payloads aboard the Final Analysis constellation, and investigators are rapidly developing science programs that conform to the proposed payload accommodations envelope. Missions that were not feasible using dedicated launches are now receiving approval under the lower cost Quick Ride approach. Final Analysis has dedicated ten out of its thirty-eight satellites in support of the Quick Ride efforts. The benefit of this type of space access extend beyond NASA science programs. Commercial space firms can now gain valuable flight heritage for new technology and satellite product offerings. Further, emerging international space programs can now place a payload in orbit enabling the country to allocate its resources against the payload and mission requirements rather htan increased launch costs of a dedicated spacecraft. Finally, the low cost nature provides University-based research educational opportunities previously out of the reach of most space-related budgets. This paper will describe the motivation, benefits, technical features, and program costs of the Final Analysis secondary payload program. Payloads can be accommodated on up to thirty-eight separate satellites. Since the secondary payloads will fly on satellites designed for global wireless data services, each user can utilize low cost communication system already in place for sending and retrieving digital information from its payload.

International Space Station Alpha user payload operations concept

NASA Technical Reports Server (NTRS)

Schlagheck, Ronald A.; Crysel, William B.; Duncan, Elaine F.; Rider, James W.

1994-01-01

International Space Station Alpha (ISSA) will accommodate a variety of user payloads investigating diverse scientific and technology disciplines on behalf of five international partners: Canada, Europe, Japan, Russia, and the United States. A combination of crew, automated systems, and ground operations teams will control payload operations that require complementary on-board and ground systems. This paper presents the current planning for the ISSA U.S. user payload operations concept and the functional architecture supporting the concept. It describes various NASA payload operations facilities, their interfaces, user facility flight support, the payload planning system, the onboard and ground data management system, and payload operations crew and ground personnel training. This paper summarizes the payload operations infrastructure and architecture developed at the Marshall Space Flight Center (MSFC) to prepare and conduct ISSA on-orbit payload operations from the Payload Operations Integration Center (POIC), and from various user operations locations. The authors pay particular attention to user data management, which includes interfaces with both the onboard data management system and the ground data system. Discussion covers the functional disciplines that define and support POIC payload operations: Planning, Operations Control, Data Management, and Training. The paper describes potential interfaces between users and the POIC disciplines, from the U.S. user perspective.

Enabling Dedicated, Affordable Space Access Through Aggressive Technology Maturation

NASA Technical Reports Server (NTRS)

Jones, Jonathan; Kibbey, Tim; Lampton, Pat; Brown, Thomas

2014-01-01

A recent explosion in nano-sat, small-sat, and university class payloads has been driven by low cost electronics and sensors, wide component availability, as well as low cost, miniature computational capability and open source code. Increasing numbers of these very small spacecraft are being launched as secondary payloads, dramatically decreasing costs, and allowing greater access to operations and experimentation using actual space flight systems. While manifesting as a secondary payload provides inexpensive rides to orbit, these arrangements also have certain limitations. Small, secondary payloads are typically included with very limited payload accommodations, supported on a non interference basis (to the prime payload), and are delivered to orbital conditions driven by the primary launch customer. Integration of propulsion systems or other hazardous capabilities will further complicate secondary launch arrangements, and accommodation requirements. The National Aeronautics and Space Administration's Marshall Space Flight Center has begun work on the development of small, low cost launch system concepts that could provide dedicated, affordable launch alternatives to small, risk tolerant university type payloads and spacecraft. These efforts include development of small propulsion systems and highly optimized structural efficiency, utilizing modern advanced manufacturing techniques. This paper outlines the plans and accomplishments of these efforts and investigates opportunities for truly revolutionary reductions in launch and operations costs. Both evolution of existing sounding rocket systems to orbital delivery, and the development of clean sheet, optimized small launch systems are addressed. A launch vehicle at the scale and price point which allows developers to take reasonable risks with new propulsion and avionics hardware solutions does not exist today. Establishing this service provides a ride through the proverbial "valley of death" that lies between demonstration in laboratory and flight environments. This effort will provide the framework to mature both on-orbit and earth-to-orbit avionics and propulsion technologies while also providing dedicated, affordable access to LEO for cubesat class payloads.

SLS Overview and Progress

NASA Technical Reports Server (NTRS)

Honeycutt, John

2017-01-01

Space Launch System will be able to offer payload accommodations with five times more volume than any contemporary launch vehicle Payload fairings of up to 10-meter diameter are being studied Space Launch System will offer an initial capability of greater than 70 metric tons to low Earth orbit; current U.S. launch vehicle maximum is 28 t Evolved version of SLS will offer Mars-enabling capability of greater than 130 metric tons to LEO SLS offers reduced transit times to the outer solar system by half or greater Higher characteristic energy (C3) also enables larger payloads to destination

Earth-orbit mission considerations and Space Tug requirements.

NASA Technical Reports Server (NTRS)

Huber, W. G.

1973-01-01

The reusable Space Tug is a major system planned to augment the Space Shuttle's capability to deliver, retrieve, and support automated payloads. The Space Tug will be designed to perform round-trip missions from low earth orbit to geosynchronous orbit. Space Tug goals and requirements are discussed together with the characteristics of the full capability Tug. The Tug is to be operated in an unmanned 'teleoperator' fashion. Details of potential teleoperator applications are considered, giving attention to related systems studies, candidate Tug mission applications, Tug 'end-effector' alternatives, technical issues associated with Tug payload retrieval, and Tug/payload accommodations.

Thermal integration of Spacelab experiments

NASA Technical Reports Server (NTRS)

Patterson, W. C.; Hopson, G. D.

1978-01-01

The method of thermally integrating the experiments for Spacelab is discussed. The scientific payload consists of a combination of European and United States sponsored experiments located in the module as well as on a single Spacelab pallet. The thermal integration must result in accomodating the individual experiment requirements as well as ensuring that the total payload is within the Spacelab Environmental Control System (ECS) resource capability. An integrated thermal/ECS analysis of the module and pallet is performed in concert with the mission timeline to ensure that the agreed upon experiment requirements are accommodated and to ensure the total payload is within the Spacelab ECS resources.

A NASA Strategy for Leveraging Emerging Launch Vehicles for Routine, Small Payload Missions

NASA Technical Reports Server (NTRS)

Underwood, Bruce E.

2005-01-01

Orbital flight opportunities for small payloads have always been few and far between, and then on February 1, 2002, the situation got worse. In the wake of the loss of the Columbia during STS- 107, changing NASA missions and priorities led to the termination of the Shuttle Small Payloads Projects, including Get-Away Special, Hitcbker, and Space Experiment Module. In spite of the limited opportunities, long queue, and restrictions associated with flying experiments on a man-rated transportation system; the carriers provided a sustained, high quality experiment services for education, science, and technology payloads, and was one of the few games in town. Attempts to establish routine opportunities aboard existing ELVs have been unsuccessful, as the cost-per-pound on small ELVs and conflicts with primary spacecraft on larger vehicles have proven prohibitive. Ths has led to a backlog of existing NASA-sponsored payloads and no prospects or plans for fbture opportunities within the NASA community. The prospects for breaking out of this paradigm appear promising as a result of NASA s partnership with DARPA in pursuit of low-cost, responsive small ELVs under the Falcon Program. Through this partnership several new small ELVs, providing 1000 lbs. to LEO will be demonstrated in less than two years that promise costs that are reasonable enough that NASA, DoD, and other sponsors can once again invest in small payload opportunities. Within NASA, planning has already begun. NASA will be populating one or more of the Falcon demonstration flights with small payloads that are already under development. To accommodate these experiments, Goddard s Wallops Flight Facility has been tasked to develop a multi-payload ejector (MPE) to accommodate the needs of these payloads. The MPE capabilities and design is described in detail in a separately submitted abstract. Beyond use of the demonstration flights however, Goddard has already begun developing strategies to leverage these new ELVs as elements of a larger system designed to provide routine, low-cost end-to-end services for small science, Exploration, and education payloads. The plan leverages the management approaches of the successful Sounding Rocket Program and Shuttle Small Payloads Projects. The strategy consists of using a systems implementation approach of elements, including 1) Falcon ELVs, 2) advanced launch site technologies and processes, 3) suite of experiment carriers accommodating different mission requirements, 4) streamlined integration and test operations, 5 ) experiment brokering and management, and 6) standardized, distributed payload operations. The envisioned suite of carriers includes the MPE, a standard interface experiment carrier, and potentially a reentry fieeflyer experiment carrier. Key to the success of this strategy is standard experiment interfaces within the carriers to limit mission- unique tasks, establishmg and managing a program of scheduled reoccurring flights rather than discrete missions, and streamlined, centralized implementation of the elements. These individual elements are each under development and Goddard will demonstrate the overall system strategy low-cost small payload missions on the initial Falcon demonstration launches from Wallops. goal is to show that this model should be converted to a sustained NASA program supporting science, technology, and education, with annual flight opportunities. The paper will define in detail the various elements of the overall program, as well as provide status, philosophy, and strategy for the program that will hopefully once-and-for-all provide low-cost, routine access to space for the small payloads community.

STS-98 crew checks out the U.S. Lab Destiny in Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- Along with Scott Thurston (left), of the VITT office, members of the STS-98 crew Mission Specialist Robert Curbeam, Commander Ken Cockrell and Mission Specialist Marsha Ivins are in Atlantis''' payload bay to check out their mission payload, the U.S. Lab Destiny. The crew is at KSC for Terminal Countdown Demonstration Test activities, which also include a simulated launch countdown. A key element in the construction of the International Space Station, Destiny is a pressurized module designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 13 locations especially designed to support experiments. The module already has five system racks installed inside. Launch of STS-98 on its 11-day mission is scheduled for Jan. 19 at 2:11 a.m. EST.

Conducting Research on the International Space Station Using the EXPRESS Rack Facilities

NASA Technical Reports Server (NTRS)

Thompson, Sean W.; Lake, Robert E.

2014-01-01

EXPRESS Racks provide capability for payload access to ISS resources. The successful on-orbit operations and versatility of the EXPRESS Rack has facilitated the operations of many scientific areas, with the promise of continued payload support for years to come. EXPRESS Racks are currently deployed in the US Lab, Columbus and JEM. Process improvements and enhancements continue to improve the accommodations and make the integration and operations process more efficient. Payload Integration Managers serve as the primary interface between the ISS Program and EXPRESS Payload Developers. EXPRESS Project coordinates across multiple functional areas and organizations to ensure integrated EXPRESS Rack and subrack products and hardware are complete, accurate, on time, safe, and certified for flight. NASA is planning to expand the EXPRESS payload capacity by developing new Basic Express Racks expected to be on ISS in 2018.

STS-98 crew checks out the U.S. Lab Destiny in Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- STS-98 Mission Specialist Marsha Ivins (center, pointing) checks out the U.S. Lab Destiny in the payload bay of the orbiter Atlantis. The crew is at KSC for Terminal Countdown Demonstration Test activities, which also include a simulated launch countdown. Destiny, a key element in the construction of the International Space Station, is a pressurized module designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 13 locations especially designed to support experiments. The module already has five system racks installed inside. Launch of STS-98 on its 11-day mission is scheduled for Jan. 19 at 2:11 a.m. EST.

Approach to Spacelab Payload mission management

NASA Technical Reports Server (NTRS)

Craft, H. G.; Lester, R. C.

1978-01-01

The nucleus of the approach to Spacelab Payload mission management is the establishment of a single point of authority for the entire payload on a given mission. This single point mission manager will serve as a 'broker' between the individual experiments and the STS, negotiating agreements by two-part interaction. The payload mission manager, along with a small support team, will represent the users in negotiating use of STS accommodations. He will provide the support needed by each individual experimenter to meet the scientific, technological, and applications objectives of the mission with minimum cost and maximum efficiency. The investigator will assume complete responsibility for his experiment hardware definition and development and will take an active role in the integration and operation of his experiment.

Hitchhiker capabilities

NASA Technical Reports Server (NTRS)

Goldsmith, Theodore C.

1988-01-01

A carrier system has been developed for economical and quick response flight of small attached payloads on the space shuttle. Hitchhiker can accommodate up to 750 lb of customer payloads in canisters or mounted to an exposed side-mount plate, or up to 1200 lb mounted on a cross-bay structure. The carrier connects to the orbiter's electrical systems and provides up to six customers with standard electrical services including power, real time telemetry and commands. A transparent data and command system concept is employed to allow the customer to easily use his own ground support equipment and personnel to control his payload during integration and flight operations. A general description of the Hitchhiker program and the Shuttle Payload of Opportunity Carrier (SPOC) is given and future enhancements are outlined.

Multipurpose satellite bus (MPS)

NASA Technical Reports Server (NTRS)

1991-01-01

The Naval Postgraduate School Advanced Design Project sponsored by the Universities Space Research Association Advanced Design Program is a multipurpose satellite bus (MPS). The design was initiated from a Statement of Work (SOW) developed by the Defense Advanced Research Projects Agency (DARPA). The SOW called for a 'proposal to design a small, low-cost, lightweight, general purpose spacecraft bus capable of accommodating any of a variety of mission payloads. Typical payloads envisioned include those associated with meteorological, communication, surveillance and tracking, target location, and navigation mission areas.' The design project investigates two dissimilar missions, a meteorological payload and a communications payload, mated with a single spacecraft bus with minimal modifications. The MPS is designed for launch aboard the Pegasus Air Launched Vehicle (ALV) or the Taurus Standard Small Launch Vehicle (SSLV).

Study of an astronomical extreme ultraviolet rocket spectrometer for use on shuttle missions

NASA Technical Reports Server (NTRS)

Bowyer, C. S.

1977-01-01

The adaptation of an extreme ultraviolet astronomy rocket payload for flight on the shuttle was studied. A sample payload for determining integration and flight procedures for experiments which may typically be flown on shuttle missions was provided. The electrical, mechanical, thermal, and operational interface requirements between the payload and the orbiter were examined. Of particular concern was establishing a baseline payload accommodation which utilizes proven common hardware for electrical, data, command, and possibly real time monitoring functions. The instrument integration and checkout procedures necessary to assure satisfactory in-orbit instrument performance were defined and those procedures which can be implemented in such a way as to minimize their impact on orbiter integration schedules were identified.

Commerce Lab: Mission analysis. Payload integration study

NASA Technical Reports Server (NTRS)

Marvin, G. D.

1984-01-01

The objectives of the commerce lab mission analysis and payload integration study are discussed. A mission model which accommodates commercial users and provides a basic data base for future mission planning is described. The data bases developed under this study include: (1) user requirements; (2) apparatus capabilities and availabilities; and (3) carrier capabilities. These data bases are synthesized in a trades and analysis phase along with the STS flight opportunities. Optimum missions are identified.

Commerce Lab: Mission analysis and payload integration study

NASA Technical Reports Server (NTRS)

1984-01-01

The needs of an aggressive commercial microgravity program are identified, space missions are defined, and infrastructural issues are identified and analyzed. A commercial laboratory, commerce lab, is conceived to be one or more an array of carriers which would fly aboard the space shuttle and accommodate microgravity science experiment payloads. Commerce lab is seen as a logical transition between currently planned space shuttle missions and future microgravity missions centered around the space station.

Materials experiment carrier concepts definition study. Volume 2: Technical report, part 2

NASA Technical Reports Server (NTRS)

1981-01-01

A materials experiment carrier (MEC) that provides effective accommodation of the given baseline materials processing in space (MPS) payloads and demonstration of the MPS platform concept for high priority materials processing science, multidiscipline MPS investigations, host carrier for commercial MPS payloads, and system economy of orbital operations is defined. The study flow of task work is shown. Study tasks featured analysis and trades to identify the MEC system concept options.

Space Congress, 29th, Cocoa Beach, FL, Apr. 21-24, 1992, Proceedings

NASA Technical Reports Server (NTRS)

1992-01-01

The present volume on the quest for new frontiers in space discusses weather impacts on space operations, planning for the performance of future space bases, a new guidance and control unit for the Titan IV vehicle, and nondestructive evaluation of Shuttle Columbia tiles. Attention is given to Space Shuttle payload accommodations and trends in customer demands, a generic propellants transfer unit, making space part of general education, space station on-orbit solar array loads during assembly, and dimensional stability of the attitude reference assembly on SSF. Topics addressed include National Launch System payload accommodations and launch operations, the integrated factory/launch site processing concept, Pioneer 10 interstellar studies, and the role of advanced nuclear propulsion systems in precursor interstellar missions. Also discussed are legal challenges in realizing interstellar initiatives, Mars transportation system synthesis, and NASA's commercial space program.

ISS External Payload Platform - a new opportunity for research in the space environment

NASA Astrophysics Data System (ADS)

Steimle, Christian; Pape, Uwe

The International Space Station (ISS) is a widely accepted platform for research activities in low Earth orbit. To a wide extent these activities are conducted in the pressurised laboratories of the station and less in the outside environment. Suitable locations outside the ISS are rare, existing facilities fully booked for the coming years. To overcome this limitation, an external payload platform accessible for small size payloads on a commercial basis will be launched to the ISS and installed on the Japanese Experiment Module External Facility (JEM-EF) in the third quarter of 2014 and will be ready to be used by the scientific community on a fully commercial basis. The new External Payload Platform (EPP) and its opportunities and constraints assessed regarding future research activities on-board the ISS. The small size platform is realised in a cooperation between the companies NanoRacks, Astrium North America in the United States, and Airbus Defence and Space in Germany. The hardware allows the fully robotic installation and operation of payloads. In the nominal mission scenario payload items are installed not later than one year after the signature of the contract, stay in operation for 15 weeks, and can be returned to the scientist thereafter. Payload items are transported among the pressurised cargo usually delivered to the station with various supply vehicles. Due to the high frequency of flights and the flexibility of the vehicle manifests the risk of a delay in the payload readiness can be mitigated by delaying to the next flight opportunity which on average is available not more than two months later. The mission is extra-ordinarily fast and of low cost in comparison to traditional research conducted on-board the ISS and can fit into short-term funding cycles available on national and multi-national levels. The size of the payload items is limited by handling constraints on-board the ISS. Therefore, the standard experiment payload size is a multiple of a 4U CubeSat, which demands miniaturised hardware solutions. But every payload can extensively use all ISS resources required: mass is not limited, power only limited by the payload heat radiation capability, the datalink is a USB 2.0 standard bus enabling a real-time and private data link. The new EPP transforms the station into a true laboratory in space with the capability to support research in various fields: exposure of biologic or material samples, experiments related to the radiation environment in low Earth orbit, and more.

STS-65 Japanese Payload Specialist Mukai at CCT side hatch during training

NASA Image and Video Library

1993-11-22

STS-65 Japanese Payload Specialist Chiaki Mukai takes a break from training at the Johnson Space Center (JSC). Wearing a training version of the orange launch and entry suit (LES), Mukai stands at the crew compartment trainer (CCT) side hatch in the Mockup and Integration Laboratory (MAIL) Bldg 9NE. Note the crew escape system (CES) pole device extending out the side hatch which would accommodate crewmembers in bailout from a troubled spacecraft. Mukai represents the National Space Development Agency (NASDA) of Japan and will serve as a payload specialist aboard Columbia, Orbiter Vehicle (OV) 102, during the STS-65 International Microgravity Laboratory 2 (IML-2) mission.

NASA's Space Launch System: Progress Toward the Proving Ground

NASA Technical Reports Server (NTRS)

Jackman, Angie

2017-01-01

Space Launch System will be able to offer payload accommodations with five times more volume than any contemporary launch vehicle. center dot Payload fairings of up to 10-meter diameter are planned. Space Launch System will offer an initial capability of greater than 70 metric tons to low Earth orbit; current U.S. launch vehicle maximum is 28 t. center dot Evolved version of SLS will offer greatest-ever capability of greater than 130 t to LEO. SLS offers reduced transit times to the outer solar system by half or greater. center dot Higher characteristic energy (C3) also enables larger payloads to destination.

STS-65 Japanese Payload Specialist Mukai at CCT side hatch during training

NASA Technical Reports Server (NTRS)

1993-01-01

STS-65 Japanese Payload Specialist Chiaki Mukai takes a break from training at the Johnson Space Center (JSC). Wearing a training version of the orange launch and entry suit (LES), Mukai stands at the crew compartment trainer (CCT) side hatch in the Mockup and Integration Laboratory (MAIL) Bldg 9NE. Note the crew escape system (CES) pole device extending out the side hatch which would accommodate crewmembers in bailout from a troubled spacecraft. Mukai represents the National Space Development Agency (NASDA) of Japan and will serve as a payload specialist aboard Columbia, Orbiter Vehicle (OV) 102, during the STS-65 International Microgravity Laboratory 2 (IML-2) mission.

Large Payload Transportation and Test Considerations

NASA Technical Reports Server (NTRS)

Rucker, Michelle A.; Pope, James C.

2011-01-01

Ironically, the limiting factor to a national heavy lift strategy may not be the rocket technology needed to throw a heavy payload, but rather the terrestrial infrastructure - roads, bridges, airframes, and buildings - necessary to transport, acceptance test, and process large spacecraft. Failure to carefully consider how large spacecraft are designed, and where they are manufactured, tested, or launched, could result in unforeseen cost to modify/develop infrastructure, or incur additional risk due to increased handling or elimination of key verifications. During test and verification planning for the Altair project, a number of transportation and test issues related to the large payload diameter were identified. Although the entire Constellation Program - including Altair - was canceled in the 2011 NASA budget, issues identified by the Altair project serve as important lessons learned for future payloads that may be developed to support national "heavy lift" strategies. A feasibility study performed by the Constellation Ground Operations (CxGO) project found that neither the Altair Ascent nor Descent Stage would fit inside available transportation aircraft. Ground transportation of a payload this large over extended distances is generally not permitted by most states, so overland transportation alone would not have been an option. Limited ground transportation to the nearest waterway may be permitted, but water transportation could take as long as 66 days per production unit, depending on point of origin and acceptance test facility; transportation from the western United States would require transit through the Panama Canal to access the Kennedy Space Center launch site. Large payloads also pose acceptance test and ground processing challenges. Although propulsion, mechanical vibration, and reverberant acoustic test facilities at NASA s Plum Brook Station have been designed to accommodate large spacecraft, special handling and test work-arounds may be necessary, which could increase cost, schedule, and technical risk. Once at the launch site, there are no facilities currently capable of accommodating the combination of large payload size and hazardous processing (which includes hypergolic fuels, pyrotechnic devices, and high pressure gasses).

Design criteria for payload workstation accommodations

NASA Technical Reports Server (NTRS)

Watters, H. H.; Stokes, J. W.

1975-01-01

Anticipated shuttle sortie payload man-system design criteria needs are investigated. Man-system interactions for the scientific disciplines are listed and the extent is assessed to which documented Skylab experience is expected to provide system design guidance for each of the identified interactions. Where the analysis revealed that the reduced Skylab data does not answer the anticipated needs candidate criteria, based on unreduced Skylab data, available prior research, original analysis, or related requirements derived from previous space programs, are provided.

Second United States Microgravity Payload: One Year Report

NASA Technical Reports Server (NTRS)

Curreri, Peter A. (Editor); McCauley, Dannah E. (Editor)

1996-01-01

The second United States Microgravity Payload (USMP-2), flown in March 1994, carried four major microgravity experiments plus a sophisticated accelerometer system. The USMP program is designed to accommodate experiments requiring extensive resources short of a full Spacelab mission. The four USMP-2 experiments dealt with understanding fundamental aspects of materials behavior, three with the formation of crystals from melts and one with the critical point of a noble gas. This successful, scientifically rich mission also demonstrated telescience operations.

Spacehab

NASA Technical Reports Server (NTRS)

Rossi, David

1991-01-01

Information is given in viewgraph form on the Spacehab company and its work on a pressurized module to be carried on the Space Shuttle. The module augments the Shuttle's capability to support man-tended microgravity experiments. The augmentation modules are designed to duplicate the resources, such as power, environmental control, and data management that are available in the Shuttle's middeck. Topics covered include a company overview, company financing, system overview, module description, payload resources, locker accommodations, program status, and a listing of candidate payloads.

Space Launch System Trans Lunar Payload Delivery Capability

NASA Technical Reports Server (NTRS)

Jackman, A. L.; Smith, D. A.

2016-01-01

NASA Marshall Space Flight Center (MSFC) has successfully completed the Critical Design Review (CDR) of the heavy lift Space Launch System (SLS) and is working towards first flight of the vehicle in 2018. SLS will begin flying crewed missions with an Orion to a lunar vicinity every year after the first 2 flights starting in the early 2020's. So as early as 2021 these Orion flights will deliver ancillary payload, termed "Co-Manifested Payload", with a mass of at least 5.5 metric tons and volume up to 280 cubic meters to a cis-lunar destination. Later SLS flights have a goal of delivering as much as 10 metric tons to a cis-lunar destination. This presentation will describe the ground and flight accommodations, interfaces, and resources planned to be made available to Co-Manifested Payload providers as part of the SLS system. An additional intention is to promote a two-way dialogue between vehicle developers and potential payload users in order to most efficiently evolve required SLS capabilities to meet diverse payload requirements.

Conceptual design study Science and Applications Space Platform SASP. Volume 2: Technical report

NASA Technical Reports Server (NTRS)

Runge, F. C.

1980-01-01

The platform payload accommodations, configuration drivers, and power system are described in detail. The platform design was analyzed and is presented. Demonstration tests are described and the results are reported.

STS-98 crew checks out the U.S. Lab Destiny in Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- In the payload bay of the orbiter Atlantis, STS-98 Mission Specialist Robert Curbeam works with equipment he will use in space to attach the U.S. Lab Destiny to the International Space Station. The crew is at KSC for Terminal Countdown Demonstration Test activities, which also include a simulated launch countdown. A key element in the construction of the International Space Station, Destiny is a pressurized module designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 13 locations especially designed to support experiments. The module already has five system racks installed inside. Launch of STS-98 on its 11-day mission is scheduled for Jan. 19 at 2:11 a.m. EST.

STS-98 crew checks out the U.S. Lab Destiny in Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- In the payload bay of the orbiter Atlantis, STS-98 Mission Specialists Thomas Jones (left) and Robert Curbeam (right) talk about their mission, attaching the U.S. Lab Destiny (in the background) to the International Space Station. The crew is at KSC for Terminal Countdown Demonstration Test activities, which also include a simulated launch countdown. A key element in the construction of the International Space Station, Destiny is a pressurized module designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 13 locations especially designed to support experiments. The module already has five system racks installed inside. Launch of STS-98 on its 11-day mission is scheduled for Jan. 19 at 2:11 a.m. EST.

International Space Station Columbus Payload SoLACES Degradation Assessment

NASA Technical Reports Server (NTRS)

Hartman, William A.; Schmidl, William D.; Mikatarian, Ron; Soares, Carlos; Schmidtke, Gerhard; Erhardt, Christian

2016-01-01

SOLAR is a European Space Agency (ESA) payload deployed on the International Space Station (ISS) and located on the Columbus Laboratory. It is located on the Columbus External Payload Facility in a zenith location. The objective of the SOLAR payload is to study the Sun. The SOLAR payload consists of three instruments that allow for measurement of virtually the entire electromagnetic spectrum (17 nm to 2900 nm). The three payload instruments are SOVIM (SOlar Variable and Irradiance Monitor), SOLSPEC (SOLar SPECctral Irradiance measurements), and SolACES (SOLar Auto-Calibrating Extreme UV/UV Spectrophotometers).

ISS External Contamination Environment for Space Science Utilization

NASA Technical Reports Server (NTRS)

Soares, Carlos; Mikatarian, Ron; Steagall, Courtney; Huang, Alvin; Koontz, Steven; Worthy, Erica

2014-01-01

(1) The International Space Station is the largest and most complex on-orbit platform for space science utilization in low Earth orbit, (2) Multiple sites for external payloads, with exposure to the associated natural and induced environments, are available to support a variety of space science utilization objectives, (3) Contamination is one of the induced environments that can impact performance, mission success and science utilization on the vehicle, and (4)The ISS has been designed, built and integrated with strict contamination requirements to provide low levels of induced contamination on external payload assets.

Astrophysical payload accommodation on the space station

NASA Technical Reports Server (NTRS)

Woods, B. P.

1985-01-01

Surveys of potential space station astrophysics payload requirements and existing point mount design concepts were performed to identify potential design approaches for accommodating astrophysics instruments from space station. Most existing instrument pointing systems were designed for operation from the space shuttle and it is unlikely that they will sustain their performance requirements when exposed to the space station disturbance environment. The technology exists or is becoming available so that precision pointing can be provided from the space station manned core. Development of a disturbance insensitive pointing mount is the key to providing a generic system for space station. It is recommended that the MSFC Suspended Experiment Mount concept be investigated for use as part of a generic pointing mount for space station. Availability of a shirtsleeve module for instrument change out, maintenance and repair is desirable from the user's point of view. Addition of a shirtsleeve module on space station would require a major program commitment.

Atmospheric, Magnetospheric and Plasmas in Space (AMPS) spacelab payload definition study. Volume 3: Interface control documents. Part 2: AMPS payload to spacelab ICD

NASA Technical Reports Server (NTRS)

1976-01-01

The AMPS to Spacelab Interface Control Document which is to be used as a guide for format and information content in generating specific AMPS Mission ICDs is presented. This document is meant to supplement the Spacelab Payload Accommodations Handbook in that it only defines interfaces which are not discussed in the handbook to the level required for design purposes. The AMPS Top Level Requirements Tree, illustrates this ICD by a shaded area and its relationship to the other AMPS technical documents. Other interface documents shown are the Level II, AMPS to Space Shuttle Vehicle ICD and the Level III, AMPS to Instruments ICD.

Materials experiment carrier concepts definition study. Volume 3: Programmatics, part 2

NASA Technical Reports Server (NTRS)

1981-01-01

Project logic, schedule and funding information was derived to enable decisions to be made regarding implementation of MEC system development. A master schedule and cost and price estimates (ROM) were developed for a project that consists of development of an all-up MEC, its integration with payloads and its flight on one 90 day mission. In Part 2 of the study a simple initial MEC was defined to accommodate three MPS baseline payloads. The design of this initial MEC is illustrated. The project logic, detailed schedules, and ROM cost estimate relate to a project in which this initial MEC is developed, integrated with payloads and flown once for 180 days.

STS-98 crew checks out the U.S. Lab Destiny in Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- Members of the STS-98 crew, along with Scott Thurston (left), with the VITT office, check out the U.S. Lab Destiny in the payload bay of the orbiter Atlantis. Wearing white caps are Commander Ken Cockrell (center) and Mission Specialist Marsha Ivins (right). The crew is at KSC for Terminal Countdown Demonstration Test activities, which include a simulated launch countdown. Destiny, a key element in the construction of the International Space Station, is a pressurized module designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 13 locations especially designed to support experiments. The module already has five system racks installed inside. Launch of STS-98 on its 11-day mission is scheduled for Jan. 19 at 2:11 a.m. EST.

STS-98 crew checks out the U.S. Lab Destiny in Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- STS-98 Mission Specialist Robert Curbeam (left), Commander Ken Cockrell (center) and Mission Specialist Marsha Ivins (right) look over the U.S. Lab Destiny in the payload bay of the orbiter Atlantis. Behind Ivins is Scott Thurston, of the VITT office. The crew is at KSC for Terminal Countdown Demonstration Test activities, which also include a simulated launch countdown. A key element in the construction of the International Space Station, Destiny is a pressurized module designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 13 locations especially designed to support experiments. The module already has five system racks installed inside. Launch of STS-98 on its 11-day mission is scheduled for Jan. 19 at 2:11 a.m. EST.

Large Payload Ground Transportation and Test Considerations

NASA Technical Reports Server (NTRS)

Rucker, Michelle A.

2016-01-01

Many spacecraft concepts under consideration by the National Aeronautics and Space Administration’s (NASA’s) Evolvable Mars Campaign take advantage of a Space Launch System payload shroud that may be 8 to 10 meters in diameter. Large payloads can theoretically save cost by reducing the number of launches needed--but only if it is possible to build, test, and transport a large payload to the launch site in the first place. Analysis performed previously for the Altair project identified several transportation and test issues with an 8.973 meters diameter payload. Although the entire Constellation Program—including Altair—has since been canceled, these issues serve as important lessons learned for spacecraft designers and program managers considering large payloads for future programs. A transportation feasibility study found that, even broken up into an Ascent and Descent Module, the Altair spacecraft would not fit inside available aircraft. Ground transportation of such large payloads over extended distances is not generally permitted, so overland transportation alone would not be an option. Limited ground transportation to the nearest waterway may be possible, but water transportation could take as long as 67 days per production unit, depending on point of origin and acceptance test facility; transportation from the western United States would require transit through the Panama Canal to access the Kennedy Space Center launch site. Large payloads also pose acceptance test and ground processing challenges. Although propulsion, mechanical vibration, and reverberant acoustic test facilities at NASA’s Plum Brook Station have been designed to accommodate large spacecraft, special handling and test work-arounds may be necessary, which could increase cost, schedule, and technical risk. Once at the launch site, there are no facilities currently capable of accommodating the combination of large payload size and hazardous processing such as hypergolic fuels, pyrotechnic devices, and high pressure gasses. Ironically, the limiting factor to a national heavy lift strategy may not be the rocket technology needed to throw a heavy payload, but rather the terrestrial infrastructure—roads, bridges, airframes, and buildings—necessary to transport, acceptance test, and process large spacecraft. Failure to carefully consider where and how large spacecraft are manufactured, tested, and launched could result in unforeseen cost to modify existing (or develop new) infrastructure, or incur additional risk due to increased handling operations or eliminating key verifications. Although this paper focuses on the canceled Altair spacecraft as a case study, the issues identified here have wide applicability to other large payloads, including concepts under consideration for NASA’s Evolvable Mars Campaign.

A study of the effect on a typical orbiter payload thermal environment resulting from specular reflections from the forward orbiter radiators

NASA Technical Reports Server (NTRS)

Humphries, R.; Turner, L.; Littles, J. W.

1979-01-01

The orbiter radiator external coating is highly specular silverized Teflon. Solar energy specularly reflected from these radiators on a typical payload which, when deployed, extends above the payload bay envelope was studied. The flux levels are compared assuming both diffuse and specular radiators.

Space Station Freedom user's guide

NASA Technical Reports Server (NTRS)

1992-01-01

This guide is intended to inform prospective users of the accommodations and resources provided by the Space Station Freedom program. Using this information, they can determine if Space Station Freedom is an appropriate laboratory or facility for their research objectives. The steps that users must follow to fly a payload on Freedom are described. This guide covers the accommodations and resources available on the Space Station during the Man-Tended Capability (MTC) period, scheduled to begin the end of 1996, and a Permanently Manned Capability (PMC) beginning in late 1999.

Space Station needs, attributes and architectural options. Volume 2, book 1, part 4: Payload element mission data sheets

NASA Technical Reports Server (NTRS)

1984-01-01

Data sheets are presented for 11 internal payloads, 30 externally mounted payloads, and 46 free flyers. The importance of the space station to each payload element is rated on a scale of 1 to 10. The type of experiment noncommercial science and applications, commercial, technological, and operational is indicated and the payload and its objectives are described. Space is provided for noting requirements for power; data/communication; thermal environment; equipment physical characteristics; crew size; and service and maintenance.

Characterization of spacecraft and environmental disturbances on a SmallSat

NASA Technical Reports Server (NTRS)

Johnson, Thomas A.; Nguyen, Dung Phu Chi; Cuda, Vince; Freesland, Doug

1994-01-01

The objective of this study is to model the on-orbit vibration environment encountered by a SmallSat. Vibration control issues are common to the Earth observing, imaging, and microgravity communities. A spacecraft may contain dozens of support systems and instruments each a potential source of vibration. The quality of payload data depends on constraining vibration so that parasitic disturbances do not affect the payload's pointing or microgravity requirement. In practice, payloads are designed incorporating existing flight hardware in many cases with nonspecific vibration performance. Thus, for the development of a payload, designers require a thorough knowledge of existing mechanical devices and their associated disturbance levels. This study evaluates a SmallSat mission and seeks to answer basic questions concerning on-orbit vibration. Payloads were considered from the Earth observing, microgravity, and imaging communities. Candidate payload requirements were matched to spacecraft bus resources of present day SmallSats. From the set of candidate payloads, the representative payload GLAS (Geoscience Laser Altimeter System) was selected. The requirements of GLAS were considered very stringent for the 150 - 500 kg class of payloads. Once the payload was selected, a generic SmallSat was designed in order to accommodate the payload requirements (weight, size, power, etc.). This study seeks to characterize the on-orbit vibration environment of a SmallSat designed for this type of mission and to determine whether a SmallSat can provide the precision pointing and jitter control required for earth observing payloads.

International Space Station (ISS)

NASA Image and Video Library

2001-02-01

The Payload Operations Center (POC) is the science command post for the International Space Station (ISS). Located at NASA's Marshall Space Flight Center in Huntsville, Alabama, it is the focal point for American and international science activities aboard the ISS. The POC's unique capabilities allow science experts and researchers around the world to perform cutting-edge science in the unique microgravity environment of space. The POC is staffed around the clock by shifts of payload flight controllers. At any given time, 8 to 10 flight controllers are on consoles operating, plarning for, and controlling various systems and payloads. This photograph shows the Timeline Change Officer (TCO) at a work station. The TCO maintains the daily schedule of science activities and work assignments, and works with planners at Mission Control at Johnson Space Center in Houston, Texas, to ensure payload activities are accommodated in overall ISS plans and schedules.

Early Spacelab missions

NASA Technical Reports Server (NTRS)

Pace, R. E., Jr.; Craft, H. G., Jr.

1977-01-01

NASA has issued payload flight assignments for the first three Spacelab missions. The first two of these missions will have dual objectives, that of verifying Spacelab system performance and accomplishing meaningful space research. The first of these missions will be a joint NASA and ESA mission with a multidisciplinary payload. The second mission will verify a different Spacelab configuration while addressing the scientific disciplines of astrophysics. The third assigned mission will concentrate on utilizing the capabilities of Spacelab to perform meaningful experiments in space applications, primarily space processing. The paper describes these missions with their objectives, planned configuration and accommodation.

KSC-07pd2416

NASA Image and Video Library

2007-09-10

KENNEDY SPACE CENTER, FLA. -- In bay 3 of the Orbiter Processing Facility, a tool storage assembly unit is being moved for storage in Discovery's payload bay. The tools may be used on a spacewalk, yet to be determined, during mission STS-120. In an unusual operation, the payload bay doors had to be reopened after closure to accommodate the storage. Space shuttle Discovery is targeted to launch Oct. 23 to the International Space Station. It will carry the U.S. Node 2, a connecting module, named Harmony, for assembly on the space station. Photo credit: NASA/Amanda Diller

Definition of technology development missions for early space station, orbit transfer vehicle servicing, volume 2

NASA Technical Reports Server (NTRS)

1983-01-01

Propellant transfer, storage, and reliquefaction TDM; docking and berthing technology development mission; maintenance technology development mission; OTV/payload integration, space station interface/accommodations; combined TDM conceptual design; programmatic analysis; and TDM equipment usage are discussed.

Attached shuttle payload carriers: Versatile and affordable access to space

NASA Technical Reports Server (NTRS)

1990-01-01

The shuttle has been primarily designed to be a versatile vehicle for placing a variety of scientific and technological equipment in space including very large payloads; however, since many large payloads do not fill the shuttle bay, the space and weight margins remaining after the major payloads are accommodated often can be made available to small payloads. The Goddard Space Flight Center (GSFC) has designed standardized mounting structures and other support systems, collectively called attached shuttle payload (ASP) carriers, to make this additional space available to researchers at a relatively modest cost. Other carrier systems for ASP's are operated by other NASA centers. A major feature of the ASP carriers is their ease of use in the world of the Space Shuttle. ASP carriers attempt to minimized the payload interaction with Space Transportation System (STS) operations whenever possible. Where this is not possible, the STS services used are not extensive. As a result, the interfaces between the carriers and the STS are simplified. With this near autonomy, the requirements for supporting documentation are considerably lessened and payload costs correspondingly reduced. The ASP carrier systems and their capabilities are discussed in detail. The range of available capabilities assures that an experimenter can select the simplest, most cost-effective carrier that is compatible with his or her experimental objectives. Examples of payloads which use ASP basic hardware in nonstandard ways are also described.

14 CFR 1214.106 - Minor delays.

Code of Federal Regulations, 2011 CFR

2011-01-01

... Space Shuttle Flights of Payloads for Non-U.S. Government, Reimbursable Customers § 1214.106 Minor delays. NASA will attempt to accommodate customer requested minor launch delays. Such delays will... will require NASA's approval and will result in an additional charge as established in the launch...

14 CFR 1214.106 - Minor delays.

Code of Federal Regulations, 2012 CFR

2012-01-01

... Space Shuttle Flights of Payloads for Non-U.S. Government, Reimbursable Customers § 1214.106 Minor delays. NASA will attempt to accommodate customer requested minor launch delays. Such delays will... will require NASA's approval and will result in an additional charge as established in the launch...

14 CFR 1214.106 - Minor delays.

Code of Federal Regulations, 2013 CFR

2013-01-01

... Space Shuttle Flights of Payloads for Non-U.S. Government, Reimbursable Customers § 1214.106 Minor delays. NASA will attempt to accommodate customer requested minor launch delays. Such delays will... will require NASA's approval and will result in an additional charge as established in the launch...

14 CFR 1214.106 - Minor delays.

Code of Federal Regulations, 2010 CFR

2010-01-01

... Space Shuttle Flights of Payloads for Non-U.S. Government, Reimbursable Customers § 1214.106 Minor delays. NASA will attempt to accommodate customer requested minor launch delays. Such delays will... will require NASA's approval and will result in an additional charge as established in the launch...

The 25 kW power module evolution study. Part 2: Payload supports system evolution

NASA Technical Reports Server (NTRS)

1978-01-01

The addition of system elements for the 25 kW power module and logical evolutionary paths, by discrete growth stages, to provide capability for accommodating the increasing mission requirements through the early 1990's within reasonable resources are conceptualized.

Japanese experiment module (JEM)

NASA Technical Reports Server (NTRS)

Kato, T.

1986-01-01

Japanese hardware elements studied during the definition phase of phase B are described. The hardware is called JEM (Japanese Experiment Module) and will be attached to the Space Station core. JEM consists of a pressurized module, an exposed facility, a scientific/equipment airlock, a local remote manipulator, and experimental logistic module. With all those hardware elements JEM will accommodate general scientific and technology development research (some of the elements are to utilize the advantage of the microgravity environment), and also accommodate control panels for the Space Station Mobile Remote Manipulator System and attached payloads.

Adaptive output-based command shaping for sway control of a 3D overhead crane with payload hoisting and wind disturbance

NASA Astrophysics Data System (ADS)

Abdullahi, Auwalu M.; Mohamed, Z.; Selamat, H.; Pota, Hemanshu R.; Zainal Abidin, M. S.; Ismail, F. S.; Haruna, A.

2018-01-01

Payload hoisting and wind disturbance during crane operations are among the challenging factors that affect a payload sway and thus, affect the crane's performance. This paper proposes a new online adaptive output-based command shaping (AOCS) technique for an effective payload sway reduction of an overhead crane under the influence of those effects. This technique enhances the previously developed output-based command shaping (OCS) which was effective only for a fixed system and without external disturbances. Unlike the conventional input shaping design technique which requires the system's natural frequency and damping ratio, the proposed technique is designed by using the output signal and thus, an online adaptive algorithm can be formulated. To test the effectiveness of the AOCS, experiments are carried out using a laboratory overhead crane with a payload hoisting in the presence of wind, and with different payloads. The superiority of the method is confirmed by 82% and 29% reductions in the overall sway and the maximum transient sway respectively, when compared to the OCS, and two robust input shapers namely Zero Vibration Derivative-Derivative and Extra-Insensitive shapers. Furthermore, the method demonstrates a uniform crane's performance under all conditions. It is envisaged that the proposed method can be very useful in designing an effective controller for a crane system with an unknown payload and under the influence of external disturbances.

An analytical method for predicting the geometrical and optical properties of the human lens under accommodation

PubMed Central

Sheil, Conor J.; Bahrami, Mehdi; Goncharov, Alexander V.

2014-01-01

We present an analytical method to describe the accommodative changes in the human crystalline lens. The method is based on the geometry-invariant lens model, in which the gradient-index (GRIN) iso-indicial contours are coupled to the external shape. This feature ensures that any given number of iso-indicial contours does not change with accommodation, which preserves the optical integrity of the GRIN structure. The coupling also enables us to define the GRIN structure if the radii and asphericities of the external lens surfaces are known. As an example, the accommodative changes in lenticular radii and central thickness were taken from the literature, while the asphericities of the external surfaces were derived analytically by adhering to the basic physical conditions of constant lens volume and its axial position. The resulting changes in lens geometry are consistent with experimental data, and the optical properties are in line with expected values for optical power and spherical aberration. The aim of the paper is to provide an anatomically and optically accurate lens model that is valid for 3 mm pupils and can be used as a new tool for better understanding of accommodation. PMID:24877022

An analytical method for predicting the geometrical and optical properties of the human lens under accommodation.

PubMed

Sheil, Conor J; Bahrami, Mehdi; Goncharov, Alexander V

2014-05-01

We present an analytical method to describe the accommodative changes in the human crystalline lens. The method is based on the geometry-invariant lens model, in which the gradient-index (GRIN) iso-indicial contours are coupled to the external shape. This feature ensures that any given number of iso-indicial contours does not change with accommodation, which preserves the optical integrity of the GRIN structure. The coupling also enables us to define the GRIN structure if the radii and asphericities of the external lens surfaces are known. As an example, the accommodative changes in lenticular radii and central thickness were taken from the literature, while the asphericities of the external surfaces were derived analytically by adhering to the basic physical conditions of constant lens volume and its axial position. The resulting changes in lens geometry are consistent with experimental data, and the optical properties are in line with expected values for optical power and spherical aberration. The aim of the paper is to provide an anatomically and optically accurate lens model that is valid for 3 mm pupils and can be used as a new tool for better understanding of accommodation.

Small Satellites for Secondary Students

NASA Astrophysics Data System (ADS)

Zack, Kevin; Cominsky, Lynn

2012-11-01

Small Satellites for Secondary Students is a program funded by a three-year grant from NASA to bridge the gap in STEM education for secondary-school students. This is accomplished by creating the educational resources that are needed to support the development of a small scientific payload in alignment with scientific and technological education standards. The prototype payloads are flexible multi-experiment platforms designed to accommodate a wide range of student abilities with minimal resource requirements. The heart of each payload is an Arduino microcontroller which communicates with components that provide sensor data, Global Positioning System information, and which offer on-board data storage. The payload is built with off-the-shelf components and a pre-etched, custom-designed connector board. The platform also supports real-time telemetry updates through the use of Wi-Fi. To date, the prototype payloads have been tested on both high-powered rockets reaching over 3km and weather balloons tethered at 300m. Multiple successful rocket test runs reaching 1km have been conducted in partnership with amateur rocket clubs including the Association of Experimental Rocketry of the Pacific. From these flights, we are continuing to improve the payload design in order to increase the likelihood of student success.

A distributed planning concept for Space Station payload operations

NASA Technical Reports Server (NTRS)

Hagopian, Jeff; Maxwell, Theresa; Reed, Tracey

1994-01-01

The complex and diverse nature of the payload operations to be performed on the Space Station requires a robust and flexible planning approach. The planning approach for Space Station payload operations must support the phased development of the Space Station, as well as the geographically distributed users of the Space Station. To date, the planning approach for manned operations in space has been one of centralized planning to the n-th degree of detail. This approach, while valid for short duration flights, incurs high operations costs and is not conducive to long duration Space Station operations. The Space Station payload operations planning concept must reduce operations costs, accommodate phased station development, support distributed users, and provide flexibility. One way to meet these objectives is to distribute the planning functions across a hierarchy of payload planning organizations based on their particular needs and expertise. This paper presents a planning concept which satisfies all phases of the development of the Space Station (manned Shuttle flights, unmanned Station operations, and permanent manned operations), and the migration from centralized to distributed planning functions. Identified in this paper are the payload planning functions which can be distributed and the process by which these functions are performed.

Preliminary study of family accommodation in youth with autism spectrum disorders and anxiety: Incidence, clinical correlates, and behavioral treatment response.

PubMed

Storch, Eric A; Zavrou, Sophia; Collier, Amanda B; Ung, Danielle; Arnold, Elysse B; Mutch, P Jane; Lewin, Adam B; Murphy, Tanya K

2015-08-01

Anxiety symptoms are common in youth with autism spectrum disorders (ASD) and directly associated with symptom severity and functional impairment. Family accommodation occurs frequently among individuals with obsessive-compulsive and anxiety disorders; to date, no data exist on the nature and correlates of family accommodation in youth with ASD and anxiety, as well as its relationship to cognitive-behavioral therapy outcome. Forty children with ASD and a comorbid anxiety disorder participated. Clinicians administered measures of ASD and anxiety disorder caseness, anxiety symptom severity, and family accommodation; parents completed questionnaires assessing social responsiveness, internalizing and externalizing behaviors, and functional impairment. A subsample of youth (n = 24) completed a course of cognitive-behavioral therapy. Family accommodation was common and positively correlated with anxiety symptom severity, but not functional impairment, general internalizing symptoms, externalizing behavior, or social responsiveness. Family accommodation decreased following cognitive-behavioral therapy with decreases in family accommodation being associated with decreases in anxiety levels. Treatment responders reported lower family accommodation frequency and lower parent impact relative to non-responders. Clinical implications of this study in assessing and psychotherapeutically treating youth with ASD and comorbid anxiety are discussed. Copyright © 2015 Elsevier Ltd. All rights reserved.

Space Station as a Long Duration Exposure Facility

NASA Technical Reports Server (NTRS)

Folley, Adrienne; Scheib, Jim

1995-01-01

There is need for a space platform for experiments investigating long duration exposure to space. This platform should be maintainable in the event of a malfunction, and experiments should be easily recoverable for analysis on Earth. The International Space Station provides such a platform. The current Space Station configuration has six external experiment attachment sites, providing utilities and data support distributed along the external truss. There are also other sites that could potentially support long duration exposure experiments. This paper describes the resources provided to payloads at these sites, and cites examples of integration of proposed long duration exposure experiments on these sites. The environments to which external attached payloads will be exposed are summarized.

FASTSAT a Mini-Satellite Mission...A Way Ahead

NASA Technical Reports Server (NTRS)

Boudreaux, Mark; Pearson, Steve; Casas, Joseph

2012-01-01

The Fast Affordable Science and Technology Spacecraft (FASTSAT) is a mini-satellite weighing less than 150 kg. FASTSAT was developed as government-industry collaborative research and development flight project targeting rapid access to space to provide an alternative, low cost platform for a variety of scientific, research, and technology payloads. The initial spacecraft was designed to carry six instruments and launch as a secondary rideshare payload. This design approach greatly reduced overall mission costs while maximizing the on-board payload accommodations. FASTSAT was designed from the ground up to meet a challenging short schedule using modular components with a flexible, configurable layout to enable a broad range of payloads at a lower cost and shorter timeline than scaling down a more complex spacecraft. The integrated spacecraft along with its payloads were readied for launch 15 months from authority to proceed. As an ESPA-class spacecraft, FASTSAT is compatible with many different launch vehicles, including Minotaur I, Minotaur IV, Delta IV, Atlas V, Pegasus, Falcon 1/1e, and Falcon 9. These vehicles offer an array of options for launch sites and provide for a variety of rideshare possibilities.

Numerical Estimation of Sound Transmission Loss in Launch Vehicle Payload Fairing

NASA Astrophysics Data System (ADS)

Chandana, Pawan Kumar; Tiwari, Shashi Bhushan; Vukkadala, Kishore Nath

2017-08-01

Coupled acoustic-structural analysis of a typical launch vehicle composite payload faring is carried out, and results are validated with experimental data. Depending on the frequency range of interest, prediction of vibro-acoustic behavior of a structure is usually done using the finite element method, boundary element method or through statistical energy analysis. The present study focuses on low frequency dynamic behavior of a composite payload fairing structure using both coupled and uncoupled vibro-acoustic finite element models up to 710 Hz. A vibro-acoustic model, characterizing the interaction between the fairing structure, air cavity, and satellite, is developed. The external sound pressure levels specified for the payload fairing's acoustic test are considered as external loads for the analysis. Analysis methodology is validated by comparing the interior noise levels with those obtained from full scale Acoustic tests conducted in a reverberation chamber. The present approach has application in the design and optimization of acoustic control mechanisms at lower frequencies.

Space Station Freedom resource allocation accommodation of technology payload requirements

NASA Technical Reports Server (NTRS)

Avery, Don E.; Collier, Lisa D.; Gartrell, Charles F.

1990-01-01

An overview of the Office of Aeronautics, Exploration, and Technology (OAET) Space Station Freedom Technology Payload Development Program is provided, and the OAET Station resource requirements are reviewed. The requirements are contrasted with current proposed resource allocations. A discussion of the issues and conclusions are provided. It is concluded that an overall 20 percent resource allocation is appropriate to support OAET's technology development program, that some resources are inadequate even at the 20 percent level, and that bartering resources among U.S. users and international partners and increasing the level of automation may be viable solutions to the resource constraint problem.

Space station needs, attributes, and architectural options study

NASA Technical Reports Server (NTRS)

1983-01-01

The top level, time-phased total space program support system architecture is described including progress from the use of ground-based space shuttle, teleoperator system, extended duration orbiter, and multimission spacecraft, to an initial 4-man crew station at 29 deg inclination in 1991, to a growth station with an 8-man crew with capabilities for OTV high energy orbit payload placement and servicing, assembly, and construction of mission payloads in 1994. System Z, proposed for Earth observation missions in high inclination orbit, can be accommodated in 1993 using a space station derivative platform. Mission definition, system architecture, and benefits are discussed.

A Simplified Shuttle Payload Thermal Analyzer /SSPTA/ program

NASA Technical Reports Server (NTRS)

Bartoszek, J. T.; Huckins, B.; Coyle, M.

1979-01-01

A simple thermal analysis program for Space Shuttle payloads has been developed to accommodate the user who requires an easily understood but dependable analytical tool. The thermal analysis program includes several thermal subprograms traditionally employed in spacecraft thermal studies, a data management system for data generated by the subprograms, and a master program to coordinate the data files and thermal subprograms. The language and logic used to run the thermal analysis program are designed for the small user. In addition, analytical and storage techniques which conserve computer time and minimize core requirements are incorporated into the program.

Boeing 747 aircraft with large external pod for transporting outsize cargo

NASA Technical Reports Server (NTRS)

Price, J. E.; Quartero, C. B.; Smith, P. M.; Washburn, G. F.

1979-01-01

The effect on structural arrangement, system weight, and range performance of the cargo pod payload carrying capability was determined to include either the bridge launcher or a spacelab module on a Boeing 747 aircraft. Modifications to the carrier aircraft and the installation time required to attach the external pod to the 747 were minimized. Results indicate that the increase in pod size was minimal, and that the basic 747 structure was adequate to safely absorb the load induced by ground or air operation while transporting either payload.

Office of Commercial Programs' research activities for Space Station Freedom utilization

NASA Technical Reports Server (NTRS)

Fountain, James A.

1992-01-01

One of the objectives of the Office of Commercial Programs (OCP) is to encourage, enable, and help implement space research which meets the needs of the U.S. industrial sector. This is done mainly through seventeen Centers for the Commercial Development of Space (CCDS's) which are located throughout the United States. The CCDS's are composed of members from U.S. companies, universities, and other government agencies. These Centers are presently engaged in industrial research in space using a variety of carriers to reach low Earth orbit. One of the goals is to produce a body of experience and knowledge that will allow U.S. industrial entities to make informed decisions regarding their participation in commercial space endeavors. A total of 32 items of payload hardware were built to date. These payloads have flown in space a total of 73 times. The carriers range from the KC-135 parabolic aircraft and expendable launch vehicles to the Space Shuttle. This range of carriers allows the experimenter to evolve payloads in complexity and cost by progressively extending the time in microgravity. They can start with a few seconds in the parabolic aircraft and go to several minutes on the rocket flights, before they progress to the complexities of manned flight on the Shuttle. Next year, two new capabilities will become available: COMET, an expendable-vehicle-launched experiment capsule that can carry experiments aloft for thirty days; and SPACEHAB, a new Shuttle borne module which will greatly add to the capability to accommodate small payloads. All of these commercial research activities and carrier capabilities are preparing the OCP to evolve those experiments that prove successful to Space Station Freedom. OCP and the CCDS's are actively involved in Space Station design and utilization planning and have proposed a set of experiments to be launched in 1996 and 1997. These experiments are to be conducted both internal and external to Space Station Freedom and will investigate industrial research topics which range from biotechnology to electronic materials to metallurgy. Some will be designed to make maximum use of the quiescent microgravity conditions in the 'ground-tended' phases during the early years of Space Station Freedom operations.

Manipulation strategies for massive space payloads

NASA Technical Reports Server (NTRS)

Book, Wayne J.

1991-01-01

The industrial and environmental applications for robots with a relatively large workspace has increased significantly in the last few years. To accommodate the demands, the manipulator is usually designed with long, lightweight links that are inherently flexible. Ongoing research at Georgia Tech into the behavior and design of these flexible links is discussed.

14 CFR § 1214.106 - Minor delays.

Code of Federal Regulations, 2014 CFR

2014-01-01

... Provisions Regarding Space Shuttle Flights of Payloads for Non-U.S. Government, Reimbursable Customers § 1214.106 Minor delays. NASA will attempt to accommodate customer requested minor launch delays. Such delays... beyond 72 hours will require NASA's approval and will result in an additional charge as established in...

Conceptual design study Science and Application Space Platform SASP. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

Runge, F. C.

1980-01-01

The system design philosphy applied in the development of this platform concept is summarized. The system is to provide for simple, low cost, initial capability of accommodating Spacelab payloads that are modified for long duration flight. The supporting research and technology are also summarized.

ER-2: Flying Laboratory for Earth Science Studies

NASA Technical Reports Server (NTRS)

Navarro, Robert

2007-01-01

The National Aeronautics and Space Administration (NASA) Dryden Flight Research Center (DFRC), (Edwards, California, USA) has two Lockheed Martin Corporation (Bethesda, Maryland) Earth Research-2 (ER-2) aircraft that serve as high-altitude and long-range flying laboratories. The ER-2 has been utilized to conduct scientific studies of stratospheric and tropospheric chemistry, land-use mapping, disaster assessment, preliminary testing and calibration and validation of satellite sensors. The ER-2 aircraft provides experimenters with a wide array of payload accommodation areas with suitable environment control with required electrical and mechanical interfaces. Missions may be flown out of DFRC or from remote bases worldwide. The NASA ER-2 is utilized by a variety of customers, including U.S. Government agencies, civilian organizations, universities, and state governments. The combination of the ER-2 s range, endurance, altitude, payload power, payload volume and payload weight capabilities complemented by a trained maintenance and operations team provides an excellent and unique platform system to the science community.

Communication satellite payload technologies - State of the art and trends in Europe

NASA Astrophysics Data System (ADS)

Mica, G.; Coirault, R.

1982-09-01

Communication satellite payload technologies are examined, in terms of past, present, and future ESA guidelines. Various existing payload systems are presented, such as Marecs, ECS, and L-Sat (which will carry four payloads). Future services within the market include 2 Mb/sec high speed data, 2-8 Mb/sec video conference, and 64 Mb/sec television distribution, and growth in these areas is dependent on traffic requirements. Pre-operational satellites are outlined, for example Telecom 1 has an estimated system capacity of 150 Mb/sec, Italsat has an expected 1180 Mb/sec, and DFS demonstrates a possible 1540 Mb/sec capacity. It is found that the 20/30 GHz band should be applied for use in wideband and high capacity trunks among heavy traffic centers. To accommodate for the noise in this waveband, the parametric amplifier developed for L-Sat must be used. Finally, development objectives for future programs include improving spectrum and geostationary orbit utilization, cost-efficiency, and standardization of systems.

LSST system analysis and integration task for an advanced science and application space platform

NASA Technical Reports Server (NTRS)

1980-01-01

To support the development of an advanced science and application space platform (ASASP) requirements of a representative set of payloads requiring large separation distances selected from the Science and Applications Space Platform data base. These payloads were a 100 meter diameter atmospheric gravity wave antenna, a 100 meter by 100 meter particle beam injection experiment, a 2 meter diameter, 18 meter long astrometric telescope, and a 15 meter diameter, 35 meter long large ambient deployable IR telescope. A low earth orbit at 500 km altitude and 56 deg inclination was selected as being the best compromise for meeting payload requirements. Platform subsystems were defined which would support the payload requirements and a physical platform concept was developed. Structural system requirements which included utilities accommodation, interface requirements, and platform strength and stiffness requirements were developed. An attitude control system concept was also described. The resultant ASASP concept was analyzed and technological developments deemed necessary in the area of large space systems were recommended.

Large Payload Ground Transportation and Test Considerations

NASA Technical Reports Server (NTRS)

Rucker, Michelle A.

2016-01-01

During test and verification planning for the Altair lunar lander project, a National Aeronautics and Space Administration (NASA) study team identified several ground transportation and test issues related to the large payload diameter. Although the entire Constellation Program-including Altair-has since been canceled, issues identified by the Altair project serve as important lessons learned for payloads greater than 7 m diameter being considered for NASA's new Space Launch System (SLS). A transportation feasibility study found that Altair's 8.97 m diameter Descent Module would not fit inside available aircraft. Although the Ascent Module cabin was only 2.35 m diameter, the long reaction control system booms extended nearly to the Descent Module diameter, making it equally unsuitable for air transportation without removing the booms and invalidating assembly workmanship screens or acceptance testing that had already been performed. Ground transportation of very large payloads over extended distances is not generally permitted by most states, so overland transportation alone would not be an option. Limited ground transportation to the nearest waterway may be possible, but water transportation could take as long as 66 days per production unit, depending on point of origin and acceptance test facility; transportation from the western United States would require transit through the Panama Canal to access the Kennedy Space Center launch site. Large payloads also pose acceptance test and ground processing challenges. Although propulsion, mechanical vibration, and reverberant acoustic test facilities at NASA's Plum Brook Station have been designed to accommodate large spacecraft, special handling and test work-arounds may be necessary, which could increase cost, schedule, and technical risk. Once at the launch site, there are no facilities currently capable of accommodating the combination of large payload size and hazardous processing such as hypergolic fuels, pyrotechnic devices, and high pressure gasses. Ironically, the limiting factor to a national heavy lift strategy may not be the rocket technology needed to throw a heavy payload, but rather the terrestrial infrastructure-roads, bridges, airframes, and buildings-necessary to transport, acceptance test, and process large spacecraft. Failure to carefully consider where and how large spacecraft are manufactured, tested, and launched could result in unforeseen cost to modify existing (or develop new) infrastructure, or incur additional risk due to increased handling operations or eliminating key verifications.

Design Features and Capabilities of the First Materials Science Research Rack

NASA Technical Reports Server (NTRS)

Pettigrew, P. J.; Lehoczky, S. L.; Cobb, S. D.; Holloway, T.; Kitchens, L.

2003-01-01

The First Materials Science Research Rack (MSRR-1) aboard the International Space Station (ISS) will offer many unique capabilities and design features to facilitate a wide range of materials science investigations. The initial configuration of MSRR-1 will accommodate two independent Experiment Modules (EMS) and provide the capability for simultaneous on-orbit processing. The facility will provide the common subsystems and interfaces required for the operation of experiment hardware and accommodate telescience capabilities. MSRR1 will utilize an International Standard Payload Rack (ISPR) equipped with an Active Rack Isolation System (ARIS) for vibration isolation of the facility.

Habitability sleep accommodations

NASA Technical Reports Server (NTRS)

Fisher, H. T.

1985-01-01

Schematic outlines are presented with various design requirements for the accommodation of the spacecrew of Space Stations. The primary concern is for sleeping accommodations. Some other general requirements given are for a rest place, entertainment, dressing area, personal item stowage, body restraint, total privacy, external viewing, and grooming provisions. Several plans are given for sleep quarters concepts.

Passive orientation apparatus

DOEpatents

Spletzer, Barry L.; Fischer, Gary J.; Martinez, Michael A.

2001-01-01

An apparatus that can return a payload to a known orientation after unknown motion, without requiring external power or complex mechanical systems. The apparatus comprises a faceted cage that causes the system to rest in a stable position and orientation after arbitrary motion. A gimbal is mounted with the faceted cage and holds the payload, allowing the payload to move relative to the stable faceted cage. The payload is thereby placed in a known orientation by the interaction of gravity with the geometry of the faceted cage, the mass of the system, and the motion of the payload and gimbal. No additional energy, control, or mechanical actuation is required. The apparatus is suitable for use in applications requiring positioning of a payload to a known orientation after arbitrary or uncontrolled motion, including remote sensing and mobile robot applications.

Space Experiment Module: A new low-cost capability for education payloads

NASA Technical Reports Server (NTRS)

Goldsmith, Theodore C.; Lewis, Ruthan

1995-01-01

The Space Experiment Module (SEM) concept is one of a number of education initiatives being pursued by the NASA Shuttle Small Payloads Project (SSPP) in an effort to increase educational access to space by means of Space Shuttle Small Payloads and associated activities. In the SEM concept, NASA will provide small containers ('modules') which can accommodate small zero-gravity experiments designed and constructed by students. A number, (nominally ten), of the modules will then be flown in an existing Get Away Special (GAS) carrier on the Shuttle for a flight of 5 to 10 days. In addition to the module container, the NASA carrier system will provide small amounts of electrical power and a computer system for controlling the operation of the experiments and recording experiment data. This paper describes the proposed SEM carrier system and program approach.

The Fluids And Combustion Facility Combustion Integrated Rack And The Multi-User Droplet Combustion Apparatus: Microgravity Combustion Science Using Modular Multi-User Hardware

NASA Technical Reports Server (NTRS)

OMalley, Terence F.; Myhre, Craig A.

2000-01-01

The Fluids and Combustion Facility (FCF) is a multi-rack payload planned for the International Space Station (ISS) that will enable the study of fluid physics and combustion science in a microgravity environment. The Combustion Integrated Rack (CIR) is one of two International Standard Payload Racks of the FCF and is being designed primarily to support combustion science experiments. The Multi-user Droplet Combustion Apparatus (MDCA) is a multi-user apparatus designed to accommodate four different droplet combustion science experiments and is the first payload for CIR. The CIR will function independently until the later launch of the Fluids Integrated Rack component of the FCF. This paper provides an overview of the capabilities and the development status of the CIR and MDCA.

Mars Mobile Lander Systems for 2005 and 2007 Launch Opportunities

NASA Technical Reports Server (NTRS)

Sabahi, D.; Graf, J. E.

2000-01-01

A series of Mars missions are proposed for the August 2005 launch opportunity on a medium class Evolved Expendable Launch Vehicle (EELV) with a injected mass capability of 2600 to 2750 kg. Known as the Ranger class, the primary objective of these Mars mission concepts are: (1) Deliver a mobile platform to Mars surface with large payload capability of 150 to 450 kg (depending on launch opportunity of 2005 or 2007); (2) Develop a robust, safe, and reliable workhorse entry, descent, and landing (EDL) capability for landed mass exceeding 750 kg; (3) Provide feed forward capability for the 2007 opportunity and beyond; and (4) Provide an option for a long life telecom relay orbiter. A number of future Mars mission concepts desire landers with large payload capability. Among these concepts are Mars sample return (MSR) which requires 300 to 450 kg landed payload capability to accommodate sampling, sample transfer equipment and a Mars ascent vehicle (MAV). In addition to MSR, large in situ payloads of 150 kg provide a significant step up from the Mars Pathfinder (MPF) and Mars Polar Lander (MPL) class payloads of 20 to 30 kg. This capability enables numerous and physically large science instruments as well as human exploration development payloads. The payload may consist of drills, scoops, rock corers, imagers, spectrometers, and in situ propellant production experiment, and dust and environmental monitoring.

Advanced APS impacts on vehicle payloads

NASA Technical Reports Server (NTRS)

Schneider, Steven J.; Reed, Brian D.

1989-01-01

Advanced auxiliary propulsion system (APS) technology has the potential to both, increase the payload capability of earth-to-orbit (ETO) vehicles by reducing APS propellant mass, and simplify ground operations and logistics by reducing the number of fluids on the vehicle and eliminating toxic, corrosive propellants. The impact of integrated cryogenic APS on vehicle payloads is addressed. In this system, launch propulsion system residuals are scavenged from integral launch propulsion tanks for use in the APS. Sufficient propellant is preloaded into the APS to return to earth with margin and noncomplete scavenging assumed. No propellant conditioning is required by the APS, but ambient heat soak is accommodated. High temperature rocket materials enable the use of the unconditioned hydrogen/oxygen in the APS and are estimated to give APS rockets specific impulse of up to about 444 sec. The payload benefits are quantified and compared with an uprated monomethylhydrazine/nitrogen tetroxide system in a conservative fashion, by assuming a 25.5 percent weight growth for the hydrogen/oxygen system and a 0 percent weight growth for the uprated system. The combination of scavenging and high performance gives payload impacts which are highly mission specific. A payload benefit of 861 kg (1898 lbm) was estimated for a Space Station Freedom rendezvous mission and 2099 kg (4626 lbm) for a sortie mission, with payload impacts varying with the amount of launch propulsion residual propellants. Missions without liquid propellant scavenging were estimated to have payload penalties, however, operational benefits were still possible.

Advanced APS Impacts on Vehicle Payloads

NASA Technical Reports Server (NTRS)

Schneider, Steven J.; Reed, Brian D.

1989-01-01

Advanced auxiliary propulsion system (APS) technology has the potential to both, increase the payload capability of earth-to-orbit (ETO) vehicles by reducing APS propellant mass, and simplify ground operations and logistics by reducing the number of fluids on the vehicle and eliminating toxic, corrosive propellants. The impact of integrated cryogenic APS on vehicle payloads is addressed. In this system, launch propulsion system residuals are scavenged from integral launch propulsion tanks for use in the APS. Sufficient propellant is preloaded into the APS to return to earth with margin and noncomplete scavenging assumed. No propellant conditioning is required by the APS, but ambient heat soak is accommodated. High temperature rocket materials enable the use of the unconditioned hydrogen/oxygen in the APS and are estimated to give APS rockets specific impulse of up to about 444 sec. The payload benefits are quantified and compared with an uprated monomethyl hydrazine/nitrogen tetroxide system in a conservative fashion, by assuming a 25.5 percent weight growth for the hydrogen/oxygen system and a 0 percent weight growth for the uprated system. The combination and scavenging and high performance gives payload impacts which are highly mission specific. A payload benefit of 861 kg (1898 lbm) was estimated for a Space Station Freedom rendezvous mission and 2099 kg (4626 lbm) for a sortie mission, with payload impacts varying with the amount of launch propulsion residual propellants. Missions without liquid propellant scavenging were estimated to have payload penalties, however, operational benefits were still possible.

14 CFR § 1214.811 - Reflight guarantee.

Code of Federal Regulations, 2014 CFR

2014-01-01

... accommodated on a standard Shuttle launch to 160 nmi, 28.5° as defined in the Shuttle policy and all dedicated-flight Spacelab payloads. (b) NASA and the customer may negotiate appropriate reflight provisions (e.g... standard Spacelab and Shuttle services if both the following occur: (1) Through no fault of the customer or...

JEM-EUSO Design for Accommodation on the SpaceX Dragon Spacecraft

NASA Technical Reports Server (NTRS)

Christl, Mark

2013-01-01

The JEM-EUSO mission has been planned for launch on JAXA's H2 Launch Vehicle. Recently, the SpaceX Dragon spacecraft has emerged as an alternative payload carrier for JEM-EUSO. This paper will discuss a concept for the re-design of JEM-EUSO so that it can be launched on Dragon.

The DSI small satellite launcher

NASA Technical Reports Server (NTRS)

Nichols, S.; Gibbons, D.; Wise, J.; Nguyen, D.

1992-01-01

A new launcher has been developed by DSI, that is compatible with the GAS canisters. It has the proven capability to deploy a satellite from an orbiting Shuttle that is 18 inches in diameter, 31 inches long, and weighing 190 pounds. These DSI Launchers were used aboard the Discovery (STS-39) in May 1991 as part of the Infrared Background Signature Survey (IBSS) to deploy three small satellites known as Chemical Release Observation (CRO) satellites A, B, and C. Because the satellites contained hazardous liquids (MMH, UDMH, and MON-10) and were launched from GAS Cylinders without motorized doors, the launchers were required to pass NASA Shuttle Payload safety and verification requirements. Some of the more interesting components of the design were the V-band retention and separation mechanism, the separation springs, and the launcher electronics which provided a properly inhibited release sequence operated through the Small Payload Accommodations Switch Panel (SPASP) on board the Orbiter. The original plan for this launcher was to use a motorized door. The launcher electronics, therefore has the capability to be modified to accommodate the door, if desired.

General view looking forward along the centerline of the Orbiter ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

General view looking forward along the centerline of the Orbiter Discovery looking into the payload bay. This view shows the external airlock and the beam-truss attach structure supporting it and attaching it to the payload bay sill longerons. Also note the protective covering over the docking mechanism on top of the airlock assembly. This external airlock configuration was for mating to the International Space Station. This photograph was taken in the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Systems integration of lunar Campsite vehicles

NASA Technical Reports Server (NTRS)

Capps, Stephen; Ruff, Theron

1992-01-01

This paper describes the configuration design and subsystems integration resolution for lunar Campsite vehicles and the crew vehicles (CVs) which support them. This concept allows early return to the moon while minimizing hardware development. Once in place, the Campsite can be revisited for extended periods. Configuration and operations issues are addressed, and explanations of the parametric subsystem analysis, as well as descriptions of the hardware concept and performance data, are provided. Within an assumed set of launch and mission constraints, a common vehicle stage design for both the Campsite and the CV landers was the chief design driver. Accommodation of a heat-shielded, ballistic crew transportation/return vehicle, scars for later system growth and upgrades, landing the crew in close proximity to the Campsite, and appropriate kinds of robotic systems were all secondary design drivers. Physical integration of the crew module and airlock, structural system, thermal radiators, power production and storage systems, external life support consumables, and payloads are covered. The vehicle performance data were derived using a Boeing lunar transportation sizing code to optimize vehicle stage sizes and commonality. Configuration trades were conducted and detailed sketches were produced.

Space Station crew workload - Station operations and customer accommodations

NASA Technical Reports Server (NTRS)

Shinkle, G. L.

1985-01-01

The features of the Space Station which permit crew members to utilize work time for payload operations are discussed. The user orientation, modular design, nonstressful flight regime, in space construction, on board control, automation and robotics, and maintenance and servicing of the Space Station are examined. The proposed crew size, skills, and functions as station operator and mission specialists are described. Mission objectives and crew functions, which include performing material processing, life science and astronomy experiments, satellite and payload equipment servicing, systems monitoring and control, maintenance and repair, Orbital Maneuvering Vehicle and Mobile Remote Manipulator System operations, on board planning, housekeeping, and health maintenance and recreation, are studied.

Hitchhiker On Space Station

NASA Technical Reports Server (NTRS)

Daelemans, Gerard; Goldsmith, Theodore

1999-01-01

The NASA/GSFC Shuttle Small Payloads Projects Office (SSPPO) has been studying the feasibility of migrating Hitchhiker customers past present and future to the International Space Station via a "Hitchhiker like" carrier system. SSPPO has been tasked to make the most use of existing hardware and software systems and infrastructure in its study of an ISS based carrier system. This paper summarizes the results of the SSPPO Hitchhiker on International Space Station (ISS) study. Included are a number of "Hitchhiker like" carrier system concepts that take advantage of the various ISS attached payload accommodation sites. Emphasis will be given to a HH concept that attaches to the Japanese Experiment Module - Exposed Facility (JEM-EF).

The Microgravity Isolation Mount (MGIM): A Columbus facility for improving the microgravity quality of payloads

NASA Technical Reports Server (NTRS)

Owen, R. G.; Jones, D. I.; Owens, A. R.; Roberts, G.; Hadfield, P.

1992-01-01

The Microgravity Isolation Mount (MGIM) is a facility for providing active vibration isolation for sensitive experiments on the Columbus Attached Laboratory and the Columbus Free-Flying Laboratory. The facility is designed to be accommodated in a standard Columbus rack, and it iterfaces with existing rack utility services. The design is based on a non-contact strategy, whereby the payload 'floats' inside the rack, and its position is controlled by a number of magnetic actuators. The main advantage of using this non-contact strategy is the improved microgravity quality available. The overall design of the facility and a description of its elements are given.

Advanced Cosmic-ray Composition Experiment for Space Station: ISS accommodation study

DOE Office of Scientific and Technical Information (OSTI.GOV)

Wefel, John P.

1999-01-22

ACCESS--Advanced Cosmic-ray Composition Experiment for Space Station--was selected as a new Mission Concept under NRA 96-OSS-03, with the goal of combining calorimeter and transition radiation techniques to provide measurements of cosmic rays from Hydrogen through Nickel up to energies approaching the 'knee' in the cosmic ray all particle spectrum, plus providing measurements of the Z>28 (Ultra-Heavy) nuclei at all energies. An instrument to perform such an investigation is undergoing an ISS/STS Accommodation Study at JSC. The instrument concept, the mission plan, and the accommodation issues for an ISS attached payload which include, in part, the carrier, ISS Site, thermal control,more » power, data and operations are described and the current status of these issues, for an ACCESS Mission, is summarized.« less

Full length view of the Spacelab module

NASA Image and Video Library

2016-08-12

STS083-312-031 (4-8 April 1997) --- Payload specialist Gregory T. Linteris (left) is seen at the Mid Deck Glove Box (MGBX), while astronaut Donald A. Thomas, mission specialist, works at the Expedite the Processing of Experiments to Space Station (EXPRESS) rack. MGBX is a facility that allows scientists the capability of doing tests on hardware and materials that are not approved to be handled in the open Spacelab. It is equipped with photographic, video and data recording capability, allowing a complete record of experiment operations. Experiments performed on STS-83 were Bubble Drop Nonlinear Dynamics and Fiber Supported Droplet Combustion. EXPRESS is designed to provide accommodations for Sub-rack payloads on Space Station. For STS-83, it held two payloads. The Physics of Hard Colloidal Spheres (PHaSE) and ASTRO-Plant Generic Bioprocessing Apparatus (ASTRO-PGBA), a facility with light and atmospheric controls which supports plant growth for commercial research.

How to get on board Space Station Freedom

NASA Technical Reports Server (NTRS)

Bartoe, John-David

1992-01-01

Space Station Freedom will accommodate researchers with interests in science, technology and commercial applications. NASA sponsors will be responsible for selecting the U.S. researchers for Space Station Freedom. The four NASA sponsors are: Office of Space Science and Applications (OSSA), Office of Aeronautics and Space Technology (OAST), Office of Commercial Programs (OCP), and the Office of Space Flight (OSF). The areas of research responsibility for each sponsor are presented. The researcher solicitation vehicles used by OSSA and OAST and the methodology for researchers seeking sponsorship from OCP and OSF as well as the pricing policy are discussed. Descriptions of flight planning, payload integration and operations functions are presented. Three categories of payloads and their respective payload integration times are discussed. Researchers are advised to contact a NASA sponsor and a source which lists the points of contact for the NASA sponsors is noted.

GSFC contamination monitors for Space Station

NASA Technical Reports Server (NTRS)

Carosso, P. A.; Tveekrem, J. L.; Coopersmith, J. D.

1988-01-01

This paper describes the Work Package 3 activities in the area of neutral contamination monitoring for the Space Station. Goddard Space Flight Center's responsibilities include the development of the Attached Payload Accommodations Equipment (APAE), the Polar Orbiting Platform (POP), and the Flight Telerobotic Servicer (FTS). GSFC will also develop the Customer Servicing Facility (CSF) in Phase 2 of the Space Station.

Spacelab payload accommodation handbook. Appendix A: Avionics interface definition

NASA Technical Reports Server (NTRS)

1978-01-01

The Spacelab side of the electrical interface between Spacelab subsystem equipment and experiments is presented. The electrical hardware which interfaces with the experiments is defined and the signal/load characteristics are stated. Major subsystems considered include: electrical power and distribution; command and data management subsystem; orbiter avionics via dedicated connectors of Spacelab; and electrical ground support equipment.

Simulating Vibrations in a Complex Loaded Structure

NASA Technical Reports Server (NTRS)

Cao, Tim T.

2005-01-01

The Dynamic Response Computation (DIRECT) computer program simulates vibrations induced in a complex structure by applied dynamic loads. Developed to enable rapid analysis of launch- and landing- induced vibrations and stresses in a space shuttle, DIRECT also can be used to analyze dynamic responses of other structures - for example, the response of a building to an earthquake, or the response of an oil-drilling platform and attached tanks to large ocean waves. For a space-shuttle simulation, the required input to DIRECT includes mathematical models of the space shuttle and its payloads, and a set of forcing functions that simulates launch and landing loads. DIRECT can accommodate multiple levels of payload attachment and substructure as well as nonlinear dynamic responses of structural interfaces. DIRECT combines the shuttle and payload models into a single structural model, to which the forcing functions are then applied. The resulting equations of motion are reduced to an optimum set and decoupled into a unique format for simulating dynamics. During the simulation, maximum vibrations, loads, and stresses are monitored and recorded for subsequent analysis to identify structural deficiencies in the shuttle and/or payloads.

External Payload Carrier (XPC) A Suborbital Research Platform

NASA Technical Reports Server (NTRS)

Schallhorn, Paul; Tatro, Chuck; Kutter, Bernard; Szatkowski, Gerald; Stopnitzky, Ben; Bulk, Tim

2011-01-01

This slide presentation details the concept of an External Payload Carrier (XPC), that can fly on ann unused Solid Rocket Booster (SRB) location on the Atlas V rocket to suborbital environment. The XPC can be used anytime there is sufficient excess lift capability available. The dimensions and possible uses of the XPC are reviewed. The completed Phase 1 study reviewed 57 variations, and arrived at three viable configurations, identified design baselines, subsystems and preliminary testing requirements. Phase II effort is planned to produce the preliminary design (i.e., PDR level), Systems Requirements Document (SRD), identify flight candidates, develop schedule and funding profiles, and identify the risk-reduction activities.

Closeup view looking forward along the centerline of the Orbiter ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Close-up view looking forward along the centerline of the Orbiter Discovery looking into the payload bay. This view is a close-up view of the external airlock and the beam-truss attach structure supporting it and attaching it to the payload bay sill longerons. Also note the protective covering over the docking mechanism on top of the airlock assembly. This external airlock configuration was for mating to the International Space Station. This photograph was taken in the Orbiter Processing Facility at Kennedy Space Cente - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Predicted Performance of a Thrust-Enhanced SR-71 Aircraft with an External Payload

NASA Technical Reports Server (NTRS)

Conners, Timothy R.

1997-01-01

NASA Dryden Flight Research Center has completed a preliminary performance analysis of the SR-71 aircraft for use as a launch platform for high-speed research vehicles and for carrying captive experimental packages to high altitude and Mach number conditions. Externally mounted research platforms can significantly increase drag, limiting test time and, in extreme cases, prohibiting penetration through the high-drag, transonic flight regime. To provide supplemental SR-71 acceleration, methods have been developed that could increase the thrust of the J58 turbojet engines. These methods include temperature and speed increases and augmentor nitrous oxide injection. The thrust-enhanced engines would allow the SR-71 aircraft to carry higher drag research platforms than it could without enhancement. This paper presents predicted SR-71 performance with and without enhanced engines. A modified climb-dive technique is shown to reduce fuel consumption when flying through the transonic flight regime with a large external payload. Estimates are included of the maximum platform drag profiles with which the aircraft could still complete a high-speed research mission. In this case, enhancement was found to increase the SR-71 payload drag capability by 25 percent. The thrust enhancement techniques and performance prediction methodology are described.

Conducting Research on the International Space Station Using the EXPRESS Rack Facilities

NASA Technical Reports Server (NTRS)

Thompson, Sean W.; Lake, Robert E.

2013-01-01

Eight "Expedite the Processing of Experiments to Space Station" (EXPRESS) Rack facilities are located within the International Space Station (ISS) laboratories to provide standard resources and interfaces for the simultaneous and independent operation of multiple experiments within each rack. Each EXPRESS Rack provides eight Middeck Locker Equivalent locations and two drawer locations for powered experiment equipment, also referred to as sub-rack payloads. Payload developers may provide their own structure to occupy the equivalent volume of one, two, or four lockers as a single unit. Resources provided for each location include power (28 Vdc, 0-500 W), command and data handling (Ethernet, RS-422, 5 Vdc discrete, +/- 5 Vdc analog), video (NTSC/RS 170A), and air cooling (0-200 W). Each rack also provides water cooling (500 W) for two locations, one vacuum exhaust interface, and one gaseous nitrogen interface. Standard interfacing cables and hoses are provided on-orbit. One laptop computer is provided with each rack to control the rack and to accommodate payload application software. Four of the racks are equipped with the Active Rack Isolation System to reduce vibration between the ISS and the rack. EXPRESS Racks are operated by the Payload Operations Integration Center at Marshall Space Flight Center and the sub-rack experiments are operated remotely by the investigating organization. Payload Integration Managers serve as a focal to assist organizations developing payloads for an EXPRESS Rack. NASA provides EXPRESS Rack simulator software for payload developers to checkout payload command and data handling at the development site before integrating the payload with the EXPRESS Functional Checkout Unit for an end-to-end test before flight. EXPRESS Racks began supporting investigations onboard ISS on April 24, 2001 and will continue through the life of the ISS.

Conducting Research on the International Space Station using the EXPRESS Rack Facilities

NASA Technical Reports Server (NTRS)

Thompson, Sean W.; Lake, Robert E.

2016-01-01

Eight "Expedite the Processing of Experiments to Space Station" (EXPRESS) Rack facilities are located within the International Space Station (ISS) laboratories to provide standard resources and interfaces for the simultaneous and independent operation of multiple experiments within each rack. Each EXPRESS Rack provides eight Middeck Locker Equivalent locations and two drawer locations for powered experiment equipment, also referred to as sub-rack payloads. Payload developers may provide their own structure to occupy the equivalent volume of one, two, or four lockers as a single unit. Resources provided for each location include power (28 Vdc, 0-500 W), command and data handling (Ethernet, RS-422, 5 Vdc discrete, +/- 5 Vdc analog), video (NTSC/RS 170A), and air cooling (0-200 W). Each rack also provides water cooling for two locations (500W ea.), one vacuum exhaust interface, and one gaseous nitrogen interface. Standard interfacing cables and hoses are provided on-orbit. One laptop computer is provided with each rack to control the rack and to accommodate payload application software. Four of the racks are equipped with the Active Rack Isolation System to reduce vibration between the ISS and the rack. EXPRESS Racks are operated by the Payload Operations Integration Center at Marshall Space Flight Center and the sub-rack experiments are operated remotely by the investigating organization. Payload Integration Managers serve as a focal to assist organizations developing payloads for an EXPRESS Rack. NASA provides EXPRESS Rack simulator software for payload developers to checkout payload command and data handling at the development site before integrating the payload with the EXPRESS Functional Checkout Unit for an end-to-end test before flight. EXPRESS Racks began supporting investigations onboard ISS on April 24, 2001 and will continue through the life of the ISS.

Contamination assessment for OSSA space station IOC payloads

NASA Technical Reports Server (NTRS)

Chinn, S.; Gordon, T.; Rantanen, R.

1987-01-01

The results are presented from a study for the Space Station Planners Group of the Office of Space Sciences and Applications. The objectives of the study are: (1) the development of contamination protection requirements for protection of Space Station attached payloads, serviced payloads and platforms; and (2) the determination of unknowns or major impacts requiring further assessment. The nature, sources, and quantitative properties of the external contaminants to be encountered on the Station are summarized. The OSSA payload contamination protection requirements provided by the payload program managers are reviewed and the level of contamination awareness among them is discussed. Preparation of revisions to the contamination protection requirements are detailed. The comparative impact of flying the Station at constant atmospheric density rather than constant altitude is assessed. The impact of the transverse boom configuration of the Station on contamination is also assessed. The contamination protection guidelines which OSSA should enforce during their development of payloads are summarized.

Overview of Space Station attached payloads in the areas of solar physics, solar terrestrial physics, and plasma processes

NASA Technical Reports Server (NTRS)

Roberts, W. T.; Kropp, J.; Taylor, W. W. L.

1986-01-01

This paper outlines the currently planned utilization of the Space Station to perform investigations in solar physics, solar terrestrial physics, and plasma physics. The investigations and instrumentation planned for the Solar Terrestrial Observatory (STO) and its associated Space Station accommodation requirements are discussed as well as the planned placement of the STO instruments and typical operational scenarios. In the area of plasma physics, some preliminary plans for scientific investigations and for the accommodation of a plasma physics facility attached to the Space Station are outlined. These preliminary experiment concepts use the space environment around the Space Station as an unconfined plasma laboratory. In solar physics, the initial instrument complement and associated accommodation requirements of the Advanced Solar Observatory are described. The planned evolutionary development of this observatory is outlined, making use of the Space Station capabilities for servicing and instrument reconfiguration.

The NASA Earth Research-2 (ER-2) Aircraft: A Flying Laboratory for Earth Science Studies

NASA Technical Reports Server (NTRS)

Navarro, Robert

2007-01-01

The National Aeronautics and Space Administration Dryden Flight Research Center, Edwards, California, has two Lockheed Martin Corporation (Bethesda, Maryland) Earth Research-2 (ER2) aircraft that serve as high-altitude and long-range flying laboratories. The ER-2 aircraft has been successfully utilized to conduct scientific studies of stratospheric and tropospheric chemistry, land-use mapping, disaster assessment, preliminary testing and calibration and validation of satellite sensors. The research missions for the ER-2 aircraft are planned, implemented, and managed by the Dryden Flight Research Center Science Mission Directorate. Maintenance and instrument payload integration is conducted by Dryden personnel. The ER-2 aircraft provides experimenters with a wide array of payload accommodations areas with suitable environment control with required electrical and mechanical interfaces. Missions may be flown out of Dryden or from remote bases worldwide, according to research requirements. The NASA ER-2 aircraft is utilized by a variety of customers, including U.S. Government agencies, civilian organizations, universities, and state governments. The combination of the ER-2 aircraft s range, endurance, altitude, payload power, payload volume and payload weight capabilities complemented by a trained maintenance and operations team provides an excellent and unique platform system to the science community and other customers.

A modular suite of hardware enabling spaceflight cell culture research

NASA Technical Reports Server (NTRS)

Hoehn, Alexander; Klaus, David M.; Stodieck, Louis S.

2004-01-01

BioServe Space Technologies, a NASA Research Partnership Center (RPC), has developed and operated various middeck payloads launched on 23 shuttle missions since 1991 in support of commercial space biotechnology projects. Modular cell culture systems are contained within the Commercial Generic Bioprocessing Apparatus (CGBA) suite of flight-qualified hardware, compatible with Space Shuttle, SPACEHAB, Spacelab and International Space Station (ISS) EXPRESS Rack interfaces. As part of the CGBA family, the Isothermal Containment Module (ICM) incubator provides thermal control, data acquisition and experiment manipulation capabilities, including accelerometer launch detection for automated activation and thermal profiling for culture incubation and sample preservation. The ICM can accommodate up to 8 individually controlled temperature zones. Command and telemetry capabilities allow real-time downlink of data and video permitting remote payload operation and ground control synchronization. Individual cell culture experiments can be accommodated in a variety of devices ranging from 'microgravity test tubes' or standard 100 mm Petri dishes, to complex, fed-batch bioreactors with automated culture feeding, waste removal and multiple sample draws. Up to 3 levels of containment can be achieved for chemical fixative addition, and passive gas exchange can be provided through hydrophobic membranes. Many additional options exist for designing customized hardware depending on specific science requirements.

Data-Driven Software Framework for Web-Based ISS Telescience

NASA Technical Reports Server (NTRS)

Tso, Kam S.

2005-01-01

Software that enables authorized users to monitor and control scientific payloads aboard the International Space Station (ISS) from diverse terrestrial locations equipped with Internet connections is undergoing development. This software reflects a data-driven approach to distributed operations. A Web-based software framework leverages prior developments in Java and Extensible Markup Language (XML) to create portable code and portable data, to which one can gain access via Web-browser software on almost any common computer. Open-source software is used extensively to minimize cost; the framework also accommodates enterprise-class server software to satisfy needs for high performance and security. To accommodate the diversity of ISS experiments and users, the framework emphasizes openness and extensibility. Users can take advantage of available viewer software to create their own client programs according to their particular preferences, and can upload these programs for custom processing of data, generation of views, and planning of experiments. The same software system, possibly augmented with a subset of data and additional software tools, could be used for public outreach by enabling public users to replay telescience experiments, conduct their experiments with simulated payloads, and create their own client programs and other custom software.

Low Noise Camera for Suborbital Science Applications

NASA Technical Reports Server (NTRS)

Hyde, David; Robertson, Bryan; Holloway, Todd

2015-01-01

Low-cost, commercial-off-the-shelf- (COTS-) based science cameras are intended for lab use only and are not suitable for flight deployment as they are difficult to ruggedize and repackage into instruments. Also, COTS implementation may not be suitable since mission science objectives are tied to specific measurement requirements, and often require performance beyond that required by the commercial market. Custom camera development for each application is cost prohibitive for the International Space Station (ISS) or midrange science payloads due to nonrecurring expenses ($2,000 K) for ground-up camera electronics design. While each new science mission has a different suite of requirements for camera performance (detector noise, speed of image acquisition, charge-coupled device (CCD) size, operation temperature, packaging, etc.), the analog-to-digital conversion, power supply, and communications can be standardized to accommodate many different applications. The low noise camera for suborbital applications is a rugged standard camera platform that can accommodate a range of detector types and science requirements for use in inexpensive to mid range payloads supporting Earth science, solar physics, robotic vision, or astronomy experiments. Cameras developed on this platform have demonstrated the performance found in custom flight cameras at a price per camera more than an order of magnitude lower.

Comparison of vibrations of a combination of solid-rocket launch vehicle and payload during a ground firing and launching

NASA Technical Reports Server (NTRS)

Schoenster, J. A.; Pierce, H. B.

1975-01-01

The results of a study into the environmental vibrations of a payload mounted on the Nike rocket launch vehicle were presented. Data were obtained during the flight acceptance test of the payload, the firing of the total vehicle in a special test stand, and the powered and unpowered flights of the vehicle. The vibrational response of the structure was measured. Data were also obtained on the fluctuating pressure on the outside surface of the vehicle and inside the forward and after ends of the rocket chamber. A comparison of the data from the three test conditions indicated that external pressure fluctuations were the major source of vibrations in the payload area, and pressure fluctuations within the rocket motor were the major source of vibrations contiguous to the payload area.

A Modular, Reusable Latch and Decking System for Securing Payloads During Launch and Planetary Surface Transport

NASA Technical Reports Server (NTRS)

Doggett, William R.; Dorsey, John T.; Jones, Thomas C.; King, Bruce D.; Mikulas, Martin M.

2011-01-01

Efficient handling of payloads destined for a planetary surface, such as the moon or mars, requires robust systems to secure the payloads during transport on the ground, in space and on the planetary surface. In addition, mechanisms to release the payloads need to be reliable to ensure successful transfer from one vehicle to another. An efficient payload handling strategy must also consider the devices available to support payload handling. Cranes used for overhead lifting are common to all phases of payload handling on Earth. Similarly, both recent and past studies have demonstrated that devices with comparable functionality will be needed to support lunar outpost operations. A first generation test-bed of a new high performance device that provides the capabilities of both a crane and a robotic manipulator, the Lunar Surface Manipulation System (LSMS), has been designed, built and field tested and is available for use in evaluating a system to secure payloads to transportation vehicles. A payload handling approach must address all phases of payload management including: ground transportation, launch, planetary transfer and installation in the final system. In addition, storage may be required during any phase of operations. Each of these phases requires the payload to be lifted and secured to a vehicle, transported, released and lifted in preparation for the next transportation or storage phase. A critical component of a successful payload handling approach is a latch and associated carrier system. The latch and carrier system should minimize requirements on the: payload, carrier support structure and payload handling devices as well as be able to accommodate a wide range of payload sizes. In addition, the latch should; be small and lightweight, support a method to apply preload, be reusable, integrate into a minimal set of hard-points and have manual interfaces to actuate the latch should a problem occur. A latching system which meets these requirements has been designed and fabricated and will be described in detail. This latching system works in conjunction with a payload handling device such as the LSMS, and the LSMS has been used to test first generation latch and carrier hardware. All tests have been successful during the first phase of operational evaluations. Plans for future tests of first generation latch and carrier hardware with the LSMS are also described.

A Modular, Reusable Latch and Decking System for Securing Payloads During Launch and Planetary Surface Transport

NASA Technical Reports Server (NTRS)

Doggett, William R.; Dorsey, John T.; Jones, Thomas C.; King, Bruce D.; Mikulas, Martin M.

2010-01-01

Efficient handling of payloads destined for a planetary surface, such as the moon or Mars, requires robust systems to secure the payloads during transport on the ground, in-space and on the planetary surface. In addition, mechanisms to release the payloads need to be reliable to ensure successful transfer from one vehicle to another. An efficient payload handling strategy must also consider the devices available to support payload handling. Cranes used for overhead lifting are common to all phases of payload handling on Earth. Similarly, both recent and past studies have demonstrated that devices with comparable functionality will be needed to support lunar outpost operations. A first generation test-bed of a new high performance device that provides the capabilities of both a crane and a robotic manipulator, the Lunar Surface Manipulation System (LSMS), has been designed, built and field tested and is available for use in evaluating a system to secure payloads to transportation vehicles. National Institute of Aerospace, Hampton Va 23662 A payload handling approach must address all phases of payload management including: ground transportation, launch, planetary transfer and installation in the final system. In addition, storage may be required during any phase of operations. Each of these phases requires the payload to be lifted and secured to a vehicle, transported, released and lifted in preparation for the next transportation or storage phase. A critical component of a successful payload handling approach is a latch and associated carrier system. The latch and carrier system should minimize requirements on the: payload, carrier support structure and payload handling devices as well as be able to accommodate a wide range of payload sizes. In addition, the latch should; be small and lightweight, support a method to apply preload, be reusable, integrate into a minimal set of hard-points and have manual interfaces to actuate the latch should a problem occur. A latching system which meets these requirements has been designed and fabricated and will be described in detail. This latching system works in conjunction with a payload handling device such as the LSMS, and the LSMS has been used to test first generation latch and carrier hardware. All tests have been successful during the first phase of operational evaluations. Plans for future tests of first generation latch and carrier hardware with the LSMS are also described.

An Overview of the Design and Development of the Geostationary Operational Environmental Satellite R-Series (GOES-R) Space Segment

NASA Technical Reports Server (NTRS)

Sullivan, Pamela C.; Krimchansky, Alexander; Walsh, Timothy J.

2017-01-01

The first of the National Oceanic and Atmospheric Administration (NOAA) Geostationary Operational Environmental Satellite R-series (GOES-R) satellites was launched in November 2016. GOES-R has been developed by NOAA in partnership with the National Aeronautics and Space Administration (NASA). The satellite represents a quantum leap in the state of the art for geostationary weather satellites by providing data from a suite of six new instruments. All instruments were developed expressly for this mission, and include two Earth-observing instruments (the Advanced Baseline Imager (ABI) and Geostationary Lightning Mapper (GLM)), two solar-viewing instruments (Solar Ultraviolet Imager (SUVI) and Extreme ultraviolet and X-ray Irradiance Sensors (EXIS)) and two in situ instruments (Space Environment In-Situ Suite (SEISS) and a magnetometer pair). In addition to hosting the instruments, GOES-R also accommodates several communication packages designed to collect and relay data for weather forecasting and emergency management. Accommodating the six instruments and four communication payloads imposed challenging and competing constraints on the satellite, including requirements for extremely stable earth and solar pointing, high-speed and nearly error-free instrument data transmission, and a very quiet electromagnetic background. To meet mission needs, GOES-R employed several technological innovations, including low-thrust rocket engines that allow instrument observations to continue during maneuvers, and the first civilian use of Global Positioning System-based orbit determination in geostationary orbit. This paper will provide a brief overview of the GOES-R satellite and its instruments as well as the developmental challenges involved in accommodating the instruments and communications payloads.

An Overview of the Design and Development of the GOES R-Series Space Segment

NASA Technical Reports Server (NTRS)

Sullivan, Pam; Krimchansky, Alexander; Walsh, Timothy

2017-01-01

The first of the National Oceanic and Atmospheric Administration (NOAA) Geostationary Operational Environmental Satellite R-series (GOES-R) satellites was launched in November 2016. GOES-R has been developed by NOAA in partnership with the National Aeronautics and Space Administration (NASA). The satellite represents a quantum leap in the state of the art for geostationary weather satellites by providing data from a suite of six new instruments. All instruments were developed expressly for this mission, and include two Earth-observing instruments (the Advanced Baseline Imager (ABI) and Geostationary Lightning Mapper (GLM)), two solar-viewing instruments (Solar Ultraviolet Imager (SUVI) and Extreme ultraviolet and X-ray Irradiance Sensors (EXIS)) and two in situ instruments (Space Environment In-Situ Suite (SEISS) and a magnetometer pair). In addition to hosting the instruments, GOES-R also accommodates several communication packages designed to collect and relay data for weather forecasting and emergency management. Accommodating the six instruments and four communication payloads imposed challenging and competing constraints on the satellite, including requirements for extremely stable earth and solar pointing, high-speed and nearly error-free instrument data transmission, and a very quiet electromagnetic background. To meet mission needs, GOES-R employed several technological innovations, including low-thrust rocket engines that allow instrument observations to continue during maneuvers, and the first civilian use of Global Positioning System-based orbit determination in geostationary orbit. This paper will provide a brief overview of the GOES-R satellite and its instruments as well as the developmental challenges involved in accommodating the instruments and communications payloads.

14 CFR 23.783 - Doors.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Doors. 23.783 Section 23.783 Aeronautics... Cargo Accommodations § 23.783 Doors. (a) Each closed cabin with passenger accommodations must have at least one adequate and easily accessible external door. (b) Passenger doors must not be located with...

Hosting a Fourier Transform Spectrometer (FTS) on CubeSat Spacecraft Platforms for Global Measurements of Three-Dimensional Winds

NASA Astrophysics Data System (ADS)

Scott, D. K.; Neilsen, T. L.; Weston, C.; Frazier, C.; Smith, T.; Shumway, A.

2015-12-01

Global measurements of vertically-resolved atmospheric wind profiles offer the potential for improved weather forecasts and superior predictions of atmospheric wind patterns. A small-satellite constellation that uses a Fourier Transform Spectrometer (FTS) instrument onboard 12U CubeSats can provide measurements of global tropospheric wind profiles from space at a very low cost. These small satellites are called FTS CubeSats. This presentation will describe a spacecraft concept that provides a stable, robust platform to host the FTS payload. Of importance to the payload are power, data, station keeping, thermal, and accommodations that enable high spectral measurements to be made from a LEO orbit. The spacecraft concept draws on Space Dynamics Laboratory (SDL) heritage and the recent success of the Dynamic Ionosphere Cubesat Experiment (DICE) and HyperAngular Rainbow Polarimeter (HARP) missions. Working with team members, SDL built a prototype observatory (spacecraft and payload) for testing and proof of concept.

NASA's commercial research plans and opportunities

NASA Technical Reports Server (NTRS)

Arnold, Ray J.

1992-01-01

One of the primary goals of the National Aeronautics and Space Administration's (NASA) commercial space development plan is to encourage the development of space-based products and markets, along with the infrastructure and transportation that will support those products and markets. A three phased program has been instituted to carry out this program. The first phase utilizes government grants through the Centers for the Commercial Development of Space (CCDS) for space-related, industry driven research; the development of a technology data base; and the development of commercial space transportation and infrastructure. The second phase includes the development of these technologies by industry for new commercial markets, and features unique industry/government collaborations such as Joint Endeavor Agreements. The final phase will feature technical applications actually brought to the marketplace. The government's role will be to support industry required infrastructure to encourage start-up markets and industries through follow-on development agreements such as the Space Systems Development Agreement. The Office of Commercial Programs has an aggressive flight program underway on the Space Shuttle, suborbital rockets, orbital expendable launch vehicles, and the Commercial Middeck Accommodation Module with SPACEHAB Inc. The Office of Commercial Program's has been allocated 35 percent of the U.S. share of the Space Station Freedom resources for 1997 utilization. A utilization plan has been developed with the Centers for the Commercial Development of Space and has identified eleven materials processing and biotechnology payloads occupying 5 double racks in the pressurized module as well as two payloads external to the module in materials exposure and environment monitoring. The Office of Commercial Programs will rely on the Space Station Freedom to provide the long duration laboratory component for space-based commercial research.

NASA's commercial research plans and opportunities

NASA Astrophysics Data System (ADS)

Arnold, Ray J.

One of the primary goals of the National Aeronautics and Space Administration's (NASA) commercial space development plan is to encourage the development of space-based products and markets, along with the infrastructure and transportation that will support those products and markets. A three phased program has been instituted to carry out this program. The first phase utilizes government grants through the Centers for the Commercial Development of Space (CCDS) for space-related, industry driven research; the development of a technology data base; and the development of commercial space transportation and infrastructure. The second phase includes the development of these technologies by industry for new commercial markets, and features unique industry/government collaborations such as Joint Endeavor Agreements. The final phase will feature technical applications actually brought to the marketplace. The government's role will be to support industry required infrastructure to encourage start-up markets and industries through follow-on development agreements such as the Space Systems Development Agreement. The Office of Commercial Programs has an aggressive flight program underway on the Space Shuttle, suborbital rockets, orbital expendable launch vehicles, and the Commercial Middeck Accommodation Module with SPACEHAB Inc. The Office of Commercial Program's has been allocated 35 percent of the U.S. share of the Space Station Freedom resources for 1997 utilization. A utilization plan has been developed with the Centers for the Commercial Development of Space and has identified eleven materials processing and biotechnology payloads occupying 5 double racks in the pressurized module as well as two payloads external to the module in materials exposure and environment monitoring. The Office of Commercial Programs will rely on the Space Station Freedom to provide the long duration laboratory component for space-based commercial research.

Conducting Research on the International Space Station Using the EXPRESS Rack Facilities

NASA Technical Reports Server (NTRS)

Thompson, Sean W.; Lake, Robert E.

2013-01-01

Conducting Research on the International Space Station using the EXPRESS Rack Facilities. Sean W. Thompson and Robert E. Lake. NASA Marshall Space Flight Center, Huntsville, AL, USA. Eight "Expedite the Processing of Experiments to Space Station" (EXPRESS) Rack facilities are located within the International Space Station (ISS) laboratories to provide standard resources and interfaces for the simultaneous and independent operation of multiple experiments within each rack. Each EXPRESS Rack provides eight Middeck Locker Equivalent locations and two drawer locations for powered experiment equipment, also referred to as sub-rack payloads. Payload developers may provide their own structure to occupy the equivalent volume of one, two, or four lockers as a single unit. Resources provided for each location include power (28 Vdc, 0-500 W), command and data handling (Ethernet, RS-422, 5 Vdc discrete, +/- 5 Vdc analog), video (NTSC/RS 170A), and air cooling (0-200 W). Each rack also provides water cooling (500 W) for two locations, one vacuum exhaust interface, and one gaseous nitrogen interface. Standard interfacing cables and hoses are provided on-orbit. One laptop computer is provided with each rack to control the rack and to accommodate payload application software. Four of the racks are equipped with the Active Rack Isolation System to reduce vibration between the ISS and the rack. EXPRESS Racks are operated by the Payload Operations Integration Center at Marshall Space Flight Center and the sub-rack experiments are operated remotely by the investigating organization. Payload Integration Managers serve as a focal to assist organizations developing payloads for an EXPRESS Rack. NASA provides EXPRESS Rack simulator software for payload developers to checkout payload command and data handling at the development site before integrating the payload with the EXPRESS Functional Checkout Unit for an end-to-end test before flight. EXPRESS Racks began supporting investigations onboard ISS on April 24, 2001 and will continue through the life of the ISS.

The US space station and its electric power system

NASA Technical Reports Server (NTRS)

Thomas, Ronald L.

1988-01-01

The United States has embarked on a major development program to have a space station operating in low earth orbit by the mid-1990s. This endeavor draws on the talents of NASA and most of the aerospace firms in the U.S. Plans are being pursued to include the participation of Canada, Japan, and the European Space Agency in the space station. From the start of the program these was a focus on the utilization of the space station for science, technology, and commercial endeavors. These requirements were utilized in the design of the station and manifest themselves in: pressurized volume; crew time; power availability and level of power; external payload accommodations; microgravity levels; servicing facilities; and the ability to grow and evolve the space station to meet future needs. President Reagan directed NASA to develop a permanently manned space station in his 1984 State of the Union message. Since then the definition phase was completed and the development phase initiated. A major subsystem of the space station is its 75 kW electric power system. The electric power system has characteristics similar to those of terrestrial power systems. Routine maintenance and replacement of failed equipment must be accomplished safely and easily and in a minimum time while providing reliable power to users. Because of the very high value placed on crew time it is essential that the power system operate in an autonomous mode to minimize crew time required. The power system design must also easily accommodate growth as the power demands by users are expected to grow. An overview of the U.S. space station is provided with special emphasis on its electrical power system.

Constructive and Unproductive Processing of Traumatic Experiences in Trauma-Focused Cognitive-Behavioral Therapy for Youth.

PubMed

Hayes, Adele M; Yasinski, Carly; Grasso, Damion; Ready, C Beth; Alpert, Elizabeth; McCauley, Thomas; Webb, Charles; Deblinger, Esther

2017-03-01

Although there is substantial evidence to support the efficacy of cognitive-behavioral treatments (CBT) for posttraumatic stress disorder (PTSD), there is some debate about how these treatments have their effects. Modern learning theory and cognitive and emotional processing theories highlight the importance of reducing avoidance, facilitating the constructive processing of feared experiences, and strengthening new inhibitory learning. We examined variables thought to be associated with unproductive and constructive processing of traumatic experiences in a sample of 81 youth with elevated PTSD symptoms, who received Trauma-Focused Cognitive Behavioral Therapy (TF-CBT) for abuse or traumatic interpersonal loss. Sessions during the trauma narrative phase of TF-CBT were coded for indicators of unproductive processing (overgeneralization, rumination, avoidance) and constructive processing (decentering, accommodation of corrective information), as well as levels of negative emotion. In previous analyses of this trial (Ready et al., 2015), more overgeneralization during the narrative phase predicted less improvement in internalizing symptoms at posttreatment and a worsening of externalizing symptoms over the 12-month follow-up. In contrast, more accommodation predicted improvement in internalizing symptoms and also moderated the negative effects of overgeneralization on internalizing and externalizing symptoms. The current study examined correlates of overgeneralization and accommodation. Overgeneralization was associated with more rumination, less decentering, and more negative emotion, suggesting immersion in trauma-related material. Accommodation was associated with less avoidance and more decentering, suggesting a healthy distance from trauma-related material that might allow for processing and cognitive change. Decentering also predicted improvement in externalizing symptoms at posttreatment. Rumination and avoidance showed important associations with overgeneralization and accommodation, respectively, but did not predict treatment outcomes. This study identifies correlates of overgeneralization and accommodation that might shed light on how these variables relate to unproductive and constructive processing of traumatic experiences. Copyright © 2016. Published by Elsevier Ltd.

DeMi Payload Progress Update and Adaptive Optics (AO) Control Comparisons – Meeting Space AO Requirements on a CubeSat

NASA Astrophysics Data System (ADS)

Grunwald, Warren; Holden, Bobby; Barnes, Derek; Allan, Gregory; Mehrle, Nicholas; Douglas, Ewan S.; Cahoy, Kerri

2018-01-01

The Deformable Mirror (DeMi) CubeSat mission utilizes an Adaptive Optics (AO) control loop to correct incoming wavefronts as a technology demonstration for space-based imaging missions, such as high contrast observations (Earthlike exoplanets) and steering light into core single mode fibers for amplification. While AO has been used extensively on ground based systems to correct for atmospheric aberrations, operating an AO system on-board a small satellite presents different challenges. The DeMi payload 140 actuator MEMS deformable mirror (DM) corrects the incoming wavefront in four different control modes: 1) internal observation with a Shack-Hartmann Wavefront Sensor (SHWFS), 2) internal observation with an image plane sensor, 3) external observation with a SHWFS, and 4) external observation with an image plane sensor. All modes have wavefront aberration from two main sources, time-invariant launch disturbances that have changed the optical path from the expected path when calibrated in the lab and very low temporal frequency thermal variations as DeMi orbits the Earth. The external observation modes has additional error from: the pointing precision error from the attitude control system and reaction wheel jitter. Updates on DeMi’s mechanical, thermal, electrical, and mission design are also presented. The analysis from the DeMi payload simulations and testing provides information on the design options when developing space-based AO systems.

Ammonia Release on ISS

NASA Technical Reports Server (NTRS)

Macatangay, Ariel

2009-01-01

Crew: Approximately 53% metabolic load Product of protein metabolism Limit production of ammonia by external regulation NOT possbile Payloads Potential source Scientific experiments Thorough safety review ensures sufficient levels of containment

Error tracking control for underactuated overhead cranes against arbitrary initial payload swing angles

NASA Astrophysics Data System (ADS)

Zhang, Menghua; Ma, Xin; Rong, Xuewen; Tian, Xincheng; Li, Yibin

2017-02-01

This paper exploits an error tracking control method for overhead crane systems for which the error trajectories for the trolley and the payload swing can be pre-specified. The proposed method does not require that the initial payload swing angle remains zero, whereas this requirement is usually assumed in conventional methods. The significant feature of the proposed method is its superior control performance as well as its strong robustness over different or uncertain rope lengths, payload masses, desired positions, initial payload swing angles, and external disturbances. Owing to the same attenuation behavior, the desired error trajectory for the trolley for each traveling distance is not needed to be reset, which is easy to implement in practical applications. By converting the error tracking overhead crane dynamics to the objective system, we obtain the error tracking control law for arbitrary initial payload swing angles. Lyapunov techniques and LaSalle's invariance theorem are utilized to prove the convergence and stability of the closed-loop system. Simulation and experimental results are illustrated to validate the superior performance of the proposed error tracking control method.

Utilizing the US Lab Nadir Research Window for Remote Sensing Operations with The Window Observational Research Facility (WORF)

NASA Technical Reports Server (NTRS)

Turner, Richard; Barley, Bryan; Gilbert, Paul A. (Technical Monitor)

2002-01-01

The Window Observational Research Facility (WORF) is an ISPR-based rack facility designed to take advantage of the high optical quality US Lab Nadir research window. The WORF is based on the ISS Expedite the Processing of Experiments to Space Station (EXPRESS) rack mechanical structure and electronic systems. The WORF has a unique payload volume located at the center of the rack that provides access to the window. The interior dimensions of the payload volume are 34-in. (86.36 cm) wide by 33-in. (83.82 cm) high by 23-in. (58.42 cm) deep. This facility supports the deployment of payloads such as 9 in. aerial photography cameras and 12 in. diameter optical equipment. The WORF coupled with the optical quality of the United States Lab window support the deployment of various payload disciplines. The WORF provides payloads with power, data command and control, air cooling, water cooling, and video processing. The WORF's payload mounting surfaces and interfaces include the interior payload mounting shelf and the interior and exterior aircraft-like seat tracks. The payload mounting shelf is limited to a maximum mass of 136 kg (299 pounds). The WORF can accommodate large payloads such as the commonly used Leica-Heerbrug RC-30 aerial photography camera (whose dimensions are 53.3 cm (21-in.) wide by 50.8 cm (20-in.) deep by 76.2 cm (30-in.) long). The performance characteristics of the WORF allow it to support an array of payload disciplines. The WORF provides a maximum of 3 Kw at 28 Vdc and has a maximum data rate of 10 Mbps. The WORF's unique payload volume is designed to be light-tight, down to 2.8 x 10(exp -11) Watts/cm2/steradian, and have low-reflective surfaces. This specially designed WORF interior supports payload investigations that observe low-light-level phenomenon such as aurora. Although the WORF rack does not employ any active rack isolation (i.e., vibration dampening) technology, the rack provides a very stable environment for payload operations (on the order of X microradians). The facility's software is capable of being updated during its period of deployment. The WORF project also includes a Suitcase Simulator to allow for a payload developer to verify data interfaces at his development site, a trainer rack for astronauts to learn how to operate the WORF prior to flight, and the use of the EXPRESS Functional Checkout Units to allow for payload checkout at the KSC prior to launch.

Detecting Payload Attacks on Programmable Logic Controllers (PLCs)

DOE Office of Scientific and Technical Information (OSTI.GOV)

Yang, Huan

Programmable logic controllers (PLCs) play critical roles in industrial control systems (ICS). Providing hardware peripherals and firmware support for control programs (i.e., a PLC’s “payload”) written in languages such as ladder logic, PLCs directly receive sensor readings and control ICS physical processes. An attacker with access to PLC development software (e.g., by compromising an engineering workstation) can modify the payload program and cause severe physical damages to the ICS. To protect critical ICS infrastructure, we propose to model runtime behaviors of legitimate PLC payload program and use runtime behavior monitoring in PLC firmware to detect payload attacks. By monitoring themore » I/O access patterns, network access patterns, as well as payload program timing characteristics, our proposed firmware-level detection mechanism can detect abnormal runtime behaviors of malicious PLC payload. Using our proof-of-concept implementation, we evaluate the memory and execution time overhead of implementing our proposed method and find that it is feasible to incorporate our method into existing PLC firmware. In addition, our evaluation results show that a wide variety of payload attacks can be effectively detected by our proposed approach. The proposed firmware-level payload attack detection scheme complements existing bumpin- the-wire solutions (e.g., external temporal-logic-based model checkers) in that it can detect payload attacks that violate realtime requirements of ICS operations and does not require any additional apparatus.« less

Experience of Data Handling with IPPM Payload

NASA Astrophysics Data System (ADS)

Errico, Walter; Tosi, Pietro; Ilstad, Jorgen; Jameux, David; Viviani, Riccardo; Collantoni, Daniele

2010-08-01

A simplified On-Board Data Handling system has been developed by CAEN AURELIA SPACE and ABSTRAQT as PUS-over-SpaceWire demonstration platform for the Onboard Payload Data Processing laboratory at ESTEC. The system is composed of three Leon2-based IPPM (Integrated Payload Processing Module) computers that play the roles of Instrument, Payload Data Handling Unit and Satellite Management Unit. Two PCs complete the test set-up simulating an external Memory Management Unit and the Ground Control Unit. Communication among units take place primarily through SpaceWire links; RMAP[2] protocol is used for configuration and housekeeping. A limited implementation of ECSS-E-70-41B Packet Utilisation Standard (PUS)[1] over CANbus and MIL-STD-1553B has been also realized. The Open Source RTEMS is running on the IPPM AT697E CPU as real-time operating system.

External Payload Carrier (XPC) - A Novel Platform for Suborbital Research

NASA Technical Reports Server (NTRS)

Schallhorn, Paul; Groves, Curtis; Tatro, Charles; Kutter, Bernard; Szatkowski, Gerald; Bulk, Tim; Pitchford, Brian

2010-01-01

ULA, SAS, and NASA LSP are examining a new platform for suborbital research utilizing the Atlas V Launch Vehicle. The new platform, XPC, fills a new niche within the suborbital realm Large Heavy Lift (approximately 1200 cubic feet, 5000 lb payload). It will not compete with the commercial suborbital launch sector. The XPC will utilize excess performance on Atlas V missions. The Preliminary Design phase is recently underway. The XPC team is soliciting input from potential users.

The Get Away Special Program: Year 2000 and Beyond

NASA Technical Reports Server (NTRS)

Wilcox, David A.

1999-01-01

The Get Away Special (GAS) Program flew its first payload in 1982. Since then, 157 payloads have flown on the STS. As the GAS program approaches the new millennium, interest in flying the low-cost access to space continues. Many changes are in store, or are already underway, that will impact the GAS user community in the coming years. This presentation will briefly outline some of those changes and other external impacts to the GAS Program.

SLS Payload Transportation Beyond LEO

NASA Technical Reports Server (NTRS)

Creech, S. D.; Baker, J. D.; Jackman, A. L.; Vane, G.

2017-01-01

NASA has successfully completed the Critical Design Review (CDR) of the heavy lift Space Launch System (SLS) and is working towards the first flight of the vehicle in 2018. SLS will begin flying crewed missions with an Orion capsule to the lunar vicinity every year after the first 2 flights starting in the early 2020's. As early as 2021, in addition to delivering an Orion capsule to a cislunar destination, SLS will also deliver ancillary payload, termed "Co-manifested Payload (CPL)", with a mass of at least 5.5 mT and volume up to 280 m3 simultaneously to that same destination. Later SLS flights have a goal of delivering as much as 10 mT of CPL to cislunar destinations. In addition to cislunar destinations, SLS flights may deliver non-crewed, science-driven missions with Primary Payload (PPL) to more distant destinations. SLS PPL missions will utilize a unique payload fairing offering payload volume (ranging from 320 m3 to 540 m3) that greatly exceeds the largest existing Expendable Launch Vehicle (ELV) fairing available. The Characteristic Energy (C3) offered by the SLS system will generate opportunities to deliver up to 40 mT to cislunar space, and deliver double PPL mass or de-crease flight time by half for some outer planet destinations when compared to existing capabilities. For example, SLS flights may deliver the Europa Clipper to a Jovian destination in under 3 years by the mid 2020's, compared to the 7+ years cruise time required for current launch capabilities. This presentation will describe ground and flight accommodations, interfaces, resources, and performance planned to be made available to potential CPL and PPL science users of SLS. In addition, this presentation should promote a dialogue between vehicle developers, potential payload users, and funding sources in order to most efficiently evolve required SLS capabilities to meet diverse payload needs as they are identified over the next 35 years and beyond.

Modal Testing of Seven Shuttle Cargo Elements for Space Station

NASA Technical Reports Server (NTRS)

Kappus, Kathy O.; Driskill, Timothy C.; Parks, Russel A.; Patterson, Alan (Technical Monitor)

2001-01-01

From December 1996 to May 2001, the Modal and Control Dynamics Team at NASA's Marshall Space Flight Center (MSFC) conducted modal tests on seven large elements of the International Space Station. Each of these elements has been or will be launched as a Space Shuttle payload for transport to the International Space Station (ISS). Like other Shuttle payloads, modal testing of these elements was required for verification of the finite element models used in coupled loads analyses for launch and landing. The seven modal tests included three modules - Node, Laboratory, and Airlock, and four truss segments - P6, P3/P4, S1/P1, and P5. Each element was installed and tested in the Shuttle Payload Modal Test Bed at MSFC. This unique facility can accommodate any Shuttle cargo element for modal test qualification. Flexure assemblies were utilized at each Shuttle-to-payload interface to simulate a constrained boundary in the load carrying degrees of freedom. For each element, multiple-input, multiple-output burst random modal testing was the primary approach with controlled input sine sweeps for linearity assessments. The accelerometer channel counts ranged from 252 channels to 1251 channels. An overview of these tests, as well as some lessons learned, will be provided in this paper.

Concept for a Lunar Transfer Vehicle for Small Satellite Delivery to the Moon from the International Space Station

NASA Technical Reports Server (NTRS)

Elliott, John; Alkalai, Leon

2010-01-01

The International Space Station (ISS) has developed as a very capable center for scientific research in Lower Earth Orbit. An additional potential of the ISS that has not thus far been exploited, is the use of this orbiting plat-form for the assembly and launching of vehicles that could be sent to more distant destinations. This paper reports the results of a recent study that looked at an architecture and conceptual flight system design for a lunar transfer vehicle (LTV) that could be delivered to the ISS in segments, assembled, loaded with payload and launched from the ISS with the objective of delivering multiple small and micro satellites to lunar orbit. The design of the LTV was optimized for low cost and high payload capability, as well as ease of assembly. The resulting design would use solar electric propulsion (SEP) to carry a total payload mass of 250 kg from the ISS to a 100 km lunar orbit. A preliminary concept of operations was developed considering currently available delivery options and ISS capabili-ties that should prove flexible enough to accommodate a variety of payloads and missions. This paper will present an overview of the study, including key trades, mission and flight system design, and notional operational concept.

NASA's Space Launch System: Deep-Space Opportunities for SmallSats

NASA Technical Reports Server (NTRS)

Robinson, Kimberly F.; Schorr, Andrew A.

2017-01-01

Designed for human exploration missions into deep space, NASA's Space Launch System (SLS) represents a new spaceflight infrastructure asset, enabling a wide variety of unique utilization opportunities. While primarily focused on launching the large systems needed for crewed spaceflight beyond Earth orbit, SLS also offers a game-changing capability for the deployment of small satellites to deep-space destinations, beginning with its first flight. Currently, SLS is making rapid progress toward readiness for its first launch in two years, using the initial configuration of the vehicle, which is capable of delivering 70 metric tons (t) to Low Earth Orbit (LEO). On its first flight test of the Orion spacecraft around the moon, accompanying Orion on SLS will be small-satellite secondary payloads, which will deploy in cislunar space. The deployment berths are sized for "6U" CubeSats, and on EM-1 the spacecraft will be deployed into cislunar space following Orion separate from the SLS Interim Cryogenic Propulsion Stage. Payloads in 6U class will be limited to 14 kg maximum mass. Secondary payloads on EM-1 will be launched in the Orion Stage Adapter (OSA). Payload dispensers will be mounted on specially designed brackets, each attached to the interior wall of the OSA. For the EM-1 mission, a total of fourteen brackets will be installed, allowing for thirteen payload locations. The final location will be used for mounting an avionics unit, which will include a battery and sequencer for executing the mission deployment sequence. Following the launch of EM-1, deployments of the secondary payloads will commence after sufficient separation of the Orion spacecraft to the upper stage vehicle to minimize any possible contact of the deployed cubesats to Orion. Currently this is estimated to require approximately 4 hours. The allowed deployment window for the cubesats will be from the time the upper stage disposal maneuvers are complete to up to 10 days after launch. The upper stage will fly past the moon at a perigee of approximately 100km, and this closest approach will occur about 5 days after launch. The limiting factor for the latest deployment time is the available power in the sequencer system. Several NASA Mission Directorates were involved in the development of programs for the competition, selection, and development of EM-1 payloads that support directorate priorities. CubeSat payloads on EM-1 will include both NASA research experiments and spacecraft developed by industry, international and potentially academia partners. The Human Exploration and Operations Mission Directorate (HEOMD) Advanced Exploration Systems (AES) Division was allocated five payload opportunities on the EM-1 mission. Near Earth Asteroid (NEA) Scout is designed to rendezvous with and characterize a candidate NEA. A solar sail, an innovation the spacecraft will demonstrated for the CubeSat class, will provide propulsion. Lunar Flashlight will use a green propellant system and will search for potential ice deposits in the moon's permanently shadowed craters. BioSentinel is a yeast radiation biosensor, planned to measure the effects of space radiation on deoxyribonucleic acid (DNA). Lunar Icecube, a collaboration with Morehead State University, will prospect for water in ice, liquid, and vapor forms as well as other lunar volatiles from a low-perigee, highly inclined lunar orbit using a compact Infrared spectrometer. Skyfire, a partnership with Lockheed Martin, is a technology demonstration mission that will perform a lunar flyby, collecting spectroscopy, and thermography data to address questions related to surface characterization, remote sensing, and site selection. NASA's Space Technology Mission Directorate (STMD) was allocated three payload opportunities on the EM-1 mission. These slots will be filled via the 2 Centennial Challenges Program, NASA's flagship program for technology prize competitions, which directly engages the public, academia, and industry in open prize competitions to stimulate innovation. The NASA Science Mission Directorate (SMD) was allocated two payload opportunities on the EM-1 mission. The CubeSat Mission to Study Solar Particles (CuSP) payload will study the sources and acceleration mechanisms of solar and interplanetary particles in near-Earth orbit, support space weather research by determining proton radiation levels during Solar Energetic Particle (SEP) events and identifying suprathermal properties that could help predict geomagnetic storms. The LunaH-Map payload will help scientists understand the quantity of H-bearing materials in lunar cold traps (10 km), determine the concentration of H-bearing materials with 1m depth, and constrain the vertical distribution of H-bearing materials. The final three payload opportunities for the EM-1 mission were allocated for NASA's international space agency counterparts. The flight opportunities are intended to benefit the international space agency and NASA as well as further the collective space exploration goals. ArgoMoon is sponsored by ESA/ASI and will fly along with the ICPS on its disposal trajectory to perform proximity operations with the ICPS post-disposal, take external imagery of engineering and historical significance, and perform an optical communications demonstration. EQUULEUS, sponsored by JAXA, will fly to a libration orbit around the Earth-Moon L2 point and demonstrate trajectory control techniques within the Sun-Earth-Moon region for the first time by a nano spacecraft. The mission will also contribute to the future human exploration scenario by understanding the radiation environment in geospace and deep space, characterizing the flux of impacting meteors on the far side of the moon, and demonstrating the future deep space exploration scenario using the "deep space port" at Lagrange points. OMOTENASHI, also sponsored by JAXA, will land the smallest lunar lander to date on the lunar surface to demonstrate the feasibility of the hardware for distributed cooperative exploration system. Small landers will enable multi-point exploration, which is complimentary with large-scale human exploration. Once on the lunar surface, the OMOTENASHI spacecraft will observe the radiation and soil environments of the lunar surface by active radiation measurements and soil shear measurements. Following EM-1, Space Launch System will evolve to the more-powerful Block 1B configuration, which uses a new Exploration Upper Stage to increase the vehicle's LEO payload capability from 70 t to 105 t. With that transition, the Orion Stage Adapter, which will carry the secondary payloads on EM-1, will be phased out, and a new Universal Stage Adapter will be introduced, creating opportunities for flying larger secondary payloads. This paper will provide a brief status of SLS progress toward first launch; an overview of smallsat accommodations, integration, and operations on EM-1; information about the specific payloads flying on that launch; and a discussion of future accommodations and opportunities for secondary payloads on SLS for Exploration Mission-2 and beyond.

NASA's Space Launch System: Deep-Space Delivery for Smallsats

NASA Technical Reports Server (NTRS)

Robinson, Kimberly F.; Norris, George

2017-01-01

Designed for human exploration missions into deep space, NASA's Space Launch System (SLS) represents a new spaceflight infrastructure asset, enabling a wide variety of unique utilization opportunities. While primarily focused on launching the large systems needed for crewed spaceflight beyond Earth orbit, SLS also offers a game-changing capability for the deployment of small satellites to deep-space destinations, beginning with its first flight. Currently, SLS is making rapid progress toward readiness for its first launch in two years, using the initial configuration of the vehicle, which is capable of delivering 70 metric tons (t) to Low Earth Orbit (LEO). On its first flight test of the Orion spacecraft around the moon, accompanying Orion on SLS will be small-satellite secondary payloads, which will deploy in cislunar space. The deployment berths are sized for "6U" CubeSats, and on EM-1 the spacecraft will be deployed into cislunar space following Orion separate from the SLS Interim Cryogenic Propulsion Stage. Payloads in 6U class will be limited to 14 kg maximum mass. Secondary payloads on EM-1 will be launched in the Orion Stage Adapter (OSA). Payload dispensers will be mounted on specially designed brackets, each attached to the interior wall of the OSA. For the EM-1 mission, a total of fourteen brackets will be installed, allowing for thirteen payload locations. The final location will be used for mounting an avionics unit, which will include a battery and sequencer for executing the mission deployment sequence. Following the launch of EM-1, deployments of the secondary payloads will commence after sufficient separation of the Orion spacecraft to the upper stage vehicle to minimize any possible contact of the deployed CubeSats to Orion. Currently this is estimated to require approximately 4 hours. The allowed deployment window for the CubeSats will be from the time the upper stage disposal maneuvers are complete to up to 10 days after launch. The upper stage will fly past the moon at a perigee of approximately 100km, and this closest approach will occur about 5 days after launch. The limiting factor for the latest deployment time is the available power in the sequencer system. Several NASA Mission Directorates were involved in the development of programs for the competition, selection, and development of EM-1 payloads that support directorate priorities. CubeSat payloads on EM-1 will include both NASA research experiments and spacecraft developed by industry, international and potentially academia partners. The Human Exploration and Operations Mission Directorate (HEOMD) Advanced Exploration Systems (AES) Division was allocated five payload opportunities on the EM-1 mission. Near Earth Asteroid (NEA) Scout is designed to rendezvous with and characterize a candidate NEA. A solar sail, an innovation the spacecraft will demonstrated for the CubeSat class, will provide propulsion. Lunar Flashlight will use a green propellant system and will search for potential ice deposits in the moon's permanently shadowed craters. BioSentinel is a yeast radiation biosensor, planned to measure the effects of space radiation on deoxyribonucleic acid (DNA). Lunar Icecube, a collaboration with Morehead State University, will prospect for water in ice, liquid, and vapor forms as well as other lunar volatiles from a low-perigee, highly inclined lunar orbit using a compact Infrared spectrometer. Skyfire, a partnership with Lockheed Martin, is a technology demonstration mission that will perform a lunar flyby, collecting spectroscopy, and thermography data to address questions related to surface characterization, remote sensing, and site selection. NASA's Space Technology Mission Directorate (STMD) was allocated three payload opportunities on the EM-1 mission. These slots will be filled via the Centennial Challenges Program, NASA's flagship program for technology prize competitions, which directly engages the public, academia, and industry in open prize competitions to stimulate innovation. The NASA Science Mission Directorate (SMD) was allocated two payload opportunities on the EM-1 mission. The CubeSat Mission to Study Solar Particles (CuSP) payload will study the sources and acceleration mechanisms of solar and interplanetary particles in near-Earth orbit, support space weather research by determining proton radiation levels during Solar Energetic Particle (SEP) events and identifying suprathermal properties that could help predict geomagnetic storms. The LunaH-Map payload will help scientists understand the quantity of H-bearing materials in lunar cold traps (10 km), determine the concentration of H-bearing materials with 1m depth, and constrain the vertical distribution of H-bearing materials. The final three payload opportunities for the EM-1 mission were allocated for NASA's international space agency counterparts. The flight opportunities are intended to benefit the international space agency and NASA as well as further the collective space exploration goals. ArgoMoon is sponsored by ESA/ASI and will fly along with the ICPS on its disposal trajectory to perform proximity operations with the ICPS post-disposal, take external imagery of engineering and historical significance, and perform an optical communications demonstration. EQUULEUS, sponsored by JAXA, will fly to a libration orbit around the Earth-Moon L2 point and demonstrate trajectory control techniques within the Sun-Earth- Moon region for the first time by a nano spacecraft. The mission will also contribute to the future human exploration scenario by understanding the radiation environment in geospace and deep space, characterizing the flux of impacting meteors on the far side of the moon, and demonstrating the future deep space exploration scenario using the "deep space port" at Lagrange points. OMOTENASHI, also sponsored by JAXA, will land the smallest lunar lander to date on the lunar surface to demonstrate the feasibility of the hardware for distributed cooperative exploration system. Small landers will enable multi-point exploration, which is complimentary with large-scale human exploration. Once on the lunar surface, the OMOTENASHI spacecraft will observe the radiation and soil environments of the lunar surface by active radiation measurements and soil shear measurements. Following EM-1, Space Launch System will evolve to the more-powerful Block 1B configuration, which uses a new Exploration Upper Stage to increase the vehicle's LEO payload capability from 70 t to 105 t. With that transition, the Orion Stage Adapter, which will carry the secondary payloads on EM-1, will be phased out, and a new Universal Stage Adapter will be introduced, creating opportunities for flying larger secondary payloads. This paper will provide a brief status of SLS progress toward first launch; an overview of smallsat accommodations, integration, and operations on EM-1; information about the specific payloads flying on that launch; and a discussion of future accommodations and opportunities for secondary payloads on SLS for Exploration Mission-2 and beyond.

Future space transportation systems analysis study. Phase 1 extension: Transportation systems reference data, volume 2

NASA Technical Reports Server (NTRS)

1975-01-01

Transportation mass requirements are developed for various mission and transportation modes based on vehicle systems sized to fit the exact needs of each mission. The parametric data used to derive the mass requirements for each mission and transportation mode are presented to enable accommodation of possible changes in mode options or payload definitions. The vehicle sizing and functional requirements used to derive the parametric data are described.

Phase A conceptual design study of the Atmospheric, Magnetospheric and Plasmas in Space (AMPS) payload

NASA Technical Reports Server (NTRS)

1974-01-01

The 12 month Phase A Conceptual Design Study of the Atmospheric, Magnetospheric and Plasmas in Space (AMPS) payload performed within the Program Development Directorate of the Marshall Space Flight Center is presented. The AMPS payload makes use of the Spacelab pressurized module and pallet, is launched by the space shuttle, and will have initial flight durations of 7 days. Scientific instruments including particle accelerators, high power transmitters, optical instruments, and chemical release devices are mounted externally on the Spacelab pallet and are controlled by the experimenters from within the pressurized module. The capability of real-time scientist interaction on-orbit with the experiment is a major characteristic of AMPS.

Development of NASA's Space Communications and Navigation Test Bed Aboard ISS to Investigate SDR, On-Board Networking and Navigation Technologies

NASA Technical Reports Server (NTRS)

Reinhart, Richard C.; Kacpura, Thomas J.; Johnson, Sandra K.; Lux, James P.

2010-01-01

NASA is developing an experimental flight payload (referred to as the Space Communication and Navigation (SCAN) Test Bed) to investigate software defined radio (SDR), networking, and navigation technologies, operationally in the space environment. The payload consists of three software defined radios each compliant to NASA s Space Telecommunications Radio System Architecture, a common software interface description standard for software defined radios. The software defined radios are new technology developments underway by NASA and industry partners. Planned for launch in early 2012, the payload will be externally mounted to the International Space Station truss and conduct experiments representative of future mission capability.

Thermal evaluation of alternative shipping cask for irradiated experiments

DOE PAGES

Guillen, Donna Post

2015-06-01

Results of a thermal evaluation are provided for a new shipping cask under consideration for transporting irradiated experiments between the test reactor and post-irradiation examination (PIE) facilities. Most of the experiments will be irradiated in the Advanced Test Reactor (ATR) at Idaho National Laboratory (INL), then later shipped to the Hot Fuel Examination Facility (HFEF) located at the Materials and Fuels Complex for PIE. To date, the General Electric (GE)-2000 cask has been used to transport experiment payloads between these facilities. However, the availability of the GE-2000 cask to support future experiment shipping is uncertain. In addition, the internal cavitymore » of the GE-2000 cask is too short to accommodate shipping the larger payloads. Therefore, an alternate shipping capability is being pursued. The Battelle Energy Alliance, LLC, Research Reactor (BRR) cask has been determined to be the best alternative to the GE-2000 cask. An evaluation of the thermal performance of the BRR cask is necessary before proceeding with fabrication of the newly designed cask hardware and the development of handling, shipping and transport procedures. This paper presents the results of the thermal evaluation of the BRR cask loaded with a representative set of fueled and non-fueled payloads. When analyzed with identical payloads, experiment temperatures were found to be lower with the BRR cask than with the GE-2000 cask. Furthermore, from a thermal standpoint, the BRR cask was found to be a suitable alternate to the GE-2000 cask for shipping irradiated experiment payloads.« less

Citizen Science and Citizen Space Exploration: Potentials for Professional Collaboration

NASA Astrophysics Data System (ADS)

Wright, E.

2012-12-01

Citizens in Space is a project of the United States Rocket Academy, with the goal of promoting citizen science and citizen space exploration. This goal is enabled by the new reusable suborbital spacecraft now under development by multiple companies in the US. For the first phase of this project, we have acquired a contract for 10 flights on the Lynx suborbital spacecraft, which is under construction by XCOR Aerospace in Mojave, CA. This represents, to the best of our knowledge, the largest single bulk purchase of suborbital flights to date. Citizens in Space has published an open call for experiments to fly on these missions, which we expect will begin in late 2013 or early 2014. We will be selecting approx. 100 small experiments and 10 citizen astronauts to fly as payload operators. Although our primary goal is to encourage citizen science, these flight opportunities are also open to professional researchers who have payloads that meet our criteria. We believe that the best citizen-science projects are collaborations between professional and citizen scientists. We will discuss various ways in which professional scientists can collaborate with citizen scientists to take advantage of the flight opportunities provided by our program. We will discuss the capabilities of the Lynx vehicle, the 1u- and 2u-CubeSat form factor we are using for our payloads, and general considerations for payload integration. As an example of the payloads we can accommodate, we will discuss a NASA-inspired experiment to collect particles from the upper atmosphere.;

Hitchhiker: Customer Accommodations and Requirements Specifications (CARS)

NASA Technical Reports Server (NTRS)

1992-01-01

In 1984, NASA Headquarters established projects at the Goddard Space Flight Center (GSFC) and the Marshall Space Flight Center (MSFC) to develop quick-reaction carrier systems for low-cost 'flight of opportunity' or secondary payloads on the Space Transportation System (STS). One of these projects is the Hitchhiker (HH) Program. GSFC has developed a family of carrier equipment known as the Shuttle Payload of Opportunity Carrier (SPOC) system for mounting small payloads such as HH to the side of the Orbiter payload bay. The side-mounted HHs are referred to as Hitchhiker-G (HH-G). MSFC developed a cross-bay 'bridge-type' carrier structure called the Hitchhiker-M (HH-M). In 1987, responsibility for the HH-M carrier was transferred to and is now managed by the HH Project Office at the GSFC. The HH-M carrier now uses the same interchangeable SPOC avionics unit and the same electrical interfaces and services developed for HH-G. National Aeronautics and Space Administration (NASA) has created this document to acquaint potential HH system customers with the facilities NASA provides and the requirements which customers must satisfy to use these facilities. This publication defines interface items required for integrating customer equipment with the HH carrier system. Those items such as mounting equipment and electrical inputs and outputs; configuration, environmental, command, telemetry, and operational constraints are described as well as weight, power, and communications. The purpose of this publication is to help the customer understand essential integration documentation requirements and to prepare a Customer Payload Requirements (CPR) document.

Manifold gasket accommodating differential movement of fuel cell stack

DOEpatents

Kelley, Dana A.; Farooque, Mohammad

2007-11-13

A gasket for use in a fuel cell system having at least one externally manifolded fuel cell stack, for sealing the manifold edge and the stack face. In accordance with the present invention, the gasket accommodates differential movement between the stack and manifold by promoting slippage at interfaces between the gasket and the dielectric and between the gasket and the stack face.

External and Internal Sport Motivations of Young Adults

ERIC Educational Resources Information Center

Bollok, Sandor; Takacs, Johanna; Kalmar, Zsuzsanna; Dobay, Beata

2011-01-01

Study aim: To determine and evaluate the spectrum of sport motivation of young adults. Material and methods: A group of 600 subjects, aged 17-19 years, participated in the study. An "ad hoc" questionnaire was applied to assess the 4 motivational factors: competition and success-oriented motivation, external accommodation, physical…

International Space Station

NASA Technical Reports Server (NTRS)

Wahlberg, Jennifer; Gordon, Randy

2010-01-01

This slide presentation reviews the research on the International Space Station (ISS), including the sponsorship of payloads by country and within NASA. Included is a description of the space available for research, the Laboratory "Rack" facilities, the external research facilities and those available from the Japanese Experiment Module (i.e., Kibo), and highlights the investigations that JAXA has maintained. There is also a review of the launch vehicles and spacecraft that are available for payload transportation to the ISS, including cargo capabilities of the spacecraft.

Space Communication and Navigation Testbed Communications Technology for Exploration

NASA Technical Reports Server (NTRS)

Reinhart, Richard

2013-01-01

NASA developed and launched an experimental flight payload (referred to as the Space Communication and Navigation Test Bed) to investigate software defined radio, networking, and navigation technologies, operationally in the space environment. The payload consists of three software defined radios each compliant to NASAs Space Telecommunications Radio System Architecture, a common software interface description standard for software defined radios. The software defined radios are new technology developed by NASA and industry partners. The payload is externally mounted to the International Space Station truss and available to NASA, industry, and university partners to conduct experiments representative of future mission capability. Experiment operations include in-flight reconfiguration of the SDR waveform functions and payload networking software. The flight system communicates with NASAs orbiting satellite relay network, the Tracking, Data Relay Satellite System at both S-band and Ka-band and to any Earth-based compatible S-band ground station.

Opportunities for research on Space Station Freedom

NASA Technical Reports Server (NTRS)

Phillips, Robert W.

1992-01-01

NASA has allocated research accommodations on Freedom (equipment, utilities, etc.) to the program offices that sponsor space-based research and development as follows: Space Science and Applications (OSSA)--52 percent, Commercial Programs (OCP)--28 percent, Aeronautics and Space Technology (OAST)--12 percent, and Space Flight (OSF)--8 percent. Most of OSSA's allocation will be used for microgravity and life science experiments; although OSSA's space physics, astrophysics, earth science and applications, and solar system exploration divisions also will use some of this allocation. Other Federal agencies have expressed an interest in using Space Station Freedom. They include the National Institutes of Health (NIH), U.S. Geological Survey, National Science Foundation, National Oceanic and Atmospheric Administration, and U.S. Departments of Agriculture and Energy. Payload interfaces with space station lab support equipment must be simple, and experiment packages must be highly contained. Freedom's research facilities will feature International Standard Payload Racks (ISPR's), experiment racks that are about twice the size of a Spacelab rack. ESA's Columbus lab will feature 20 racks, the U.S. lab will have 12 racks, and the Japanese lab will have 10. Thus, Freedom will have a total of 42 racks versus 8 for Space lab. NASA is considering outfitting some rack space to accommodate small, self-contained payloads similar to the Get-Away-Special canisters and middeck-locker experiment packages flown on Space Shuttle missions. Crew time allotted to experiments on Freedom at permanently occupied capability will average 25 minutes per rack per day, compared to six hours per rack per day on Spacelab missions. Hence, telescience--the remote operation of space-based experiments by researchers on the ground--will play a very important role in space station research. Plans for supporting life sciences research on Freedom focus on the two basic goals of NASA 's space life sciences program: to ensure the health, safety, and productivity of humans in space and to acquire fundamental knowledge of biological processes. Space-based research has already shown that people and plants respond the same way to the microgravity environment: they lose structure. However, the mechanisms by which they respond are different, and researchers do not yet know much about these mechanisms. Life science research accommodations on Freedom will include facilities for experiments designed to address this and other questions, in fields such as gravitational biology, space physiology, and biomedical monitoring and countermeasures research.

SMART-1/CLEMENTINE Study of Humorum and Procellarum Basins

NASA Astrophysics Data System (ADS)

Carey, William; Foing, Bernard H.; Koschny, Detlef; Pio Rossi, Angelo; Josset, Jean-Luc

A study undertaken by ESA to define a European Reference Architecture for Space Exploration is due to be completed in September 2008. The development of this architecture over the past twelve months has identified a number of key capabilities, among them a lunar lander system, which could form the basis for Europe's contribution to the future exploration of space in collaboration with International Partners. The focus of this paper will be on the lunar lander system, and will present the results of an analysis of possible payloads that could be accommodated by the lander. As the industrial study is at the Phase 0 or Pre-Phase A level, the design of such a lander system is at a very early stage in its development, but an estimation of the payload capacity allows a general assessment of the types of possible payloads that could be carried, currently this capacity is estimated at 1.1 tonnes of gross payload mass to the lunar surface (assuming an Ariane 5 ECA launch). An important characteristic of the lunar lander is that it provides a versatile and flexible system for utilisation in a broad range of lunar missions which include: - Independent lunar exploration missions for science, technology demonstration and research. - Delivery of logistics and cargo to support human surface sortie missions. - Delivery of logistics to a lunar base/outpost. - Deployment of individual infrastructure elements in support of a lunar base/outpost. Based on the above different types of missions, a number of configurations of "reference payload" sets are in the process of being defined that cover specific exploration objectives related primarily to capability demonstration, exploration enabling research and enabled science. Aspects covered include: ISRU, robotics, mobility, human preparation, life science and geology. This paper will present the current status of definition of the Reference Payload sets.

SPACEHAB: A giant step in the commercial development of space

NASA Astrophysics Data System (ADS)

Shepard, James E.

SPACEHAB is a privately developed and operated system offering customers a crew-tended microgravity environment for experimentation and product development. The first SPACEHAB flight module was delivered to the SPACEHAB Payload Processing Facility (SPPF) in Florida and 22 experiments are being integrated for an April 1993 mission. SPACEHAB modules are flown in the forward quarter-bay of the NASA Orbiter and are supported by two crew members. The paylaod accommodations include up to 61 experiment lockers, double and single racks and standard mounting plates for mounting unique payload containers directly to the module structure. Experiments designed for the Orbiter mid-deck, Spacelab or Space Station Freedom can be flown in SPACEHAB. The 24-month integration cycle is currently the shortest for any crew-tended carrier; a goal of 18 months is being actively pursued.

Performance analysis of two-degree of freedom fractional order PID controllers for robotic manipulator with payload.

PubMed

Sharma, Richa; Gaur, Prerna; Mittal, A P

2015-09-01

The robotic manipulators are multi-input multi-output (MIMO), coupled and highly nonlinear systems. The presence of external disturbances and time-varying parameters adversely affects the performance of these systems. Therefore, the controller designed for these systems should effectively deal with such complexities, and it is an intriguing task for control engineers. This paper presents two-degree of freedom fractional order proportional-integral-derivative (2-DOF FOPID) controller scheme for a two-link planar rigid robotic manipulator with payload for trajectory tracking task. The tuning of all controller parameters is done using cuckoo search algorithm (CSA). The performance of proposed 2-DOF FOPID controllers is compared with those of their integer order designs, i.e., 2-DOF PID controllers, and with the traditional PID controllers. In order to show effectiveness of proposed scheme, the robustness testing is carried out for model uncertainties, payload variations with time, external disturbance and random noise. Numerical simulation results indicate that the 2-DOF FOPID controllers are superior to their integer order counterparts and the traditional PID controllers. Copyright © 2015 ISA. Published by Elsevier Ltd. All rights reserved.

Experiment definition and integration study for the accommodation of magnetic spectrometer payload on Spacelab/shuttle missions

NASA Technical Reports Server (NTRS)

Buffington, A.

1978-01-01

A super-cooled magnetic spectrometer for a cosmic-ray experiment is considered for application in the high energy astronomical observatory which may be used on a space shuttle spacelab mission. New cryostat parameters are reported which are appropriate to shuttle mission weight and mission duration constraints. Since a super-conducting magnetic spectrometer has a magnetic fringe field, methods for shielding sensitive electronic and mechanical components on nearby experiments are described.

Space station operations task force. Panel 3 report: User development and integration

NASA Technical Reports Server (NTRS)

1987-01-01

The User Development and Integration Panel of the Space Station Operations Task Force was chartered to develop concepts relating to the operations of the Space Station manned base and the platforms, user accommodation and integration activities. The needs of the user community are addressed in the context with the mature operations phase of the Space Station. Issues addressed include space station pricing options, marketing strategies, payload selection and resource allocation options, and manifesting techniques.

STS-39 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W.

1991-01-01

The STS-39 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem operations during the fortieth flight of the Space Shuttle and the twelfth flight of the Orbiter Vehicle Discovery (OV-103). In addition to the Discovery vehicle, the flight vehicle consisted of the following: an External Tank (ET) (designated as ET-46 (LWT-39); three Space Shuttle main engines (SSME's) (serial numbers 2026, 2030, and 2029 in positions 1, 2, and 3, respectively); and two Solid Rocket Boosters (SRB's) designated as BI-043. The primary objective of this flight was to successfully perform the planned operations of the Infrared Background Signature Survey (IBSS), Air Force Payload (AFP)-675, Space Test Payload (STP)-1, and the Multipurpose Experiment Canister (MPEC) payloads.

STS-39 Space Shuttle mission report

NASA Astrophysics Data System (ADS)

Fricke, Robert W.

1991-06-01

The STS-39 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem operations during the fortieth flight of the Space Shuttle and the twelfth flight of the Orbiter Vehicle Discovery (OV-103). In addition to the Discovery vehicle, the flight vehicle consisted of the following: an External Tank (ET) (designated as ET-46 (LWT-39); three Space Shuttle main engines (SSME's) (serial numbers 2026, 2030, and 2029 in positions 1, 2, and 3, respectively); and two Solid Rocket Boosters (SRB's) designated as BI-043. The primary objective of this flight was to successfully perform the planned operations of the Infrared Background Signature Survey (IBSS), Air Force Payload (AFP)-675, Space Test Payload (STP)-1, and the Multipurpose Experiment Canister (MPEC) payloads.

Ares V: Shifting the Payload Design Paradigm

NASA Technical Reports Server (NTRS)

Sumrall, Phil; Creech, Steve; Cockrell, Charles E.

2009-01-01

NASA is designing the Ares V heavy-lift cargo launch vehicle to send more crew and cargo to more places on the lunar surface than the 1960s-era Saturn V and to provide ongoing support for a permanent lunar outpost. This uncrewed cargo vehicle is designed to operate together with the Ares I crew vehicle (Figure 1). In addition to this role, however, its unmatched mass and volume capability represent a national asset for exploration, science, and commerce. The Ares V also enables or significantly enhances a large class of space missions not thought possible by scientists and engineers since the Saturn V program ended over 30 years ago. Compared to current systems, it will offer approximately five times the mass and volume to most orbits and locations. This should allow prospective mission planners to build robust payloads with margins that are three to five times the industry norm. The space inside the planned payload shroud has enough usable volume to launch the volumetric equivalent of approximately 10 Apollo Lunar Modules or approximately five equivalent Hubble Space Telescopes. This mass and volume capability to low-Earth orbit (LEO) enables a host of new scientific and observation platforms, such as telescopes, satellites, planetary and solar missions, as well as being able to provide the lift for future large in-space infrastructure missions, such as space based solar power and mining, Earth asteroid defense, propellant depots, etc. In addition, payload designers may also have the option of simplifying their designs or employing Ares V s payload as dumb mass to reduce technical and operational risk. The Ares V team is engaging the potential payload community now, two to three years before System Requirements Review (SRR), in order to better understand the additional requirements from the payload community that could be accommodated in the Ares V design in its conceptual phase. This paper will discuss the Ares V reference mission and capability, as well as its potential to perform other missions in the future.

KSC-07pd1811

NASA Image and Video Library

2007-07-08

KENNEDY SPACE CENTER, FLA. -- The payload canister is lifted off its transporter up to the payload changeout room. Inside the canister are the S5 truss, SPACEHAB module and external stowage platform 3, the payload for mission STS-118. The red umbilical lines are still attached. The payloads will be transferred inside the changeout room to wait for Space Shuttle Endeavour to arrive at the pad. The changeout room is the enclosed, environmentally controlled portion of the rotating service structure that supports cargo delivery to the pad and subsequent vertical installation into the orbiter payload bay. The mission will be Endeavour's first flight in more than four years. The shuttle has undergone extensive modifications, including the addition of safety upgrades already added to shuttles Discovery and Atlantis. Endeavour also features new hardware, such as the Station-to-Shuttle Power Transfer System that will allow the docked shuttle to draw electrical power from the station and extend its visits to the orbiting lab. Space Shuttle Endeavour is targeted for launch on Aug. 7 from Launch Pad 39A. Photo credit: NASA/Kim Shiflett

KSC-07pd1813

NASA Image and Video Library

2007-07-08

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 39A, the payload canister is lifted up to the payload changeout room. Inside the canister are the S5 truss, SPACEHAB module and external stowage platform 3, the payload for mission STS-118. The red umbilical lines are still attached. The payloads will be transferred inside the changeout room to wait for Space Shuttle Endeavour to arrive at the pad. The changeout room is the enclosed, environmentally controlled portion of the rotating service structure that supports cargo delivery to the pad and subsequent vertical installation into the orbiter payload bay. The mission will be Endeavour's first flight in more than four years. The shuttle has undergone extensive modifications, including the addition of safety upgrades already added to shuttles Discovery and Atlantis. Endeavour also features new hardware, such as the Station-to-Shuttle Power Transfer System that will allow the docked shuttle to draw electrical power from the station and extend its visits to the orbiting lab. Space Shuttle Endeavour is targeted for launch on Aug. 7 from Launch Pad 39A. Photo credit: NASA/Kim Shiflett

The Potential for Hosted Payloads at NASA

NASA Technical Reports Server (NTRS)

Andraschko, Mark; Antol, Jeffrey; Baize, Rosemary; Horan, Stephen; Neil, Doreen; Rinsland, Pamela; Zaiceva, Rita

2012-01-01

The 2010 National Space Policy encourages federal agencies to actively explore the use of inventive, nontraditional arrangements for acquiring commercial space goods and services to meet United States Government requirements, including...hosting government capabilities on commercial spacecraft. NASA's Science Mission Directorate has taken an important step towards this goal by adding an option for hosted payload responses to its recent Announcement of Opportunity (AO) for Earth Venture-2 missions. Since NASA selects a significant portion of its science missions through a competitive process, it is useful to understand the implications that this process has on the feasibility of successfully proposing a commercially hosted payload mission. This paper describes some of the impediments associated with proposing a hosted payload mission to NASA, and offers suggestions on how these impediments might be addressed. Commercially hosted payloads provide a novel way to serve the needs of the science and technology demonstration communities at a fraction of the cost of a traditional Geostationary Earth Orbit (GEO) mission. The commercial communications industry launches over 20 satellites to GEO each year. By exercising this repeatable commercial paradigm of privately financed access to space with proven vendors, NASA can achieve science goals at a significantly lower cost than the current dedicated spacecraft and launch vehicle approach affords. Commercial hosting could open up a new realm of opportunities for NASA science missions to make measurements from GEO. This paper also briefly describes two GEO missions recommended by the National Academies of Science Earth Science Decadal Survey, the Geostationary Coastal and Air Pollution Events (GEO-CAPE) mission and the Precipitation and All-weather Temperature and Humidity (PATH) mission. Hosted payload missions recently selected for implementation by the Office of the Chief Technologist are also discussed. Finally, there are technical differences specific to hosted payloads and the GEO environment that must be considered when planning and developing a hosted payload mission. This paper addresses some of payload accommodation differences from the typical NASA LEO mission, including spacecraft interfaces, attitude control and knowledge, communications, data handling, mission operations, ground systems, and the thermal, radiation, and electromagnetic environment. The paper also discusses technical and programmatic differences such as limits to NASA's involvement with commercial quality assurance processes to conform to the commercial schedule and minimizing the price that makes hosted payloads an attractive option.

KSC-02pd0392

NASA Image and Video Library

2002-04-03

KENNEDY SPACE CENTER, FLA. -- With the Rotating Service Structure rolled back, Space Shuttle Atlantis stands ready for launch on mission STS-110. The Orbiter Access Arm extends from the Fixed Service Structure (FSS) to the crew compartment hatch, through which the STS-110 crew will enter Atlantis. Above the golden external tank is the vent hood (known as the "beanie cap") at the end of the gaseous oxygen vent arm. Vapors are created as the liquid oxygen in the external tank boil off. The hood vents the gaseous oxygen vapors away from the Space Shuttle vehicle. The RSS provides protected access to the orbiter for changeout and servicing of payloads at the pad. The structure has access platforms at five levels to provide access to the payload bay. The FSS provides access to the orbiter and the RSS. Mission STS-110 is scheduled to launch April 4 on its 11-day mission to the International Space Station

KSC-02pd0390

NASA Image and Video Library

2002-04-03

KENNEDY SPACE CENTER, FLA. -- Space Shuttle Atlantis is revealed as the Rotating Service Structure rolls back into launch position. The RSS provides protected access to the orbiter for changeout and servicing of payloads at the pad. The structure has access platforms at five levels to provide access to the payload bay. The Shuttle rests on the Mobile Launcher Platform (MLP), which straddles the flame trench below. The flame trench is part of the Flame Deflector System that insulates pad structures from the intense heat of the launch. Above the golden external tank is the vent hood (known as the "beanie cap") at the end of the gaseous oxygen vent arm. Vapors are created as the liquid oxygen in the external tank boil off. The hood vents the gaseous oxygen vapors away from the Space Shuttle vehicle. Mission STS-110 is scheduled to launch April 4 on its 11-day mission to the International Space Station

Shuttle/tethered satellite system conceptual design study

NASA Technical Reports Server (NTRS)

1976-01-01

A closed-loop control system was added to the tether reel which improves control over the tethered satellite. In addition to increasing the stability of the tethered satellite along local vertical, this control system is used for deployment and retrieval of tethered satellites. This conceptual design study describes a tether system for suspending a science payload at an altitude of 120 km from space shuttle orbiter flying at an altitude of 200 km. In addition to the hardware conceptual designs, various aspects concerning Orbiter accommodations are discussed.

Is Weapon System Cost Growth Increasing? A Quantitative Assessment of Completed and Ongoing Programs

DTIC Science & Technology

2007-01-01

analysis of the point at five years past MS B may be prudent. 49 APPENDIX A Completed Programs Aircraft A-7D Corsair II Data are from September 1969...rocket vehicle used to deploy satellites to higher orbits from the space shuttle payload bay or atop the Titan IV booster. SARs report that quantities...Cost Growth Increasing? Other Common Strategic Rotary Launcher This program designed and built mechanisms housed within bomb bays to accommodate the

Demonstration of the B4C/NaIO4/PTFE Delay in the U.S. Army Hand-Held Signal

DTIC Science & Technology

2015-05-20

Figure 1. Partial cross section diagram of a hand-held signal showing the rocket motor , delay element, expelling charge, and pyrotechnic payload as...The black powder-based rocket motor , consisting of propellant pellets (G) encased in a cardboard tube, contains an axial core hole to accommodate the...that ignites the rocket motor . Simultaneously, the delay element is ignited and burns for an interval (preferably 5−6 s) before it ignites the black

Experiment definition and integration study for the accommodation of giant, passive detector of Exotic Particles In the Cosmic Rays (EPIC) payload on shuttle/spacelab missions

NASA Technical Reports Server (NTRS)

Price, P. B.

1978-01-01

The feasibility of the design, construction, launch and retrieval of a hinged 15 ft by 110 ft the platform containing an array of interleaved CR-39 and Lexan track-recording detectors to be placed into circular orbit by space shuttle is assessed. The total weight of the detector assembly plus supporting structure and accessories is 32,000 pounds. The modular construction permits as little as one fourth of the payload to be exposed at one time. The CR-39 detector has sensitivity adequate to detect and study cosmic rays ranging from minimum ionizing iron-group nuclei to the heaviest elements. The detectors will survive a one year exposure to trapped protons without losing their high resolution. Advantages include low cost, huge collecting power (approximately 150 sq m) as well as the high resolution previously attainable only with electronic detectors.

Structural design, analysis, and modal testing of the petite amateur navy satellite (PANSAT)

NASA Astrophysics Data System (ADS)

Sakoda, Daniel J.

1992-09-01

The Naval Postgraduate School's (NPS) Space Systems Academic Group is developing the Petite Amateur Navy Satellite (PANSAT), a small satellite for digital store-and-forward communication in the amateur frequency band. PANSAT is intended to be a payload of opportunity amendable to a number of launch vehicles. The Shuttle Small Self-Contained Payload (SSCP) program was chosen as a design baseline because of its high margins of safety as a manned system. The PANSAT structure design is presented for the launch requirements of a Shuttle SSCP. A finite element model was developed and studied for the design loads of a SSCP. The results showed the structure to be very robust and likely to accommodate the requirements of other launch vehicles. The finite element analysis was verified by model testing, correlating the fundamental mode of the finite element model with that of an engineering test structure.

Backshell Radiative Heating on Human-Scale Mars Entry Vehicles

NASA Technical Reports Server (NTRS)

West,Thomas K., IV; Theisinger, John E.; Brune, Andrew J.; Johnston, Christopher O.

2017-01-01

This work quantifies the backshell radiative heating experienced by payloads on human- scale vehicles entering the Martian atmosphere. Three underlying configurations were studied: a generic sphere, a sphere-cone forebody with a cylindrical payload, and an ellipsled. Computational fluid dynamics simulations of the flow field and radiation were performed using the LAURA and HARA codes, respectively. Results of this work indicated the primary contributor to radiative heating is emission from the CO2 IR band system. Furthermore, the backshell radiation component of heating can persist lower than 2 km/s during entry and descent. For the sphere-cone configuration a peak heat flux of about 3.5 W/cm(exp. 2) was observed at the payload juncture during entry. At similar conditions, the ellipsled geometry experienced about 1.25 W/cm(exp. 2) on the backshell, but as much as 8 W/cm(exp. 2) on the base at very high angle of attack. Overall, this study sheds light on the potential magnitudes of backshell radiative heating that various configurations may experience. These results may serve as a starting point for thermal protection system design or configuration changes necessary to accommodate thermal radiation levels.

Hydraulic manipulator research at ORNL

DOE Office of Scientific and Technical Information (OSTI.GOV)

Kress, R.L.; Jansen, J.F.; Love, L.J.

1997-03-01

Recently, task requirements have dictated that manipulator payload capacity increase to accommodate greater payloads, greater manipulator length, and larger environmental interaction forces. General tasks such as waste storage tank cleanup and facility dismantlement and decommissioning require manipulator life capacities in the range of hundreds of pounds rather than tens of pounds. To meet the increased payload capacities demanded by present-day tasks, manipulator designers have turned once again to hydraulics as a means of actuation. In order to successfully design, build, and deploy a new hydraulic manipulator (or subsystem), sophisticated modeling, analysis, and control experiments are usually needed. Oak Ridge Nationalmore » Laboratory (ORNL) has a history of projects that incorporate hydraulics technology, including mobile robots, teleoperated manipulators, and full-scale construction equipment. In addition, to support the development and deployment of new hydraulic manipulators, ORNL has outfitted a significant experimental laboratory and has developed the software capability for research into hydraulic manipulators, hydraulic actuators, hydraulic systems, modeling of hydraulic systems, and hydraulic controls. The purpose of this article is to describe the past hydraulic manipulator developments and current hydraulic manipulator research capabilities at ORNL. Included are example experimental results from ORNL`s flexible/prismatic test stand.« less

STS-40 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W.

1991-01-01

The STS-40 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem operations during the forty-first flight of the Space Shuttle and the eleventh flight of the Orbiter Vehicle Columbia (OV-102). In addition to the Columbia vehicle, the flight vehicle consisted of an External Tank (ET) designated as ET-41 (LWT-34), three Space Shuttle main engines (SSME's) (serial numbers 2015, 2022, and 2027 in positions 1, 2, and 3, respectively), and two Solid Rocket Boosters (SRB's) designated as BI-044. The primary objective of the STS-40 flight was to successfully perform the planned operations of the Spacelab Life Sciences-1 (SLS-1) payload. The secondary objectives of this flight were to perform the operations required by the Getaway Special (GAS) payloads and the Middeck O-Gravity Dynamics Experiment (MODE) payload.

STS-40 Space Shuttle mission report

NASA Astrophysics Data System (ADS)

Fricke, Robert W.

1991-07-01

The STS-40 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem operations during the forty-first flight of the Space Shuttle and the eleventh flight of the Orbiter Vehicle Columbia (OV-102). In addition to the Columbia vehicle, the flight vehicle consisted of an External Tank (ET) designated as ET-41 (LWT-34), three Space Shuttle main engines (SSME's) (serial numbers 2015, 2022, and 2027 in positions 1, 2, and 3, respectively), and two Solid Rocket Boosters (SRB's) designated as BI-044. The primary objective of the STS-40 flight was to successfully perform the planned operations of the Spacelab Life Sciences-1 (SLS-1) payload. The secondary objectives of this flight were to perform the operations required by the Getaway Special (GAS) payloads and the Middeck O-Gravity Dynamics Experiment (MODE) payload.

Space Communication and Navigation SDR Testbed, Overview and Opportunity for Experiments

NASA Technical Reports Server (NTRS)

Reinhart, Richard C.

2013-01-01

NASA has developed an experimental flight payload (referred to as the Space Communication and Navigation (SCAN) Test Bed) to investigate software defined radio (SDR) communications, networking, and navigation technologies, operationally in the space environment. The payload consists of three software defined radios each compliant to NASAs Space Telecommunications Radio System Architecture, a common software interface description standard for software defined radios. The software defined radios are new technology developments underway by NASA and industry partners launched in 2012. The payload is externally mounted to the International Space Station truss to conduct experiments representative of future mission capability. Experiment operations include in-flight reconfiguration of the SDR waveform functions and payload networking software. The flight system will communicate with NASAs orbiting satellite relay network, the Tracking and Data Relay Satellite System at both S-band and Ka-band and to any Earth-based compatible S-band ground station. The system is available for experiments by industry, academia, and other government agencies to participate in the SDR technology assessments and standards advancements.

STS-55 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1993-01-01

A summary of the Space Shuttle Payloads, Orbiter, External Tank, Solid Rocket Booster, Redesigned Solid Rocket Motor, and the Main Engine subsystems performance during the 55th flight of the Space Shuttle Program and the 14th flight of Columbia is presented.

The international space station as a free flyer servicing node

NASA Astrophysics Data System (ADS)

Antol, Jeffrey; Headley, David E.

1999-01-01

The International Space Station will provide a multitude of opportunities for an expanding customer base to make use of this international resource. One such opportunity is servicing of various visiting vehicles that are in a similar orbit to the station. Servicing may include change-out of payloads, replenishment of consumables, repair, and refurbishment operations. Previous studies have been conducted in which ``paper'' free flyers have been assessed against the station's ability to accommodate them. Over the last several months though, an already flown free flyer, EURECA, was assessed as a real-life visiting free flyer design reference mission. Issues such as capture/berthing, servicing, logistics support, and stowage were assessed for station design and operational approaches. This paper will highlight critical visiting vehicle design considerations, identify station issues, and provide recommendations for accommodation of a wide range of visiting vehicle requirements of the future.

The International Space Station As a Free Flyer Servicing Node

NASA Technical Reports Server (NTRS)

Antol, Jeffrey; Headley, David E.

1999-01-01

The International Space Station will provide a multitude of opportunities for an expanding customer base to make use of this international resource. One such opportunity is servicing of various visiting vehicles that are in a similar orbit to the station. Servicing may include change-out of payloads, replenishment of consumables, repair, and refurbishment operations. Previous studies have been conducted in which "paper" free flyers have been assessed against the station s ability to accommodate them. Over the last several months though, an already flown free flyer, EURECA, was assessed as a real-life visiting free flyer design reference mission. Issues such as capture/berthing, servicing, logistics support, and stowage were assessed for station design and operational approaches. This paper will highlight critical visiting vehicle design considerations, identify station issues, and provide recommendations for accommodation of a wide range of visiting vehicle requirements of the future.

First Materials Science Research Rack Capabilities and Design Features

NASA Technical Reports Server (NTRS)

Schaefer, D.; King, R.; Cobb, S.; Whitaker, Ann F. (Technical Monitor)

2001-01-01

The first Materials Science Research Rack (MSRR-1) will accommodate dual Experiment Modules (EM's) and provide simultaneous on-orbit processing operations capability. The first international Materials Science Experiment Module for the MSRR-1 is an international cooperative research activity between NASA's Marshall Space Flight Center (MSFC) and the European Space Agency's (ESA) European Space Research and Technology Center. (ESTEC). This International Standard Payload Rack (ISPR) will contain the Materials Science Laboratory (MSL) developed by ESA as an Experiment Module. The MSL Experiment Module will accommodate several on-orbit exchangeable experiment-specific Module Inserts. Module Inserts currently planned are a Quench Module Insert, Low Gradient Furnace, Solidification with Quench Furnace, and Diffusion Module Insert. The second Experiment Module for the MSRR-1 configuration is a commercial device supplied by MSFC's Space Products Department (SPD). It includes capabilities for vapor transport processes and liquid metal sintering. This Experiment Module will be replaced on-orbit with other NASA Materials Science EMs.

Advanced Cosmic-Ray Composition Experiment for Space Station (ACCESS): ACCESS Accommodation Study Report

NASA Technical Reports Server (NTRS)

Wilson, Thomas L. (Editor); Wefel, John P. (Editor)

1999-01-01

In 1994 NASA Administrator selected the first high-energy particle physics experiment for the Space Station, the Alpha Magnetic Spectrometer (AMS), to place a magnetic spectrometer in Earth orbit and search for cosmic antimatter. A natural consequence of this decision was that NASA would begin to explore cost-effective ways through which the design and implementation of AMS might benefit other promising payload experiments. The first such experiment to come forward was Advanced Cosmic-Ray Composition Experiment for Space Station (ACCESS) in 1996. It was proposed as a new mission concept in space physics to attach a cosmic-ray experiment of weight, volume, and geometry similar to the AMS on the International Space Station (ISS), and replace the latter as its successor when the AMS is returned to Earth. This was to be an extension of NASA's suborbital balloon program, with balloon payloads serving as the precursor flights and heritage for ACCESS. The balloon programs have always been a cost-effective NASA resource since the particle physics instrumentation for balloon and space applications are directly related. The next step was to expand the process, pooling together expertise from various NASA centers and universities while opening up definition of the ACCESS science goals to the international community through the standard practice of peer review. This process is still ongoing, and the accommodation study presented here will discuss the baseline definition of ACCESS as we understand it today.

KENNEDY SPACE CENTER, FLA. - An overhead crane in the Space Station Processing Facility lifts the U.S. Node 2 out of its shipping container. The node will be moved to a workstand. The second of three connecting modules on the International Space Station, the Italian-built Node 2 attaches to the end of the U.S. Lab and provides attach locations for the Japanese laboratory, European laboratory, the Centrifuge Accommodation Module and, later, Multipurpose Logistics Modules. It will provide the primary docking location for the Shuttle when a pressurized mating adapter is attached to Node 2. Installation of the module will complete the U.S. Core of the ISS. Node 2 is the designated payload for mission STS-120. No orbiter or launch date has been determined yet.

NASA Image and Video Library

2003-06-03

KENNEDY SPACE CENTER, FLA. - An overhead crane in the Space Station Processing Facility lifts the U.S. Node 2 out of its shipping container. The node will be moved to a workstand. The second of three connecting modules on the International Space Station, the Italian-built Node 2 attaches to the end of the U.S. Lab and provides attach locations for the Japanese laboratory, European laboratory, the Centrifuge Accommodation Module and, later, Multipurpose Logistics Modules. It will provide the primary docking location for the Shuttle when a pressurized mating adapter is attached to Node 2. Installation of the module will complete the U.S. Core of the ISS. Node 2 is the designated payload for mission STS-120. No orbiter or launch date has been determined yet.

Space shuttle phase B extension, volume 1

NASA Technical Reports Server (NTRS)

1971-01-01

In order to define a system which would significantly reduce payload delivery costs, activities were extended to modifications of the reusable space shuttle design concept. Considered were systems using orbiters with external propellant tanks and an interim expendable booster which allowed phased development of the usable orbiter and booster. Analyzed were: Merits of internal and external propellant tanks and the impact of external LH2 compared to L02 and LH2; impact of cargo bay size; impact abort; merit of expendable booster options; and merit of a phased development program. Studies showed that external L02/LH2 and the continued use of the J-2S engine on the orbiter reduced program cost and risk.

KSC-00pp1736

NASA Image and Video Library

2000-11-14

KENNEDY SPACE CENTER, FLA. -- The payload transport canister, with the P6 integrated truss segment inside, is close to the payload changeout room on the Rotating Service Structure (RSS) at left. The PCR is the enclosed, environmentally controlled portion of the RSS that supports payload delivery at the pad. At right is Space Shuttle Endeavour with its orange external tank and one solid rocket booster showing behind it. When the RSS is closed around Endeavour, the P6 truss will be moved into the orbiter’s payload bay. The P6, payload on mission STS-97, comprises Solar Array Wing-3 and the Integrated Electronic Assembly, to be installed on the International Space Station. The Station’s electrical power system will use eight photovoltaic solar arrays, each 112 feet long by 39 feet wide, to convert sunlight to electricity. The solar arrays are mounted on a “blanket” that can be folded like an accordion for delivery. Once in orbit, astronauts will deploy the blankets to their full size. Gimbals will be used to rotate the arrays so that they will face the Sun to provide maximum power to the Space Station. Launch of STS-97 is scheduled for Nov. 30 at 10:06 p.m. EST

KSC00pp1736

NASA Image and Video Library

2000-11-14

KENNEDY SPACE CENTER, FLA. -- The payload transport canister, with the P6 integrated truss segment inside, is close to the payload changeout room on the Rotating Service Structure (RSS) at left. The PCR is the enclosed, environmentally controlled portion of the RSS that supports payload delivery at the pad. At right is Space Shuttle Endeavour with its orange external tank and one solid rocket booster showing behind it. When the RSS is closed around Endeavour, the P6 truss will be moved into the orbiter’s payload bay. The P6, payload on mission STS-97, comprises Solar Array Wing-3 and the Integrated Electronic Assembly, to be installed on the International Space Station. The Station’s electrical power system will use eight photovoltaic solar arrays, each 112 feet long by 39 feet wide, to convert sunlight to electricity. The solar arrays are mounted on a “blanket” that can be folded like an accordion for delivery. Once in orbit, astronauts will deploy the blankets to their full size. Gimbals will be used to rotate the arrays so that they will face the Sun to provide maximum power to the Space Station. Launch of STS-97 is scheduled for Nov. 30 at 10:06 p.m. EST

KSC-97PC880

NASA Image and Video Library

1997-06-04

The Space Shuttle Orbiter Columbia is reflected in a nearby pond as it rolls over to the Vehicle Assembly Building (VAB) June 4 from Orbiter Processing Facility (OPF) 1 atop its transporter in preparation for the STS-94 mission. Once inside the VAB, Columbia will be hoisted to be mated with its solid rocket boosters and external tank. Columbia was moved to the OPF April 8 after the completion of the STS-83 mission. KSC payloads processing employees then began work to reservice the Microgravity Science Laboratory-1 (MSL-1) Spacelab module in the orbiter’s payload bay for the STS-94 mission. This was the first time that this type of payload was reserviced without removing it from the payload bay. This new procedure pioneers processing efforts for possible quick relaunch turnaround times for future payloads. The MSL-1 module will fly again with the full complement of STS-83 experiments after that mission was cut short due to indications of a faulty fuel cell. During the scheduled 16-day STS-94 mission, the experiments will be used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducts combustion, protein crystal growth and materials processing experiments

MACSAT - A Near Equatorial Earth Observation Mission

NASA Astrophysics Data System (ADS)

Kim, B. J.; Park, S.; Kim, E.-E.; Park, W.; Chang, H.; Seon, J.

MACSAT mission was initiated by Malaysia to launch a high-resolution remote sensing satellite into Near Equatorial Orbit (NEO). Due to its geographical location, Malaysia can have large benefits from NEO satellite operation. From the baseline circular orbit of 685 km altitude with 7 degrees of inclination, the neighboring regions around Malaysian territory can be frequently monitored. The equatorial environment around the globe can also be regularly observed with unique revisit characteristics. The primary mission objective of MACSAT program is to develop and validate technologies for a near equatorial orbit remote sensing satellite system. MACSAT is optimally designed to accommodate an electro-optic Earth observation payload, Medium-sized Aperture Camera (MAC). Malaysian and Korean joint engineering teams are formed for the effective implementation of the satellite system. An integrated team approach is adopted for the joint development for MACSAT. MAC is a pushbroom type camera with 2.5 m of Ground Sampling Distance (GSD) in panchromatic band and 5 m of GSD in four multi-spectral bands. The satellite platform is a mini-class satellite. Including MAC payload, the satellite weighs under 200 kg. Spacecraft bus is designed optimally to support payload operations during 3 years of mission life. The payload has 20 km of swath width with +/- 30 o of tilting capability. 32 Gbits of solid state recorder is implemented as the mass image storage. The ground element is an integrated ground station for mission control and payload operation. It is equipped with S- band up/down link for commanding and telemetry reception as well as 30 Mbps class X-band down link for image reception and processing. The MACSAT system is capable of generating 1:25,000-scale image maps. It is also anticipated to have capability for cross-track stereo imaging for Digital elevation Model (DEM) generation.

A comparison of the Shuttle remote manipulator system and the Space Station Freedom mobile servicing center

NASA Technical Reports Server (NTRS)

Taylor, Edith C.; Ross, Michael

1989-01-01

The Shuttle Remote Manipulator System is a mature system which has successfully completed 18 flights. Its primary functional design driver was the capability to deploy and retrieve payloads from the Orbiter cargo bay. The Space Station Freedom Mobile Servicing Center is still in the requirements definition and early design stage. Its primary function design drivers are the capabilities: to support Space Station construction and assembly tasks; to provide external transportation about the Space Station; to provide handling capabilities for the Orbiter, free flyers, and payloads; to support attached payload servicing in the extravehicular environment; and to perform scheduled and un-scheduled maintenance on the Space Station. The differences between the two systems in the area of geometric configuration, mobility, sensor capabilities, control stations, control algorithms, handling performance, end effector dexterity, and fault tolerance are discussed.

Robust adaptive antiswing control of underactuated crane systems with two parallel payloads and rail length constraint.

PubMed

Zhang, Zhongcai; Wu, Yuqiang; Huang, Jinming

2016-11-01

The antiswing control and accurate positioning are simultaneously investigated for underactuated crane systems in the presence of two parallel payloads on the trolley and rail length limitation. The equations of motion for the crane system in question are established via the Euler-Lagrange equation. An adaptive control strategy is proposed with the help of system energy function and energy shaping technique. Stability analysis shows that under the designed adaptive controller, the payload swings can be suppressed ultimately and the trolley can be regulated to the destination while not exceeding the pre-specified boundaries. Simulation results are provided to show the satisfactory control performances of the presented control method in terms of working efficiency as well as robustness with respect to external disturbances. Copyright © 2016 ISA. Published by Elsevier Ltd. All rights reserved.

Overview of the Life Science Glovebox (LSG) Facility and the Research Performed in the LSG

NASA Technical Reports Server (NTRS)

Cole, J. Michael; Young, Yancy

2016-01-01

The Life Science Glovebox (LSG) is a rack facility currently under development with a projected availability for International Space Station (ISS) utilization in the FY2018 timeframe. Development of the LSG is being managed by the Marshal Space Flight Center (MSFC) with support from Ames Research Center (ARC) and Johnson Space Center (JSC). The MSFC will continue management of LSG operations, payload integration, and sustaining following delivery to the ISS. The LSG will accommodate life science and technology investigations in a "workbench" type environment. The facility has a.Ii enclosed working volume that is held at a negative pressure with respect to the crew living area. This allows the facility to provide two levels of containment for handling Biohazard Level II and lower biological materials. This containment approach protects the crew from possible hazardous operations that take place inside the LSG work volume. Research investigations operating inside the LSG are provided approximately 15 cubic feet of enclosed work space, 350 watts of28Vdc and l IOVac power (combined), video and data recording, and real time downlink. These capabilities will make the LSG a highly utilized facility on ISS. The LSG will be used for biological studies including rodent research and cell biology. The LSG facility is operated by the Payloads Operations Integration Center at MSFC. Payloads may also operate remotely from different telescience centers located in the United States and different countries. The Investigative Payload Integration Manager (IPIM) is the focal to assist organizations that have payloads operating in the LSG facility. NASA provides an LSG qualification unit for payload developers to verify that their hardware is operating properly before actual operation on the ISS. This poster will provide an overview of the LSG facility and a synopsis of the research that will be accomplished in the LSG. The authors would like to acknowledge Ames Research Center, Johnson Space Center, Teledyne Brown Engineering, MOOG-Bradford Engineering and the entire LSG Team for their inputs into this abstract.

Space Shuttle/TDRSS communication and tracking systems analysis

NASA Astrophysics Data System (ADS)

Lindsey, W. C.; Chie, C. M.; Cideciyan, R.; Dessouky, K.; Su, Y. T.; Tsang, C. S.

1986-04-01

In order to evaluate the technical and operational problem areas and provide a recommendation, the enhancements to the Tracking and Data Delay Satellite System (TDRSS) and Shuttle must be evaluated through simulation and analysis. These enhancement techniques must first be characterized, then modeled mathematically, and finally updated into LinCsim (analytical simulation package). The LinCsim package can then be used as an evaluation tool. Three areas of potential enhancements were identified: shuttle payload accommodations, TDRSS SSA and KSA services, and shuttle tracking system and navigation sensors. Recommendations for each area were discussed.

Space station integrated propulsion and fluid system study: Fluid systems configuration databook

NASA Technical Reports Server (NTRS)

Rose, L.; Bicknell, B.; Bergman, D.; Wilson, S.

1987-01-01

This databook contains fluid system requirements and system descriptions for Space Station program elements including the United States and International modules, integrated fluid systems, attached payloads, fluid servicers and vehicle accommodation facilities. Separate sections are devoted to each of the program elements and include a discussion of the overall system requirements, specific fluid systems requirements and systems descriptions. The systems descriptions contain configurations, fluid inventory data and component lists. In addition, a list of information sources is referenced at the end of each section.

MGBX - PS Crouch with experiment module

NASA Image and Video Library

2016-08-12

STS083-346-024 (4-8 April 1997) --- Payload specialist Roger K. Crouch performs the activation for the Mid Deck Glove Box (MGBX). Made to accommodate a variety of hardware and materials testing, the facility offers physical isolation and a negative air pressure environment so that items that are not suitable for handling in the open Spacelab can be protected. One experiment that was performed on STS-83 is the Internal Flows in a Free Drop (IFFD), an experiment that investigates rotation and position control of drops by varying acoustic pressures.

Space Shuttle/TDRSS communication and tracking systems analysis

NASA Technical Reports Server (NTRS)

Lindsey, W. C.; Chie, C. M.; Cideciyan, R.; Dessouky, K.; Su, Y. T.; Tsang, C. S.

1986-01-01

In order to evaluate the technical and operational problem areas and provide a recommendation, the enhancements to the Tracking and Data Delay Satellite System (TDRSS) and Shuttle must be evaluated through simulation and analysis. These enhancement techniques must first be characterized, then modeled mathematically, and finally updated into LinCsim (analytical simulation package). The LinCsim package can then be used as an evaluation tool. Three areas of potential enhancements were identified: shuttle payload accommodations, TDRSS SSA and KSA services, and shuttle tracking system and navigation sensors. Recommendations for each area were discussed.

Microgravity

NASA Image and Video Library

1995-04-06

An experiment vehicle plunges into the deceleration at the end of a 5.18-second drop in the Zero-Gravity Research Facility at NASA's Glenn Research Center. The Zero-Gravity Research Facility was developed to support microgravity research and development programs that investigate various physical sciences, materials, fluid physics, and combustion and processing systems. Payloads up to one-meter in diameter and 455 kg in weight can be accommodated. The facility has a 145-meter evacuated shaft to ensure a disturbance-free drop. This is No. 3 of a sequence of 4 images. (Credit: NASA/Glenn Research Center)

Microgravity

NASA Image and Video Library

1995-04-06

An experiment vehicle plunges into the deceleration pit at the end of a 5.18-second drop in the Zero-Gravity Research Facility at NASA's Glenn Research Center. The Zero-Gravity Research Facility was developed to support microgravity research and development programs that investigate various physical sciences, materials, fluid physcis, and combustion and processing systems. Payloads up to 1 meter in diameter and 455 kg in weight can be accommodated. The facility has a 145-meter evacuated shaft to ensure a disturbance-free drop. This is No. 2 of a sequence of 4 images. (Credit: NASA/Glenn Research Center)

Microgravity

NASA Image and Video Library

1995-04-06

An experiment vehicle plunges into the deceleration pit at the end of a 5.18-second drop in the Zero-Gravity Research Facility at NASA's Glenn Research Center. The Zero-Gravity Research Facility was developed to support microgravity research and development programs that investigate various physical sciences, materials, fluid physics, and combustion and processing systems. Payloads up to one meter in diameter and 455 kg in weight can be accommodated. The facility has a 145-meter evacuated shaft to ensure a disturbance-free drop. This is No. 4 of a sequence of 4 images. (Credit: NASA/Glenn Research Center)

Microgravity

NASA Image and Video Library

1995-04-06

An experiment vehicle plunges into the deceleration pit at the end of a 5.18-second drop in the Zero-Gravity Research Facility at NASA's Glenn Research Center. The Zero-Gravity Research Facility was developed to support microgravity research and development programs that investigate various physical sciences, materials, fluid physics, and combustion and processing systems. Payloads up to 1 meter in diameter and 455 kg in weight can be accommodated. The facility has a 145-meter evacuated shaft to ensure a disturbance-free drop. This is No.1 of a sequence of 4 images. (Credit: NASA/Glenn Research Center)

The Cloud-Aerosol Transport System (CATS): A New Earth Science Capability for ISS (Invited)

NASA Astrophysics Data System (ADS)

McGill, M. J.; Yorks, J. E.; Scott, S.; Kupchock, A.; Selmer, P.

2013-12-01

The Cloud-Aerosol Transport System (CATS) is a lidar remote sensing instrument developed for deployment to the International Space Station (ISS). The CATS lidar will provide range-resolved profile measurements of atmospheric aerosol and cloud distributions and properties. The CATS instrument uses a high repetition rate laser operating at three wavelengths (1064, 532, and 355 nm) to derive properties of cloud/aerosol layers including: layer height, layer thickness, backscatter, optical depth, extinction, and depolarization-based discrimination of particle type. The CATS mission was designed to capitalize on the Space Station's unique orbit and facilities to continue existing Earth Science data records, to provide observational data for use in forecast models, and to demonstrate new technologies for use in future missions. The CATS payload will be installed on the Japanese Experiment Module - Exposed Facility (JEM-EF). The payload is designed to operate on-orbit for at least six months, and up to three years. The payload is completed and currently scheduled for a mid-2014 launch. The ISS and, in particular, the JEM-EF, is an exciting new platform for spaceborne Earth observations. The ability to leverage existing aircraft instrument designs coupled with the lower cost possible for ISS external attached payloads permits rapid and cost effective development of spaceborne sensors. The CATS payload is based on existing instrumentation built and operated on the high-altitude NASA ER-2 aircraft. The payload is housed in a 1.5 m x 1 m x 0.8 m volume that attaches to the JEM-EF. The allowed volume limits the maximum size for the collecting telescope to 60 cm diameter. Figure 1 shows a schematic layout of the CATS payload, with the primary instrument components identified. Figure 2 is a photo of the completed payload. CATS payload cut-away view. Completed CATS payload assembly.

Shuttle to space station transfer of the materials exposure facility

NASA Technical Reports Server (NTRS)

Shannon, David T., Jr.; Klich, Phillip J.

1995-01-01

The Materials Exposure Facility (MEF) is being proposed by LaRC as the first long-term space materials exposure facility with real-time interaction with materials experiments in actual conditions of orbital space flight. The MEF is proposed as a Space Station external payload dedicated to technology advancement in spacecraft materials and coatings research. This paper will define a set of potential logistics for removing the MEF from the Shuttle cargo bay and the process required for transferring the MEF to a specific external payload site on Space Station Freedom (SSF). The SSF UF-2 configuration is used for this study. The kinematics and ability to successfully perform the appropriate MEF maneuvers required were verified. During completion of this work, the Space Station was redesigned and the International Space Station Alpha (ISSA) configuration evolved. The transfer procedure for SSF was valid for ISSA; however, a verification of kinematics and clearances was essential. Also, SSF and ISSA robotic interfaces with the Orbiter were different.

Continuous Microfluidic Self-Assembly of Hybrid Janus-Like Vesicular Motors: Autonomous Propulsion and Controlled Release.

PubMed

Wang, Lei; Liu, Yijing; He, Jie; Hourwitz, Matthew J; Yang, Yunlong; Fourkas, John T; Han, Xiaojun; Nie, Zhihong

2015-08-01

A microfluidic strategy is developed for the continuous fabrication of hybrid Janus vesicular motors that uniquely combine the capability of autonomous propulsion and externally controlled delivery of encapsulated payload. © 2015 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim.

KSC-00pp1680

NASA Image and Video Library

2000-11-08

During Terminal Countdown Demonstration Test (TCDT) activities at Launch Pad 39B, the STS-97 crew poses for a photo at the 215-foot level. From left, they are Mission Specialist Carlos Noriega, Commander Brent Jett, Pilot Mike Bloomfield and Mission Specialists Marc Garneau and Joe Tanner. Behind them at left can be seen the top of the solid rocket booster and external tank on Space Shuttle Endeavour. The TCDT includes emergency egress training, opportunities to inspect the mission payloads in the orbiter’s payload bay and a simulated launch countdown. Mission STS-97is the sixth construction flight to the International Space Station. Its payload includes the P6 Integrated Truss Structure and a photovoltaic (PV) module, with giant solar arrays that will provide power to the Station. The mission includes two spacewalks to complete the solar array connections. STS-97 is scheduled to launch Nov. 30 at 10:05 p.m. EST

STS-97 crew poses for photo on Launch Pad 39B

NASA Technical Reports Server (NTRS)

2000-01-01

During Terminal Countdown Demonstration Test (TCDT) activities at Launch Pad 39B, the STS-97 crew poses for a photo at the 215-foot level. From left, they are Mission Specialist Carlos Noriega, Commander Brent Jett, Pilot Mike Bloomfield and Mission Specialists Marc Garneau and Joe Tanner. Behind them at left can be seen the top of the solid rocket booster and external tank on Space Shuttle Endeavour. The TCDT includes emergency egress training, opportunities to inspect the mission payloads in the orbiter'''s payload bay and a simulated launch countdown. Mission STS-97is the sixth construction flight to the International Space Station. Its payload includes the P6 Integrated Truss Structure and a photovoltaic (PV) module, with giant solar arrays that will provide power to the Station. The mission includes two spacewalks to complete the solar array connections. STS-97 is scheduled to launch Nov. 30 at 10:05 p.m. EST.

KSC-00pp1734

NASA Image and Video Library

2000-11-14

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 39B, the payload transport canister, with the P6 integrated truss segment inside, moves higher toward the payload changeout room (PCR). The PCR is the enclosed, environmentally controlled portion of the Rotating Service Structure (RSS) (at left) that supports payload delivery at the pad. At right is Space Shuttle Endeavour with its orange external tank and solid rocket boosters showing behind it. When the RSS is closed around Endeavour, the P6 truss will be able to be moved into the orbiter’s payload bay. The P6, payload on mission STS-97, comprises Solar Array Wing-3 and the Integrated Electronic Assembly, to be installed on the International Space Station. The Station’s electrical power system will use eight photovoltaic solar arrays, each 112 feet long by 39 feet wide, to convert sunlight to electricity. The solar arrays are mounted on a “blanket” that can be folded like an accordion for delivery. Once in orbit, astronauts will deploy the blankets to their full size. Gimbals will be used to rotate the arrays so that they will face the Sun to provide maximum power to the Space Station. Launch of STS-97 is scheduled for Nov. 30 at 10:06 p.m. EST

KSC00pp1734

NASA Image and Video Library

2000-11-14

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 39B, the payload transport canister, with the P6 integrated truss segment inside, moves higher toward the payload changeout room (PCR). The PCR is the enclosed, environmentally controlled portion of the Rotating Service Structure (RSS) (at left) that supports payload delivery at the pad. At right is Space Shuttle Endeavour with its orange external tank and solid rocket boosters showing behind it. When the RSS is closed around Endeavour, the P6 truss will be able to be moved into the orbiter’s payload bay. The P6, payload on mission STS-97, comprises Solar Array Wing-3 and the Integrated Electronic Assembly, to be installed on the International Space Station. The Station’s electrical power system will use eight photovoltaic solar arrays, each 112 feet long by 39 feet wide, to convert sunlight to electricity. The solar arrays are mounted on a “blanket” that can be folded like an accordion for delivery. Once in orbit, astronauts will deploy the blankets to their full size. Gimbals will be used to rotate the arrays so that they will face the Sun to provide maximum power to the Space Station. Launch of STS-97 is scheduled for Nov. 30 at 10:06 p.m. EST

KSC00pp1735

NASA Image and Video Library

2000-11-14

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 39B, the payload transport canister, with the P6 integrated truss segment inside, is lifted higher toward the payload changeout room (PCR) above it. The PCR is the enclosed, environmentally controlled portion of the Rotating Service Structure (RSS) (at left) that supports payload delivery at the pad. At right is Space Shuttle Endeavour with its orange external tank and one solid rocket booster showing behind it. When the RSS is closed around Endeavour, the P6 truss will be moved into the orbiter’s payload bay. The P6, payload on mission STS-97, comprises Solar Array Wing-3 and the Integrated Electronic Assembly, to be installed on the International Space Station. The Station’s electrical power system will use eight photovoltaic solar arrays, each 112 feet long by 39 feet wide, to convert sunlight to electricity. The solar arrays are mounted on a “blanket” that can be folded like an accordion for delivery. Once in orbit, astronauts will deploy the blankets to their full size. Gimbals will be used to rotate the arrays so that they will face the Sun to provide maximum power to the Space Station. Launch of STS-97 is scheduled for Nov. 30 at 10:06 p.m. EST

KSC-00pp1733

NASA Image and Video Library

2000-11-14

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 39B, the payload transport canister, with the P6 integrated truss segment inside, is lifted toward the payload changeout room (PCR). The PCR is the enclosed, environmentally controlled portion of the Rotating Service Structure (RSS) (on the left) that supports payload delivery at the pad. At right is Space Shuttle Endeavour with its orange external tank and one solid rocket booster showing behind it. When the RSS is closed around Endeavour, the P6 truss will be able to be moved into the orbiter’s payload bay. The P6, payload on mission STS-97, comprises Solar Array Wing-3 and the Integrated Electronic Assembly, to be installed on the International Space Station. The Station’s electrical power system will use eight photovoltaic solar arrays, each 112 feet long by 39 feet wide, to convert sunlight to electricity. The solar arrays are mounted on a “blanket” that can be folded like an accordion for delivery. Once in orbit, astronauts will deploy the blankets to their full size. Gimbals will be used to rotate the arrays so that they will face the Sun to provide maximum power to the Space Station. Launch of STS-97 is scheduled for Nov. 30 at 10:06 p.m. EST

KSC00pp1733

NASA Image and Video Library

2000-11-14

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 39B, the payload transport canister, with the P6 integrated truss segment inside, is lifted toward the payload changeout room (PCR). The PCR is the enclosed, environmentally controlled portion of the Rotating Service Structure (RSS) (on the left) that supports payload delivery at the pad. At right is Space Shuttle Endeavour with its orange external tank and one solid rocket booster showing behind it. When the RSS is closed around Endeavour, the P6 truss will be able to be moved into the orbiter’s payload bay. The P6, payload on mission STS-97, comprises Solar Array Wing-3 and the Integrated Electronic Assembly, to be installed on the International Space Station. The Station’s electrical power system will use eight photovoltaic solar arrays, each 112 feet long by 39 feet wide, to convert sunlight to electricity. The solar arrays are mounted on a “blanket” that can be folded like an accordion for delivery. Once in orbit, astronauts will deploy the blankets to their full size. Gimbals will be used to rotate the arrays so that they will face the Sun to provide maximum power to the Space Station. Launch of STS-97 is scheduled for Nov. 30 at 10:06 p.m. EST

KSC-00pp1735

NASA Image and Video Library

2000-11-14

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 39B, the payload transport canister, with the P6 integrated truss segment inside, is lifted higher toward the payload changeout room (PCR) above it. The PCR is the enclosed, environmentally controlled portion of the Rotating Service Structure (RSS) (at left) that supports payload delivery at the pad. At right is Space Shuttle Endeavour with its orange external tank and one solid rocket booster showing behind it. When the RSS is closed around Endeavour, the P6 truss will be moved into the orbiter’s payload bay. The P6, payload on mission STS-97, comprises Solar Array Wing-3 and the Integrated Electronic Assembly, to be installed on the International Space Station. The Station’s electrical power system will use eight photovoltaic solar arrays, each 112 feet long by 39 feet wide, to convert sunlight to electricity. The solar arrays are mounted on a “blanket” that can be folded like an accordion for delivery. Once in orbit, astronauts will deploy the blankets to their full size. Gimbals will be used to rotate the arrays so that they will face the Sun to provide maximum power to the Space Station. Launch of STS-97 is scheduled for Nov. 30 at 10:06 p.m. EST

KSC-97PC879

NASA Image and Video Library

1997-06-04

While KSC workers in the Launch Complex 39 Area watch, The Space Shuttle Orbiter Columbia rolls over to the Vehicle Assembly Building (VAB) June 4 from Orbiter Processing Facility (OPF)1 atop its transporter in preparation for the STS-94 mission. Once inside the VAB, Columbia will be hoisted to be mated with its solid rocket boosters and external tank. Columbia was moved to the OPF April 8 after the completion of the STS-83 mission. KSC payloads processing employees then began work to reservice the Microgravity Science Laboratory-1 (MSL-1) Spacelab module in the orbiter’s payload bay for the STS-94 mission. This was the first time that this type of payload was reserviced without removing it from the payload bay. This new procedure pioneers processing efforts for possible quick relaunch turnaround times for future payloads. The MSL-1 module will fly again with the full complement of STS-83 experiments after that mission was cut short due to indications of a faulty fuel cell. During the scheduled 16-day STS-94 mission, the experiments will be used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducts combustion, protein crystal growth and materials processing experiments

STS-98 Onboard Photograph-U.S. Laboratory, Destiny

NASA Technical Reports Server (NTRS)

2001-01-01

This STS-98 Shuttle mission image shows an overall interior view of the newly attached U.S. Laboratory, Destiny. The American-made Destiny module is the cornerstone for space-based research aboard the orbiting platform and the centerpiece of the International Space Station (ISS), where unprecedented science experiments will be performed in the near-zero gravity of space. Destiny will also serve as the command and control center for the ISS. The aluminum module is 8.5-meters (28-feet) long and 4.3-meters (14-feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 15 locations especially designed to support experiments. The Destiny module was built by the Boeing Company under the direction of the Marshall Space Flight Center.

RESOLVE Mission Architecture for Lunar Resource Prospecting and Utilization

NASA Technical Reports Server (NTRS)

George, J. A.; Mattes, G. W.; Rogers, K. N.; Magruder, D. F.; Paz, A. J.; Vaccaro, H. M.; Baird, R. S.; Sanders, G. B.; Smith, J. T.; Quinn, J. W.;

International Space Station (ISS)

NASA Image and Video Library

2001-02-11

This STS-98 mission photograph shows astronauts Thomas D. Jones (foreground) and Kerneth D. Cockrell floating inside the newly installed Laboratory aboard the International Space Station (ISS). The American-made Destiny module is the cornerstone for space-based research aboard the orbiting platform and the centerpiece of the ISS, where unprecedented science experiments will be performed in the near-zero gravity of space. Destiny will also serve as the command and control center for the ISS. The aluminum module is 8.5-meters (28-feet) long and 4.3-meters (14-feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 15 locations especially designed to support experiments. The Destiny module was built by the Boeing Company under the direction of the Marshall Space Flight Center.

KENNEDY SPACE CENTER, FLA. - An overhead crane in the Space Station Processing Facility is attached to the U.S. Node 2 to lift it out of its shipping container. The node will be moved to a workstand. The second of three connecting modules on the International Space Station, the Italian-built Node 2 attaches to the end of the U.S. Lab and provides attach locations for the Japanese laboratory, European laboratory, the Centrifuge Accommodation Module and, later, Multipurpose Logistics Modules. It will provide the primary docking location for the Shuttle when a pressurized mating adapter is attached to Node 2. Installation of the module will complete the U.S. Core of the ISS. Node 2 is the designated payload for mission STS-120. No orbiter or launch date has been determined yet.

NASA Image and Video Library

2003-06-03

KENNEDY SPACE CENTER, FLA. - An overhead crane in the Space Station Processing Facility is attached to the U.S. Node 2 to lift it out of its shipping container. The node will be moved to a workstand. The second of three connecting modules on the International Space Station, the Italian-built Node 2 attaches to the end of the U.S. Lab and provides attach locations for the Japanese laboratory, European laboratory, the Centrifuge Accommodation Module and, later, Multipurpose Logistics Modules. It will provide the primary docking location for the Shuttle when a pressurized mating adapter is attached to Node 2. Installation of the module will complete the U.S. Core of the ISS. Node 2 is the designated payload for mission STS-120. No orbiter or launch date has been determined yet.

KSC-07pd1885

NASA Image and Video Library

2007-07-17

KENNEDY SPACE CENTER, Fla. -- STS-118 Commander Scott Kelly practices driving an M-113 armored personnel carrier with fellow crew members Tracy Caldwell, Alvin Drew and Dave Williams, all mission specialists, as passengers. They are at Kennedy for the Terminal Countdown Demonstration Test (TCDT), a dress rehearsal for launch. TCDT activities include the M-113 training, payload familiarization, emergency egress training at the pad and a simulated launch countdown. The STS-118 payload aboard Space Shuttle Endeavour includes the S5 truss, a SPACEHAB module and external stowage platform 3. The mission is the 22nd flight to the International Space Station and is targeted for launch on Aug.7. NASA/George Shelton

KSC-07pd2025

NASA Image and Video Library

2007-07-19

KENNEDY SPACE CENTER, Fla. -- In the Orbiter Processing Facility bay 3, a crane lowers the main bus switching unit into Discovery's payload bay. The unit is part of the payload on mission STS-120.A main bus switching unit is used for power distribution, circuit protection and fault isolation on the space station's power system. The units route power to proper locations in the space station, such as from solar arrays through umbilicals into the U.S. Lab. The unit will be installed on the external stowage platform 2 attached to the Quest airlock for temporary storage. Discovery is targeted to launch mission STS-120 no earlier than Oct. 20. Photo credit: NASA/Jim Grossmann

WEB - A Wireless Experiment Box for the Dextre Pointing Package ELC Payload

NASA Technical Reports Server (NTRS)

Bleier, Leor Z.; Marrero-Fontanez, Victor J.; Sparacino, Pietro A.; Moreau, Michael C.; Mitchell, Jason William

2012-01-01

The Wireless Experiment Box (WEB) was proposed to work with the International Space Station (ISS) External Wireless Communication (EWC) system to support high-definition video from the Dextre Pointing Package (DPP). DPP/WEB was a NASA GSFC proposed ExPRESS Logistics Carrier (ELC) payload designed to flight test an integrated suite of Autonomous Rendezvous and Docking (AR&D) technologies to enable a wide spectrum of future missions across NASA and other US Government agencies. The ISS EWC uses COTS Wireless Access Points (WAPs) to provide high-rate bi-directional communications to ISS. In this paper, we discuss WEB s packaging, operation, antenna development, and performance testing.

Web: A Wireless Experiment Box for the Dextre Pointing Package ELC Payload

NASA Technical Reports Server (NTRS)

Bleier, Leor Z.; Marrero-Fontanez, Victor J.; Sparacino, Pietro A.; Moreau, Michael C.; Mitchell, Jason W.

2012-01-01

The Wireless Experiment Box (WEB) was proposed to work with the International Space Station (ISS) External Wireless Communication (EWC) system to support high-definition video from the Dextre Pointing Package (DPP). DPP/WEB was a NASA GSFC proposed ExPRESS Logistics Carrier (ELC) payload designed to flight test an integrated suite of Autonomous Rendezvous and Docking (AR&D) technologies to enable a wide spectrum of future missions across NASA and other US Government agencies. The ISS EWC uses COTS Wireless Access Points (WAPs) to provide high-rate bi-directional communications to ISS. In this paper, we discuss WEB s packaging, operation, antenna development, and performance testing.

Boeing-747 aircraft with external cargo pod

NASA Technical Reports Server (NTRS)

Quartero, C. B.; Washburn, G. F.; Price, J. E.

1978-01-01

An analysis was conducted to investigate the feasibility of mounting a detachable pod to the underside of the fuselage of a Boeing Model 747 aircraft to carry outsized cargo in case of military emergency. The analysis showed that the 747 configured with the pod and carrying only a bridge launcher as payload attained a range of 8.70 Mm (4 700 n. mi.) at Mach .68. This range was based on a maximum take-off gross weight of 3.447 MN (775 000 1bf) which included 212 kN (47 700 lbf) pod weight and 543 kN (122 000 lbf) payload (bridge launcher).

STS-114 Discovery Return to Flight: International Space Station Processing Overview

NASA Technical Reports Server (NTRS)

2005-01-01

Bruce Buckingham, NASA Public Affairs, introduces Scott Higgenbotham, STS-114 Payload Manager. Higgenbotham gives a power point presentation on the hardware that is going to fly in the Discovery Mission to the International Space Station. He presents a layout of the hardware which includes The Logistics Flight 1 (LF1) launch package configuration Multipurpose Logistics Module (MPLM), External Stowage Platform-2 (ESP-2) and the Lightweight Mission Peculiar Equipment Support Structure Carrier (LMC). He explains these payloads in detail. The LF-1 team is also shown in the International Space Station Processing Facility. This presentation ends with a brief question and answer period.

Early Program Development

NASA Image and Video Library

1989-01-01

This 1989 artist's rendering shows how a Shuttle-C would look during launch. As envisioned by Marshall Space Flight Center plarners, the Shuttle-C would be an unmanned heavy-lift cargo vehicle derived from Space Shuttle elements. The vehicle would utilize the basic Shuttle propulsion units (Solid Rocket Boosters, Space Shuttle Main Engine, External Tank), but would replace the Orbiter with an unmanned Shuttle-C Cargo Element (SCE). The SCE would have a payload bay lenght of eighty-two feet, compared to sixty feet for the Orbiter cargo bay, and would be able to deliver 170,000 pound payloads to low Earth orbit, more than three times the Orbiter's capacity.

Early Program Development

NASA Image and Video Library

1989-01-01

In this 1989 artist's concept, the Shuttle-C floats in space with its cargo bay doors open. As envisioned by Marshall Space Flight Center plarners, the Shuttle-C would be an unmanned heavy lift cargo vehicle derived from Space Shuttle elements. The vehicle would utilize the basic Shuttle propulsion units (Solid Rocket Boosters, Space Shuttle Main Engine, External Tank), but would replace the Oribiter with an unmanned Shuttle-C Cargo Element (SCE). The SCE would have a payload bay length of eighty-two feet, compared to sixty feet for the Orbiter cargo bay, and would be able to deliver 170,000 pound payloads to low Earth orbit, more than three times the Orbiter's capacity.

Correlates of accommodation of pediatric obsessive-compulsive disorder: parent, child, and family characteristics.

PubMed

Peris, Tara S; Bergman, R Lindsey; Langley, Audra; Chang, Susanna; McCracken, James T; Piacentini, John

2008-10-01

Pediatric obsessive-compulsive disorder (OCD) is a chronic, impairing condition associated with high levels of family accommodation (i.e., participation in symptoms). Understanding of factors that may engender accommodation of pediatric OCD is limited. This study conducted exploratory analyses of parent-, child-, and family-level correlates of family accommodation, considering both behavioral and affective components of the response. The sample included 65 youths (mean age 12.3 years, 62% male) with OCD and their parents who completed a standardized assessment battery composed of both clinical and self-report measures (e.g., Children's Yale-Brown Obsessive-Compulsive Scale, Brief Symptom Inventory). Family accommodation was common, with the provision of reassurance and participation in rituals the most frequent practices (occurring on a daily basis among 56% and 46% of parents, respectively). Total scores on the Family Accommodation Scale were not associated with child OCD symptom severity; however, parental involvement in rituals was associated with higher levels of child OCD severity and parental psychopathology and with lower levels of family organization. Comorbid externalizing symptomatology and family conflict were associated with parent report of worse consequences when not accommodating. Although these findings must be interpreted in light of potential type I error, they suggest that accommodation is the norm in pediatric OCD. Family-focused interventions must consider the parent, child, and family-level variables associated with this familial response when teaching disengagement strategies.

Correlates of Accommodation of Pediatric Obsessive Compulsive Disorder: Parent, Child, and Family Characteristics

PubMed Central

Peris, Tara S.; Bergman, R. Lindsey; Langley, Audra; Chang, Susanna; McCracken, James T.; Piacentini, John

2012-01-01

Objective Pediatric obsessive-compulsive disorder (OCD) is a chronic, impairing condition associated with high levels of family accommodation (i.e., participation in symptoms). Understanding of factors that may engender accommodation of pediatric OCD is limited. This study conducted exploratory analyses of parent-, child-, and family-level correlates of family accommodation, considering both behavioral and affective components of the response. Method The sample included 65 youth (mean age = 12.3 years; 62% male) with OCD and their parents who completed a standardized assessment battery comprised of both clinical and self-report measures (e.g., CY-BOCS, Brief Symptom Inventory). Results Family accommodation was common, with the provision of reassurance and participation in rituals the most frequent practices (respectively occurring on a daily basis among 56% and 46% of parents). Total scores on the Family Accommodation Scale were not associated with child OCD symptom severity; however, parental involvement in rituals was associated with higher levels of child OCD severity and parental psychopathology, and with lower levels of family organization. Comorbid externalizing symptomatology and family conflict were associated with parent report of worse consequences when not accommodating. Conclusions Although these findings must be interpreted in light of potential Type I error, they suggest that accommodation is the norm in pediatric OCD. Family-focused interventions must consider the parent, child, and family-level variables associated with this familial response when teaching disengagement strategies. PMID:18724255

Partial and total actuator faults accommodation for input-affine nonlinear process plants.

PubMed

Mihankhah, Amin; Salmasi, Farzad R; Salahshoor, Karim

2013-05-01

In this paper, a new fault-tolerant control system is proposed for input-affine nonlinear plants based on Model Reference Adaptive System (MRAS) structure. The proposed method has the capability to accommodate both partial and total actuator failures along with bounded external disturbances. In this methodology, the conventional MRAS control law is modified by augmenting two compensating terms. One of these terms is added to eliminate the nonlinear dynamic, while the other is reinforced to compensate the distractive effects of the total actuator faults and external disturbances. In addition, no Fault Detection and Diagnosis (FDD) unit is needed in the proposed method. Moreover, the control structure has good robustness capability against the parameter variation. The performance of this scheme is evaluated using a CSTR system and the results were satisfactory. Copyright © 2013 ISA. Published by Elsevier Ltd. All rights reserved.

What Works? Toward a New Classification System for Mental Health Supported Accommodation Services: The Simple Taxonomy for Supported Accommodation (STAX-SA)

PubMed Central

McPherson, Peter; Krotofil, Joanna

2018-01-01

Inconsistent terminology and variation in service models have made synthesis of the supported accommodation literature challenging. To overcome this, we developed a brief, categorical taxonomy that aimed to capture the defining features of different supported accommodation models: the simple taxonomy for supported accommodation (STAX-SA). Data from a previous review of existing classification systems were used to develop the taxonomy structure. After initial testing and amendments, the STAX-SA and an existing taxonomy were applied to 132 supported accommodation service descriptions drawn from two systematic reviews and their performance compared. To assess external validity, the STAX-SA was distributed to a sample of supported accommodation managers in England and they were asked to use it to classify their services. The final version of the STAX-SA comprised of five supported accommodation ‘types’, based on four domains; Staffing location; Level of support; Emphasis on move-on; and Physical setting. The STAX-SA accurately categorized 71.1% (n = 94) of service descriptions, outperforming the comparison tool, and was not affected by publication date or research design. The STAX-SA effectively discriminated between ‘real world’ service models in England and 53.2% (n = 17) of service managers indicated that the taxonomy was ‘Very effective’ or ‘Extremely effective’ in capturing key characteristics of their service. The STAX-SA is an effective tool for classifying supported accommodation models and represents a promising approach to synthesizing the extant effectiveness literature. The authors recommend the development of reporting guidelines for future supported accommodation publications to facilitate comparison between models. PMID:29364171

What Works? Toward a New Classification System for Mental Health Supported Accommodation Services: The Simple Taxonomy for Supported Accommodation (STAX-SA).

PubMed

McPherson, Peter; Krotofil, Joanna; Killaspy, Helen

2018-01-24

Inconsistent terminology and variation in service models have made synthesis of the supported accommodation literature challenging. To overcome this, we developed a brief, categorical taxonomy that aimed to capture the defining features of different supported accommodation models: the simple taxonomy for supported accommodation (STAX-SA). Data from a previous review of existing classification systems were used to develop the taxonomy structure. After initial testing and amendments, the STAX-SA and an existing taxonomy were applied to 132 supported accommodation service descriptions drawn from two systematic reviews and their performance compared. To assess external validity, the STAX-SA was distributed to a sample of supported accommodation managers in England and they were asked to use it to classify their services. The final version of the STAX-SA comprised of five supported accommodation 'types', based on four domains; Staffing location ; Level of support ; Emphasis on move-on ; and Physical setting . The STAX-SA accurately categorized 71.1% ( n = 94) of service descriptions, outperforming the comparison tool, and was not affected by publication date or research design. The STAX-SA effectively discriminated between 'real world' service models in England and 53.2% ( n = 17) of service managers indicated that the taxonomy was ' Very effective ' or ' Extremely effective ' in capturing key characteristics of their service. The STAX-SA is an effective tool for classifying supported accommodation models and represents a promising approach to synthesizing the extant effectiveness literature. The authors recommend the development of reporting guidelines for future supported accommodation publications to facilitate comparison between models.

Earth-Affecting Solar Causes Observatory (EASCO): Results of the Mission Concept Study

NASA Technical Reports Server (NTRS)

Gopalswamy, Natchimuthuk

2011-01-01

Coronal mass ejections (CMEs) corotating interaction regions (CIRs) are two large-scale structures that originate from the Sun and affect the heliosphere in general and Earth in particular. While CIRs are generally detected by in-situ plasma signatures, CMEs are remote-sensed when they are still close to the Sun. The current understanding of CMEs primarily come from the SOHO and STEREO missions. In spite of the enormous progress made, there are some serious deficiencies in these missions. For example, these missions did not carry all the necessary instruments (STEREO did not have a magnetograph; SOHO did not have in-situ magnetometer). From the Sun-Earth line, SOHO was not well-suited for observing Earth-directed CMEs because of the occulting disk. STEREO's angle with the Sun-Earth line is changing constantly, so only a limited number of Earth-directed CMEs were observed in profile. In order to overcome these difficulties, we proposed a news L5 mission concept known as the Earth-Affecting Solar Causes Observatory (EASCO). The mission concept was recently studied at the Mission Design Laboratory (MDL), NASA Goddard Space Flight Center. The aim of the MDL study was to see how the scientific payload consisting of ten instruments can be accommodated in the spacecraft bus, what propulsion system can transfer the payload to the Sun-Earth L5, and what launch vehicles are appropriate. The study found that all the ten instruments can be readily accommodated and can be launched using an intermediate size vehicle such as Taurus II with enhanced faring. The study also found that a hybrid propulsion system consisting of an ion thruster (using approximately 55 kg of Xenon) and hydrazine (approximately 10 kg) is adequate to place the payload at L5. The transfer will take about 2 years and the science mission will last for 4 years around the next solar maximum in 2025. The mission can be readily extended for another solar cycle to get a solar-cycle worth of data on Earth-affecting CMEs and CIRs. This paper provides a highlight of the MDL study results.

Full load of ESA experiments on Maxus-2 sounding rocket

NASA Astrophysics Data System (ADS)

1995-11-01

Maxus sounding rockets are built and commercialised by an industrial joint venture, a team comprising of the Swedish Space Corporation (SSC) and DASA of Germany. ESA is fully funding the scientific payload for this mission. The payload comprises 8 experiments spanning the fields of fluid physics, electrophoresis and cell biology. Scientists from Belgium, France, Germany and Switzerland designed these experiments and the hardware was built by Swedish, German and Italian firms. The experiments are accommodated in 5 autonomous experiment modules and account for an overall mass of about 500 kg out of a total payload of about 800 kg. The first module contains an experiment which aims to check the static and dynamic behaviour of liquids at corners and edges. The second contains a biological experiment on two unicellular organisms (loxodes and paramecium). In their natural habitat (lakes), these organisms make use of the gravity vector for their orientation. Their swimming behaviour in microgravity will be observed on Earth in real time. The third module houses two other biology experiments. One examines the effect of microgravity on particle ingestion of gold beads by human macrophage cells (a type of white blood cell). Macrophage cells digest foreign particles, such as bacteria and viruses, thereby performing an important function in our immune system. The other experiment investigates the influence of weightlessness on the structure of lymphocytes (white blood cells). The fourth module accommodates three different experiments all dealing with convection phenomena due to surface-tension instabilities (Marangoni convection). Surface tension is that property of liquids which makes raindrops nearly spherical and allows insects to move on water surfaces. These phenomena, which are masked by the effect of gravity on Earth, can be easily studied in microgravity conditions. The fifth module contains an experiment that deals with electrophoresis, i.e. a process which is used to separate biological products in solution by application of a strong electric field. A highly concentrated solution with two proteins will be separated into its fractions and collected in a set of 59 syringes.

Space Shuttle External Tank Project status

NASA Technical Reports Server (NTRS)

Davis, R. M.

1980-01-01

The External Tank Project is reviewed with emphasis on the DDT&E and production phases and the lightweight tank development. It is noted that the DDT&E phase is progressing well with the structural and ground vibration test article programs complete, the propulsion test article program progressing well, and the component qualification and verification testing 92% complete. New tools and facilities are being brought on line to support the increased build rate for the production phase. The lightweight tank, which will provide additional payload in orbit, is progressing to schedule with first delivery in early 1982.

Internal and external 2-d boundary layer flows

NASA Technical Reports Server (NTRS)

Crawford, M. E.; Kays, W. M.

1978-01-01

Computer program computes general two dimensional turbulent boundary-layer flow using finite-difference techniques. Structure allows for user modification to accommodate unique problems. Program should prove useful in many applications where accurate boundary-layer flow calculations are required.

Student Residence.

ERIC Educational Resources Information Center

Department of Education and Science, London (England).

Principal facility requirements and costs of residential accommodations for students are discussed. After specifying the various space and facility requirements and providing cost information for the various classes of facilities, the report details requirements pertaining to external works (road access; car parking; grassing, planting, and…

Analysis of Lidar Remote Sensing Concepts

NASA Technical Reports Server (NTRS)

Spiers, Gary D.

1999-01-01

Line of sight velocity and measurement position sensitivity analyses for an orbiting coherent Doppler lidar are developed and applied to two lidars, one with a nadir angle of 30 deg. in a 300 km altitude, 58 deg. inclination orbit and the second for a 45 deg. nadir angle instrument in a 833 km altitude, 89 deg. inclination orbit. The effect of orbit related effects on the backscatter sensitivity of a coherent Doppler lidar is also discussed. Draft performance estimate, error budgets and payload accommodation requirements for the SPARCLE (Space Readiness Coherent Lidar) instrument were also developed and documented.

Space shuttle engineering and operations support. Avionics system engineering

NASA Technical Reports Server (NTRS)

Broome, P. A.; Neubaur, R. J.; Welsh, R. T.

1976-01-01

The shuttle avionics integration laboratory (SAIL) requirements for supporting the Spacelab/orbiter avionics verification process are defined. The principal topics are a Spacelab avionics hardware assessment, test operations center/electronic systems test laboratory (TOC/ESL) data processing requirements definition, SAIL (Building 16) payload accommodations study, and projected funding and test scheduling. Because of the complex nature of the Spacelab/orbiter computer systems, the PCM data link, and the high rate digital data system hardware/software relationships, early avionics interface verification is required. The SAIL is a prime candidate test location to accomplish this early avionics verification.

Study of application of adaptive systems to the exploration of the solar system. Volume 3: Mars landed systems

NASA Technical Reports Server (NTRS)

1973-01-01

The results of a more detailed study of three missions to the surface of Mars: (1) an advanced lander, (2) a lander with a small tethered rover, and (3) a lander with a medium sized rover that operates independently of the lander for most of its functions but communicates with Earth through the lander are presented. For all three missions it was assumed that the Viking orbiter and lander would be used with modifications as required to improve the science package, to accommodate the rovers, and to handle the increased payloads.

Design of a 7kW power transfer solar array drive mechanism

NASA Technical Reports Server (NTRS)

Sheppard, J. G.

1982-01-01

With the availability of the Shuttle and the European launcher, Ariane, there will be a continuing trend towards large payload satellite missions requiring high-power, high-inertia, flexible solar arrays. The need arises for a solar array drive with a large power transfer capability which can rotate these solar arrays without disturbing the satellite body pointing. The modular design of such a Solar Array Drive Mechanism (SADM) which is capable of transferring 7kW of power or more is described. Total design flexibility has been achieved, enabling different spacecraft power requirements to be accommodated within the SADM design.

Zero-Gravity Research Facility Drop Test (2/4)

NASA Technical Reports Server (NTRS)

1995-01-01

An experiment vehicle plunges into the deceleration pit at the end of a 5.18-second drop in the Zero-Gravity Research Facility at NASA's Glenn Research Center. The Zero-Gravity Research Facility was developed to support microgravity research and development programs that investigate various physical sciences, materials, fluid physcis, and combustion and processing systems. Payloads up to 1 meter in diameter and 455 kg in weight can be accommodated. The facility has a 145-meter evacuated shaft to ensure a disturbance-free drop. This is No. 2 of a sequence of 4 images. (Credit: NASA/Glenn Research Center)

Zero-Gravity Research Facility Drop Test (1/4)

NASA Technical Reports Server (NTRS)

1995-01-01

An experiment vehicle plunges into the deceleration pit at the end of a 5.18-second drop in the Zero-Gravity Research Facility at NASA's Glenn Research Center. The Zero-Gravity Research Facility was developed to support microgravity research and development programs that investigate various physical sciences, materials, fluid physics, and combustion and processing systems. Payloads up to 1 meter in diameter and 455 kg in weight can be accommodated. The facility has a 145-meter evacuated shaft to ensure a disturbance-free drop. This is No.1 of a sequence of 4 images. (Credit: NASA/Glenn Research Center)

Zero-Gravity Research Facility Drop Test (3/4)

NASA Technical Reports Server (NTRS)

1995-01-01

An experiment vehicle plunges into the deceleration at the end of a 5.18-second drop in the Zero-Gravity Research Facility at NASA's Glenn Research Center. The Zero-Gravity Research Facility was developed to support microgravity research and development programs that investigate various physical sciences, materials, fluid physics, and combustion and processing systems. Payloads up to one-meter in diameter and 455 kg in weight can be accommodated. The facility has a 145-meter evacuated shaft to ensure a disturbance-free drop. This is No. 3 of a sequence of 4 images. (Credit: NASA/Glenn Research Center)

Zero-Gravity Research Facility Drop Test (4/4)

NASA Technical Reports Server (NTRS)

1995-01-01

An experiment vehicle plunges into the deceleration pit at the end of a 5.18-second drop in the Zero-Gravity Research Facility at NASA's Glenn Research Center. The Zero-Gravity Research Facility was developed to support microgravity research and development programs that investigate various physical sciences, materials, fluid physics, and combustion and processing systems. Payloads up to one meter in diameter and 455 kg in weight can be accommodated. The facility has a 145-meter evacuated shaft to ensure a disturbance-free drop. This is No. 4 of a sequence of 4 images. (Credit: NASA/Glenn Research Center)

NASA Global Hawk: A New Tool for Earth Science Research

NASA Technical Reports Server (NTRS)

Naftel, J. Chris

2009-01-01

Scientists have eagerly anticipated the performance capability of the National Aeronautics and Space Administration (NASA) Global Hawk for over a decade. In 2009 this capability becomes operational. One of the most desired performance capabilities of the Global Hawk aircraft is very long endurance. The Global Hawk aircraft can remain airborne longer than almost all other jet-powered aircraft currently flying, and longer than all other aircraft available for airborne science use. This paper describes the NASA Global Hawk system, payload accommodations, concept of operations, and the first scientific data-gathering mission: Global Hawk Pacific 2009.

Mapping Sequence performed during the STS-117 R-Bar Pitch Maneuver

NASA Image and Video Library

2007-06-10

ISS015-E-11351 (10 June 2007) --- This is one of a series of images photographed with a digital still camera using an 800mm focal length featuring the different areas of the Space Shuttle Atlantis as it approached the International Space Station and performed a back-flip to accommodate close scrutiny by eyeballs and cameras. This image shows part of Atlantis' underside thermal protection system and part of the port side cabin, including the hatch, as well as a section of the open payload bay cover. Distance from the station and shuttle at this time was approximately 600 feet.

Mapping Sequence performed during the STS-118 R-Bar Pitch Maneuver

NASA Image and Video Library

2007-08-10

ISS015-E-21340 (10 Aug. 2007) --- This is one of a series of images photographed with a digital still camera using an 800mm focal length featuring the different areas of the Space Shuttle Endeavour as it approached the International Space Station and performed a back-flip to accommodate close scrutiny by eyeballs and cameras. This image shows part of the commander's side or port side of Endeavour's cabin, including the hatch, as well as a section of the open payload bay cover. Distance between the station and shuttle at this time was approximately 600 feet.

International Space Station Columbus Payload SoLACES Degradation Assessment

NASA Technical Reports Server (NTRS)

Harman, William; Schmidl, William; Mikatarian, Ron; Soares, Carlos; Schmidtke, Gerhard; Erhardt, Christian

2014-01-01

SOLAR is a European Space Agency (ESA) payload deployed on the International Space Station (ISS) and located on the Columbus Laboratory. It is located on the Columbus External Payload Facility in a zenith location. The objective of the SOLAR payload is to study the Sun. The SOLAR payload consists of three instruments that allow for measurement of virtually the entire electromagnetic spectrum (17 nm to 100 um). The three payload instruments are SOVIM (SOlar Variable and Irradiance Monitor), SOLSPEC (SOLar SPECctral Irradiance measurements), and SolACES (SOLar Auto-Calibrating Extreme UV/UV Spectrophotometers). The SolACES payload includes a set of 4 spectrometers that measure the solar EUV flux from 17 nm to 220 nm. One of these 4 spectrometers failed early on (before deployment). EUV data is important in understanding the solar dynamo. Also, EUV flux is the source of most of the ionization that produces the ionosphere plasma. Plasma production is important in understanding the ionosphere environment. The ionosphere conditions affect many subjects including spacecraft charging, dynamo processes, instabilities, and communications. The 3 remaining spectrometers have collected valuable data during the historically low solar cycle 24. Some of this data will be presented. A significant trend in degradation of the remaining SolACES spectrometers was observed towards the end of CY2010 (GMT 310) through mid CY 2011 (GMT 132). The Principle Investigators of SolACES initiated a Mission Evaluation Room (MER) Chit to request an investigation of the degradation in CY 2011 (GMT 230). The Boeing Space Environments team was asked to respond to the ESA initiated MER Chit request to investigate the cause of the degradation. This paper will discuss the findings of that investigation.

Exomars mission description and architecture

NASA Astrophysics Data System (ADS)

Giorgio, Vincenzo; Cassi, Carlo; Santoro, Pasquale

Msftedit 5.41.15.1507; INTRODUCTION ExoMars is the first mission of the ESA Exploration Programme. It will demonstrate flight and in-situ verification of key exploration enabling technologies to support the European ambitions for future human exploration missions. The main technology demonstration objectives are: Entry, Descent and Landing (EDL) of a large payload on the surface of Mars, Surface mobility via a Rover having several kilometres of mobility range, Access to sub-surface via a Drill to acquire samples down to 2 meters, Automatic sample preparation and distribution for analyses of scientific experiments. In parallel, important scientific objectives will be accomplished through a state-of-the art scientific payload. The ExoMars scientific objectives, in order of priority, are: The search for traces of past and present life, To characterise the water/geochemical environment as a function of depth in the shallow subsurface; To study the surface environment and identify hazards to future human missions; To investigate the planet's subsurface and deep interior to better understand the evolution and habitability of Mars. mission scenario The combinations of the above constraints and other considerations have recently led to a re-definition of the baseline mission that can be summarised as follows: Launch date: Dec 2013 Spacecraft Composite: Carrier + Descent Module Launcher: Ariane 5 from Kourou (back-up Proton from Baikonur) Descent Module released from Mars orbit Courier Module expendable (crash on Mars) Landing between 5° South and 34 ° North Descent Module landing configuration with vented airbags Data relay function provided by a NASA spacecraft. This scenario has been named enhanced baseline, as it basically responds to the need of increasing the payload mass (larger DM mass) and improving the landing accuracy to meet a semi-major axis of the landing error ellipse, downrange of the nominal landing site, of 50 km (3σ) which proved to be unfeasible with the hyperbolic arrival. DESCENT MODULE CONFIGURATION The main DM elements are: the Front Shield, the Back Shell, and the Lander. The Front Shield is an Al honeycomb composite with CFRP skins, covered with light ablative material. Its diameter is 3.4 m. It is separated from the back shell after the deployment of the parachute. The conical Back Shell is made up of a structure covered by a back shield made from the same materials as the front one. This structure provides support for the accommodation of the CM/DM separation mechanisms, some DM equipment such as parachute and thrusters, and the interfaces with the Front Shield and Landing Platform. The Lander is formed by the Landing Platform (Support and Egress Structure, SES and Air Bag System, ABS) and the DM avionic subsystems. It also accommodates the Humboldt Payload. A view is provided in (note the use of the old terminology of GEP for the box housing some of the Humboldt instruments). The Rover with its Pasteur Payload is installed and locked onto the Lander.

An Overview of the Microgravity Science Glovebox (MSG) Facility and the Research Performed in the MSG on the International Space Station (ISS)

NASA Technical Reports Server (NTRS)

Jordan, Lee P.

2013-01-01

The Microgravity Science Glovebox (MSG) is a rack facility aboard the International Space Station (ISS) designed for investigation handling. The MSG was built by the European Space Agency (ESA) which also provides sustaining engineering support for the facility. The MSG has been operating on the ISS since July 2002 and is currently located in the US Laboratory Module. The unique design of the facility allows it to accommodate science and technology investigations in a "workbench" type environment. The facility has an enclosed working volume that is held at a negative pressure with respect to the crew living area. This allows the facility to provide two levels of containment for small parts, particulates, fluids, and gases. This containment approach protects the crew from possible hazardous operations that take place inside the MSG work volume. Research investigations operating inside the MSG are provided a large 255 liter enclosed work space, 1000 watts of dc power via a versatile supply interface (120, 28, +/- 12, and 5 Vdc), 1000 watts of cooling capability, video and data recording and real time downlink, ground commanding capabilities, access to ISS Vacuum Exhaust and Vacuum Resource Systems, and gaseous nitrogen supply. These capabilities make the MSG one of the most utilized facilities on ISS. The MSG has been used for over 14500 hours of scientific payload operations. MSG investigations involve research in cryogenic fluid management, fluid physics, spacecraft fire safety, materials science, combustion, plant growth, and life support technology. The MSG facility is operated by the Payloads Operations Integration Center at Marshall Space flight Center. Payloads may also operate remotely from different telescience centers located in the United States and Europe. The investigative Payload Integration Manager (iPIM) is the focal to assist organizations that have payloads operating in the MSG facility. NASA provides an MSG engineering unit for payload developers to verify that their hardware is operating properly before actual operation on the ISS. This paper will provide an overview of the MSG facility, a synopsis of the research that has already been accomplished in the MSG, and an overview of video and biological upgrades.

NASA's Space Launch System: Deep-Space Delivery for SmallSats

NASA Technical Reports Server (NTRS)

Robinson, Kimberly F.; Norris, George

2017-01-01

Designed for human exploration missions into deep space, NASA's Space Launch System (SLS) represents a new spaceflight infrastructure asset, enabling a wide variety of unique utilization opportunities. While primarily focused on launching the large systems needed for crewed spaceflight beyond Earth orbit, SLS also offers a game-changing capability for the deployment of small satellites to deep-space destinations, beginning with its first flight. Currently, SLS is making rapid progress toward readiness for its first launch in two years, using the initial configuration of the vehicle, which is capable of delivering more than 70 metric tons (t) to Low Earth Orbit (LEO). On its first flight, an uncrewed test of the Orion spacecraft into distant retrograde orbit around the moon, accompanying Orion on SLS will be 13 small-satellite secondary payloads, which will deploy in cislunar space. These secondary payloads will include not only NASA research, but also spacecraft from industry and international partners and academia. The payloads also represent a variety of disciplines including, but not limited to, studies of the moon, Earth, sun, and asteroids. The Space Launch System Program is working actively with the developers of the payloads toward vehicle integration. Following its first flight and potentially as early as its second, SLS will evolve into a more powerful configuration with a larger upper stage. This configuration will initially be able to deliver 105 t to LEO, and will continue to be upgraded to a performance of greater than 130 t to LEO. While the addition of the more powerful upper stage will mean a change to the secondary payload accommodations from those on the first launch, the SLS Program is already evaluating options for future secondary payload opportunities. Early discussions are also already underway for the use of SLS to launch spacecraft on interplanetary trajectories, which could open additional opportunities for small satellites. This presentation will include an overview of the SLS vehicle and its capabilities, including the current status of progress toward first launch. It will also explain the opportunities the vehicle offers for small satellites, including an overview of the CubeSat manifest for Exploration Mission-1 in 2018 and a discussion of future capabilities.

Investigating the Impact of a Solar Eclipse on Atmospheric Radiation

NASA Astrophysics Data System (ADS)

Fender, Josh; Morse, Justin; Ringler, John; Galovich, Cynthia; Kuehn, Charles A.; Semak, Matthew

2018-06-01

We present a project that measured atmospheric muon flux as a function of altitude during a total solar eclipse. An auxiliary goal was to design and build a cost-effective muon detection device that is simple enough for those with minimal training to build. The detector is part of a self-contained autonomous payload that is carried to altitude aboard a weather balloon. The detection system consists of three Geiger counters connected to a coincidence circuit. This system, along with internal and external temperature sensors and an altimeter, are controlled by an onboard Arduino Mega microcontroller. An internal frame was constructed to house and protect the payload components using modular 3D-printed parts. The payload was launched during the 2017 solar eclipse from Guernsey, Wyoming, along the path of totality. Initial data analysis indicates that line-of-sight blockage of the sun due to a total eclipse produces a negligible difference in muon flux when compared to the results of previous daytime flights. The successful performance of the payload, its low overall cost, and its ease of use suggest that this project would be well-suited for individuals or groups such as high school or undergraduate science students to reproduce and enhance.

Magnetic hyperthermia controlled drug release in the GI tract: solving the problem of detection.

PubMed

Bear, Joseph C; Patrick, P Stephen; Casson, Alfred; Southern, Paul; Lin, Fang-Yu; Powell, Michael J; Pankhurst, Quentin A; Kalber, Tammy; Lythgoe, Mark; Parkin, Ivan P; Mayes, Andrew G

2016-09-27

Drug delivery to the gastrointestinal (GI) tract is highly challenging due to the harsh environments any drug- delivery vehicle must experience before it releases it's drug payload. Effective targeted drug delivery systems often rely on external stimuli to effect release, therefore knowing the exact location of the capsule and when to apply an external stimulus is paramount. We present a drug delivery system for the GI tract based on coating standard gelatin drug capsules with a model eicosane- superparamagnetic iron oxide nanoparticle composite coating, which is activated using magnetic hyperthermia as an on-demand release mechanism to heat and melt the coating. We also show that the capsules can be readily detected via rapid X-ray computed tomography (CT) and magnetic resonance imaging (MRI), vital for progressing such a system towards clinical applications. This also offers the opportunity to image the dispersion of the drug payload post release. These imaging techniques also influenced capsule content and design and the delivered dosage form. The ability to easily change design demonstrates the versatility of this system, a vital advantage for modern, patient-specific medicine.

University of Virginia infrared sensor experiment (UVIRSE)

NASA Astrophysics Data System (ADS)

Dawson, Jeffrey R.; Bell, Meredith A.; Powers, Michael C.; Laufer, Gabriel

2001-03-01

A suite consisting of an infrared sensor, optical sensors and a video camera are prepared for launch by a group of students at University of Virginia (UVA) and James Madison University (JMU). The sensors are a first step in the development of a Gas Filter Correlation Radiometer (GFCR) that will detect stratospheric methane (CH4) when flown on sub-orbital sounding rockets and/or from the hypersonic X-34 reusable launch vehicle. The current payload has a threefold purpose: (a) to provide space heritage to a thermoelectrically cooled mercury cadmium telluride sensor, (b) to demonstrate methods for correlating the IR reading of the sensor with ground topography, and (c) to flight test all the payload components that will become part of the sub- orbital methane GFCR sensor. Once completed the system will serve as host to other undergraduate research design projects that require space environment, microgravity, or remote sensing capabilities. The payload components have been received and tested, and the supporting structure has been designed and built. Data from previous rocket flights was used to analyze the environmental strains placed on the experiment and components. Payload components are being integrated and tested as a system to ensure functionality in the flight environment. This includes thermal testing for individual components, vibration testing from individual components and overall payload, and load testing of the external structure. Launch is scheduled for Spring 2001.

KSC-2010-4543

NASA Image and Video Library

2010-09-01

CAPE CANAVERAL, Fla. -- In the Space Station Processing Facility at NASA's Kennedy Space Center in Florida, an overhead crane is poised over the Alpha Magnetic Spectrometer, or AMS, to lift the Payload Attach System, or PAS, up to the AMS. The PAS provides a method of securely connecting the payload to the International Space Station. AMS, a state-of-the-art particle physics detector, is designed to operate as an external module on the International Space Station. It will use the unique environment of space to study the universe and its origin by searching for dark matter. AMS will fly to the station aboard space shuttle Endeavour's STS-134 mission targeted to launch Feb. 26, 2011. Photo credit: NASA/Jack Pfaller

KSC-07pd2024

NASA Image and Video Library

2007-07-19

KENNEDY SPACE CENTER, Fla. -- In the Orbiter Processing Facility bay 3, a crane moves the main bus switching unit that will be installed in Discovery's payload bay. The unit is part of the payload on mission STS-120. A main bus switching unit is used for power distribution, circuit protection and fault isolation on the space station's power system. The units route power to proper locations in the space station, such as from solar arrays through umbilicals into the U.S. Lab. The unit will be installed on the external stowage platform 2 attached to the Quest airlock for temporary storage. Discovery is targeted to launch mission STS-120 no earlier than Oct. 20. Photo credit: NASA/Jim Grossmann

KSC-07pd2023

NASA Image and Video Library

2007-07-19

KENNEDY SPACE CENTER, Fla. -- In the Orbiter Processing Facility bay 3, a crane lifts the main bus switching unit that will be installed in Discovery's payload bay. The unit is part of the payload on mission STS-120. A main bus switching unit is used for power distribution, circuit protection and fault isolation on the space station's power system. The units route power to proper locations in the space station, such as from solar arrays through umbilicals into the U.S. Lab. The unit will be installed on the external stowage platform 2 attached to the Quest airlock for temporary storage. Discovery is targeted to launch mission STS-120 no earlier than Oct. 20. Photo credit: NASA/Jim Grossmann

KSC-07pd1990

NASA Image and Video Library

2007-07-19

KENNEDY SPACE CENTER, Fla. --In the White Room on Launch Pad 39A, STS-118 Mission Specialist Rick Mastracchio is eager to enter Space Shuttle Endeavour for a simulated launch countdown, the culmination of terminal countdown demonstration test activities. The White Room is situated at the end of the orbiter access arm and provides entry into the orbiter. TCDT activities also include M-113 training, payload familiarization and emergency egress training at the pad. The mission is the 22nd flight to the International Space Station and Space Shuttle Endeavour will carry a payload including the S5 truss, a SPACEHAB module and external stowage platform 3. STS-118 is targeted for launch on Aug. 7. Photo credit: NASA/Amanda Diller

The ESA Laboratory Support Equipment for the ISS.

PubMed

Petrivelli, A

2002-02-01

The Laboratory Support Equipment (LSE) for the International Space Station (ISS) is a suite of general-purpose items that will be available onboard the Station either as self-standing facilities or as equipment that can be used at defined locations. Dedicated to supporting system maintenance and payload operations, some LSE items are derived from commercial equipment, while others have been specifically developed for the ISS. ESA is currently engaged in developing three pressurised facilities and one pointing mechanism that will become part of the LSE complement, namely: the Minus Eighty degree centigrade Laboratory Freezer for the ISS (MELFI), the Microgravity Science Glovebox (MSG), the cryogenic storage and quick/snap freezer system (Cryosystem), the external-payload pointing system (Hexapod).

NASA 60 GHz intersatellite communication link definition study. Baseline document

NASA Technical Reports Server (NTRS)

1986-01-01

The overall system and component concepts for a 60 GHz intersatellite communications link system (ICLS) are described. The ICLS was designed to augment the capabilities of the current Tracking and Data Relay Satellite System (TDRSS), providing a data rate capacity large enough to accommodate the expected rates for user satellites (USAT's) in the post-1995 timeframe. The use of 60 GHz for the anticipated successor to TDRSS, the Tracking and Data Acquisition System (TDAS), was selected because of current technology development that will enable multigigibit data rates. Additionally, the attenuation of the earth's atmosphere at 60 GHz means that there is virtually no possibility of terrestrially generated interference (intentional or accidental) or terrestrially based intercept. The ICLS includes the following functional areas: (1) the ICLS payload package on the GEO TDAS satellite that communicates simultaneously with up to five LEO USAT's; (2) the payload package on the USAT that communicates with the TDAS satellite; and (3) the crosslink payload package on the TDAS satellite that communicates with another TDAS satellite. Two methods of data relay on-board the TDAS spacecraft were addressed. One is a complete baseband system (demod and remod) with a bi-directional 2 Gbps data stream; the other is a channelized system wherein some of the channels are baseband and others are merely frequency translated before re-transmission. Descriptions of the TDAS antenna, transmitter, receiver, and mechanical designs are presented.

Teaching the Next Generation of Scientists and Engineers the NASA Design Process

NASA Technical Reports Server (NTRS)

Caruso, Pamela W.; Benfield, Michael P. J.; Justice, Stefanie H.

2011-01-01

The Integrated Product Team (IPT) program, led by The University of Alabama in Huntsville (UAH), is a multidisciplinary, multi-university, multi-level program whose goal is to provide opportunities for high school and undergraduate scientists and engineers to translate stakeholder needs and requirements into viable engineering design solutions via a distributed multidisciplinary team environment. The current program supports three projects. The core of the program is the two-semester senior design experience where science, engineering, and liberal arts undergraduate students from UAH, the College of Charleston, Southern University at Baton Rouge, and Ecole Suprieure des Techniques Aronautiques et de Construction Automobile (ESTACA) in Paris, France form multidisciplinary competitive teams to develop system concepts of interest to the local aerospace community. External review boards form to provide guidance and feedback throughout the semester and to ultimately choose a winner from the competing teams. The other two projects, the Innovative Student Project for the Increased Recruitment of Engineering and Science Students (InSPIRESS) Level I and Level II focus exclusively on high school students. InSPIRESS Level I allows high schools to develop a payload to be accommodated on the system being developed by senior design experience teams. InSPIRESS Level II provides local high school students first-hand experience in the senior design experience by allowing them to develop a subsystem or component of the UAH-led system over the two semesters. This program provides a model for NASA centers to engage the local community to become more involved in design projects.

Advanced helium purge seals for Liquid Oxygen (LOX) turbopumps

NASA Technical Reports Server (NTRS)

Shapiro, Wilbur; Lee, Chester C.

1989-01-01

Program objectives were to determine three advanced configurations of helium buffer seals capable of providing improved performance in a space shuttle main engine (SSME), high-pressure liquid oxygen (LOX) turbopump environment, and to provide NASA with the analytical tools to determine performance of a variety of seal configurations. The three seal designs included solid-ring fluid-film seals often referred to as floating ring seals, back-to-back fluid-film face seals, and a circumferential sectored seal that incorporated inherent clearance adjustment capabilities. Of the three seals designed, the sectored seal is favored because the self-adjusting clearance features accommodate the variations in clearance that will occur because of thermal and centrifugal distortions without compromising performance. Moreover, leakage can be contained well below the maximum target values; minimizing leakage is important on the SSME since helium is provided by an external tank. A reduction in tank size translates to an increase in payload that can be carried on board the shuttle. The computer codes supplied under this program included a code for analyzing a variety of gas-lubricated, floating ring, and sector seals; a code for analyzing gas-lubricated face seals; a code for optimizing and analyzing gas-lubricated spiral-groove face seals; and a code for determining fluid-film face seal response to runner excitations in as many as five degrees of freedom. These codes proved invaluable for optimizing designs and estimating final performance of the seals described.

A System For Load Isolation And Precision Pointing

NASA Astrophysics Data System (ADS)

Keckler, Claude R.; Hamilton, Brian J.

1983-11-01

A system capable of satisfying the accuracy and stability requirements dictated by Shuttle-borne payloads utilizing large optics has been under joint NASA/Sperry development. This device, denoted the Annular Suspension and Pointing System, employs a unique combination of conventional gimbals and magnetic bearing actuators, thereby providing for the "complete" isolation of the payload from its external environment, as well as for extremely accurate and stable pointing (≍0.01 arcseconds). This effort has been pursued through the fabrication and laboratory evaluation of engineering model hardware. Results from these tests have been instrumental in generating high fidelity computer simulations of this load isolation and precision pointing system, and in permitting confident predictions of the system's on-orbit performance. Applicability of this system to the Solar Optical Telescope mission has been examined using the computer simulation. The worst case pointing error predicted for this payload while subjected to vernier reaction control system thruster firings and crew motions aboard Shuttle was approximately 0.006 arcseconds.

Our Human Journey to Mars - The Next Steps

NASA Technical Reports Server (NTRS)

Singer, Jody

2016-01-01

The United States National Aeronautics and Space Administration (NASA) will be launching the super-heavy-lift Space Launch System (SLS) by the end of the decade. This launch marks the next steps of human exploration of Mars and continues the journey that began over 50 years ago with Mariner and most recently ExoMars. SLS is the only rocket with the power capable of sending humans to deep space and the large systems necessary for human exploration all the way to Mars. Exploration Mission (EM)-1 will be the first integrated flight of the SLS rocket and Orion spacecraft - journeying farther into space than Apollo. NASA will also expand the science and exploration capability of SLS by deploying thirteen small satellites into deep space for the first time. These small satellites, created through partnerships with small businesses, Universities and international partners, will carry out various scientific missions to better understand our universe and the challenges of living and working in deep space. SLS EM-1 will provide the framework and serve as a test flight, not only for vehicle systems, but also for payload accommodations, ground processing and on-orbit operations. The results of this mission will validate capabilities for sending explorers to Mars and create the opportunity to pioneer solutions to challenges to deep space exploration. SLS's versatile design will evolve for future exploration needs and accommodate bigger payloads, such as large aperture telescopes for scientific research or manned human deep space exploration missions to Mars. The achievement of EM-1 will demonstrate NASA's commitment and capability to extend human existence to deep space and inspire the world to pursue greatness in the exploration of our universe.

Shuttle Endeavour Mated to 747 SCA Taxi to Runway for Delivery to Kennedy Space Center, Florida

NASA Technical Reports Server (NTRS)

1991-01-01

NASA's 747 Shuttle Carrier Aircraft No. 911, with the space shuttle orbiter Endeavour securely mounted atop its fuselage, taxies to the runway to begin the ferry flight from Rockwell's Plant 42 at Palmdale, California, where the orbiter was built, to the Kennedy Space Center, Florida. At Kennedy, the space vehicle was processed and launched on orbital mission STS-49, which landed at NASA's Ames-Dryden Flight Research Facility (later redesignated Dryden Flight Research Center), Edwards, California, 16 May 1992. NASA 911, the second modified 747 that went into service in November 1990, has special support struts atop the fuselage and internal strengthening to accommodate the added weight of the orbiters. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Shuttle Endeavour Mated to 747 SCA Takeoff for Delivery to Kennedy Space Center, Florida

NASA Technical Reports Server (NTRS)

1991-01-01

NASA's 747 Shuttle Carrier Aircraft No. 911, with the space shuttle orbiter Endeavour securely mounted atop its fuselage, begins the ferry flight from Rockwell's Plant 42 at Palmdale, California, where the orbiter was built, to the Kennedy Space Center, Florida. At Kennedy, the space vehicle was processed and launched on orbital mission STS-49, which landed at NASA's Ames-Dryden Flight Research Facility (later redesignated Dryden Flight Research Center), Edwards, California, 16 May 1992. NASA 911, the second modified 747 that went into service in November 1990, has special support struts atop the fuselage and internal strengthening to accommodate the added weight of the orbiters. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Shuttle Discovery Mated to 747 SCA

NASA Technical Reports Server (NTRS)

1983-01-01

The Space Shuttle Discovery rides atop '905,' NASA's 747 Shuttle Carrier Aircraft, on its delivery flight from California to the Kennedy Space Center, Florida, where it was prepared for its first orbital mission for 30 August to 5 September 1984. The NASA 747, obtained in 1974, has special support struts atop the fuselage and internal strengthening to accommodate the additional weight of the orbiters. Small vertical fins have also been added to the tips of the horizontal stabilizers for additional stability due to air turbulence on the control surfaces caused by the orbiters. A second modified 747, no. 911, went in to service in November 1990 and is also used to ferry orbiters to destinations where ground transportation is not practical. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Shuttle Columbia Mated to 747 SCA with Crew

NASA Technical Reports Server (NTRS)

1981-01-01

The crew of NASA's 747 Shuttle Carrier Aircraft (SCA), seen mated with the Space Shuttle Columbia behind them, are from viewers left: Tom McMurtry, pilot; Vic Horton, flight engineer; Fitz Fulton, command pilot; and Ray Young, flight engineer. The SCA is used to ferry the shuttle between California and the Kennedy Space Center, Florida, and other destinations where ground transportation is not practical. The NASA 747 has special support struts atop the fuselage and internal strengthening to accommodate the additional weight of the orbiters. Small vertical fins have also been added to the tips of the horizontal stabilizers for additional stability due to air turbulence on the control surfaces caused by the orbiters. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into space, the laboratories remain inside the payload bay throughout the mission. They are then removed after the Space Shuttle returns to Earth and can be reused on future flights. Some of these orbital laboratories, like the Spacelab, provide facilities for several specialists to conduct experiments in such fields as medicine, astronomy, and materials manufacturing. Some types of satellites deployed by Space Shuttles include those involved in environmental and resources protection, astronomy, weather forecasting, navigation, oceanographic studies, and other scientific fields. The Space Shuttles can also launch spacecraft into orbits higher than the Shuttle's altitude limit through the use of Inertial Upper Stage (IUS) propulsion units. After release from the Space Shuttle payload bay, the IUS is ignited to carry the spacecraft into deep space. The Space Shuttles are also being used to carry elements of the International Space Station into space where they are assembled in orbit. The Space Shuttles were built by Rockwell International's Space Transportation Systems Division, Downey, California. Rockwell's Rocketdyne Division (now part of Boeing) builds the three main engines, and Thiokol, Brigham City, Utah, makes the solid rocket booster motors. Martin Marietta Corporation (now Lockheed Martin), New Orleans, Louisiana, makes the external tanks. Each orbiter (Space Shuttle) is 121 feet long, has a wingspan of 78 feet, and a height of 57 feet. The Space Shuttle is approximately the size of a DC-9 commercial airliner and can carry a payload of 65,000 pounds into orbit. The payload bay is 60 feet long and 15 feet in diameter. Each main engine is capable of producing a sea level thrust of 375,000 pounds and a vacuum (orbital) thrust of 470,000 pounds. The engines burn a mixture of liquid oxygen and liquid hydrogen. In orbit, the Space Shuttles circle the earth at a speed of 17,500 miles per hour with each orbit taking about 90 minutes. A Space Shuttle crew sees a sunrise or sunset every 45 minutes. When Space Shuttle flights began in April 1981, Dryden Flight Research Center, Edwards, California, was the primary landing site for the Shuttles. Now Kennedy Space Center, Florida, is the primary landing site with Dryden remaining as the principal alternate landing site.

Technology Survey of Advanced Army Weapon Systems and Their Support Requirements.

DTIC Science & Technology

1981-03-01

the YAH-64A is eight HELLFIRE missiles and 320 rounds of 30mm ADEN /DEFA ammunition, With this payload, it will have the following performance under...improved suspension that permits 14-in. vertical tra- vel of the road wheels. The XM-3 CFV is identical to the XM-2 IFV (see Figure 6) in external

KSC-06pd2292

NASA Image and Video Library

2006-10-13

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is mated to its twin solid rocket boosters on the mobile launch platform in high bay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6 feet wide and 154 feet tall. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2291

NASA Image and Video Library

2006-10-13

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is mated to its twin solid rocket boosters on the mobile launch platform in high bay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6 feet wide and 154 feet tall. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2289

NASA Image and Video Library

2006-10-13

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is mated to its twin solid rocket boosters on the mobile launch platform in high bay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2290

NASA Image and Video Library

2006-10-13

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is mated to its twin solid rocket boosters on the mobile launch platform in high bay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the space shuttle system at 27.6 feet wide and 154 feet tall. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2293

NASA Image and Video Library

2006-10-13

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is mated to its twin solid rocket boosters on the mobile launch platform in high bay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6 feet wide and 154 feet tall. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

Research Opportunities on board Virgin Galactic's SpaceShipTwo

NASA Astrophysics Data System (ADS)

Attenborough, S.; Pomerantz, W.; Stephens, K.

2013-09-01

Virgin Galactic is building the world's first commercial spaceline. Our suborbital spaceflight system, pictured in Figure 1, consists of two vehicles: WhiteKnightTwo (WK2) and SpaceShipTwo (SS2). WhiteKnightTwo is a four-engine, dual-fuselage jet aircraft capable of high-altitude heavy lift missions, including, but not limited to fulfilling its role as a mothership for SpaceShipTwo, an air-launched, suborbital spaceplane capable of routinely reaching an apogee up to 110 kilometers. In conjunction, these two vehicles allow access to space and to regions of the atmosphere ranging from the troposphere to the thermosphere; additionally, they provide extended periods of microgravity in a reliable and affordable way. SpaceShipTwo, with a payload capacity of up to 1,300 lbs. (~600 kg), features payload mounting interfaces that are compatible with standard architectures such as NASA Space Shuttle Middeck Lockers, Cargo Transfer Bags, and server racks, in addition to custom structures. With the standard interface, payloads are allowed access to the large 17 inch diameter cabin windows for external observations. Each dedicated research flight will be accompanied by a Virgin Galactic Flight Test Engineer, providing an opportunity for limited in-flight interaction. In addition, tended payloads - a flight that includes the researcher and his or her payload - are also an option. At a price point that is highly competitive with parabolic aircraft and sounding rockets and significantly cheaper than orbital flights, SpaceShipTwo is a unique platform that can provide frequent and repeatable research opportunities. Suborbital flights on SpaceShipTwo offer researchers several minutes of microgravity time and views of the external environment in the upper atmosphere and in outer space. In addition to serving as an important research platform in and of itself, SpaceShipTwo also offers researchers a means to test, iterate, and calibrate experiments designed for orbital platforms, including the International Space Station as well as LauncherOne, Virgin Galactic's dedicated launch vehicle for small (~500 lbs. / ~225 kg) satellites. Flights on SpaceShipTwo can be booked directly through Virgin Galactic. Various funding sources may be available for the research, including through NASA programs such as the Flight Opportunities Program, Game Changing Development Program, or Research Opportunities in Space and Earth Science (ROSES). More information about the SpaceShipTwo research platform, including a detailed Payload User's Guide, can be found at our website: http://www.virgingalactic.com/research.

STS-98 Onboard Photograph-U.S. Laboratory, Destiny

NASA Technical Reports Server (NTRS)

2001-01-01

This STS-98 mission photograph shows astronauts Thomas D. Jones (foreground) and Kerneth D. Cockrell floating inside the newly installed Laboratory aboard the International Space Station (ISS). The American-made Destiny module is the cornerstone for space-based research aboard the orbiting platform and the centerpiece of the ISS, where unprecedented science experiments will be performed in the near-zero gravity of space. Destiny will also serve as the command and control center for the ISS. The aluminum module is 8.5-meters (28-feet) long and 4.3-meters (14-feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 15 locations especially designed to support experiments. The Destiny module was built by the Boeing Company under the direction of the Marshall Space Flight Center.

U.S. Laboratory Module (Destiny) for the International Space Station

NASA Technical Reports Server (NTRS)

1997-01-01

In this photograph, the U.S. Laboratory Module (also called Destiny) for the International Space Station (ISS) is shown under construction in the West High Bay of the Space Station manufacturing facility (building 4708) at the Marshall Space Flight Center. The U.S. Laboratory module is the centerpiece of the ISS, where science experiments will be performed in the near-zero gravity of space. The Destiny Module was launched aboard the Space Shuttle orbiter Atlantis (STS-98 mission) on February 7, 2001. The aluminum module is 8.5 meters (28 feet) long and 4.3 meters (14 feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations, and payload racks will occupy 13 locations especially designed to support experiments. The ISS is a multidisciplinary laboratory, technology test bed, and observatory that will provide unprecedented undertakings in scientific, technological, and international experimentation.

U.S. Laboratory Module (Destiny) for the International Space Station

NASA Technical Reports Server (NTRS)

1998-01-01

This photograph shows the U.S. Laboratory Module (also called Destiny) for the International Space Station (ISS), in the Space Station manufacturing facility at the Marshall Space Flight Center, being readied for shipment to the Kennedy Space Center. The U.S. Laboratory module is the centerpiece of the ISS, where science experiments will be performed in the near-zero gravity of space. The Destiny Module was launched aboard the Space Shuttle orbiter Atlantis (STS-67 mission) on February 7, 2001. The aluminum module is 8.5 meters (28 feet) long and 4.3 meters (14 feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations, and payload racks will occupy 13 locations especially designed to support experiments. The ISS is a multidisciplinary laboratory, technology test bed, and observatory that will provide unprecedented undertakings in scientific, technological, and international experimentation.

U.S. Laboratory Module (Destiny) for the International Space Station

NASA Technical Reports Server (NTRS)

1997-01-01

This photograph shows the U.S. Laboratory Module (also called Destiny) for the International Space Station (ISS), under construction in the Space Station manufacturing facility at the Marshall Space Flight Center. The U.S. Laboratory module is the centerpiece of the ISS, where science experiments will be performed in the near-zero gravity of space. The Destiny Module was launched aboard the Space Shuttle orbiter Atlantis (STS-67 mission) on February 7, 2001. The aluminum module is 8.5 meters (28 feet) long and 4.3 meters (14 feet) in diameter. The laboratory consists of three cylindrical sections and two end cones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations, and payload racks will occupy 13 locations especially designed to support experiments. The ISS is a multidisciplinary laboratory, technology test bed, and observatory that will provide unprecedented undertakings in scientific, technological, and international experimentation.

STS-98 Onboard Photograph-U.S. Laboratory, Destiny

NASA Technical Reports Server (NTRS)

2001-01-01

This closer image of the International Space Station (ISS) showing the newly installed U.S. Laboratory, Destiny (left), was taken from the departing Space Shuttle Atlantis. The American-made Destiny module is the cornerstone for space-based research aboard the orbiting platform and the centerpiece of the ISS, where unprecedented science experiments will be performed in the near-zero gravity of space. Destiny will also serve as the command and control center for the ISS. The aluminum module is 8.5-meters (28-feet) long and 4.3-meters (14-feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 15 locations especially designed to support experiments. The Destiny module was built by the Boeing Company under the direction of the Marshall Space Flight Center.

Investigation of Propulsion System Requirements for Spartan Lite

NASA Technical Reports Server (NTRS)

Urban, Mike; Gruner, Timothy; Morrissey, James; Sneiderman, Gary

1998-01-01

This paper discusses the (chemical or electric) propulsion system requirements necessary to increase the Spartan Lite science mission lifetime to over a year. Spartan Lite is an extremely low-cost (less than 10 M) spacecraft bus being developed at the NASA Goddard Space Flight Center to accommodate sounding rocket class (40 W, 45 kg, 35 cm dia by 1 m length) payloads. While Spartan Lite is compatible with expendable launch vehicles, most missions are expected to be tertiary payloads deployed by. the Space Shuttle. To achieve a one year or longer mission life from typical Shuttle orbits, some form of propulsion system is required. Chemical propulsion systems (characterized by high thrust impulsive maneuvers) and electrical propulsion systems (characterized by low-thrust long duration maneuvers and the additional requirement for electrical power) are discussed. The performance of the Spartan Lite attitude control system in the presence of large disturbance torques is evaluated using the Trectops(Tm) dynamic simulator. This paper discusses the performance goals and resource constraints for candidate Spartan Lite propulsion systems and uses them to specify quantitative requirements against which the systems are evaluated.

International Space Station (ISS)

NASA Image and Video Library

1998-11-01

This photograph shows the U.S. Laboratory Module (also called Destiny) for the International Space Station (ISS), in the Space Station manufacturing facility at the Marshall Space Flight Center, being readied for shipment to the Kennedy Space Center. The U.S. Laboratory module is the centerpiece of the ISS, where science experiments will be performed in the near-zero gravity of space. The Destiny Module was launched aboard the Space Shuttle orbiter Atlantis (STS-67 mission) on February 7, 2001. The aluminum module is 8.5 meters (28 feet) long and 4.3 meters (14 feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations, and payload racks will occupy 13 locations especially designed to support experiments. The ISS is a multidisciplinary laboratory, technology test bed, and observatory that will provide unprecedented undertakings in scientific, technological, and international experimentation.

International Space Station (ISS)

NASA Image and Video Library

1997-01-01

In this photograph, the U.S. Laboratory Module (also called Destiny) for the International Space Station (ISS) is shown under construction in the West High Bay of the Space Station manufacturing facility (building 4708) at the Marshall Space Flight Center. The U.S. Laboratory module is the centerpiece of the ISS, where science experiments will be performed in the near-zero gravity of space. The Destiny Module was launched aboard the Space Shuttle orbiter Atlantis (STS-98 mission) on February 7, 2001. The aluminum module is 8.5 meters (28 feet) long and 4.3 meters (14 feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations, and payload racks will occupy 13 locations especially designed to support experiments. The ISS is a multidisciplinary laboratory, technology test bed, and observatory that will provide unprecedented undertakings in scientific, technological, and international experimentation.

International Space Station (ISS)

NASA Image and Video Library

1997-11-01

In this photograph, the U.S. Laboratory Module (also called Destiny) for the International Space Station (ISS) is shown under construction in the West High Bay of the Space Station manufacturing facility (building 4708) at the Marshall Space Flight Center. The U.S. Laboratory module is the centerpiece of the ISS, where science experiments will be performed in the near-zero gravity of space. The Destiny Module was launched aboard the Space Shuttle orbiter Atlantis (STS-98 mission) on February 7, 2001. The aluminum module is 8.5 meters (28 feet) long and 4.3 meters (14 feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations, and payload racks will occupy 13 locations especially designed to support experiments. The ISS is a multidisciplinary laboratory, technology test bed, and observatory that will provide unprecedented undertakings in scientific, technological, and international experimentation.

International Space Station (ISS)

NASA Image and Video Library

1997-11-26

This photograph shows the U.S. Laboratory Module (also called Destiny) for the International Space Station (ISS), under construction in the Space Station manufacturing facility at the Marshall Space Flight Center. The U.S. Laboratory module is the centerpiece of the ISS, where science experiments will be performed in the near-zero gravity of space. The Destiny Module was launched aboard the Space Shuttle orbiter Atlantis (STS-67 mission) on February 7, 2001. The aluminum module is 8.5 meters (28 feet) long and 4.3 meters (14 feet) in diameter. The laboratory consists of three cylindrical sections and two end cones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations, and payload racks will occupy 13 locations especially designed to support experiments. The ISS is a multidisciplinary laboratory, technology test bed, and observatory that will provide unprecedented undertakings in scientific, technological, and international experimentation.

Low-SWAP Lidar Instrument for Arctic Ice Sheet Mass Balance Monitoring Final Report

DOE Office of Scientific and Technical Information (OSTI.GOV)

Williams, George; Barsic, David

To meet the need to obtain statistically significant data in the North Slope of Alaska (NSA) in support of climate models, Voxtel is developing an nmanned-aircraft-system (UAS)-optimized lidar focal plane array (FPA) and lidar instrument design that integrates the most recent developments in optics, electronics, and computing. Bound by the size, weight, and power (SWAP) budget of low altitude/long endurance (LALE) small UAS (SUAS) platforms—a design tradeoff study was conducted. The class of SUAS considered typically: operates at altitudes between 150 meters and 2,000 meters; accommodates payloads weighing less than 5 kg; encompasses no more than 4,000 cm3 of space;more » and consumes no more than 50 watts of power. To address the SWAP constraints, a lowpower standalone strap-down (gimbal-less) lidar was developed based on single-photon-counting silicon avalanche photodiodes. To reduce SWAP, a lidar FPA design capable of simultaneous imaging and lidar was developed. The 532-nm-optimized FPA modular design was developed for easy integration, as a lidar payload, in any of a variety of SUAS platforms.« less

Preliminary flight results from the second U.S. Microgravity Payload (USMP-2)

NASA Technical Reports Server (NTRS)

Curreri, Peter; Reiss, Donald

1994-01-01

The second U.S. Microgravity Payload (USMP-2) was flown on the Space Shuttle in March 1994. It carried four major microgravity experiments plus a sophisticated accelerometer system to record the microgravity environment during USMP-2 operations. The USMP program is designed to accommodate experiments requiring extensive resources short of a full Spacelab mission, and the experiments are remotely operated and monitored. Results are reviewed from the four experiments: the Advanced Automated Directional Solidification Facility (AADSF), the Isothermal Dendrite Growth Experiment (IDGE), the Materiel por Etude des Phenomenes Interessant la Soldification sur Terre et en Orbite (MEPHISTO), and the Critical Fluid Light Scattering Experiment (Zeno). AASDF grew what is expected to be the largest steady-state sample ever of HgCdTe during 240 hours of operation. IDGE provided 60 growth cycles over a wide range of supercooling conditions studying the dendritic solidification of succinonitrile. MEPHISTO achieved 55 melt-solidify cycles and grew over 1 m of Bi/Sn alloy. Zeno located the critical point temperature for liquid Xe to 0.00001 K. IDGE and Zeno also provided the most extensive demonstrations to date of telescience.

Pharmacologically and Edinger-Westphal stimulated accommodation in rhesus monkeys does not rely on changes in anterior chamber pressure.

PubMed

He, Lin; Wendt, Mark; Glasser, Adrian

2014-08-01

This study was undertaken to understand the role of anterior chamber pressure (ACP) during pharmacological and Edinger-Westphal (EW) stimulated accommodation in anesthetized monkeys. Experiments were performed on one iridectomized eye each of 7 anesthetized adolescent rhesus monkeys. Accommodation was induced by EW stimulation (n = 2) and intravenous administration of 0.25-4.0 mg/kg pilocarpine (n = 6). Accommodative refractive and biometric changes were measured with continuous 60 Hz infrared photorefraction (n = 6) and 100 Hz A-scan ultrasound biometry (n = 1). An ocular perfusion system was used to measure and manipulate ACP. Pressure was recorded via a 27-gauge needle in the anterior chamber connected to a pressure transducer (n = 7). The needle was also connected to a fluid reservoir to allow ACP to be manipulated and clamped (n = 4) by raising or lowering the fluid reservoir. In all six pharmacologically stimulated monkeys ACP increased during accommodation, from 0.70 to 2.38 mmHg, four of which showed pressure decreases preceding the pressure increases. Two eyes also showed increases in ACP during EW-stimulated accommodation of 2.8 and 7.2 mmHg. ACP increased with increasing EW stimulus amplitudes (n = 2). Clamping or externally manipulating ACP had no effect on resting refraction or on EW and pharmacologically stimulated accommodation in four eyes. The results show that EW stimulated and pharmacologically stimulated accommodation do not rely on ACP in rhesus monkeys. Copyright © 2014 Elsevier Ltd. All rights reserved.

Hyperelastic modelling of the crystalline lens: Accommodation and presbyopia

PubMed Central

Lanchares, Elena; Navarro, Rafael; Calvo, Begoña

2012-01-01

Purpose The modification of the mechanical properties of the human crystalline lens with age can be a major cause of presbyopia. Since these properties cannot be measured in vivo, numerical simulation can be used to estimate them. We propose an inverse method to determine age-dependent change in the material properties of the tissues composing the human crystalline lens. Methods A finite element model of a 30-year-old lens in the accommodated state was developed. The force necessary to achieve full accommodation in a 30-year-old lens of known external geometry was computed using this model. Two additional numerical models of the lens corresponding to the ages of 40 and 50 years were then built. Assuming that the accommodative force applied to the lens remains constant with age, the material properties of nucleus and cortex were estimated by inverse analysis. Results The zonular force necessary to reshape the model of a 30-year-old lens from the accommodated to the unaccommodated geometry was 0.078 newton (N). Both nucleus and cortex became stiffer with age. The stiffness of the nucleus increased with age at a higher rate than the cortex. Conclusions In agreement with the classical theory of Helmholtz, on which we based our model, our results indicate that a major cause of presbyopia is that both nucleus and cortex become stiffer with age; therefore, a constant value of the zonular forces with aging does not achieve full accommodation, that is, the accommodation capability decreases.

Operation and maintenance requirements of the Army Remotely Piloted Vehicle (RPV)

NASA Technical Reports Server (NTRS)

1983-01-01

The Remotely Piloted Vehicle (RPV) system is being developed to provide the Army with a target acquistion, target location, and laser designation capability that will significantly enhance the effectiveness of the artillery. Iterative analyses of the manpower, personnel, and training (MPT) requirements for an RPV system configured to accommodate both a daylight television and a forward looking infrared (FLIR) mission payload subsystem (FMPS) and related support subsystems are examined. Additionally, this analysis incorporates a 24 hour-a-day operational scenario. Therefore, the information presented was developed with a view towards delineating the differences (or deltas) imposed by the new requirements resulting from FMPS/24 hour operating day functions.

Balloon-borne three-meter telescope for far-infrared and submillimeter astronomy

NASA Technical Reports Server (NTRS)

Fazio, Giovanni G.; Hoffmann, William F.; Harper, Doyal A.

1988-01-01

The scientific objectives, engineering analysis and design, results of technology development, and focal-plane instrumentation for a two-meter balloon-borne telescope for far-infrared and submillimeter astronomy are presented. The unique capabilities of balloon-borne observations are discussed. A program summary emphasizes the development of the two-meter design. The relationship of the Large Deployable Reflector (LDR) is also discussed. Detailed treatment is given to scientific objectives, gondola design, the mirror development program, experiment accommodations, ground support equipment requirements, NSBF design drivers and payload support requirements, the implementation phase summary development plan, and a comparison of three-meter and two-meter gondola concepts.

Computer-aided controllability assessment of generic manned Space Station concepts

NASA Technical Reports Server (NTRS)

Ferebee, M. J.; Deryder, L. J.; Heck, M. L.

1984-01-01

NASA's Concept Development Group assessment methodology for the on-orbit rigid body controllability characteristics of each generic configuration proposed for the manned space station is presented; the preliminary results obtained represent the first step in the analysis of these eight configurations. Analytical computer models of each configuration were developed by means of the Interactive Design Evaluation of Advanced Spacecraft CAD system, which created three-dimensional geometry models of each configuration to establish dimensional requirements for module connectivity, payload accommodation, and Space Shuttle berthing; mass, center-of-gravity, inertia, and aerodynamic drag areas were then derived. Attention was also given to the preferred flight attitude of each station concept.

Environmental Control Systems for Exploration Missions One and Two

NASA Technical Reports Server (NTRS)

Falcone, Mark A.

2017-01-01

In preparing for Exploration Missions One and Two (EM-1 & EM-2), the Ground Systems Development and Operations Program has significant updates to be made to nearly all facilities. This is all being done to accommodate the Space Launch System, which will be the world’s largest rocket in history upon fruition. Facilitating the launch of such a rocket requires an updated Vehicle Assembly Building, an upgraded Launchpad, Payload Processing Facility, and more. In this project, Environmental Control Systems across several facilities were involved, though there is a focus around the Mobile Launcher and Launchpad. Parts were ordered, analysis models were updated, design drawings were updated, and more.

Study of novel concepts of power transmission gears

NASA Technical Reports Server (NTRS)

Rivin, Eugene I.

1991-01-01

Two concepts in power transmission gear design are proposed which provide a potential for large noise reduction and for improving weight to payload ratio due to use of advanced fiber reinforced and ceramic materials. These concepts are briefly discussed. Since both concepts use ultrathin layered rubber-metal laminates for accommodating limited travel displacements, properties of the laminates, such as their compressive strength, compressive and shear moduli were studied. Extensive testing and computational analysis were performed on the first concept gears (laminate coated conformal gears). Design and testing of the second conceptual design (composite gear with separation of sliding and rolling motions) are specifically described.

NASA Global Hawk: Project Overview and Future Plans

NASA Technical Reports Server (NTRS)

Naftel, J. Chris

2011-01-01

The National Aeronautics and Space Administration (NASA) Global Hawk Project became operational in 2009 and began support of Earth science in 2010. Thus far, the NASA Global Hawk has completed three Earth science campaigns and preparations are under way for two extensive multi-year campaigns. One of the most desired performance capabilities of the Global Hawk aircraft is very long endurance: the Global Hawk aircraft can remain airborne longer than almost all other jet-powered aircraft currently flying, and longer than all other aircraft available for airborne science use. This paper describes the NASA Global Hawk system, payload accommodations, concept of operations, and the scientific data-gathering campaigns.

Mapping Sequence performed during the STS-117 R-Bar Pitch Maneuver

NASA Image and Video Library

2007-06-10

ISS015-E-11328 (10 June 2007) --- This is one of a series of images photographed with a digital still camera using an 800mm focal length featuring the different areas of the Space Shuttle Atlantis as it approached the International Space Station and performed a back-flip to accommodate close scrutiny by eyeballs and cameras. This image shows part of the commander's side or port side of Atlantis' cabin, including the hatch, as well as a section of the open payload bay cover and part of the docking system. Distance from the station and shuttle at this time was approximately 600 feet.

NASA Global Hawk: A New Tool for Earth Science Research

NASA Technical Reports Server (NTRS)

Hall, Phill

2009-01-01

This slide presentation reviews the Global Hawk, a unmanned aerial vehicle (UAV) that NASA plans to use for Earth Sciences research. The Global Hawk is the world's first fully autonomous high-altitude, long-endurance aircraft, and is capable of conducting long duration missions. Plans are being made for the use of the aircraft on missions in the Arctic, Pacific and Western Atlantic Oceans. There are slides showing the Global Hawk Operations Center (GHOC), Flight Control and Air Traffic Control Communications Architecture, and Payload Integration and Accommodations on the Global Hawk. The first science campaign, planned for a study of the Pacific Ocean, is reviewed.

KSC-2010-4545

NASA Image and Video Library

2010-09-01

CAPE CANAVERAL, Fla. -- Technicians in the Space Station Processing Facility at NASA's Kennedy Space Center in Florida, check the progress of the Payload Attach System, or PAS, as it is lifted up to the Alpha Magnetic Spectrometer, where it will be attached to the bottom of the AMS. The PAS provides a method of securely connecting the payload to the International Space Station. AMS, a state-of-the-art particle physics detector, is designed to operate as an external module on the International Space Station. It will use the unique environment of space to study the universe and its origin by searching for dark matter. AMS will fly to the station aboard space shuttle Endeavour's STS-134 mission targeted to launch Feb. 26, 2011. Photo credit: NASA/Jack Pfaller

KSC-2010-4546

NASA Image and Video Library

2010-09-01

CAPE CANAVERAL, Fla. -- In the Space Station Processing Facility at NASA's Kennedy Space Center in Florida, a technician monitors the progress of the Payload Attach System, or PAS, as it is lifted up to the Alpha Magnetic Spectrometer, or AMS, where it will be attached to the bottom of the AMS. The PAS provides a method of securely connecting the payload to the International Space Station. AMS, a state-of-the-art particle physics detector, is designed to operate as an external module on the International Space Station. It will use the unique environment of space to study the universe and its origin by searching for dark matter. AMS will fly to the station aboard space shuttle Endeavour's STS-134 mission targeted to launch Feb. 26, 2011. Photo credit: NASA/Jack Pfaller

KSC-2010-4544

NASA Image and Video Library

2010-09-01

CAPE CANAVERAL, Fla. -- Technicians in the Space Station Processing Facility at NASA's Kennedy Space Center in Florida, monitor the guide wires of the overhead crane as it lifts the Payload Attach System, or PAS, up to the Alpha Magnetic Spectrometer, or AMS, for installation. The PAS provides a method of securely connecting the payload to the International Space Station. AMS, a state-of-the-art particle physics detector, is designed to operate as an external module on the International Space Station. It will use the unique environment of space to study the universe and its origin by searching for dark matter. AMS will fly to the station aboard space shuttle Endeavour's STS-134 mission targeted to launch Feb. 26, 2011. Photo credit: NASA/Jack Pfaller

KSC-2010-4547

NASA Image and Video Library

2010-09-01

CAPE CANAVERAL, Fla. -- A technicians in the Space Station Processing Facility at NASA's Kennedy Space Center in Florida, check the progress of the Payload Attach System, or PAS, as it is lifted up to the Alpha Magnetic Spectrometer, or AMS, where it will be attached to the bottom of the AMS. The PAS provides a method of securely connecting the payload to the International Space Station. AMS, a state-of-the-art particle physics detector, is designed to operate as an external module on the International Space Station. It will use the unique environment of space to study the universe and its origin by searching for dark matter. AMS will fly to the station aboard space shuttle Endeavour's STS-134 mission targeted to launch Feb. 26, 2011. Photo credit: NASA/Jack Pfaller

KSC-07pd1896

NASA Image and Video Library

2007-07-17

KENNEDY SPACE CENTER, Fla. -- STS-118 Mission Specialist Dave Williams, who represents the Canadian Space Agency, signals success after driving an M-113 armored personnel carrier as part of emergency exit training. Behind him are, at left, Pilot Charlie Hobaugh and, right, Mission Specialist Tracy Caldwell. They and other crew members are at Kennedy for the Terminal Countdown Demonstration Test (TCDT), a dress rehearsal for launch. TCDT activities include the M-113 training, payload familiarization, emergency egress training at the pad and a simulated launch countdown. The STS-118 payload aboard Space Shuttle Endeavour includes the S5 truss, a SPACEHAB module and external stowage platform 3. The mission is the 22nd flight to the International Space Station and is targeted for launch on Aug.7. NASA/George Shelton

Space Transportation System (STS) propellant scavenging system study. Volume 1: Technical report

NASA Technical Reports Server (NTRS)

1985-01-01

The objectives are to define the most efficient and cost effective methods for scavenging cryogenic and storable propellants and then define the requirements for these scavenging systems. For cryogenic propellants, scavenging is the transfer of propellants from the Shuttle orbiter external tank (ET) and/or main propulsion subsystems (MPS) propellant lines into storage tanks located in the orbiter payload bay for delivery to the user station by a space based transfer stage or the Space Transportation System (STS) by direct insertion. For storable propellants, scavenging is the direct transfer from the orbital maneuvering subsystem (OMS) and/or tankage in the payload bay to users in LEO as well as users in the vicinity of the Space Station.

Expert System for Building TRU Waste Payloads - 13554

DOE Office of Scientific and Technical Information (OSTI.GOV)

Bruemmer, Heather; Slater, Bryant

2013-07-01

The process for grouping TRU waste drums into payloads for shipment to the Waste Isolation Pilot Plant (WIPP) for disposal is a very complex process. Transportation and regulatory requirements must be met, along with striving for the goals of shipment efficiency: maximize the number of waste drums in a shipment and minimize the use of empty drums which take up precious underground storage space. The restrictions on payloads range from weight restrictions, to limitations on flammable gas in the headspace, to minimum TRU alpha activity concentration requirements. The Overpack and Payload Assistant Tool (OPAT) has been developed as a mixed-initiativemore » intelligent system within the WIPP Waste Data System (WDS) to guide the construction of multiple acceptable payloads. OPAT saves the user time while at the same time maximizes the efficiency of shipments for the given drum population. The tool provides the user with the flexibility to tune critical factors that guide OPAT's operation based on real-time feedback concerning the results of the execution. This feedback complements the user's external knowledge of the drum population (such as location of drums, known challenges, internal shipment goals). This work demonstrates how software can be utilized to complement the unique domain knowledge of the users. The mixed-initiative approach combines the insight and intuition of the human expert with the proficiency of automated computational algorithms. The result is the ability to thoroughly and efficiently explore the search space of possible solutions and derive the best waste management decision. (authors)« less

Development of a shuttle recovery Commercial Materials Processing in Space (CMPS) program

NASA Technical Reports Server (NTRS)

1989-01-01

The work performed has covered the following tasks: update commercial users requirements; assess availability of carriers and facilities; shuttle availability assessment; development of optimum accommodations plan; and payload documentation requirements assessment. The results from the first four tasks are presented. To update commercial user requirements, contacts were made with the JEA and CCDS partners to obtain copies of their most recent official flight requests. From these requests the commercial partners' short and long range plans for flight dates, flight frequency, experiment hardware and carriers was determined. A 34 by 44 inch chart was completed to give a snapshot view of the progress of commercialization in space. Further, an assessment was made of the availability of carriers and facilities. Both existing carriers and those under development were identified for use by the commercial partners. A data base was compiled to show the capabilities of the carriers. A shuttle availability assessment was performed using the primary and secondary shuttle manifests released by NASA. Analysis of the manifest produced a flight-by-flight list of flight opportunities available to commercial users. Using inputs from the first three tasks, an Optimum Accommodations Plan was developed. The Accommodation Plan shows the commercial users manifested by flight, the experiment flown, the carrier used and complete list of commercial users that could not be manifested in each calendar year.

KSC-99pp1369

NASA Image and Video Library

1999-11-29

KENNEDY SPACE CENTER, FLA. -- Viewed end to end, the interior of orbiter Endeavour's payload bay can be seen with its cargo (center and right) in place, before the close of its payload bay doors. The Ku-band antenna (lower right) is now in its closed position inside the payload bay. Endeavour is expected to roll over to the Vehicle Assembly Building in three days for mating to the external tank and solid rocket boosters in high bay 1. Space Shuttle Endeavour is targeted for launch on mission STS-99 Jan. 13, 2000 at 1:11 p.m. EST. STS-99 is the Shuttle Radar Topography Mission, an international project spearheaded by the National Imagery and Mapping Agency and NASA, with participation of the German Aerospace Center DLR. The SRTM consists of a specially modified radar system that will gather data for the most accurate and complete topographic map of the Earth's surface that has ever been assembled. SRTM will make use of radar interferometry, wherein two radar images are taken from slightly different locations. Differences between these images allow for the calculation of surface elevation, or change. The SRTM hardware will consist of one radar antenna in the shuttle payload bay and a second radar antenna attached to the end of a mast extended 60 meters (195 feet) out from the shuttle

STS-65 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1994-01-01

The STS-65 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixty-third flight of the Space Shuttle Program and the seventeenth flight of the Orbiter vehicle Columbia (OV-102). In addition to the Orbits the flight vehicle consisted of an ET that was designated ET-64; three SSME's that were designated as serial numbers 2019, 2030, and 2017 in positions 1, 2, and 3, respectively; and two SRB's that were designated Bl-066. The RSRM's that were installed in each SRB were designated as 360P039A for the left SRB, and 360W039 for the right SRB. The primary objective of this flight was to complete the operation of the second International Microgravity Laboratory (IML-2). The secondary objectives of this flight were to complete the operations of the Commercial Protein Crystal Growth (CPCG), Orbital Acceleration Research Experiment (OARE), and the Shuttle Amateur Radio Experiment (SAREX) II payloads. Additional secondary objectives were to meet the requirements of the Air Force Maui Optical Site (AMOS) and the Military Application Ship Tracks (MAST) payloads, which were manifested as payloads of opportunity.

Public Management Information Systems: Theory and Prescription.

ERIC Educational Resources Information Center

Bozeman, Barry; Bretschneider, Stuart

1986-01-01

The existing theoretical framework for research in management information systems (MIS) is criticized for its lack of attention to the external environment of organizations, and a new framework is developed which better accommodates MIS in public organizations: public management information systems. Four models of publicness that reflect external…

Accommodation: The role of the external muscles of the eye: A consideration of refractive errors in relation to extraocular malfunction.

PubMed

Hargrave, B K

2014-11-01

Speculation as to optical malfunction has led to dissatisfaction with the theory that the lens is the sole agent in accommodation and to the suggestion that other parts of the eye are also conjointly involved. Around half-a-century ago, Robert Brooks Simpkins suggested that the mechanical features of the human eye were precisely such as to allow for a lengthening of the globe when the eye accommodated. Simpkins was not an optical man but his theory is both imaginative and comprehensive and deserves consideration. It is submitted here that accommodation is in fact a twofold process, and that although involving the lens, is achieved primarily by means of a give - and - take interplay between adducting and abducting external muscles, whereby an elongation of the eyeball is brought about by a stretching of the delicate elastic fibres immediately behind the cornea. The three muscles responsible for convergence (superior, internal and inferior recti) all pull from in front backwards, while of the three abductors (external rectus and the two obliques) the obliques pull from behind forwards, allowing for an easy elongation as the eye turns inwards and a return to its original length as the abducting muscles regain their former tension, returning the eye to distance vision. In refractive errors, the altered length of the eyeball disturbs the harmonious give - and - take relationship between adductors and abductors. Such stresses are likely to be perpetuated and the error exacerbated. Speculation is not directed towards a search for a possible cause of the muscular imbalance, since none is suspected. Muscles not used rapidly lose tone, as evidenced after removal of a limb from plaster. Early attention to the need for restorative exercise is essential and results usually impressive. If flexibility of the external muscles of the eyes is essential for continuing good sight, presbyopia can be avoided and with it the supposed necessity of glasses in middle life. Early attention to the need for muscle flexibility and for frequent change of focus, it is believed, leads to ocular wellbeing and obviates the reliance on glasses. It is a consideration yet to be widely entertained. The alarming increase in myopia has led to considerable investigation in recent years as to increase in the length of the eyeball. Thus far however there is little agreement regarding causes. Copyright © 2014 Elsevier Ltd. All rights reserved.

Misfit of Three Different Implant-Abutment Connections Before and After Cyclic Load Application: An In Vitro Study.

PubMed

Gehrke, Sergio Alexandre; Delgado-Ruiz, Rafael Arcesio; Prados Frutos, Juan Carlos; Prados-Privado, María; Dedavid, Berenice Anina; Granero Marín, Jose Manuel; Calvo Guirado, José Luiz

This study aimed to evaluate the misfit of three different implant-abutment connections before and after cycling load. One hundred twenty dental implants and correspondent prefabricated titanium abutments were used. Three different implant-abutment connections were evaluated: Morse taper (MT group), external hexagon (EH group), and internal hexagon (IH group). Forty implants and 40 abutments were used per group. The parameters for the mechanical evaluation were set as: 360,000 cycles, load of 150 N, and frequency of 4 Hz. Samples were sectioned in their longitudinal and transversal axes, and the misfit of the implant-abutment connection was evaluated by scanning electron microscopy analysis. One-way analyses of variance, Tukey post hoc analyses (α = .05), and t test (P < .05) were used to determine differences between groups. At the longitudinal direction, all the groups showed the presence of microgaps before cycling load; after cycling load, microgaps were reduced in all groups (P > .05). Transversally, only the MT group showed full fitting after cycling load compared with the other groups (EH and IH) (P < .0001). The application of cycling load produces an accommodation of the implant-abutment connection in internal, external, and Morse taper connections. In the longitudinal direction, the accommodation decreases and/or eliminates the gap observed initially (before load). In the horizontal direction, Morse cone implant-abutment connections experience a complete accommodation with the elimination of the gap.

Potential role for microfluctuations as a temporal directional cue to accommodation

PubMed Central

Metlapally, Sangeetha; Tong, Jianliang L.; Tahir, Humza J.; Schor, Clifton M.

2016-01-01

The goal was to revisit an important, yet unproven notion that accommodative microfluctuations facilitate the determination of direction (sign) of abrupt focus changes in the stimulus to accommodation. We contaminated the potential temporal cues from natural accommodative microfluctuations by presenting uncorrelated external (screen) temporal defocus noise that combined with the retinal image effects of natural microfluctuations. A polychromatic Maltese spoke pattern thus either modulated defocus at a combination of two temporal frequencies (on-screen noise condition) or was static (control condition). The on-screen conditions were combined with step changes in optical vergence that were randomized in direction and magnitude. Five subjects monocularly viewed stimuli through a Badal optical system in a Maxwellian view. An artificial 4-mm aperture was imaged at the entrance pupil of the eye. Wavefront aberrations were measured dynamically at 50 Hz using a custom Shack–Hartmann aberrometer. Dynamic changes in the Zernike defocus term with step changes in optical vergence were analyzed. We calculated the percentage of correct directional responses for 1, 2, and 3 D accommodative and disaccommodative step stimuli using preset criteria for latency, velocity, and persistence of the response. The on-screen noise condition reduced the percent-correct responses compared to the static stimulus, suggesting that this manipulation affected the detectability of the sign of the accommodative stimulus. Several possible reasons and implications of this result are discussed. PMID:27120075

Versatile fluid-mixing device for cell and tissue microgravity research applications.

PubMed

Wilfinger, W W; Baker, C S; Kunze, E L; Phillips, A T; Hammerstedt, R H

1996-01-01

Microgravity life-science research requires hardware that can be easily adapted to a variety of experimental designs and working environments. The Biomodule is a patented, computer-controlled fluid-mixing device that can accommodate these diverse requirements. A typical shuttle payload contains eight Biomodules with a total of 64 samples, a sealed containment vessel, and a NASA refrigeration-incubation module. Each Biomodule contains eight gas-permeable Silastic T tubes that are partitioned into three fluid-filled compartments. The fluids can be mixed at any user-specified time. Multiple investigators and complex experimental designs can be easily accommodated with the hardware. During flight, the Biomodules are sealed in a vessel that provides two levels of containment (liquids and gas) and a stable, investigator-controlled experimental environment that includes regulated temperature, internal pressure, humidity, and gas composition. A cell microencapsulation methodology has also been developed to streamline launch-site sample manipulation and accelerate postflight analysis through the use of fluorescent-activated cell sorting. The Biomodule flight hardware and analytical cell encapsulation methodology are ideally suited for temporal, qualitative, or quantitative life-science investigations.

BaR-SPOrt: the instrument to be accommodated at Dome C

NASA Astrophysics Data System (ADS)

Zannoni, M.; Carretti, E.; Cortiglioni, S.; Macculi, C.; Ramponi, M.; Sbarra, C.; Ventura, G.; Monari, J.; Poloni, M.; Poppi, S.; Natale, V.; Nesti, R.; Baralis, M.; Peverini, O.; Tascone, R.; Virone, G.; Boscaleri, A.; Boella, G.; Sironi, G.; Gervasi, M.; de Bernardis, P.; Masi, S.; de Petris, M.

The BaR-SPOrt (Balloon-Borne Radiometers for Sky Polarization Observations) experiment, a program of the Agenzia Spaziale Italiana (ASI) co-funded by PNRA (Progetto Nazionale di Ricerca in Antartide) was originally designed as a payload for long duration balloons flights. The changing scenario, both scientific and strategic, has led us to propose it for the starting winter campaign of at the Concordia Base. Here the instrument and the features making it suitable to operate at Dome-C are described. After the initial setup, BaR-SPOrt should not require any kind of routine intervention by a dedicated base staff. The experiment will just need electrical power (less than 2 kW) and a suitable accommodation on the field. It can be fully monitored and controlled, including the data acquisition, through its own telemetry/telecommand link using IRIDIUM modems. Both the receiver and the critical electronics are housed inside a temperature-controlled vacuum chamber, providing the properly stabilized environment. The cold part of the radiometer employs a closed loop mechanical cryo-cooler that provides temperatures <70 ±0.1 K with low power consumption (<200 W).

KSC-06pd2287

NASA Image and Video Library

2006-10-12

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is transferred from the checkout cell for attaching to its twin solid rocket boosters on the mobile launch platform in highbay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. STS-116 will be mission no. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

Progress toward Modular UAS for Geoscience Applications

NASA Astrophysics Data System (ADS)

Dahlgren, R. P.; Clark, M. A.; Comstock, R. J.; Fladeland, M.; Gascot, H., III; Haig, T. H.; Lam, S. J.; Mazhari, A. A.; Palomares, R. R.; Pinsker, E. A.; Prathipati, R. T.; Sagaga, J.; Thurling, J. S.; Travers, S. V.

2017-12-01

Small Unmanned Aerial Systems (UAS) have become accepted tools for geoscience, ecology, agriculture, disaster response, land management, and industry. A variety of consumer UAS options exist as science and engineering payload platforms, but their incompatibilities with one another contribute to high operational costs compared with those of piloted aircraft. This research explores the concept of modular UAS, demonstrating airframes that can be reconfigured in the field for experimental optimization, to enable multi-mission support, facilitate rapid repair, or respond to changing field conditions. Modular UAS is revolutionary in allowing aircraft to be optimized around the payload, reversing the conventional wisdom of designing the payload to accommodate an unmodifiable aircraft. UAS that are reconfigurable like Legos™ are ideal for airborne science service providers, system integrators, instrument designers and end users to fulfill a wide range of geoscience experiments. Modular UAS facilitate the adoption of open-source software and rapid prototyping technology where design reuse is important in the context of a highly regulated industry like aerospace. The industry is now at a stage where consolidation, acquisition, and attrition will reduce the number of small manufacturers, with a reduction of innovation and motivation to reduce costs. Modularity leads to interface specifications, which can evolve into de facto or formal standards which contain minimum (but sufficient) details such that multiple vendors can then design to those standards and demonstrate interoperability. At that stage, vendor coopetition leads to robust interface standards, interoperability standards and multi-source agreements which in turn drive costs down significantly.

International Cooperation in the Field of International Space Station Payload Safety: Overcoming Differences and Working for Future

NASA Astrophysics Data System (ADS)

Nakamura, Yasuhiro; Ozawa, Masayuki; Takeyasu, Yoshioka; Griffith, Gerald; Goto, Katsuhito; Mitsui, Masami

2010-09-01

The importance of international cooperation among the International Space Station(ISS) Program participants is ever increasing as the ISS nears assembly complete. In the field of payload safety assurance, NASA and JAXA have enhanced their cooperation level. The authors describe the evolution of cooperation between the two agencies and the challenges encountered and overcame. NASA and JAXA have been working toward development of a NASA Payload Safety Review Panel(PSRP) franchise panel at JAXA for several years. When the JAXA Safety Review Panel(SRP) becomes a fully franchised panel of the NASA PSRP, the JAXA SRP will have the authority review and approve all JAXA ISS payloads operated on USOS and JEM, although NASA and JAXA joint reviews may be conducted as necessary. A NASA PSRP franchised panel at JAXA will streamline the conventional review process. Japanese payload organizations will not have to go through both JAXA and NASA payload safety reviews, while NASA will be relieved of a certain amount of review activities. The persistent efforts have recently born fruit. For the past two years, NASA and JAXA have increased emphasis on efforts to develop a NASA PSRP Franchised Panel at JAXA with concrete results. In 2009, NASA and JAXA signed Charter and Joint Development Plan. At the end of 2009, NASA PSRP transferred some review responsibility to the JAXA SRP under the franchising charter. Although JAXA had long history of reviewing payloads by their own panel prior to NASA PSRP reviews, it took several years for JAXA to receive NASA PSRP approval for delegation of franchised review authority to JAXA. This paper discusses challenges JAXA and NAXA faced. Considerations were required in developing a franchise at JAXA for history and experiences of the JAXA SRP as well as language and cultural differences. The JAXA panel, not only had its own well-established processes and supporting organizational structures which had some differences from its NASA PSRP counterparts, but the JAXA SRP also had a practice of emphasizing pre-coordination instead of addressing issues in formal reviews, reflecting Japanese cultural influences. These points are illustrated in the paper. The authors will also discuss how NASA and JAXA overcame these issues by providing specific examples including review responsibilities of NASA and JAXA panels, panel and supporting positions, and accommodation of language differences. In conclusion, the current status and future plan for NASA PSRP franchise efforts at JAXA are described and significance of having a NASA PSRP franchise panel at JAXA will be reviewed.

Overview of the Microgravity Science Glovebox (MSG) Facility and the Research Performed in the MSG

NASA Technical Reports Server (NTRS)

Jordan, Lee

2016-01-01

The Microgravity Science Glovebox (MSG) is a rack facility aboard the International Space Station (ISS) designed for investigation handling. The MSG was built by the European Space Agency (ESA) which also provides sustaining engineering support for the facility. The MSG has been operating on the ISS since July 2002 and is currently located in the US Laboratory Module. The unique design of the facility allows it to accommodate science and technology investigations in a "workbench" type environment. The facility has an enclosed working volume that is held at a negative pressure with respect to the crew living area. This allows the facility to provide two levels of containment for small parts, particulates, fluids, and gases. This containment approach protects the crew from possible hazardous operations that take place inside the MSG work volume. Research investigations operating inside the MSG are provided a large 255 liter enclosed work space, 1000 watts of direct current power via a versatile supply interface (120, 28, plus or minus 12, and 5 volts direct current), 1000 watts of cooling capability, video and data recording and real time downlink, ground commanding capabilities, access to ISS Vacuum Exhaust and Vacuum Resource Systems, and gaseous nitrogen supply. These capabilities make the MSG one of the most utilized facilities on ISS. The MSG has been used for over 27,000 hours of scientific payload operations. MSG investigations involve research in cryogenic fluid management, fluid physics, spacecraft fire safety, materials science, combustion, plant growth, biological studies and life support technology. The MSG facility is operated by the Payloads Operations Integration Center at Marshall Space Flight Center. Payloads may also operate remotely from different telescience centers located in the United States and Europe. The Investigative Payload Integration Manager (IPIM) is the focal to assist organizations that have payloads operating in the MSG facility. NASA provides an MSG engineering unit for payload developers to verify that their hardware is operating properly before actual operation on the ISS. This poster will provide an overview of the MSG facility, a synopsis of the research that has already been accomplished in the MSG, and an overview of video and biological upgrades. The author would like to acknowledge Teledyne Brown Engineering and the entire MSG Team for their inputs into this poster.

Method and apparatus for production of subsea hydrocarbon formations

DOEpatents

Blandford, Joseph W.

1995-01-01

A system for controlling, separating, processing and exporting well fluids produced from subsea hydrocarbon formations is disclosed. The subsea well tender system includes a surface buoy supporting one or more decks above the water surface for accommodating equipment to process oil, gas and water recovered from the subsea hydrocarbon formation. The surface buoy includes a surface-piercing central flotation column connected to one or more external floatation tanks located below the water surface. The surface buoy is secured to the seabed by one or more tendons which are anchored to a foundation with piles imbedded in the seabed. The system accommodates multiple versions on the surface buoy configuration.

Opportunities for Geoscience Research Onboard Virgin Galactic's SpaceShipTwo

NASA Astrophysics Data System (ADS)

Pomerantz, W.; Beerer, I.; Stephens, K.; Griffith, J.; Persall, W.; Tizard, J.

2012-12-01

Virgin Galactic has developed a reusable spaceplane, called SpaceShipTwo (SS2), designed to make routine voyages into suborbital space. SS2 is air-launched from a jet aircraft at an altitude of 50,000 ft. before igniting its rocket motor engine. The vehicle reaches a maximum apogee as high as 110 km before gliding to a conventional runway landing. With the ability to fly multiple times per week, SS2 will be capable of providing routine access to a rarely sampled and poorly understood region of the atmosphere and ionosphere, making it a valuable platform for geoscience research. With a payload capacity up to 1300 lbs., SS2 provides access to space and the upper atmosphere for substantially larger payloads than sounding rockets and at a dramatically lower cost than orbital satellites. The main cabin provides as much as 500 cubic ft. of useable volume in a shirt-sleeve environment and payload mounting interfaces that are compatible with standard architectures, such as Middeck Lockers, Cargo Transfer Bags, and server racks. A flight test engineer will be available on board to operate payloads during flight. In the future, SS2 will also offer a variety of external payload mounting locations, enabling researchers to make frequent in situ measurements in the mesosphere (50-90 km), lower thermosphere (above 80 km), and lower ionosphere (above 60 km). SS2 may also offer optical quality windows, allowing optical investigations from main cabin payloads. Researchers will have access to their payloads until just hours before flight and within three hours post-flight. While commercial operations will begin out of Spaceport America in New Mexico, SS2 may eventually be able to launch from a variety of geographic locations. Funding to develop and fly payloads for SS2 is currently available through many NASA programs including the Flight Opportunities Program and the Game Changing Development Program. Virgin Galactic expects the SS2 research platform to enable significant progress in atmospheric chemistry and dynamics, climate science, space weather, numerical weather predictions, and many other fields of geoscience.

KSC-06pd2284

NASA Image and Video Library

2006-10-12

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, workers prepare to transfer the external tank from the checkout cell for attaching to its twin solid rocket boosters on the mobile launch platform in highbay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. STS-116 will be mission no. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2286

NASA Image and Video Library

2006-10-12

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is transferred from the checkout cell for attaching to its twin solid rocket boosters on the mobile launch platform in highbay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. STS-116 will be mission no. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2283

NASA Image and Video Library

2006-10-12

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, workers prepare to transfer the external tank from the checkout cell for attaching to its twin solid rocket boosters on the mobile launch platform in highbay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. STS-116 will be mission no. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2288

NASA Image and Video Library

2006-10-12

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is transferred from the checkout cell for attaching to its twin solid rocket boosters on the mobile launch platform in highbay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. STS-116 will be mission no. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2285

NASA Image and Video Library

2006-10-12

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, workers prepare to transfer the external tank from the checkout cell for attaching to its twin solid rocket boosters on the mobile launch platform in highbay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. STS-116 will be mission no. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

The STS-96 crew takes part in a Crew Equipment Interface Test at KSC

NASA Technical Reports Server (NTRS)

1999-01-01

In the Orbiter Processing Facility bay 1, STS-96 Mission Specialists Daniel Barry (M.D., Ph.D.), Valery Ivanovich Tokarev and Tamara E. Jernigan (Ph.D.) look into the payload bay of the orbiter Discovery. The STS-96 crew is at KSC for a Crew Equipment Interface Test. Other crew members participating are Commander Kent V. Rominger, Pilot Rick Douglas Husband, and Mission Specialists Ellen Ochoa (Ph.D.) and Julie Payette, with the Canadian Space Agency. The primary payload of STS-96 is the SPACEHAB Double Module. In addition, the Space Shuttle will carry unpressurized cargo such as the external Russian cargo crane known as STRELA; the Spacehab Oceaneering Space System Box (SHOSS), which is a logistics items carrier; and an ORU Transfer Device (OTD), a U.S.-built crane that will be stowed on the station for use during future ISS assembly missions. These cargo items will be stowed on the International Cargo Carrier, fitted inside the payload bay behind the SPACEHAB module. STS-96 is targeted for launch on May 24 from Launch Pad 39B.

Thermal Design and Analysis of an ISS Science Payload - SAGE III on ISS

NASA Technical Reports Server (NTRS)

Liles, Kaitlin, A. K.; Amundsen, Ruth M.; Davis, Warren T.; Carrillo, Laurie Y.

2017-01-01

The Stratospheric Aerosol and Gas Experiment III (SAGE III) instrument is the fifth in a series of instruments developed for monitoring aerosols and gaseous constituents in the stratosphere and troposphere. SAGE III will be launched in the SpaceX Dragon vehicle in 2017 and mounted to an external stowage platform on the International Space Station (ISS) to begin its three-year mission. The SAGE III thermal team at NASA Langley Research Center (LaRC) worked with ISS thermal engineers to ensure that SAGE III, as an ISS payload, would meet requirements specific to ISS and the Dragon vehicle. This document presents an overview of the SAGE III thermal design and analysis efforts, focusing on aspects that are relevant for future ISS payload developers. This includes development of detailed and reduced Thermal Desktop (TD) models integrated with the ISS and launch vehicle models, definition of analysis cases necessary to verify thermal requirements considering all mission phases from launch through installation and operation on-orbit, and challenges associated with thermal hardware selection including heaters, multi-layer insulation (MLI) blankets, and thermal tapes.

KSC-07pd2035

NASA Image and Video Library

2007-07-19

KENNEDY SPACE CENTER, FLA. -- The STS-118 crew breaks for a photo with the Endeavour team and key personnel during payload familiarization. Kneeling in front are Eve Stavros, Boeing flow manager for the mission; Dave Brashinger, with NASA; Paul Boehm, EVA trainer; S. Adam Niev, with NASA Electrical; Louise Kleba, with the KSC payload VITT office; Lance Rogers, a NASA summer co-op; and Jackie Kagey, an EVA trainer. Standing in the back, from left, are photographer Cory Huston; Darren Welsh, EVA trainer; Jack Keifenheim, with NASA Engineering; Mission Specialist Barbara R. Morgan, Pilot Charlie Hobaugh, Mission Specialist Alvin Drew, Commander Scott Kelly, and Mission Specialists Dave Williams and Tracy Caldwell, Lisa Alonso, a NASA summer intern; and (far right) Mission Specialist Rick Mastracchio. Morgan joined NASA's Teacher in Space program in 1985 and was selected as an astronaut in 1998. Williams represents the Canadian Space Agency. The 22nd shuttle flight to the International Space Station, the STS-118 mission will continue space station construction by delivering a third starboard truss segment, S5, and other payloads such as the SPACEHAB module and the external stowage platform 3. Photo credit: NASA/George Shelton

OPALS: Mission System Operations Architecture for an Optical Communications Demonstration on the ISS

NASA Technical Reports Server (NTRS)

Abrahamson, Matthew J.; Sindiy, Oleg V.; Oaida, Bogdan V.; Fregoso, Santos; Bowles-Martinez, Jessica N.; Kokorowski, Michael; Wilkerson, Marcus W.; Konyha, Alexander L.

2014-01-01

In spring 2014, the Optical PAyload for Lasercomm Science (OPALS) will launch to the International Space Station (ISS) to demonstrate space-to-ground optical communications. During a 90-day baseline mission, OPALS will downlink high quality, short duration videos to the Optical Communications Telescope Laboratory (OCTL) in Wrightwood, California. To achieve mission success, interfaces to the ISS payload operations infrastructure are established. For OPALS, the interfaces facilitate activity planning, hazardous laser operations, commanding, and telemetry transmission. In addition, internal processes such as pointing prediction and data processing satisfy the technical requirements of the mission. The OPALS operations team participates in Operational Readiness Tests (ORTs) with external partners to exercise coordination processes and train for the overall mission. The tests have provided valuable insight into operational considerations on the ISS.

KSC-07pd0230

NASA Image and Video Library

2007-02-02

KENNEDY SPACE CENTER, FLA. -- In the Space Station Processing Facility, members of the STS-118 crew learn important information from technicians about the control moment gyro (CMG) in front of them that is part of the payload on their mission. Second from left is Mission Specialist Tracy Caldwell; at right are Mission Specialists Richard Mastracchio (pointing) and Clayton Anderson, who will be flying on STS-118 to join the Expedition 15 crew as flight engineer on the International Space Station. The CMG will replace a faulty one on the International Space Station. The payload also includes the SPACEHAB single cargo module, the third starboard truss segment (ITS S5) and the external stowage platform 3 (ESP3). STS-118 is targeted to launch June 28 from Launch Pad 39A. Photo credit: NASA/Kim Shiflett

STS-55 Columbia, OV-102, mated to ET and SRBs, heads to KSC LC during rollout

NASA Technical Reports Server (NTRS)

1993-01-01

German payload processing team members watch as STS-55 Columbia, Orbiter Vehicle (OV) 102, mated to the external tank (ET) and solid rocket boosters (SRBs), heads to Kennedy Space Center (KSC) Launch Complex (LC) Pad 39A. OV-102, the ET, and SRBs ride atop the mobile launch platform and the crawler transporter. A spectator in the foreground is wearing an STS-55 t-shirt. The German-managed Spacelab Deutsche 2 (SL-D2) and the Unique Support Structure (USS) are already integrated in OV-102's payload bay as it makes its way to LC Pad 39A. OV-102 is targeted for liftoff on Space Shuttle Mission STS-55 in late February. View provided by KSC with alternate KSC number KSC-93PC-283.

NICER ground verification: as-built timing, spectroscopy, and throughout performance of NASA's next X-raytiming astrophysics mission

NASA Astrophysics Data System (ADS)

Gendreau, Keith; Arzoumanian, Zaven; NICER Team

2017-01-01

The Neutron star Interior Composition Explorer (NICER) Mission of Opportunity will fly to the International Space Station (ISS) in 2017 aboard a SpaceX resupply vehicle. Once installed as an external attached payload, NICER will provide an unprecedented soft X-ray timing spectroscopy capability for neutron stars and other phenomena. In June 2016, the NICER payload was delivered from NASA Goddard Space Flight Center to Cape Canaveral to await launch processing. We present measurements made as part of NICER's preship testing to verify performance of its X-ray Timing Instrument and associated subsystems; these measurements demonstrate that NICER meets or surpasses its design requirements in the areas of photon time-tagging resolution, energy resolution, effective collecting area, and high-rate throughput.

STS-59 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1994-01-01

The STS-59 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixty-second flight of the Space Shuttle Program and sixth flight of the Orbiter vehicle Endeavor (OV-105). In addition to the Orbiter, the flight vehicle consisted of an ET designated as ET-63; three SSME's which were designated as serial numbers 2028, 2033, and 2018 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-065. The RSRM's that were installed in each SRB were designated as 360W037A (welterweight) for the left SRB, and 360H037B (heavyweight) for the right SRB. This STS-59 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement as documented in NSTS 07700, Volume 8, Appendix E. That document requires that each major organizational element supporting the Program report the results of its hardware evaluation and mission performance plus identify all related in-flight anomalies. The primary objective of the STS-59 mission was to successfully perform the operations of the Space Radar Laboratory-1 (SRL-1). The secondary objectives of this flight were to perform the operations of the Space Tissue Loss-A (STL-A) and STL-B payloads, the Visual Function Tester-4 (VFT-4) payload, the Shuttle Amateur Radio Experiment-2 (SAREX-2) experiment, the Consortium for Materials Development in Space Complex Autonomous Payload-4 (CONCAP-4), and the three Get-Away Special (GAS) payloads.

STS-80 Space Shuttle Mission Report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1997-01-01

The STS-80 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Reusable Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the eightieth flight of the Space Shuttle Program, the fifty-fifth flight since the return-to-flight, and the twenty-first flight of the Orbiter Columbia (OV-102).

Space Shuttle Solid Rocket Booster Lightweight Recovery System

NASA Technical Reports Server (NTRS)

Wolf, Dean; Runkle, Roy E.

1995-01-01

The cancellation of the Advanced Solid Rocket Booster Project and the earth-to-orbit payload requirements for the Space Station dictated that the National Aeronautics and Space Administration (NASA) look at performance enhancements from all Space Transportation System (STS) elements (Orbiter Project, Space Shuttle Main Engine Project, External Tank Project, Solid Rocket Motor Project, & Solid Rocket Booster Project). The manifest for launching of Space Station components indicated that an additional 12-13000 pound lift capability was required on 10 missions and 15-20,000 pound additional lift capability is required on two missions. Trade studies conducted by all STS elements indicate that by deleting the parachute Recovery System (and associated hardware) from the Solid Rocket Boosters (SRBS) and going to a lightweight External Tank (ET) the 20,000 pound additional lift capability can be realized for the two missions. The deletion of the parachute Recovery System means the loss of four SRBs and this option is two expensive (loss of reusable hardware) to be used on the other 10 Space Station missions. Accordingly, each STS element looked at potential methods of weight savings, increased performance, etc. As the SRB and ET projects are non-propulsive (i.e. does not have launch thrust elements) their only contribution to overall payload enhancement can be achieved by the saving of weight while maintaining adequate safety factors and margins. The enhancement factor for the SRB project is 1:10. That is for each 10 pounds saved on the two SRBS; approximately 1 additional pound of payload in the orbiter bay can be placed into orbit. The SRB project decided early that the SRB recovery system was a prime candidate for weight reduction as it was designed in the early 1970s and weight optimization had never been a primary criteria.

The FCF Combustion Integrated Rack: Microgravity Combustion Science Onboard the International Space Station

NASA Technical Reports Server (NTRS)

OMalley, Terence F.; Weiland, Karen J.

2002-01-01

The Combustion Integrated Rack (CIR) is one of three facility payload racks being developed for the International Space Station (ISS) Fluids and Combustion Facility (FCF). Most microgravity combustion experiments will be performed onboard the Space Station in the Combustion Integrated Rack. Experiment-specific equipment will be installed on orbit in the CIR to customize it to perform many different scientific experiments during the ten or more years that it will operate on orbit. This paper provides an overview of the CIR, including a description of its preliminary design and planned accommodations for microgravity combustion science experiments, and descriptions of the combustion science experiments currently planned for the CIR.

Raman Laser Spectrometer (RLS) on-board data processing and compression

NASA Astrophysics Data System (ADS)

Diaz, C.; Lopez, G.; Hermosilla, I.; Catalá, A.; Rodriguez, J. A.; Perez, C.; Diaz, E.

2013-09-01

The Raman Laser Spectrometer (RLS) is one of the Pasteur Payload instruments, within the ESA's Aurora Exploration Programme, ExoMars mission. Particularly, the RLS scientific objectives are as follows: identify organic compound and search for life; identify the mineral products and indicators of biologic activities; characterize mineral phases produced by water-related processes; characterize igneous minerals and their alteration products; characterise water/geochemical environment as a function of depth in the shallow subsurface. The straightforward approach of operating the instrument would result in a vast amount of spectrum images. A flexible on-board data processing concept has been designed to accommodate scientific return to the sample nature and data downlink bandwidth.

Evolving Dispensers: How to Take Benefit from Heritage

NASA Astrophysics Data System (ADS)

Veilleraud, Fredderic; Larcher, Virginie

2014-06-01

Thanks to its large know-how in the field of accommodation and launch of multiple payloads on civil and military programs, Airbus Defence and Space has developed since 1996 dispensers for various constellations on various launchers.Taking into account time and cost constraints of this market, Airbus D&S early based its solutions on adaptation of previous products enabling to limit engineering and manufacturing effort. Thus, Airbus D&S has developed a family of prequalified technological elements allowing adaptation of design to requirement while limiting drastically qualification need.Doing that, Airbus Defence and Space has also gathered a strong experience on various primary concepts that could be easily tuned and customized to new customer needs.

KSC-03PD-1776

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. The Italian-built module, U.S. Node 2, for the International Space Station is offloaded from a Beluga at the Shuttle Landing Facility. The second of three Station connecting modules, Node 2 attaches to the end of the U.S. Lab and provides attach locations for the Japanese laboratory, European laboratory, the Centrifuge Accommodation Module and, later, Multipurpose Logistics Modules. It will provide the primary docking location for the Shuttle when a pressurized mating adapter is attached to Node 2. Installation of the module will complete the U.S. Core of the ISS. Node 2 is the designated payload for mission STS-120. No orbiter or launch date has been determined yet.

STS-64 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1995-01-01

The STS-64 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixty-fourth flight of the Space Shuttle Program and the nineteenth flight of the Orbiter vehicle Discovery (OV-103). In addition to the Orbiter, the flight vehicle consisted of an ET that was designated ET-66; three SSMEs that were designated as serial numbers 2031, 2109, and 2029 in positions 1, 2, and 3, respectively; and two SRB's that were designated Bl-068. The RSRM's that were installed in each SRB were designated as 360L041 A for the left SRB, and 360L041 B for the right SRB. The primary objective of this flight was to successfully perform the planned operations of the Lidar In-Space Technology Experiment (LITE), and to deploy the Shuttle Pointed Autonomous Research Tool for Astronomy (SPARTAN) -201 payload. The secondary objectives were to perform the planned activities of the Robot Operated Materials Processing System (ROMPS), the Shuttle Amateur Radio Experiment - 2 (SAREX-2), the Solid Surface Combustion Experiment (SSCE), the Biological Research in Canisters (BRIC) experiment, the Radiation Monitoring Equipment-3 (RME-3) payload, the Military Application of Ship Tracks (MAST) experiment, and the Air Force Maui Optical Site Calibration Test (AMOS) payload.

STS-47 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1992-01-01

The STS-47 Space Shuttle Program Mission Report provides a summary of the Orbiter, External Tank (ET), Solid Rocket Booster/Redesigned Solid Rocket Motor (SRB/RSRM), and the Space Shuttle main engine (SSME) subsystem performance during the fiftieth Space Shuttle Program flight and the second flight of the Orbiter Vehicle Endeavour (OV-105). In addition to the Endeavour vehicle, the flight vehicle consisted of the following: an ET which was designated ET-45 (LWT-38); three SSME's which were serial numbers 2026, 2022, and 2029 and were located in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-053. The lightweight/redesigned RSRM that was installed in the left SRB was designated 360L026A, and the RSRM that was installed in the right SRB was 360W026B. The primary objective of the STS-47 flight was to successfully perform the planned operations of the Spacelab-J (SL-J) payload (containing 43 experiments--of which 34 were provided by the Japanese National Space Development Agency (NASDA)). The secondary objectives of this flight were to perform the operations of the Israeli Space Agency Investigation About Hornets (ISAIAH) payload, the Solid Surface Combustion Experiment (SSCE), the Shuttle Amateur Radio Experiment-2 (SAREX-2), and the Get-Away Special (GAS) payloads. The Ultraviolet Plume Instrument (UVPI) was flown as a payload of opportunity.

A Vibration Isolation System for Use in a Large Thermal Vacuum Test Facility

NASA Technical Reports Server (NTRS)

Hershfeld, Donald; VanCampen, Julie

2002-01-01

A thermal vacuum payload platform that is isolated from background vibration is required to support the development of future instruments for Hubble Space Telescope (HST) and the Next Generation Space Telescope (NGST) at the Goddard Space Flight Center (GSFC). Because of the size and weight of the thermal/vacuum facility in which the instruments are tested, it is not practical to isolate the entire facility externally. Therefore, a vibration isolation system has been designed and fabricated to be installed inside the chamber. The isolation system provides a payload interface of 3.05 m (10 feet) in diameter and is capable of supporting a maximum payload weight of 4536 kg (10,000 Lbs). A counterweight system has been included to insure stability of payloads having high centers of gravity. The vibration isolation system poses a potential problem in that leakage into the chamber could compromise the ability to maintain vacuum. Strict specifications were imposed on the isolation system design to minimize leakage. Vibration measurements, obtained inside the chamber, prior to installing the vibration isolation system, indicated levels in all axes of approximately 1 milli-g at about 20 Hz. The vibration isolation system was designed to provide a minimum attenuation of 40 dB to these levels. This paper describes the design and testing of this unique vibration isolation system. Problems with leakage and corrective methods are presented. Isolation performance results are also presented.

KSC-98pc639

NASA Image and Video Library

1998-05-26

The Alpha Magnetic Spectrometer (AMS) experiment and four Get Away Special (GAS) payload canisters are secure in Discovery's payload bay shortly before the payload bay doors are closed for the flight of STS-91 at Launch Pad 39A. Launch is planned for June 2 with a window opening around 6:10 p.m. EDT. The AMS experiment is the first of a new generation of space-based experiments which will use particles, instead of light, to study the Universe and will search for both antimatter and "dark matter," as well as measure normal matter cosmic and gamma rays. The GAS Program, initiated to provide extremely low-cost access to space, is managed by the Shuttle Small Payloads Project at NASA's Goddard Space Flight Center. Eight GAS experiments will be conducted on STS-91. The mission will also feature the ninth Shuttle docking with the Russian Space Station Mir, the first Mir docking for Discovery, the conclusion of Phase I of the joint U.S.-Russian International Space Station Program, and the first flight of the new Space Shuttle super lightweight external tank. The STS-91 flight crew includes Commander Charles Precourt; Pilot Dominic Gorie; and Mission Specialists Wendy B. Lawrence; Franklin Chang-Diaz, Ph.D.; Janet Kavandi, Ph.D.; and Valery Ryumin, with the Russian Space Agency. Andrew Thomas, Ph.D., will be returning to Earth with the crew after living more than four months aboard Mir

STS-47 Space Shuttle mission report

NASA Astrophysics Data System (ADS)

Fricke, Robert W., Jr.

1992-10-01

The STS-47 Space Shuttle Program Mission Report provides a summary of the Orbiter, External Tank (ET), Solid Rocket Booster/Redesigned Solid Rocket Motor (SRB/RSRM), and the Space Shuttle main engine (SSME) subsystem performance during the fiftieth Space Shuttle Program flight and the second flight of the Orbiter Vehicle Endeavour (OV-105). In addition to the Endeavour vehicle, the flight vehicle consisted of the following: an ET which was designated ET-45 (LWT-38); three SSME's which were serial numbers 2026, 2022, and 2029 and were located in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-053. The lightweight/redesigned RSRM that was installed in the left SRB was designated 360L026A, and the RSRM that was installed in the right SRB was 360W026B. The primary objective of the STS-47 flight was to successfully perform the planned operations of the Spacelab-J (SL-J) payload (containing 43 experiments--of which 34 were provided by the Japanese National Space Development Agency (NASDA)). The secondary objectives of this flight were to perform the operations of the Israeli Space Agency Investigation About Hornets (ISAIAH) payload, the Solid Surface Combustion Experiment (SSCE), the Shuttle Amateur Radio Experiment-2 (SAREX-2), and the Get-Away Special (GAS) payloads. The Ultraviolet Plume Instrument (UVPI) was flown as a payload of opportunity.

Neck/shoulder discomfort due to visually demanding experimental near work is influenced by previous neck pain, task duration, astigmatism, internal eye discomfort and accommodation

PubMed Central

Forsman, Mikael; Richter, Hans O.

2017-01-01

Visually demanding near work can cause eye discomfort, and eye and neck/shoulder discomfort during, e.g., computer work are associated. To investigate direct effects of experimental near work on eye and neck/shoulder discomfort, 33 individuals with chronic neck pain and 33 healthy control subjects performed a visual task four times using four different trial lenses (referred to as four different viewing conditions), and they rated eye and neck/shoulder discomfort at baseline and after each task. Since symptoms of eye discomfort may differ depending on the underlying cause, two categories were used; internal eye discomfort, such as ache and strain, that may be caused by accommodative or vergence stress; and external eye discomfort, such as burning and smarting, that may be caused by dry-eye disorders. The cumulative performance time (reflected in the temporal order of the tasks), astigmatism, accommodation response and concurrent symptoms of internal eye discomfort all aggravated neck/shoulder discomfort, but there was no significant effect of external eye discomfort. There was also an interaction effect between the temporal order and internal eye discomfort: participants with a greater mean increase in internal eye discomfort also developed more neck/shoulder discomfort with time. Since moderate musculoskeletal symptoms are a risk factor for more severe symptoms, it is important to ensure a good visual environment in occupations involving visually demanding near work. PMID:28832612

Neck/shoulder discomfort due to visually demanding experimental near work is influenced by previous neck pain, task duration, astigmatism, internal eye discomfort and accommodation.

PubMed

Zetterberg, Camilla; Forsman, Mikael; Richter, Hans O

2017-01-01

Visually demanding near work can cause eye discomfort, and eye and neck/shoulder discomfort during, e.g., computer work are associated. To investigate direct effects of experimental near work on eye and neck/shoulder discomfort, 33 individuals with chronic neck pain and 33 healthy control subjects performed a visual task four times using four different trial lenses (referred to as four different viewing conditions), and they rated eye and neck/shoulder discomfort at baseline and after each task. Since symptoms of eye discomfort may differ depending on the underlying cause, two categories were used; internal eye discomfort, such as ache and strain, that may be caused by accommodative or vergence stress; and external eye discomfort, such as burning and smarting, that may be caused by dry-eye disorders. The cumulative performance time (reflected in the temporal order of the tasks), astigmatism, accommodation response and concurrent symptoms of internal eye discomfort all aggravated neck/shoulder discomfort, but there was no significant effect of external eye discomfort. There was also an interaction effect between the temporal order and internal eye discomfort: participants with a greater mean increase in internal eye discomfort also developed more neck/shoulder discomfort with time. Since moderate musculoskeletal symptoms are a risk factor for more severe symptoms, it is important to ensure a good visual environment in occupations involving visually demanding near work.

STS-98 Onboard Photograph-U.S. Laboratory, Destiny

NASA Technical Reports Server (NTRS)

2001-01-01

In the grasp of the Shuttle's Remote Manipulator System (RMS) robot arm, the U.S. Laboratory, Destiny, is moved from its stowage position in the cargo bay of the Space Shuttle Atlantis. This photograph was taken by astronaut Thomas D. Jones during his Extravehicular Activity (EVA). The American-made Destiny module is the cornerstone for space-based research aboard the orbiting platform and the centerpiece of the International Space Station (ISS), where unprecedented science experiments will be performed in the near-zero gravity of space. Destiny will also serve as the command and control center for the ISS. The aluminum module is 8.5- meters (28-feet) long and 4.3-meters (14-feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 15 locations especially designed to support experiments. The Destiny module was built by the Boeing Company under the direction of the Marshall Space Flight Center.

STS-98 Onboard Photograph-U.S. Laboratory, Destiny

NASA Technical Reports Server (NTRS)

2001-01-01

In the grasp of the Shuttle's Remote Manipulator System (RMS) robot arm, the U.S. Laboratory, Destiny, is moved from its stowage position in the cargo bay of the Space Shuttle Atlantis. This photograph was taken by astronaut Thomas D. Jones during his Extravehicular Activity (EVA). The American-made Destiny module is the cornerstone for space-based research aboard the orbiting platform and the centerpiece of the International Space Station (ISS), where unprecedented science experiments will be performed in the near-zero gravity of space. Destiny will also serve as the command and control center for the ISS. The aluminum module is 8.5- meters (28-feet) long and 4.3-meters (14-feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 15 locations especially designed to support experiments. The Destiny module was built by the Boeing Company under the direction of the Marshall Space Flight Center.

STS-98 Onboard Photograph-U.S. Laboratory, Destiny

NASA Technical Reports Server (NTRS)

2001-01-01

With its new U.S. Laboratory, Destiny, contrasted over a blue and white Earth, the International Space Station (ISS) was photographed by one of the STS-98 crew members aboard the Space Shuttle Atlantis following separation of the Shuttle and Station. The Laboratory is shown at the lower right of the Station. The American-made Destiny module is the cornerstone for space-based research aboard the orbiting platform and the centerpiece of the ISS, where unprecedented science experiments will be performed in the near-zero gravity of space. Destiny will also serve as the command and control center for the ISS. The aluminum module is 8.5- meters (28-feet) long and 4.3-meters (14-feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 15 locations especially designed to support experiments. The Destiny module was built by the Boeing Company under the direction of the Marshall Space Flight Center.

Cosmonaut Gidzenko Near Hatch Between Unity and Destiny

NASA Technical Reports Server (NTRS)

2001-01-01

Cosmonaut Yuri P. Gidzenko, Expedition One Soyuz commander, stands near the hatch leading from the Unity node into the newly-attached Destiny laboratory aboard the International Space Station (ISS). The Node 1, or Unity, serves as a cornecting passageway to Space Station modules. The U.S.-built Unity module was launched aboard the Orbiter Endeavour (STS-88 mission) on December 4, 1998, and connected to Zarya, the Russian-built Functional Cargo Block (FGB). The U.S. Laboratory (Destiny) module is the centerpiece of the ISS, where science experiments will be performed in the near-zero gravity in space. The Destiny Module was launched aboard the Space Shuttle Orbiter Atlantis (STS-98 mission) on February 7, 2001. The aluminum module is 8.5 meters (28 feet) long and 4.3 meters (14 feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations, and payload racks will occupy 13 locations especially designed to support experiments.

EXPRESS Rack Technology for Space Station

NASA Technical Reports Server (NTRS)

Davis, Ted B.; Adams, J. Brian; Fisher, Edward M., Jr.; Prickett, Guy B.; Smith, Timothy G.

1999-01-01

The EXPRESS rack provides accommodations for standard Mid-deck Locker and ISIS drawer payloads on the International Space Station. A design overview of the basic EXPRESS rack and two derivatives, the Human Research Facility and the Habitat Holding Rack, is given in Part I. In Part II, the design of the Solid State Power Control Module (SSPCM) is reviewed. The SSPCM is a programmable and remotely controllable power switching and voltage conversion unit which distributes and protects up to 3kW of 12OVDC and 28VDC power to payloads and rack subsystem components. Part III details the development and testing of a new data storage device, the BRP EXPRESS Memory Unit (BEMU). The BEMU is a conduction-cooled device which operates on 28VDC and is based on Boeing-modified 9GB commercial disk-drive technology. In Part IV results of a preliminary design effort for a rack Passive Damping System (PDS) are reported. The PDS is intended to isolate ISPR-based experiment racks from on-orbit vibration. System performance predictions based on component developmental testing indicate that such a system can provide effective isolation at frequencies of 1 Hz and above.

International Space Station (ISS)

NASA Image and Video Library

2001-02-16

The International Space Station (ISS), with its newly attached U.S. Laboratory, Destiny, was photographed by a crew member aboard the Space Shuttle Orbiter Atlantis during a fly-around inspection after Atlantis separated from the Space Station. The Laboratory is shown in the foreground of this photograph. The American-made Destiny module is the cornerstone for space-based research aboard the orbiting platform and the centerpiece of the International Space Station (ISS), where unprecedented science experiments will be performed in the near-zero gravity of space. Destiny will also serve as the command and control center for the ISS. The aluminum module is 8.5-meters (28-feet) long and 4.3-meters (14-feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 15 locations especially designed to support experiments. The Destiny module was built by the Boeing Company under the direction of the Marshall Space Flight Center.

International Space Station (ISS)

NASA Image and Video Library

2001-02-16

With its new U.S. Laboratory, Destiny, contrasted over a blue and white Earth, the International Space Station (ISS) was photographed by one of the STS-98 crew members aboard the Space Shuttle Atlantis following separation of the Shuttle and Station. The Laboratory is shown at the lower right of the Station. The American-made Destiny module is the cornerstone for space-based research aboard the orbiting platform and the centerpiece of the ISS, where unprecedented science experiments will be performed in the near-zero gravity of space. Destiny will also serve as the command and control center for the ISS. The aluminum module is 8.5- meters (28-feet) long and 4.3-meters (14-feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 15 locations especially designed to support experiments. The Destiny module was built by the Boeing Company under the direction of the Marshall Space Flight Center.

International Space Station (ISS)

NASA Image and Video Library

2001-02-01

In the grasp of the Shuttle's Remote Manipulator System (RMS) robot arm, the U.S. Laboratory, Destiny, is moved from its stowage position in the cargo bay of the Space Shuttle Atlantis. This photograph was taken by astronaut Thomas D. Jones during his Extravehicular Activity (EVA). The American-made Destiny module is the cornerstone for space-based research aboard the orbiting platform and the centerpiece of the International Space Station (ISS), where unprecedented science experiments will be performed in the near-zero gravity of space. Destiny will also serve as the command and control center for the ISS. The aluminum module is 8.5- meters (28-feet) long and 4.3-meters (14-feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 15 locations especially designed to support experiments. The Destiny module was built by the Boeing Company under the direction of the Marshall Space Flight Center.

International Space Station (ISS)

NASA Image and Video Library

2001-02-10

Cosmonaut Yuri P. Gidzenko, Expedition One Soyuz commander, stands near the hatch leading from the Unity node into the newly-attached Destiny laboratory aboard the International Space Station (ISS). The Node 1, or Unity, serves as a cornecting passageway to Space Station modules. The U.S.-built Unity module was launched aboard the Orbiter Endeavour (STS-88 mission) on December 4, 1998, and connected to Zarya, the Russian-built Functional Cargo Block (FGB). The U.S. Laboratory (Destiny) module is the centerpiece of the ISS, where science experiments will be performed in the near-zero gravity in space. The Destiny Module was launched aboard the Space Shuttle Orbiter Atlantis (STS-98 mission) on February 7, 2001. The aluminum module is 8.5 meters (28 feet) long and 4.3 meters (14 feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations, and payload racks will occupy 13 locations especially designed to support experiments.

International Space Station (ISS)

NASA Image and Video Library

2001-02-01

In the grasp of the Shuttle's Remote Manipulator System (RMS) robot arm, the U.S. Laboratory, Destiny, is moved from its stowage position in the cargo bay of the Space Shuttle Atlantis. This photograph was taken by astronaut Thomas D. Jones during his Extravehicular Activity (EVA). The American-made Destiny module is the cornerstone for space-based research aboard the orbiting platform and the centerpiece of the International Space Station (ISS), where unprecedented science experiments will be performed in the near-zero gravity of space. Destiny will also serve as the command and control center for the ISS. The aluminum module is 8.5- meters (28-feet) long and 4.3-meters (14-feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 15 locations especially designed to support experiments. The Destiny module was built by the Boeing Company under the direction of the Marshall Space Flight Center.

Design of multi-mission chemical propulsion modules for planetary orbiters. Volume 1: Summary report

NASA Technical Reports Server (NTRS)

1975-01-01

Results are presented of a conceptual design and feasibility study of chemical propulsion stages that can serve as modular propulsion units, with little or no modification, on a variety of planetary orbit missions, including orbiters of Mercury, Saturn, and Uranus. Planetary spacecraft of existing design or currently under development, viz., spacecraft of the Pioneer and Mariner families, are assumed as payload vehicles. Thus, operating requirements of spin-stabilized and 3-axis stabilized spacecraft have to be met by the respective propulsion module designs. As launch vehicle for these missions the Shuttle orbiter and interplanetary injection stage, or Tug, plus solid-propellant kick motor was assumed. Accommodation constraints and interfaces involving the payloads and the launch vehicle are considered in the propulsion module design. The applicability and performance advantages were evaluated of the space-storable high-energy bipropellants. The incentive for using this advanced propulsion technology on planetary missions is the much greater performance potential when orbit insertion velocities in excess of 4 km/sec are required, as in the Mercury orbiter. Design analyses and performance tradeoffs regarding earth-storable versus space-storable propulsion systems are included. Cost and development schedules of multi-mission versus custom-designed propulsion modules are examined.

Quality of life and burden in caregivers of youth with obsessive-compulsive disorder presenting for intensive treatment

PubMed Central

Wu, Monica S.; Hamblin, Rebecca; Nadeau, Joshua; Simmons, Jessica; Smith, Ashley; Wilson, Meredith; Eken, Stephanie; Small, Brent; Phares, Vicky; Storch, Eric A.

2018-01-01

Background Pediatric obsessive-compulsive disorder (OCD) is associated with deleterious familial effects; caregivers are often enmeshed in the disorder and can experience considerable burden and decreased quality of life (QoL). Consequently, this study examined burden and QoL in caregivers of youth with OCD enrolled in an intensive outpatient or partial hospitalization program. Method The relationships between caregiver QoL and burden and the following variables were investigated: OCD symptom severity, functioning (youth functional impairment, general family functioning), family (family accommodation, parental relationship satisfaction, positive aspects of caregiving), and comorbid psychopathology (caregiver anxiety and depressive symptoms, youth internalizing and externalizing behaviors). Seventy-two child and caregiver dyads completed clinician- and self-rated questionnaires. Results Components of caregiver QoL correlated with caregiver-rated functional impairment, family accommodation, youth externalizing behaviors, and caregiver psychopathology. Aspects of caregiver burden correlated with child OCD symptom severity, functional impairment related to OCD, as well as caregiver and child comorbid psychopathology. Caregiver depressive symptoms predicted caregiver QoL, and caregiver depressive symptoms and child externalizing symptoms both predicted caregiver burden. Caregiver burden did not mediate the relationship between obsessive-compulsive symptom severity and caregiver QoL. Conclusion Ultimately, elucidating factors associated with increased caregiver burden and poorer QoL is pertinent for identifying at-risk families and developing targeted interventions. PMID:29031217

Method and apparatus for production of subsea hydrocarbon formations

DOEpatents

Blandford, J.W.

1995-01-17

A system for controlling, separating, processing and exporting well fluids produced from subsea hydrocarbon formations is disclosed. The subsea well tender system includes a surface buoy supporting one or more decks above the water surface for accommodating equipment to process oil, gas and water recovered from the subsea hydrocarbon formation. The surface buoy includes a surface-piercing central flotation column connected to one or more external flotation tanks located below the water surface. The surface buoy is secured to the sea bed by one or more tendons which are anchored to a foundation with piles imbedded in the sea bed. The system accommodates multiple versions on the surface buoy configuration. 20 figures.

Re-Engineering the ISS Payload Operations Control Center During Increased Utilization and Critical Onboard Events

NASA Technical Reports Server (NTRS)

Marsh, Angela L.; Dudley, Stephanie R. B.

2014-01-01

With an increase in the utilization and hours of payload operations being executed onboard the International Space Station (ISS), upgrading the NASA Marshall Space Flight Center (MSFC) Huntsville Operations Support Center (HOSC) ISS Payload Control Area (PCA) was essential to gaining efficiencies and assurance of current and future payload health and science return. PCA houses the Payload Operations Integration Center (POIC) responsible for the execution of all NASA payloads onboard the ISS. POIC Flight Controllers are responsible for the operation of voice, stowage, command, telemetry, video, power, thermal, and environmental control in support of ISS science experiments. The methodologies and execution of the PCA refurbishment were planned and performed within a four month period in order to assure uninterrupted operation of ISS payloads and minimal impacts to payload operations teams. To vacate the PCA, three additional HOSC control rooms were reconfigured to handle ISS realtime operations, Backup Control Center (BCC) to Mission Control in Houston, simulations, and testing functions. This involved coordination and cooperation from teams of ISS operations controllers, multiple engineering and design disciplines, management, and construction companies performing an array of activities simultaneously and in sync delivering a final product with no issues that impacted the schedule. For each console operator discipline, studies of Information Technology (IT) tools and equipment layouts, ergonomics, and lines of sight were performed. Infusing some of the latest IT into the project was an essential goal in ensuring future growth and success of the ISS payload science returns. Engineering evaluations led to a state of the art media wall implementation and more efficient ethernet cabling distribution providing the latest products and the best solution for the POIC. These engineering innovations led to cost savings for the project. Constraints involved in the management of the project included executing over 450 crew-hours of ISS real-time payload operations including a major onboard communications upgrade, SpaceX un-berth, a Soyuz launch, roll-out of ISS live video and interviews from the POIC, annual BCC certification and hurricane season, and ISS simulations and testing. Continuous ISS payload operations were possible during the PCA facility modifications with the reconfiguration of four control rooms and standup of two temporary control areas. Another major restriction to the project was an ongoing facility upgrade that included a NASA Headquarters mandated replacement of all electrical and mechanical systems and replacement of an external generator. These upgrades required a facility power outage during the PCA upgrades. The project also encompassed console layout designs and ordering, amenities selections and ordering, excessing of old equipment, moves, disposal of old IT equipment, camera installations, facility tour re-schedules, and contract justifications. These were just some of the tasks needed for a successful project.

Design of a power management and distribution system for a thermionic-diode powered spacecraft

NASA Technical Reports Server (NTRS)

Kimnach, Greg L.

1996-01-01

The Electrical Systems Development Branch of the Power Technology Division at the NASA Lewis Research Center in Cleveland, Ohio is designing a Power Management and Distribution (PMAD) System for the Air Force's Integrated Solar Upper Stage (ISUS) Engine Ground Test Demonstration (EGD). The ISUS program uses solar-thermal propulsion to perform orbit transfers from Low Earth Orbit (LEO) to Geosynchronous Orbit (GEO) and from LEO to Molnya. The ISUS uses the same energy conversion receiver to perform the LEO to High Earth Orbit (HEO) transfer and to generate on-orbit electric power for the payloads. On-orbit power generation is accomplished via two solar concentrators heating a dual-cavity graphite-core which has Thermionic Diodes (TMD's) encircling each cavity. The graphite core and concentrators together are called the Receiver and Concentrator (RAC). The TDM-emitters reach peak temperatures of approximately 2200K, and the TID-collectors are run at approximately 1000K. Because of the high Specific Impulse (I(sup sp)) of solar thermal propulsion relative to chemical propulsion, and because a common bus is used for communications, GN&C, power, etc., a substantial increase in payload weight is possible. This potentially allows for a stepdown in the required launch vehicle size or class for similar payload weight using conventional chemical propulsion and a separate spacecraft bus. The ISUS power system is to provide 1000W(sub e) at 28+/-6V(sub dc) to the payload/spacecraft from a maximum TID generation capability of 1070W(sub e) at 2200K. Producing power with this quality, protecting the spacecraft from electrical faults and accommodating operational constraints of the TID's are the responsibilities of the PMAD system. The design strategy and system options examined along with the proposed designs for the Flight and EGD configurations are discussed herein.

NASA's Space Launch System: An Evolving Capability for Exploration

NASA Technical Reports Server (NTRS)

Robinson, Kimberly F.; Hefner, Keith; Hitt, David

2015-01-01

Designed to enable human space exploration missions, including eventually landings on Mars, NASA's Space Launch System (SLS) represents a unique launch capability with a wide range of utilization opportunities, from delivering habitation systems into the "proving ground" of lunar-vicinity space to enabling high-energy transits through the outer solar system. Substantial progress has been made toward the first launch of the initial configuration of SLS, which will be able to deliver more than 70 metric tons of payload into low Earth orbit (LEO). Preparations are also underway to evolve the vehicle into more powerful configurations, culminating with the capability to deliver more than 130 metric tons to LEO. Even the initial configuration of SLS will be able to deliver greater mass to orbit than any contemporary launch vehicle, and the evolved configuration will have greater performance than the Saturn V rocket that enabled human landings on the moon. SLS will also be able to carry larger payload fairings than any contemporary launch vehicle, and will offer opportunities for co-manifested and secondary payloads. Because of its substantial mass-lift capability, SLS will also offer unrivaled departure energy, enabling mission profiles currently not possible. The basic capabilities of SLS have been driven by studies on the requirements of human deep-space exploration missions, and continue to be validated by maturing analysis of Mars mission options, including the Global Exploration Roadmap. Early collaboration with science teams planning future decadal-class missions have contributed to a greater understanding of the vehicle's potential range of utilization. As SLS draws closer to its first launch, the Program is maturing concepts for future capability upgrades, which could begin being available within a decade. These upgrades, from multiple unique payload accommodations to an upper stage providing more power for inspace propulsion, have ramifications for a variety of missions, from human exploration to robotic science.

Prediction of anthropometric accommodation in aircraft cockpits

NASA Astrophysics Data System (ADS)

Zehner, Gregory Franklin

Designing aircraft cockpits to accommodate the wide range of body sizes existing in the U.S. population has always been a difficult problem for Crewstation Engineers. The approach taken in the design of military aircraft has been to restrict the range of body sizes allowed into flight training, and then to develop standards and specifications to ensure that the majority of the pilots are accommodated. Accommodation in this instance is defined as the ability to: (1) Adequately see, reach, and actuate controls; (2) Have external visual fields so that the pilot can see to land, clear for other aircraft, and perform a wide variety of missions (ground support/attack or air to air combat); and (3) Finally, if problems arise, the pilot has to be able to escape safely. Each of these areas is directly affected by the body size of the pilot. Unfortunately, accommodation problems persist and may get worse. Currently the USAF is considering relaxing body size entrance requirements so that smaller and larger people could become pilots. This will make existing accommodation problems much worse. This dissertation describes a methodology for correcting this problem and demonstrates the method by predicting pilot fit and performance in the USAF T-38A aircraft based on anthropometric data. The methods described can be applied to a variety of design applications where fitting the human operator into a system is a major concern. A systematic approach is described which includes: defining the user population, setting functional requirements that operators must be able to perform, testing the ability of the user population to perform the functional requirements, and developing predictive equations for selecting future users of the system. Also described is a process for the development of new anthropometric design criteria and cockpit design methods that assure body size accommodation is improved in the future.

Design, testing, and installation of a high-precision hexapod for the Hobby-Eberly Telescope dark energy experiment (HETDEX)

NASA Astrophysics Data System (ADS)

Zierer, Joseph J.; Beno, Joseph H.; Weeks, Damon A.; Soukup, Ian M.; Good, John M.; Booth, John A.; Hill, Gary J.; Rafal, Marc D.

2012-09-01

Engineers from The University of Texas at Austin Center for Electromechanics and McDonald Observatory have designed, built, and laboratory tested a high payload capacity, precision hexapod for use on the Hobby-Eberly telescope as part of the HETDEX Wide Field Upgrade (WFU). The hexapod supports the 4200 kg payload which includes the wide field corrector, support structure, and other optical/electronic components. This paper provides a recap of the hexapod actuator mechanical and electrical design including a discussion on the methods used to help determine the actuator travel to prevent the hexapod payload from hitting any adjacent, stationary hardware. The paper describes in detail the tooling and methods used to assemble the full hexapod, including many of the structures and components which are supported on the upper hexapod frame. Additionally, details are provided on the installation of the hexapod onto the new tracker bridge, including design decisions that were made to accommodate the lift capacity of the Hobby- Eberly Telescope dome crane. Laboratory testing results will be presented verifying that the performance goals for the hexapod, including positioning, actuator travel, and speeds have all been achieved. This paper may be of interest to mechanical and electrical engineers responsible for the design and operations of precision hardware on large, ground based telescopes. In summary, the hexapod development cycle from the initial hexapod actuator performance requirements and design, to the deployment and testing on the newly designed HET tracker system is all discussed, including lessons learned through the process.

Intumescent coating development

NASA Technical Reports Server (NTRS)

Sayler, I. O.; Griffen, C. W.

1983-01-01

A program was completed at the University of Dayton Research Institute in which polyimide and phenolic intumescent coatings were evaluated as supplemental thermal insulation for the sprayed-on foam insulation on the aft bulkhead of the space shuttle external tank. The purpose of the intumescent coating was to provide additional thermal protection during lift-off in order to replace the ablative heat resistant layer with a lighter weight material for increased payload in the shuttle.

Part Count: Monolithic Part Effects On Manufacturing Labor Cost, An Aircraft Applied Model

DTIC Science & Technology

2010-03-01

Fulfillment of the Requirements for the Degree of Master of Science in Financial Analysis Aaron M. Lemke, BS Captain, USAF March 2010... ACCA ), provides substantial support for the impact of part size on life cycle cost for payload aircraft. This research evaluates select methods used...1: Boeing 787 External Skin Materials (Boeing, 2010) ..........................................9 Figure 2: ACCA Task Sequence (Neumeier et al, 2009

Economic evaluation of interventions for problem drinking and alcohol dependence: do within-family external effects make a difference?

PubMed

Mortimer, Duncan; Segal, Leonie

2006-01-01

To propose methods for the inclusion of within-family external effects in clinical and economic evaluations. To demonstrate the extent of bias due to the exclusion of within-family external effects when measuring the relative performance of interventions for problem drinking and alcohol dependence. The timing and magnitude of treatment effects are modified to accommodate the external health-related quality of life impact of having a problem or dependent drinker in the family home. The inclusion of within-family external effects reduces cost per QALY estimates of interventions for problem drinking and alcohol dependence thereby improving the performance of all evaluated interventions. In addition, the inclusion of within-family external effects improves the relative performance of interventions targeted at those with moderate-to-severe alcohol dependence as compared to interventions targeted at less severe alcohol problems. Failure to take account of external effects in clinical and economic evaluations results in an uneven playing field. Interventions with readily quantifiable health benefits (where social costs and benefits are predominantly comprised of private costs and benefits) are at a distinct advantage when competing for public funding against interventions with quantitatively important external effects.

Opals: Mission System Operations Architecture for an Optical Communications Demonstration on the ISS

NASA Technical Reports Server (NTRS)

Abrahamson, Matthew J.; Sindiy, Oleg V.; Oaida, Bogdan V.; Fregoso, Santos; Bowles-Martinez, Jessica N.; Kokorowski, Michael; Wilkerson, Marcus W.; Konyha, Alexander L.

2014-01-01

In April of 2014, the Optical PAyload for Lasercomm Science (OPALS) Flight System (FS) launched to the International Space Station (ISS) to demonstrate space-to-ground optical communications. During a planned 90-day baseline mission, the OPALS FS will downlink high quality, short duration videos to the Optical Communications Telescope Laboratory (OCTL) ground station in Wrightwood, California. Interfaces to the ISS payload operations infrastructure have been established to facilitate activity planning, hazardous laser operations, commanding, and telemetry transmission. In addition, internal processes, such as pointing prediction and data processing, satisfy the technical requirements of the mission. The OPALS operations team participates in Operational Readiness Tests (ORTs) with external partners to exercise coordination processes and train for the overall mission. The ORTs have provided valuable insight into operational considerations for the instrument on the ISS.

ISS-CREAM Thermal and Fluid System Design and Analysis

NASA Technical Reports Server (NTRS)

Thorpe, Rosemary S.

2015-01-01

Thermal and Fluids Analysis Workshop (TFAWS), Silver Spring MD NCTS 21070-15. The ISS-CREAM (Cosmic Ray Energetics And Mass for the International Space Station) payload is being developed by an international team and will provide significant cosmic ray characterization over a long time frame. Cold fluid provided by the ISS Exposed Facility (EF) is the primary means of cooling for 5 science instruments and over 7 electronics boxes. Thermal fluid integrated design and analysis was performed for CREAM using a Thermal Desktop model. This presentation will provide some specific design and modeling examples from the fluid cooling system, complex SCD (Silicon Charge Detector) and calorimeter hardware, and integrated payload and ISS level modeling. Features of Thermal Desktop such as CAD simplification, meshing of complex hardware, External References (Xrefs), and FloCAD modeling will be discussed.

Generic aerocapture atmospheric entry study, volume 1

NASA Technical Reports Server (NTRS)

1980-01-01

An atmospheric entry study to fine a generic aerocapture vehicle capable of missions to Mars, Saturn, and Uranus is reported. A single external geometry was developed through atmospheric entry simulations. Aerocapture is a system design concept which uses an aerodynamically controlled atmospheric entry to provide the necessary velocity depletion to capture payloads into planetary orbit. Design concepts are presented which provide the control accuracy required while giving thermal protection for the mission payload. The system design concepts consist of the following elements: (1) an extendable biconic aerodynamic configuration with lift to drag ratio between 1.0 and 2.0; (2) roll control system concepts to control aerodynamic lift and disturbance torques; (3) aeroshell design concepts capable of meeting dynamic pressure loads during aerocapture; and (4) entry thermal protection system design concepts to meet thermodynamic loads during aerocapture.

KSC-07pd0229

NASA Image and Video Library

2007-02-02

KENNEDY SPACE CENTER, FLA. -- In the Space Station Processing Facility, members of the STS-118 crew learn important information from technicians about the control moment gyro (CMG) in front of them that is part of the payload on their mission. Second from left is Mission Specialist Tracy Caldwell; at center, behind the CMG, is Mission Specialist Richard Mastracchio; second from right is Mission Specialist Clayton Anderson, who will be flying on STS-118 to join the Expedition 15 crew as flight engineer on the International Space Station. The CMG will replace a faulty one on the International Space Station. The payload also includes the SPACEHAB single cargo module, the third starboard truss segment (ITS S5) and the external stowage platform 3 (ESP3). STS-118 is targeted to launch June 28 from Launch Pad 39A. Photo credit: NASA/Kim Shiflett

Using space for technology development - Planning for the Space Station era

NASA Technical Reports Server (NTRS)

Ambrus, Judith H.; Couch, Lana M.; Rosen, Robert R.; Gartrell, Charles F.

1989-01-01

Experience with the Shuttle and free-flying satellites as technology test-beds has shown the feasibility and desirability of using space assets as a facility for technology development. Thus, by the time the Space Station era will have arrived, the technologist will be ready for an accessible engineering facility in space. As the 21st century is approached, it is expected that virtually every flight to the Space Station Freedom will be required to carry one or more research, technology, and engineering experiments. The experiments planned will utilize both the pressurized volume, and the external payload attachment facilities. A unique, but extremely important, class of experiments will use the Space Station itself as an experimental vehicle. Based upon recent examination of possible Space Station Freedom assembly sequences, technology payloads may well utilize 20-30 percent of available resources.

Adaptive model of the aging emmetropic eye and its changes with accommodation.

PubMed

Navarro, Rafael

2014-11-20

A general schematic model of the optical system of the emmetropic human eye is proposed, capable of adapting to changes with age and accommodation through adjustment of the optical surfaces and the internal gradient index structure of the lens. The specific models of the cornea and lens consist of minor generalizations of previous work by assuming them to be the sum of a biconic plus three higher order Zernike modes. The internal gradient index distribution adapts to the external shape so that the analytical expression is invariant with the changes with age and accommodation. The model also includes tips, tilts, and decentrations of the surfaces according to experimental findings. The specific parameters of these models are either constants or functions of age and/or accommodation. The model is polychromatic, and its optical performance was evaluated along the keratometric axis. Chromatic aberrations (longitudinal and transverse), astigmatism, coma, trefoil, and spherical aberration show good agreement with experimental averages. The change of these aberrations as a function of age or accommodation is also consistent with experimental findings (except for trefoil in eyes older than 50 years). This means that the average structure seems to predict the average performance. Nevertheless, the present model is too schematic to account for other higher order aberrations, such as tetrafoil, also present in real eyes. © 2014 ARVO.

Development of external regeneration models for FVS: Another wrench in the toolkit

Treesearch

Donald C. E. Robinson

2008-01-01

Despite more than three decades of development, only one full-featured regeneration model has been developed for the Forest Vegetation Simulator (FVS). Regeneration remains a challenging problem because of its all-or-none nature: the need for field inventories that span the vast range of stand structure conditions; the need to accommodate environmental and climatic...

THE FLUIDS AND COMBUSTION FACILITY: ENABLING THE EXPLORATION OF SPACE

NASA Technical Reports Server (NTRS)

Weiland, Karen J.; Gati, Frank G.; Hill, Myron E.; OMalley, Terence; Zurawski, Robert L.

2005-01-01

The Fluids and Combustion Facility (FCF) is an International Space Station facility designed to support physical and biological research as well as technology experiments in space. The FCF consists of two racks called the Combustion Integrated Rack (CIR) and the Fluids Integrated Rack (FIR). The capabilities of the CIR and the FIR and plans for their utilization will support the President s vision for space exploration. The CIR will accommodate physical research and technology experiments that address needs in the areas of spacecraft fire prevention, detection and suppression, incineration of solid wastes, and power generation. Initial experiments will provide data to support design decisions for exploration spacecraft. The CIR provides a large sealed chamber in a near-weightless environment. The chamber supports many simulated atmospheres including lunar or Martian environments. The FIR will accommodate experiments that address needs for advanced life support, power, propulsion, and spacecraft thermal control systems. The FIR can also serve as a platform for experiments that address human health and performance, medical technologies, and biological sciences. The FIR provides a large volume for payload hardware, reconfigurable diagnostics, customizable software, active rack-level vibration isolation, and data acquisition and management in a nearly uniform temperature environment.

The Fluids and Combustion Facility: Enabling the Exploration of Space

NASA Technical Reports Server (NTRS)

Weiland, Karen J.; Gati, Frank G.; Hill, Myron E.; O'Malley Terence F.; Zurawski, Robert L.

2005-01-01

The Fluids and Combustion Facility (FCF) is an International Space Station facility designed to support physical and biological research as well as technology experiments in space. The FCF consists of two racks called the Combustion Integrated Rack (CIR) and the Fluids Integrated Rack (FIR). The capabilities of the CIR and the FIR and plans for their utilization will support the President's vision for space exploration. The CIR will accommodate physical research and technology experiments that address needs in the areas of spacecraft fire prevention, detection and suppression, incineration of solid wastes, and power generation. Initial experiments will provide data to support design decisions for exploration spacecraft. The CIR provides a large sealed chamber in a near-weightless environment. The chamber supports many simulated atmospheres including lunar or Martian environments. The FIR will accommodate experiments that address needs for advanced life support, power, propulsion, and spacecraft thermal control systems. The FIR can also serve as a platform for experiments that address human health and performance, medical technologies, and biological sciences. The FIR provides a large volume for payload hardware, reconfigurable diagnostics, customizable software, active rack-level vibration isolation, and data acquisition and management in a nearly uniform temperature environment.

First Materials Science Research Facility Rack Capabilities and Design Features

NASA Technical Reports Server (NTRS)

Cobb, S.; Higgins, D.; Kitchens, L.; Curreri, Peter (Technical Monitor)

2002-01-01

The first Materials Science Research Rack (MSRR-1) is the primary facility for U.S. sponsored materials science research on the International Space Station. MSRR-1 is contained in an International Standard Payload Rack (ISPR) equipped with the Active Rack Isolation System (ARIS) for the best possible microgravity environment. MSRR-1 will accommodate dual Experiment Modules and provide simultaneous on-orbit processing operations capability. The first Experiment Module for the MSRR-1, the Materials Science Laboratory (MSL), is an international cooperative activity between NASA's Marshall Space Flight Center (MSFC) and the European Space Agency's (ESA) European Space Research and Technology Center (ESTEC). The MSL Experiment Module will accommodate several on-orbit exchangeable experiment-specific Module Inserts which provide distinct thermal processing capabilities. Module Inserts currently planned for the MSL are a Quench Module Insert, Low Gradient Furnace, and a Solidification with Quench Furnace. The second Experiment Module for the MSRR-1 configuration is a commercial device supplied by MSFC's Space Products Development (SPD) Group. Transparent furnace assemblies include capabilities for vapor transport processes and annealing of glass fiber preforms. This Experiment Module is replaceable on-orbit. This paper will describe facility capabilities, schedule to flight and research opportunities.

STS-107 Mission Highlights Resource Tape, Part 1 of 4

NASA Technical Reports Server (NTRS)

2003-01-01

This video, Part 1 of 4, shows the activities of the STS-107 crew during flight days 1 through 3 of the Columbia orbiter's final flight. The crew consists of Commander Rick Husband, Pilot William McCool, Payload Commander Michael Anderson, Mission Specialists David Brown, Kalpana Chawla, and Laurel Clark, and Payload Specialist Ilan Ramon. Before launch on flight day 1 the astronauts are seen at their pre-flight banquet, during suit-up, and while being seated on the orbiter. David Brown takes footage of the space shuttle's external tank after it is jettisoned. The video includes replays of the launch from several angles. The onboard views of launch are narrated by William McCool and Kalpana Chawla. On flight days 2 and 3 student microgravity experiments in the SpaceHab module in the shuttle's payload bay are profiled. These experiments address microgravity effects on crystal growth, ants, bees, fish embryos, silkworms, and spiders. Other experiments profiled include the Mediterranean Israeli Dust Experiment (MEIDEX), FAST (surface tension of bubbles), SOLS (Ozone), an experiment to culture prostate cancer cells in a bioreactor, and a commercial plant growth experiment. Earth views include lightning at night, and a view of the Strait of Gibraltar, including Spain and Morocco.

KSC-99pp1367

NASA Image and Video Library

1999-11-29

KENNEDY SPACE CENTER, FLA. -- Orbiter Endeavour waits in the Orbiter Processing Facility bay 2 for the closing of its payload bay doors. The Ku-band antenna (upper right) is still in the open position, outside the payload bay. Endeavour is expected to roll over to the Vehicle Assembly Building in three days for mating to the external tank and solid rocket boosters in high bay 1. Space Shuttle Endeavour is targeted for launch on mission STS-99 Jan. 13, 2000 at 1:11 p.m. EST. STS-99 is the Shuttle Radar Topography Mission, an international project spearheaded by the National Imagery and Mapping Agency and NASA, with participation of the German Aerospace Center DLR. The SRTM consists of a specially modified radar system that will gather data for the most accurate and complete topographic map of the Earth's surface that has ever been assembled. SRTM will make use of radar interferometry, wherein two radar images are taken from slightly different locations. Differences between these images allow for the calculation of surface elevation, or change. The SRTM hardware will consist of one radar antenna in the shuttle payload bay and a second radar antenna attached to the end of a mast extended 60 meters (195 feet) out from the shuttle

KSC-99pp1368

NASA Image and Video Library

1999-11-01

KENNEDY SPACE CENTER, FLA. -- Orbiter Endeavour waits in the Orbiter Processing Facility bay 2 for the closing of its payload bay doors. The Ku-band antenna (upper right) is now in its closed position inside the payload bay. Endeavour is expected to roll over to the Vehicle Assembly Building in three days for mating to the external tank and solid rocket boosters in high bay 1. Space Shuttle Endeavour is targeted for launch on mission STS-99 Jan. 13, 2000 at 1:11 p.m. EST. STS-99 is the Shuttle Radar Topography Mission, an international project spearheaded by the National Imagery and Mapping Agency and NASA, with participation of the German Aerospace Center DLR. The SRTM consists of a specially modified radar system that will gather data for the most accurate and complete topographic map of the Earth's surface that has ever been assembled. SRTM will make use of radar interferometry, wherein two radar images are taken from slightly different locations. Differences between these images allow for the calculation of surface elevation, or change. The SRTM hardware will consist of one radar antenna in the shuttle payload bay and a second radar antenna attached to the end of a mast extended 60 meters (195 feet) out from the shuttle

STS-50 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W.

1992-01-01

The STS-50 Space Shuttle Program Mission Report contains a summary of the Orbiter, External Tank (ET), Solid Rocket Booster/Redesigned Solid Rocket Motor (SRB/RSRM), and the Space Shuttle main engine (SSME) subsystem performance during the forty-eighth flight of the Space Shuttle Program, and the twelfth flight of the Orbiter vehicle Columbia (OV-102). In addition to the Columbia vehicle, the flight vehicle consisted of the following: an ET which was designated ET-50 (LUT-43); three SSME's which were serial numbers 2019, 2031, and 2011 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-051. The lightweight/redesigned RSRM's installed in each SRB were designated 360L024A for the left RSRM and 360M024B for the right RSRM. The primary objective of the STS-50 flight was to successfully perform the planned operations of the United States Microgravity Laboratory (USML-1) payload. The secondary objectives of this flight were to perform the operations required by the Investigations into Polymer Membrane Processing (IPMP), and the Shuttle Amateur Radio Experiment 2 (SAREX-2) payloads. An additional secondary objective was to meet the requirements of the Ultraviolet Plume Instrument (UVPI), which was flown as a payload of opportunity.

Backstepping Design of Adaptive Neural Fault-Tolerant Control for MIMO Nonlinear Systems.

PubMed

Gao, Hui; Song, Yongduan; Wen, Changyun

In this paper, an adaptive controller is developed for a class of multi-input and multioutput nonlinear systems with neural networks (NNs) used as a modeling tool. It is shown that all the signals in the closed-loop system with the proposed adaptive neural controller are globally uniformly bounded for any external input in . In our control design, the upper bound of the NN modeling error and the gains of external disturbance are characterized by unknown upper bounds, which is more rational to establish the stability in the adaptive NN control. Filter-based modification terms are used in the update laws of unknown parameters to improve the transient performance. Finally, fault-tolerant control is developed to accommodate actuator failure. An illustrative example applying the adaptive controller to control a rigid robot arm shows the validation of the proposed controller.In this paper, an adaptive controller is developed for a class of multi-input and multioutput nonlinear systems with neural networks (NNs) used as a modeling tool. It is shown that all the signals in the closed-loop system with the proposed adaptive neural controller are globally uniformly bounded for any external input in . In our control design, the upper bound of the NN modeling error and the gains of external disturbance are characterized by unknown upper bounds, which is more rational to establish the stability in the adaptive NN control. Filter-based modification terms are used in the update laws of unknown parameters to improve the transient performance. Finally, fault-tolerant control is developed to accommodate actuator failure. An illustrative example applying the adaptive controller to control a rigid robot arm shows the validation of the proposed controller.

A risk based approach for SSTO/TSTO comparisons

NASA Astrophysics Data System (ADS)

Greenberg, Joel S.

1996-03-01

An approach has been developed for performing early comparisons of transportation architectures explicitly taking into account quantitative measures of uncertainty and resulting risk. Risk considerations are necessary since the transportation systems are likely to have significantly different levels of risk, both because of differing degrees of freedom in achieving desired performance levels and their different states of development and utilization. The approach considers the uncertainty of achievement of technology goals, effect that the achieved technology level will have on transportation system performance and the relationship between system performance/capability and the ability to accommodate variations in payload mass. The consequences of system performance are developed in terms of nonrecurring, recurring, and the present value of transportation system life cycle costs.

ExoMars Raman laser spectrometer overview

NASA Astrophysics Data System (ADS)

Rull, F.; Sansano, A.; Díaz, E.; Canora, C. P.; Moral, A. G.; Tato, C.; Colombo, M.; Belenguer, T.; Fernández, M.; Manfredi, J. A. R.; Canchal, R.; Dávila, B.; Jiménez, A.; Gallego, P.; Ibarmia, S.; Prieto, J. A. R.; Santiago, A.; Pla, J.; Ramos, G.; González, C.

2010-09-01

The Raman Laser Spectrometer (RLS) is one of the Pasteur Payload instruments, within the ESA's Aurora Exploration Programme, ExoMars mission. The RLS Instrument will perform Raman spectroscopy on crushed powered samples deposited on a small container after crushing the cores obtained by the Rover's drill system. This is the first time that a Raman spectrometer will be launched in an out planetary mission. The Instrument will be accommodated and operate inside the Rover's ALD (Analytical Laboratory Drawer), complying with COSPAR (Committee on Space Research) Planetary Protection requirements. The RLS Instrument is composed by the following units: SPU (Spectrometer Unit); iOH: (Internal Optical Head); ICEU (Instrument Control and Excitation Unit). Other instrument units are EH (Electrical Harness), OH (Optical Harness) and RLS SW On-Board.

Mars mission effects on Space Station evolution

NASA Technical Reports Server (NTRS)

Askins, Barbara S.; Cook, Stephen G.

1989-01-01

The permanently manned Space Station scheduled to be operational in low earth by the mid 1990's, will provide accommodations for science, applications, technology, and commercial users, and will develop enabling capabilities for future missions. A major aspect of the baseline Space Station design is that provisions for evolution to greater capabilities are included in the systems and subsystems designs. User requirements are the basis for conceptual evolution modes or infrastructure to support the paths. Four such modes are discussed in support of a Human to Mars mission, along with some of the near term actions protecting the future of supporting Mars missions on the Space Station. The evolution modes include crew and payload transfer, storage, checkout, assembly, maintenance, repair, and fueling.

Mars MetNet Precursor Mission Status

NASA Astrophysics Data System (ADS)

Harri, Ari-Matti; Aleksashkin, Sergey; Guerrero, Héctor; Schmidt, Walter; Genzer, Maria; Vazquez, Luis; Haukka, Harri

2013-04-01

A new kind of planetary exploration mission for Mars is being developed in collaboration between the Finnish Meteorological Institute (FMI), Lavochkin Association (LA), Space Research Institute (IKI) and Institutio Nacional de Tecnica Aerospacial (INTA). The Mars MetNet mission is based on a new semi-hard landing vehicle called MetNet Lander (MNL), using an inflatable entry and descent system instead of rigid heat shields and parachutes as earlier semi-hard landing devices have used. This way the ratio of the payload mass to the overall mass is optimized. The landing impact will burrow the payload container into the Martian soil providing a more favorable thermal environment for the electronics and a suitable orientation of the telescopic boom with external sensors and the radio link antenna. It is planned to deploy several tens of MNLs on the Martian surface operating at least partly at the same time to allow meteorological network science. For the precursor mission (MMPM) intended to verify the landing concept and key technology during a real Mars mission all qualification activities are completed and the payload and system flight model components are being manufactured. The descent processes dynamic properties are monitored by a special 3-axis accelerometer combined with a 3-axis gyrometer. The data will be sent via auxiliary beacon antenna throughout the descent phase starting shortly after separation from the spacecraft. Details of the current MMPM system and payload configuration and their performance parameters will be shown.

STS-44 Atlantis, Orbiter Vehicle (OV) 104, is moved from KSC's OPF

NASA Image and Video Library

1991-10-18

S91-50776 (18 Oct 1991) --- The Space Shuttle Atlantis is moved from the Orbital Processing Facility (OPF) Bay 2 to the Vehicle Assembly Building (VAB) at Kennedy Space Center, Florida. The Atlantis will be mated with the external fuel tank and solid rocket boosters before it is transported to Pad 39A, where it will launch a Department of Defense payload, Mission STS-44, in late 1991.

Economic benefits of commercial space activities

NASA Technical Reports Server (NTRS)

Stone, Barbara A.

1988-01-01

This paper discusses the current and potential impact on the economy of selected private sector space activities including materials processing in space and satellite communications. Spacehab, a commercially developed and manufactured pressurized metal cylinder which fits in the Shuttle payload bay and connects to the crew compartment is examined along with potential uses of the Shuttle external tank. Private sector upper stage development, the privatization of expendable launch vehicles, and the transfer of NASA technology are discussed.

Mechanisms of postprandial abdominal bloating and distension in functional dyspepsia.

PubMed

Burri, Emanuel; Barba, Elizabeth; Huaman, Jose Walter; Cisternas, Daniel; Accarino, Anna; Soldevilla, Alfredo; Malagelada, Juan-R; Azpiroz, Fernando

2014-03-01

Patients with irritable bowel syndrome and abdominal bloating exhibit abnormal responses of the abdominal wall to colonic gas loads. We hypothesised that in patients with postprandial bloating, ingestion of a meal triggers comparable abdominal wall dyssynergia. Our aim was to characterise abdominal accommodation to a meal in patients with postprandial bloating. A test meal (0.8 kcal/ml nutrients plus 27 g/litre polyethylenglycol 4000) was administered at 50 ml/min as long as tolerated in 10 patients with postprandial bloating (fulfilling Rome III criteria for postprandial distress syndrome) and 12 healthy subjects, while electromyographic (EMG) responses of the anterior wall (upper and lower rectus, external and internal oblique via bipolar surface electrodes) and the diaphragm (via six ring electrodes over an oesophageal tube in the hiatus) were measured. Means +/- SD were calculated. Healthy subjects tolerated a meal volume of 913±308 ml; normal abdominal wall accommodation to the meal consisted of diaphragmatic relaxation (EMG activity decreased by 15±6%) and a compensatory contraction (25±9% increase) of the upper abdominal wall muscles (upper rectus and external oblique), with no changes in the lower anterior muscles (lower rectus and internal oblique). Patients tolerated lower volume loads (604±310 ml; p=0.030 vs healthy subjects) and developed a paradoxical response, that is, diaphragmatic contraction (14±3% EMG increment; p<0.01 vs healthy subjects) and upper anterior wall relaxation (9±4% inhibition; p<0.01 vs healthy subjects). In functional dyspepsia, postprandial abdominal distension is produced by an abnormal viscerosomatic response to meal ingestion that alters normal abdominal accommodation.

A Jupiter Ganymede Orbiter for the EJSM mission: the JGO assessment phase study by the Thales Alenia Space consortium

NASA Astrophysics Data System (ADS)

Poncy, Joel; Couzin, Patrice; Mercier, Manuel; Boschetti, Demis

2010-05-01

ESA and NASA have undertaken advanced studies of a common mission to Jupiter's system, EJSM (Europa Jupiter System Mission). This mission comprises two spacecrafts launched independently in 2020 and reaching the system in 2026. This is a one-in-a-generation opportunity for Europe to contribute significantly to the science of this part of the Solar System, and as such, all efforts shall subsequently be made to maximize the scientific return without jeopardizing the technical and programmatic feasibility of the mission. A sub-glacial ocean on Europa and potentially two others on Ganymede and Callisto, the monitoring of Io's volcanic activity, the upper atmosphere of Jupiter, its rings, its tens of irregular moons, the tides, the magnetic fields of Jupiter and Ganymede and the behaviour of the plasma, the list of science objectives is not only impressive but also generates enthusiasm in the mission. In this NASA-ESA joint mission, NASA will take charge of both Io and Europa with the Jupiter Europa Orbiter (JEO). Europe will get a fascinating share with the Jupiter Ganymede Orbiter (JGO), which will achieve the close study of the two largest and outermost Galilean moons Ganymede and Callisto and in addition, at-a-distance, the observation of the other targets mentioned above. ESA has awarded three industrial contracts for an assessment phase of JGO. As leader of one of the consortia, Thales Alenia Space is proud to present in this poster its achievements on this exciting mission. The requirements are discussed and the mission drivers identified. The main trades and the resulting architecture are recalled, along with the main selection drivers. The major system interrelated trades have covered the launcher and propulsion type, the number of regulated phases, the strategy for communications and science timeline, the need for HGA pointing, the sizing and configuration of the Solar Array, the accommodation of external appendages, the accommodation of the payload, the autonomy, the modularity of the platform, the radiation shielding strategies, the planetary protection etc. We then present a brief justification of the design and the resulting performance. We conclude by assessing the feasibility of the mission in its current technical and programmatic requirements.