STS-98 payload U.S. Lab Destiny is moved into Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- The U.S. Lab Destiny is ready to move into the orbiter'''s payload bay from the Payload Changeout Room. The PCR is the enclosed, environmentally controlled portion of the rotating service structure that supports payload delivery at the launch pad and vertical installation in the orbiter payload bay. Destiny, a key element in the construction of the International Space Station is designed for space science experiments and already has five system racks installed inside. STS-98 is the seventh construction flight to the ISS. Launch of STS-98 is scheduled for Jan. 19 at 2:11 a.m. EST.

STS-98 payload U.S. Lab Destiny is moved into Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- Technicians in the Payload Changeout Room oversee the transfer of the U.S. Lab Destiny to the orbiter'''s payload bay. The PCR is the enclosed, environmentally controlled portion of the rotating service structure that supports payload delivery at the launch pad and vertical installation in the orbiter payload bay. Destiny, a key element in the construction of the International Space Station is designed for space science experiments and already has five system racks installed inside. STS-98 is the seventh construction flight to the ISS. Launch of STS-98 is scheduled for Jan. 19 at 2:11 a.m. EST.

Conceptual Design of Future Undersea Unmanned Vehicle (UUV) System for Mine Disposal

DTIC Science & Technology

2012-01-01

disproportionate effect of a single mine strike might be enough to threaten mission accomplishment of combat forces. Some potential impacts of enemy mining...parameters, which include vehicle conditions, hotel power, payload conditions, and environmental conditions. The vehicle configuration options are...transit, execution of mission, return transit, and recovery. Each of them is defined by key mission and environmental parameters such as range

KSC-06pd1673

NASA Image and Video Library

2006-07-26

KENNEDY SPACE CENTER, FLA. - On Launch Pad 39B, the payload canister is moved into position beneath the payload changeout room (PCR) for transfer of its cargo into the PCR. The canister holds the payload for Atlantis and mission STS-115, the Port 3/4 truss segment with two large solar arrays. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payload will then be transferred into Atlantis' payload bay. Atlantis' launch window begins Aug. 28. During its 11-day mission to the International Space Station, the STS-115 crew of six astronauts will install the truss, a 17-ton segment of the space station's truss backbone. Photo credit: NASA/George Shelton

STS-98 payload U.S. Lab Destiny is moved into Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- Workers in the Payload Changeout Room check the movement of the U.S. Lab Destiny, which is being transferred to the orbiter'''s payload bay. The PCR is the enclosed, environmentally controlled portion of the rotating service structure that supports payload delivery at the launch pad and vertical installation in the orbiter payload bay. Destiny, a key element in the construction of the International Space Station is designed for space science experiments and already has five system racks installed inside. STS-98 is the seventh construction flight to the ISS. Launch of STS-98 is scheduled for Jan. 19 at 2:11 a.m. EST.

KSC-07pd0363

NASA Image and Video Library

2007-02-12

KENNEDY SPACE CENTER, FLA. -- A worker in the payload changeout room (PCR) on Launch Pad 39A monitors the payload ground-handling mechanism that is used to transfer the payload into the PCR and the shuttle's payload bay. The PCR 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 truss is the payload for Space Shuttle Atlantis on mission STS-117 to the International Space Station. The Atlantis crew will install the new truss segment, retract a set of solar arrays and unfold a new set on the starboard side of the station. Launch is targeted for March 15. Photo credit: NASA/Jack Pfaller

KSC-08pd3751

NASA Image and Video Library

2008-11-19

CAPE CANAVERAL, Fla. – In the Space Station Processing Facility at NASA's Kennedy Space Center in Florida, workers check the mast deployment on the SEDA-AP or Space Environment Data Acquisition equipment--Attached Payload. SEDA-AP will measure space environment in ISS orbit and environmental effects on materials and electronic devices to investigate the interaction with and from the environment at the Kibo exposed facility. The payload will be installed on the Japanese Experiment Module's Experiment Logistics Module-Exposed Section, or ELM-ES. The ELM-ES is one of the final components of the Japan Aerospace Exploration Agency's Kibo laboratory for the International Space Station. It can provide payload storage space and can carry up to three payloads at launch. In addition, the ELM-ES provides a logistics function where it can be returned to the ground aboard the space shuttle. The ELM-ES will be carried aboard space shuttle Endeavour on the STS-127 mission targeted for launch May 15. Photo credit: NASA/Cory Huston

KSC-08pd3750

NASA Image and Video Library

2008-11-19

CAPE CANAVERAL, Fla. – In the Space Station Processing Facility at NASA's Kennedy Space Center in Florida, workers deploy the mast on the SEDA-AP or Space Environment Data Acquisition equipment--Attached Payload. SEDA-AP will measure space environment in ISS orbit and environmental effects on materials and electronic devices to investigate the interaction with and from the environment at the Kibo exposed facility. The payload will be installed on the Japanese Experiment Module's Experiment Logistics Module-Exposed Section, or ELM-ES. The ELM-ES is one of the final components of the Japan Aerospace Exploration Agency's Kibo laboratory for the International Space Station. It can provide payload storage space and can carry up to three payloads at launch. In addition, the ELM-ES provides a logistics function where it can be returned to the ground aboard the space shuttle. The ELM-ES will be carried aboard space shuttle Endeavour on the STS-127 mission targeted for launch May 15. Photo credit: NASA/Cory Huston

KSC-08pd3752

NASA Image and Video Library

2008-11-19

CAPE CANAVERAL, Fla. – In the Space Station Processing Facility at NASA's Kennedy Space Center in Florida, workers check the mast deployment on the SEDA-AP or Space Environment Data Acquisition equipment--Attached Payload. SEDA-AP will measure space environment in ISS orbit and environmental effects on materials and electronic devices to investigate the interaction with and from the environment at the Kibo exposed facility. The payload will be installed on the Japanese Experiment Module's Experiment Logistics Module-Exposed Section, or ELM-ES. The ELM-ES is one of the final components of the Japan Aerospace Exploration Agency's Kibo laboratory for the International Space Station. It can provide payload storage space and can carry up to three payloads at launch. In addition, the ELM-ES provides a logistics function where it can be returned to the ground aboard the space shuttle. The ELM-ES will be carried aboard space shuttle Endeavour on the STS-127 mission targeted for launch May 15. Photo credit: NASA/Cory Huston

Strawman payload data for science and applications space platforms

NASA Technical Reports Server (NTRS)

1980-01-01

The need for a free flying science and applications space platform to host compatible long duration experiment groupings in Earth orbit is discussed. Experiment level information on strawman payload models is presented which serves to identify and quantify the requirements for the space platform system. A description data base on the strawman payload model is presented along with experiment level and group level summaries. Payloads identified in the strawman model include the disciplines of resources observations and environmental observations.

KSC-06pd1670

NASA Image and Video Library

2006-07-26

KENNEDY SPACE CENTER, FLA. - Shortly after midnight, the payload canister makes a slow journey to Launch Pad 39B. Inside the canister is the payload for Atlantis and mission STS-115, the Port 3/4 truss segment with two large solar arrays. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payload will then be transferred into Atlantis' payload bay. Atlantis' launch window begins Aug. 28. During its 11-day mission to the International Space Station, the STS-115 crew of six astronauts will install the truss, a 17-ton segment of the space station's truss backbone. Photo credit: NASA/George Shelton

KSC-06pd0857

NASA Image and Video Library

2006-05-17

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 39B at NASA's Kennedy Space Center, the payload canister holding Space Shuttle Discovery's payloads nears the payload changeout room on the rotating service structure. The red umbilical lines are still attached. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payloads, which include the multi-purpose logistics module and integrated cargo carrier, will then be transferred from the changeout room into Discovery's payload bay. Discovery's launch to the International Space Station on mission STS-121 is targeted for July 1 in a launch window that extends to July 19. During the 12-day mission, crew members will test new hardware and techniques to improve shuttle safety. Photo credit: NASA/Kim Shiflett

KSC-06pd0858

NASA Image and Video Library

2006-05-17

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 39B at NASA's Kennedy Space Center, the payload canister holding Space Shuttle Discovery's payloads nears the payload changeout room on the rotating service structure. The red umbilical lines are still attached. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payloads, which include the multi-purpose logistics module and integrated cargo carrier, will then be transferred from the changeout room into Discovery's payload bay. Discovery's launch to the International Space Station on mission STS-121 is targeted for July 1 in a launch window that extends to July 19. During the 12-day mission, crew members will test new hardware and techniques to improve shuttle safety. Photo credit: NASA/Kim Shiflett

KSC-06pd0856

NASA Image and Video Library

2006-05-17

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 39B at NASA's Kennedy Space Center, the payload canister holding Space Shuttle Discovery's payloads is lifted toward the payload changeout room on the rotating service structure. The red umbilical lines are still attached. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payloads, which include the multi-purpose logistics module and integrated cargo carrier, will then be transferred from the changeout room into Discovery's payload bay. Discovery's launch to the International Space Station on mission STS-121 is targeted for July 1 in a launch window that extends to July 19. During the 12-day mission, crew members will test new hardware and techniques to improve shuttle safety. Photo credit: NASA/Kim Shiflett

KSC-06pd1674

NASA Image and Video Library

2006-07-26

KENNEDY SPACE CENTER, FLA. - Nearing dawn on Launch Pad 39B, the payload canister is in position to be lifted into the payload changeout room (PCR) for transfer of its cargo into the PCR. The canister holds the payload for Atlantis and mission STS-115, the Port 3/4 truss segment with two large solar arrays. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payload will then be transferred into Atlantis' payload bay. Atlantis' launch window begins Aug. 28. During its 11-day mission to the International Space Station, the STS-115 crew of six astronauts will install the truss, a 17-ton segment of the space station's truss backbone. Photo credit: NASA/George Shelton

KSC-06pd1676

NASA Image and Video Library

2006-07-26

KENNEDY SPACE CENTER, FLA. - On Launch Pad 39B, the payload canister is lifted toward the payload changeout room (PCR) for transfer of its cargo into the PCR. The canister holds the payload for Atlantis and mission STS-115, the Port 3/4 truss segment with two large solar arrays. The red umbilical lines are still attached to the transporter, lower right. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payload will then be transferred into Atlantis' payload bay. Atlantis' launch window begins Aug. 28. During its 11-day mission to the International Space Station, the STS-115 crew of six astronauts will install the truss, a 17-ton segment of the space station's truss backbone. Photo credit: NASA/George Shelton

KSC-06pd1672

NASA Image and Video Library

2006-07-26

KENNEDY SPACE CENTER, FLA. - After a several-hour trip from the Canister Rotation Facility, the payload canister arrives on Launch Pad 39B. Inside the canister is the payload for Atlantis and mission STS-115, the Port 3/4 truss segment with two large solar arrays. The canister will be positioned alongside the rotating service structure and beneath the payload changeout room (PCR) for transfer of the truss into the PCR. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payload will then be transferred into Atlantis' payload bay. Atlantis' launch window begins Aug. 28. During its 11-day mission to the International Space Station, the STS-115 crew of six astronauts will install the truss, a 17-ton segment of the space station's truss backbone. Photo credit: NASA/George Shelton

KSC-06pd1675

NASA Image and Video Library

2006-07-26

KENNEDY SPACE CENTER, FLA. - On Launch Pad 39B, the payload canister is lifted toward the payload changeout room (PCR) for transfer of its cargo into the PCR. The canister holds the payload for Atlantis and mission STS-115, the Port 3/4 truss segment with two large solar arrays. The red umbilical lines are still attached, lower right. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payload will then be transferred into Atlantis' payload bay. Atlantis' launch window begins Aug. 28. During its 11-day mission to the International Space Station, the STS-115 crew of six astronauts will install the truss, a 17-ton segment of the space station's truss backbone. Photo credit: NASA/George Shelton

STS-1 mission contamination evaluation approach

NASA Technical Reports Server (NTRS)

Jacobs, S.; Ehlers, H.; Miller, E. R.

1980-01-01

The space transportation system 1 mission will be the first opportunity to assess the induced environment of the orbiter payload bay region. Two tools were developed to aid in this assessment. The shuttle payload contamination evaluation computer program was developed to provide an analytical tool for prediction of the induced molecular contamination environment of the space shuttle orbiter during its onorbit operations. An induced environment contamination monitor was constructed and tested to measure the space shuttle orbiter contamination environment inside the payload bay during ascent and descent and inside and outside the payload bay during the onorbit phase. Measurements are to be performed during the four orbital flight test series. Measurements planned for the first flight are described and predicted environmental data are discussed. The results indicate that the expected data are within the measurement range of the induced environment contamination monitor instruments evaluated, and therefore it is expected that useful contamination environmental data will be available after the first flight.

KSC-08pd0340

NASA Image and Video Library

2008-02-15

KENNEDY SPACE CENTER, FLA. -- The payload canister containing the first section of the Japan Aerospace Exploration Agency's Kibo laboratory and the Canadian Space Agency's two-armed robotic system, Dextre, nears the rotating service structure on Launch Pad 39A at NASA's Kennedy Space Center. The payload will be transferred to the payload changeout room on the service structure. 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 an orbiter's payload bay. The payload will be installed into Endeavour for launch on the STS-123 mission targeted for March 11. Photo credit: NASA/Kim Shiflett

Cost prediction model for various payloads and instruments for the Space Shuttle Orbiter

NASA Technical Reports Server (NTRS)

Hoffman, F. E.

1984-01-01

The following cost parameters of the space shuttle were undertaken: (1) to develop a cost prediction model for various payload classes of instruments and experiments for the Space Shuttle Orbiter; and (2) to show the implications of various payload classes on the cost of: reliability analysis, quality assurance, environmental design requirements, documentation, parts selection, and other reliability enhancing activities.

KSC-06pd1671

NASA Image and Video Library

2006-07-26

KENNEDY SPACE CENTER, FLA. - Shortly after midnight, the payload canister and convoy negotiate the turn on the Saturn Causeway, heading for Launch Pad 39B. Inside the canister is the payload for Atlantis and mission STS-115, the Port 3/4 truss segment with two large solar arrays. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payload will then be transferred into Atlantis' payload bay. Atlantis' launch window begins Aug. 28. During its 11-day mission to the International Space Station, the STS-115 crew of six astronauts will install the truss, a 17-ton segment of the space station's truss backbone. Photo credit: NASA/George Shelton

STS-98 payload U.S. Lab Destiny is moved into Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- Workers in the Payload Changeout Room begin moving the U.S. Lab Destiny to the orbiter'''s payload bay. The PCR is the enclosed, environmentally controlled portion of the rotating service structure that supports payload delivery at the launch pad and vertical installation in the orbiter payload bay. Destiny, a key element in the construction of the International Space Station, is 28 feet long and weighs 16 tons. This research and command-and- control center is the most sophisticated and versatile space laboratory ever built. It will ultimately house a total of 23 experiment racks for crew support and scientific research. STS-98 is the seventh construction flight to the ISS. Launch of STS-98 is scheduled for Jan. 19 at 2:11 a.m. EST.

Environmental impact statement for the Kennedy Space Center, 1978 - 1979 revision

NASA Technical Reports Server (NTRS)

1979-01-01

The ongoing operation of KSC for expendable launch vehicles and automated spacecraft, continued development of facility capabilities, and the approved follow-on operations of the Space Transportation System and associated payloads are described. Emphasis is placed on the expendable launch vehicle and space shuttle traffic projected as of January, 1979. The maximum potential effect on the environment is addressed. Site specific environmental effects are summarized. It is indicated that all potential impacts will be localized, of short duration, controllable, and of minimum severity. The impact on land use, air and water quality, weather, and noise effects is covered.

KSC-06pd1677

NASA Image and Video Library

2006-07-26

KENNEDY SPACE CENTER, FLA. - On Launch Pad 39B, the payload canister is lifted toward the payload changeout room (PCR) for transfer of its cargo into the PCR. The canister holds the payload for Atlantis and mission STS-115, the Port 3/4 truss segment with two large solar arrays. The red umbilical lines are still attached to the transporter, below it. To the right of the rotating structure is the fixed service structure with the 80-foot lightning mast on top. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payload will then be transferred into Atlantis' payload bay. Atlantis' launch window begins Aug. 28. During its 11-day mission to the International Space Station, the STS-115 crew of six astronauts will install the truss, a 17-ton segment of the space station's truss backbone. Photo credit: NASA/George Shelton

14 CFR 415.203 - Environmental information.

Code of Federal Regulations, 2012 CFR

2012-01-01

... parameters of any existing environmental impact statement that applies to that site; (d) A proposed payload that may have significant environmental impacts in the event of a mishap; and (e) Other factors as...

14 CFR 415.203 - Environmental information.

Code of Federal Regulations, 2013 CFR

2013-01-01

... parameters of any existing environmental impact statement that applies to that site; (d) A proposed payload that may have significant environmental impacts in the event of a mishap; and (e) Other factors as...

14 CFR 415.203 - Environmental information.

Code of Federal Regulations, 2011 CFR

2011-01-01

... parameters of any existing environmental impact statement that applies to that site; (d) A proposed payload that may have significant environmental impacts in the event of a mishap; and (e) Other factors as...

14 CFR 415.203 - Environmental information.

Code of Federal Regulations, 2014 CFR

2014-01-01

... parameters of any existing environmental impact statement that applies to that site; (d) A proposed payload that may have significant environmental impacts in the event of a mishap; and (e) Other factors as...

14 CFR 431.93 - Environmental information.

Code of Federal Regulations, 2011 CFR

2011-01-01

... the parameters of existing environmental impact statements covering that site; (d) A proposed payload that may have significant environmental impacts in the event of a reentry accident; and (e) Other factors as necessary to comply with the National Environmental Policy Act. ...

14 CFR 431.93 - Environmental information.

Code of Federal Regulations, 2013 CFR

2013-01-01

... the parameters of existing environmental impact statements covering that site; (d) A proposed payload that may have significant environmental impacts in the event of a reentry accident; and (e) Other factors as necessary to comply with the National Environmental Policy Act. ...

14 CFR 431.93 - Environmental information.

Code of Federal Regulations, 2012 CFR

2012-01-01

... the parameters of existing environmental impact statements covering that site; (d) A proposed payload that may have significant environmental impacts in the event of a reentry accident; and (e) Other factors as necessary to comply with the National Environmental Policy Act. ...

14 CFR 431.93 - Environmental information.

Code of Federal Regulations, 2014 CFR

2014-01-01

... the parameters of existing environmental impact statements covering that site; (d) A proposed payload that may have significant environmental impacts in the event of a reentry accident; and (e) Other factors as necessary to comply with the National Environmental Policy Act. ...

STS-98 payload U.S. Lab Destiny is moved into Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- Technicians in the Payload Changeout Room work to secure the U.S. Lab Destiny in the orbiter'''s payload bay. The PCR is the enclosed, environmentally controlled portion of the rotating service structure that supports payload delivery at the launch pad and vertical installation in the orbiter payload bay. Destiny, a key element in the construction of the International Space Station, is 28 feet long and weighs 16 tons. This research and command-and- control center is the most sophisticated and versatile space laboratory ever built. It will ultimately house a total of 23 experiment racks for crew support and scientific research. STS-98 is the seventh construction flight to the ISS. Launch of STS-98 is scheduled for Jan. 19 at 2:11 a.m. EST.

Orbiter ECLSS support of Shuttle payloads

NASA Technical Reports Server (NTRS)

Jaax, J. R.; Morris, D. W.; Prince, R. N.

1974-01-01

The orbiter ECLSS (Environmental Control and Life Support System) provides the functions of atmosphere revitalization, crew life support, and active thermal control. This paper describes these functions as they relate to the support of Shuttle payloads, including automated spacecraft, Spacelab and Department of Defense missions. Functional and performance requirements for the orbiter ECLSS which affect payload support are presented for the atmosphere revitalization subsystem, the food, water and waste subsystem, and the active thermal control subsystem. Schematics for these subsystems are also described. Finally, based on the selected orbiter configuration, preliminary design and off-design thermodynamic data are presented to quantify the baseline orbiter capability; to quantify the payload chargeable penalties for increasing this support; and to identify the significant limits of orbiter ECLSS support available to Shuttle payloads.

Environmental effects of the US Antarctic Program`s use of balloons in Antarctica

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

McCold, L.N.; Eddlemon, G.K.; Blasing, T.J.

1995-06-01

The USAP uses balloons in Antarctica to conduct scientific research, to facilitate safe air transport, and to provide data for global weather predictions. However, there is the possibility that balloons or their payloads may adversely affect Antarctic fauna or flora. The purpose of this study is to provide background information upon which the USAP may draw when complying with its responsibilities under the National Environmental Policy Act of 1969, the Antarctic Treaty, and the Madrid Protocol.

KSC-07pd0364

NASA Image and Video Library

2007-02-12

KENNEDY SPACE CENTER, FLA. -- In the payload changeout room (PCR) on Launch Pad 39A, the S3/S4 integrated truss is being moved out of the payload canister. The PCR 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 truss is the payload for Space Shuttle Atlantis on mission STS-117 to the International Space Station. The Atlantis crew will install the new truss segment, retract a set of solar arrays and unfold a new set on the starboard side of the station. Launch is targeted for March 15. Photo credit: NASA/Jack Pfaller

KSC-08pd0342

NASA Image and Video Library

2008-02-15

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 39A at NASA's Kennedy Space Center, the payload canister containing the first section of the Japan Aerospace Exploration Agency's Kibo laboratory and the Canadian Space Agency's two-armed robotic system, Dextre, is lifted up toward the payload changeout room in the rotating service structure. Umbilical lines are still attached. 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 an orbiter's payload bay. The payload will be installed into Endeavour for launch on the STS-123 mission targeted for March 11. Photo credit: NASA/Kim Shiflett

Flight evaluation of Spacelab 1 payload thermal/ECS interfaces

NASA Technical Reports Server (NTRS)

Ray, C. D.; Humphries, W. R.; Patterson, W. C.

1984-01-01

The Spacelab (SL-1) thermal/Environmental Control Systems (ECS) are discussed. Preflight analyses and flight data are compared in order to validate payload to Spacelab interfaces as well as corroborate modeling/analysis techniques. In doing so, a brief description of the Spacelab 1 payload configuration and the interactive Spacelab thermal/ECS systems are given. In particular, these interfaces address equipment cooling air, thermal and fluid conditions, humidity levels, both freon and water loop temperatures and load states, as well as passive radiant environment interfaces.

KSC-08pd3127

NASA Image and Video Library

2008-10-15

CAPE CANAVERAL, Fla. – After transfer of space shuttle Atlantis’ HST payload on Launch Pad 39A on NASA's Kennedy Space Center in Florida, the payload canister is lowered toward the transporter below. The red umbilical lines keep the payload in an environmentally controlled environment. The payload comprises four carriers holding various equipment for the mission. The hardware will be transported back to Kennedy’s Payload Hazardous Servicing Facility where it will be stored until a new target launch date can be set for Atlantis’ STS-125 mission in 2009. Atlantis’ October target launch date was delayed after a device on board Hubble used in the storage and transmission of science data to Earth shut down on Sept. 27. Replacing the broken device will be added to Atlantis’ servicing mission to the telescope. Photo credit: NASA/Kim Shiflett

KSC-08pd3128

NASA Image and Video Library

2008-10-15

CAPE CANAVERAL, Fla. – After transfer of space shuttle Atlantis’ HST payload on Launch Pad 39A on NASA's Kennedy Space Center in Florida, the payload canister has been lowered onto the transporter. Umbilical lines keep the payload in an environmentally controlled environment. The payload comprises four carriers holding various equipment for the mission. The hardware will be transported back to Kennedy’s Payload Hazardous Servicing Facility where it will be stored until a new target launch date can be set for Atlantis’ STS-125 mission in 2009. Atlantis’ October target launch date was delayed after a device on board Hubble used in the storage and transmission of science data to Earth shut down on Sept. 27. Replacing the broken device will be added to Atlantis’ servicing mission to the telescope. Photo credit: NASA/Kim Shiflett

Payload test philosophy. [JPL views on qualification/acceptance testing

NASA Technical Reports Server (NTRS)

Gindorf, T.

1979-01-01

The general philosophy of how JPL views payload qualification/acceptance testing for programs that are done either in-house or by contractors is described. Particular attention is given to mission risk classifications, preliminary critical design reviews, environmental design requirements, the thermal and dynamics development tests, and the flight spacecraft system test.

76 FR 72218 - National Environmental Policy Act; NASA Routine Payloads on Expendable Launch Vehicles

Federal Register 2010, 2011, 2012, 2013, 2014

2011-11-22

...; NASA Routine Payloads on Expendable Launch Vehicles AGENCY: National Aeronautics and Space... (CEQ) Regulations for Implementing the Procedural Provisions of NEPA (40 CFR parts 1500-1508), and NASA policy and procedures (14 CFR part 1216 subpart 1216.3), NASA has made a Finding of No Significant Impact...

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.

The Z1 truss is transported to Launch Pad 39A

NASA Technical Reports Server (NTRS)

2000-01-01

At Launch Pad 39A, workers attach umbilical hoses onto the payload canister with the Integrated Truss Structure Z1 inside. The hoses will maintain the environmentally controlled environment while the canister is lifted up the Rotating Service Structure to the Payload Changeout Room. There the Z1 truss will be removed and later transferred to Space Shuttle Discovery's payload bay. The Z1 truss is the first of 10 that will become the backbone of the International Space Station, eventually stretching the length of a football field. Along with its companion payload, the third Pressurized Mating Adapter, the Z1 is scheduled to be launched aboard Discovery Oct. 5 at 9:38 p.m. EDT.

KSC00pp1353

NASA Image and Video Library

2000-09-13

KENNEDY SPACE CENTER, Fla. -- At Launch Pad 39A, workers attach umbilical hoses onto the payload canister with the Integrated Truss Structure Z1 inside. The hoses will maintain the environmentally controlled environment while the canister is lifted up the Rotating Service Structure to the Payload Changeout Room. There the Z1 truss will be removed and later transferred to Space Shuttle Discovery’s payload bay. The Z1 truss is the first of 10 that will become the backbone of the International Space Station, eventually stretching the length of a football field. Along with its companion payload, the third Pressurized Mating Adapter, the Z1 is scheduled to be launched aboard Discovery Oct. 5 at 9:38 p.m. EDT

KSC-00pp1353

NASA Image and Video Library

2000-09-13

KENNEDY SPACE CENTER, Fla. -- At Launch Pad 39A, workers attach umbilical hoses onto the payload canister with the Integrated Truss Structure Z1 inside. The hoses will maintain the environmentally controlled environment while the canister is lifted up the Rotating Service Structure to the Payload Changeout Room. There the Z1 truss will be removed and later transferred to Space Shuttle Discovery’s payload bay. The Z1 truss is the first of 10 that will become the backbone of the International Space Station, eventually stretching the length of a football field. Along with its companion payload, the third Pressurized Mating Adapter, the Z1 is scheduled to be launched aboard Discovery Oct. 5 at 9:38 p.m. EDT

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.

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.

Shuttle payload bay dynamic environments: Summary and conclusion report for STS flights 1-5 and 9

NASA Technical Reports Server (NTRS)

Oconnell, M.; Garba, J.; Kern, D.

1984-01-01

The vibration, acoustic and low frequency loads data from the first 5 shuttle flights are presented. The engineering analysis of that data is also presented. Vibroacoustic data from STS-9 are also presented because they represent the only data taken on a large payload. Payload dynamic environment predictions developed by the participation of various NASA and industrial centers are presented along with a comparison of analytical loads methodology predictions with flight data, including a brief description of the methodologies employed in developing those predictions for payloads. The review of prediction methodologies illustrates how different centers have approached the problems of developing shuttle dynamic environmental predictions and criteria. Ongoing research activities related to the shuttle dynamic environments are also described. Analytical software recently developed for the prediction of payload acoustic and vibration environments are also described.

KSC00pp0369

NASA Image and Video Library

2000-03-21

KENNEDY SPACE CENTER, FLA. -- At Launch Pad 39A, the payload canister with the SPACEHAB Double Module and the Integrated Cargo Carrier (ICC) inside is lifted off the payload transporter toward the Payload Changeout Room (PCR) on the Rotating Service Structure (RSS). The PCR is an environmentally controlled facility supporting cargo delivery to the pad and vertical installation in the orbiter cargo bay. At right of the RSS is the Fixed Service Structure. The primary payloads on mission STS-101, the module and ICC contain internal logistics and resupply cargo for restoring full redundancy to the International Space Station power system in preparation for the arrival of the next pressurized module, the Russian-built Zvezda. The payloads will be transferred to Space Shuttle Atlantis after Atlantis rolls out to the pad. Launch of Atlantis on mission STS-101 is scheduled no earlier than April 17, 2000

KSC-00pp0369

NASA Image and Video Library

2000-03-21

KENNEDY SPACE CENTER, FLA. -- At Launch Pad 39A, the payload canister with the SPACEHAB Double Module and the Integrated Cargo Carrier (ICC) inside is lifted off the payload transporter toward the Payload Changeout Room (PCR) on the Rotating Service Structure (RSS). The PCR is an environmentally controlled facility supporting cargo delivery to the pad and vertical installation in the orbiter cargo bay. At right of the RSS is the Fixed Service Structure. The primary payloads on mission STS-101, the module and ICC contain internal logistics and resupply cargo for restoring full redundancy to the International Space Station power system in preparation for the arrival of the next pressurized module, the Russian-built Zvezda. The payloads will be transferred to Space Shuttle Atlantis after Atlantis rolls out to the pad. Launch of Atlantis on mission STS-101 is scheduled no earlier than April 17, 2000

KSC-08pd3126

NASA Image and Video Library

2008-10-15

CAPE CANAVERAL, Fla. – After transfer of space shuttle Atlantis’ HST payload on Launch Pad 39A on NASA's Kennedy Space Center in Florida, the payload canister, at left, is lowered toward the transporter below. The red umbilical lines keep the payload in an environmentally controlled environment. The payload comprises four carriers holding various equipment for the mission. The hardware will be transported back to Kennedy’s Payload Hazardous Servicing Facility where it will be stored until a new target launch date can be set for Atlantis’ STS-125 mission in 2009. Atlantis’ October target launch date was delayed after a device on board Hubble used in the storage and transmission of science data to Earth shut down on Sept. 27. Replacing the broken device will be added to Atlantis’ servicing mission to the telescope. Photo credit: NASA/Kim Shiflett

KSC-08pd3125

NASA Image and Video Library

2008-10-15

CAPE CANAVERAL, Fla. – After transfer of space shuttle Atlantis’ HST payload on Launch Pad 39A on NASA's Kennedy Space Center in Florida, the payload canister, at left, is lowered toward the transporter below. The red umbilical lines keep the payload in an environmentally controlled environment. The payload comprises four carriers holding various equipment for the mission. The hardware will be transported back to Kennedy’s Payload Hazardous Servicing Facility where it will be stored until a new target launch date can be set for Atlantis’ STS-125 mission in 2009. Atlantis’ October target launch date was delayed after a device on board Hubble used in the storage and transmission of science data to Earth shut down on Sept. 27. Replacing the broken device will be added to Atlantis’ servicing mission to the telescope. Photo credit: NASA/Kim Shiflett

KSC-08pd2798

NASA Image and Video Library

2008-09-21

CAPE CANAVERAL, Fla. - On Launch Pad 39A at NASA's Kennedy Space Center, the payload canister is lifted to the payload changeout room above. The canister contains four carriers holding various equipment for the STS-125 mission aboard space shuttle Atlantis to service NASA’s Hubble Space Telescope. 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 shuttle’s payload bay. Launch of Atlantis is targeted for Oct. 10. Photo credit: NASA/Jack Pfaller

KSC-08pd2796

NASA Image and Video Library

2008-09-21

CAPE CANAVERAL, Fla. - On Launch Pad 39A at NASA's Kennedy Space Center, the payload canister is lifted toward the payload changeout room above. The canister contains four carriers holding various equipment for the STS-125 mission aboard space shuttle Atlantis to service NASA’s Hubble Space Telescope. 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 shuttle’s payload bay. Launch of Atlantis is targeted for Oct. 10. Photo credit: NASA/Jack Pfaller

KSC-08pd2797

NASA Image and Video Library

2008-09-21

CAPE CANAVERAL, Fla. - On Launch Pad 39A at NASA's Kennedy Space Center, the payload canister is lifted toward the payload changeout room above. The canister contains four carriers holding various equipment for the STS-125 mission aboard space shuttle Atlantis to service NASA’s Hubble Space Telescope. 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 shuttle’s payload bay. Launch of Atlantis is targeted for Oct. 10. Photo credit: NASA/Jack Pfaller

GOES-R Encapsulation

NASA Image and Video Library

2016-10-21

The two halves of the payload fairing are fully closed around the Geostationary Operational Environmental Satellite (GOES-R) inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

Status report on the activities of National Balloon Facility at Hyderabad

NASA Astrophysics Data System (ADS)

Shankarnarayan, Sreenivasan; S, Sreenivasan; Shankarnarayan, Sreenivasan; Manchanda, R. K.; Subba Rao Jonnalagadda, Venkata; Buduru, Suneelkumar

National balloon facility at Hyderabad has been mandated to provide launch support for Indian and International scientific balloon experiments and also perform the necessary research and development in the design and fabrication of plastic balloons. In the last 4 years, since our last report, NBF has launched many successful balloon flights for the astronomy payloads and a large number of high altitude GPS Sonde flights at different places in the country. We have also continued our efforts on qualification of raw materials for zero-failure performance of our balloons and major focus on upgrading of various facilities and load-line instrumentation for launching from remote sites. We foresee a surge of balloon based experimental activity for in-situ measurements in atmospheric sciences and concept validation payloads for future space based instruments. A new centre for research in Environmental Sciences and Payload Engineering (ESPE) has also been set up at the National Balloon Facility campus to develop and conduct research in various aspects of Environmental sciences in collaboration with other groups, with a specific goal to identify, development of advanced technologies leading to an improved understanding of the earth system. The Payload Engineering facility is geared to the Design and Fabrication of Micro and Nano Satellites and will act as Inter -University Centre for payload fabrication. In this paper we present an overview of the present and planned activities in scientific ballooning at National Balloon Facility Hyderabad.

KSC-08pd2704

NASA Image and Video Library

2008-09-18

CAPE CANAVERAL, Fla. - The payload canister moves back into the environmentally controlled high bay of the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center. The canister was moved out of the high bay during contamination of the Super Lightweight Integration Carrier, one of four associated with the STS-125 mission to service the Hubble Space Telescope. The carriers are being installed in the payload canister for transfer to Launch Pad 39A. At the pad, all the carriers will be loaded into space shuttle Atlantis’ payload bay. Launch of Atlantis is targeted for Oct. 10. On the left next to the canister is the Multi-Use Logistic Equipment, or MULE, carrier, which will be transferred to the canister. Photo credit: NASA/Jack Pfaller

A white super-stable source for the metrology of astronomical photometers

NASA Astrophysics Data System (ADS)

Wildi, F. P.; Deline, A.; Chazelas, B.

2015-09-01

The testing of photometers and in particular the testing of high precision photometers for the detection of planetary transits requires a light source which photometric stability is to par or better than the goal stability of the photometer to be tested. In the frame of the CHEOPS mission, a comprehensive calibration bench has been developed. Aside from measuring the sensibility of the CHEOPS payload to the different environmental conditions, this bench will also be used to test the relative accuracy of the payload. A key element of this bench is an extremely stable light source that is used to create an artificial star which is then projected into the payload's telescope. We present here the development of this payload and the performance achieved.

KSC-2009-4354

NASA Image and Video Library

2009-07-31

CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the payload canister is lifted up to the Payload Changeout Room in the rotating service structure. Umbilical lines that keep the payload in an environmentally controlled environment are still attached. Inside is the payload for space shuttle Discovery and the STS-128 mission, the Multi-Purpose Logistics Module Leonardo and the Lightweight Multi-Purpose Experiment Support Structure Carrier. Discovery's 13-day flight will deliver a new crew member and 33,000 pounds of equipment to the station. The equipment includes science and storage racks, a freezer to store research samples, a new sleeping compartment and the COLBERT treadmill. Launch of Discovery on its STS-128 mission is targeted for August 25. Photo credit: NASA/Kim Shiflett

KSC-2009-4352

NASA Image and Video Library

2009-07-31

CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the payload canister is lifted up to the Payload Changeout Room in the rotating service structure. Umbilical lines that keep the payload in an environmentally controlled environment are still attached. Inside is the payload for space shuttle Discovery and the STS-128 mission, the Multi-Purpose Logistics Module Leonardo and the Lightweight Multi-Purpose Experiment Support Structure Carrier. Discovery's 13-day flight will deliver a new crew member and 33,000 pounds of equipment to the station. The equipment includes science and storage racks, a freezer to store research samples, a new sleeping compartment and the COLBERT treadmill. Launch of Discovery on its STS-128 mission is targeted for August 25. Photo credit: NASA/Kim Shiflett

KSC-2009-4355

NASA Image and Video Library

2009-07-31

CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the payload canister is lifted up to the Payload Changeout Room in the rotating service structure. Umbilical lines that keep the payload in an environmentally controlled environment are still attached. Inside is the payload for space shuttle Discovery and the STS-128 mission, the Multi-Purpose Logistics Module Leonardo and the Lightweight Multi-Purpose Experiment Support Structure Carrier. Discovery's 13-day flight will deliver a new crew member and 33,000 pounds of equipment to the station. The equipment includes science and storage racks, a freezer to store research samples, a new sleeping compartment and the COLBERT treadmill. Launch of Discovery on its STS-128 mission is targeted for August 25. Photo credit: NASA/Kim Shiflett

KSC-2009-4353

NASA Image and Video Library

2009-07-31

CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the payload canister is lifted up to the Payload Changeout Room in the rotating service structure. Umbilical lines that keep the payload in an environmentally controlled environment are still attached. Inside is the payload for space shuttle Discovery and the STS-128 mission, the Multi-Purpose Logistics Module Leonardo and the Lightweight Multi-Purpose Experiment Support Structure Carrier. Discovery's 13-day flight will deliver a new crew member and 33,000 pounds of equipment to the station. The equipment includes science and storage racks, a freezer to store research samples, a new sleeping compartment and the COLBERT treadmill. Launch of Discovery on its STS-128 mission is targeted for August 25. Photo credit: NASA/Kim Shiflett

KSC-00pp0367

NASA Image and Video Library

2000-03-21

KENNEDY SPACE CENTER, FLA. -- At Launch Pad 39A, the payload canister with the SPACEHAB Double Module and Integrated Cargo Carrier (ICC) inside is lifted up the Rotating Service Structure toward the Payload Changeout Room, an environmentally controlled facility supporting cargo delivery to the pad and vertical installation in the orbiter cargo bay. The primary payloads on mission STS-101, the module and ICC contain internal logistics and resupply cargo for restoring full redundancy to the International Space Station power system in preparation for the arrival of the next pressurized module, the Russian-built Zvezda. The payloads will be transferred to Space Shuttle Atlantis after Atlantis rolls out to the pad. Launch of Atlantis on mission STS-101 is scheduled no earlier than April 17, 2000

KSC00pp0367

NASA Image and Video Library

2000-03-21

KENNEDY SPACE CENTER, FLA. -- At Launch Pad 39A, the payload canister with the SPACEHAB Double Module and Integrated Cargo Carrier (ICC) inside is lifted up the Rotating Service Structure toward the Payload Changeout Room, an environmentally controlled facility supporting cargo delivery to the pad and vertical installation in the orbiter cargo bay. The primary payloads on mission STS-101, the module and ICC contain internal logistics and resupply cargo for restoring full redundancy to the International Space Station power system in preparation for the arrival of the next pressurized module, the Russian-built Zvezda. The payloads will be transferred to Space Shuttle Atlantis after Atlantis rolls out to the pad. Launch of Atlantis on mission STS-101 is scheduled no earlier than April 17, 2000

Study of space shuttle environmental control and life support problems

NASA Technical Reports Server (NTRS)

Dibble, K. P.; Riley, F. E.

1971-01-01

Four problem areas were treated: (1) cargo module environmental control and life support systems; (2) space shuttle/space station interfaces; (3) thermal control considerations for payloads; and (4) feasibility of improving system reusability.

GOES-R Encapsulation

NASA Image and Video Library

2016-10-21

Team members with United Launch Alliance (ULA) prepare the Geostationary Operational Environmental Satellite (GOES-R) for encapsulation in the payload fairing inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a ULA Atlas V rocket in November.

A preliminary investigation of the environmental Control and Life Support Subsystems (EC/LSS) for animal and plant experiment payloads

NASA Technical Reports Server (NTRS)

Wells, H. B.

1972-01-01

A preliminary study of the environmental control and life support subsystems (EC/LSS) necessary for an earth orbital spacecraft to conduct biological experiments is presented. The primary spacecraft models available for conducting these biological experiments are the space shuttle and modular space station. The experiments would be housed in a separate module that would be contained in either the shuttle payload bay or attached to the modular space station. This module would be manned only for experiment-related tasks, and would contain a separate EC/LSS for the crew and animals. Metabolic data were tabulated on various animals that are considered useful for a typical experiment program. The minimum payload for the 30-day space shuttle module was found to require about the equivalent of a one-man EC/LSS; however, the selected two-man shuttle assemblies will give a growth and contingency factor of about 50 percent. The maximum payloads for the space station mission will require at least a seven-man EC/LSS for the laboratory colony and a nine-man EC/LSS for the centrifuge colony. There is practically no room for growth or contingencies in these areas.

Final payload test results for the RemoveDebris active debris removal mission

NASA Astrophysics Data System (ADS)

Forshaw, Jason L.; Aglietti, Guglielmo S.; Salmon, Thierry; Retat, Ingo; Roe, Mark; Burgess, Christopher; Chabot, Thomas; Pisseloup, Aurélien; Phipps, Andy; Bernal, Cesar; Chaumette, François; Pollini, Alexandre; Steyn, Willem H.

2017-09-01

Since the beginning of the space era, a significant amount of debris has progressively been generated in space. Active Debris Removal (ADR) missions have been suggested as a way of limiting and controlling future growth in orbital space debris by actively deploying vehicles to remove debris. The European Commission FP7-sponsored RemoveDebris mission, which started in 2013, draws on the expertise of some of Europe's most prominent space institutions in order to demonstrate key ADR technologies in a cost effective ambitious manner: net capture, harpoon capture, vision-based navigation, dragsail de-orbiting. This paper provides an overview of some of the final payload test results before launch. A comprehensive test campaign is underway on both payloads and platform. The tests aim to demonstrate both functional success of the experiments and that the experiments can survive the space environment. Space environmental tests (EVT) include vibration, thermal, vacuum or thermal-vacuum (TVAC) and in some cases EMC and shock. The test flow differs for each payload and depends on the heritage of the constituent payload parts. The paper will also provide an update to the launch, expected in 2017 from the International Space Station (ISS), and test philosophy that has been influenced from the launch and prerequisite NASA safety review for the mission. The RemoveDebris mission aims to be one of the world's first in-orbit demonstrations of key technologies for active debris removal and is a vital prerequisite to achieving the ultimate goal of a cleaner Earth orbital environment.

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.

KSC-08pd2799

NASA Image and Video Library

2008-09-21

CAPE CANAVERAL, Fla. - On Launch Pad 39A at NASA's Kennedy Space Center, the payload canister is in place at the payload changeout room on the rotating service structure. The canister contains four carriers holding various equipment for the STS-125 mission aboard space shuttle Atlantis to service NASA’s Hubble Space Telescope. At right is Atlantis, atop the mobile launcher platform. 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 shuttle’s payload bay. Launch of Atlantis is targeted for Oct. 10. Photo credit: NASA/Jack Pfaller

Payload advisory panel recommendations

NASA Technical Reports Server (NTRS)

Moore, Berrien, III

1991-01-01

The Payload Advisory Panel proposes a restructured Earth Observing System (EOS) mission to address high-priority science and environmental policy issues in Earth System Science. These issues have been identified through studies conducted by the Intergovernmental Panel on Climate Change (IPCC), the United States Environmental Protection Agency (EPA), and the Committee on Earth and Environmental Sciences (CEES). The restructured EOS defers efforts to improve the understanding of the middle and upper stratosphere and solid earth geophysics. The strategy of the mission combines high priority new measurements with continuation of critical data sets begun by missions which precede EOS. Collaborative arrangements with international partners are an essential part of the program and additional arrangements are posed. The need for continuity in Earth observations and the urgency of environmental questions require launch of some EOS elements as soon as possible. They further require maintenance of the EOS objective of obtaining consistent 15-year measurement records.

Payload advisory panel recommendations

NASA Astrophysics Data System (ADS)

Moore, Berrien, III

1991-11-01

The Payload Advisory Panel proposes a restructured Earth Observing System (EOS) mission to address high-priority science and environmental policy issues in Earth System Science. These issues have been identified through studies conducted by the Intergovernmental Panel on Climate Change (IPCC), the United States Environmental Protection Agency (EPA), and the Committee on Earth and Environmental Sciences (CEES). The restructured EOS defers efforts to improve the understanding of the middle and upper stratosphere and solid earth geophysics. The strategy of the mission combines high priority new measurements with continuation of critical data sets begun by missions which precede EOS. Collaborative arrangements with international partners are an essential part of the program and additional arrangements are posed. The need for continuity in Earth observations and the urgency of environmental questions require launch of some EOS elements as soon as possible. They further require maintenance of the EOS objective of obtaining consistent 15-year measurement records.

STS-97 P6 truss payload canister is lifted into payload changeout room

NASA Technical Reports Server (NTRS)

2000-01-01

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 that supports payload delivery at the pad and subsequent vertical installation in the orbiter payload bay. Attached to the canister are the red umbilical lines that maintain the controlled environment inside. 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.

Selection of extreme environmental conditions, albedo coefficient and Earth infrared radiation, for polar summer Long Duration Balloon missions

NASA Astrophysics Data System (ADS)

González-Llana, Arturo; González-Bárcena, David; Pérez-Grande, Isabel; Sanz-Andrés, Ángel

2018-07-01

The selection of the extreme thermal environmental conditions -albedo coefficient and Earth infrared radiation- for the thermal design of stratospheric balloon missions is usually based on the methodologies applied in space missions. However, the particularities of stratospheric balloon missions, such as the much higher residence time of the balloon payload over a determined area, make necessary an approach centered in the actual environment the balloon is going to find, in terms of geographic area and season of flight. In this sense, this work is focussed on stratospheric balloon missions circumnavigating the North Pole during the summer period. Pairs of albedo and Earth infrared radiation satellite data restricted to this area and season of interest have been treated statistically. Furthermore, the environmental conditions leading to the extreme temperatures of the payload depend in turn on the surface finish, and more particularly on the ratio between the solar absorptance and the infrared emissivity α/ε. A simple but representative thermal model of a balloon and its payload has been set up in order to identify the pairs of albedo coefficient and Earth infrared radiation leading to extreme temperatures for each value of α/ε.

KSC00pp0370

NASA Image and Video Library

2000-03-21

KENNEDY SPACE CENTER, FLA. -- The doors of the payload canister open in the Payload Changeout Room (PCR) at Launch Pad 39A to reveal the SPACEHAB Double Module (bottom) and Integrated Cargo Carrier (ICC). Part of the Rotating Service Structure, the PCR is an environmentally controlled facility supporting cargo delivery to the pad and vertical installation in the orbiter cargo bay. The primary payloads on mission STS-101, the module and ICC contain internal logistics and resupply cargo for restoring full redundancy to the International Space Station power system in preparation for the arrival of the next pressurized module, the Russian-built Zvezda. The payloads will be transferred to Space Shuttle Atlantis after Atlantis rolls out to the pad. Launch of Atlantis on mission STS-101 is scheduled no earlier than April 17, 2000

KSC00pp0371

NASA Image and Video Library

2000-03-21

KENNEDY SPACE CENTER, FLA. -- The SPACEHAB Double Module (bottom) and Integrated Cargo Carrier (above) are ready to be moved from the payload canister into the Payload Changeout Room (PCR) at Launch Pad 39A. Part of the Rotating Service Structure, the PCR is an environmentally controlled facility supporting cargo delivery to the pad and vertical installation in the orbiter cargo bay. The primary payloads on mission STS-101, the module and ICC contain internal logistics and resupply cargo for restoring full redundancy to the International Space Station power system in preparation for the arrival of the next pressurized module, the Russian-built Zvezda. The payloads will be transferred to Space Shuttle Atlantis after Atlantis rolls out to the pad. Launch of Atlantis on mission STS-101 is scheduled no earlier than April 17, 2000

KSC-00pp0371

NASA Image and Video Library

2000-03-21

KENNEDY SPACE CENTER, FLA. -- The SPACEHAB Double Module (bottom) and Integrated Cargo Carrier (above) are ready to be moved from the payload canister into the Payload Changeout Room (PCR) at Launch Pad 39A. Part of the Rotating Service Structure, the PCR is an environmentally controlled facility supporting cargo delivery to the pad and vertical installation in the orbiter cargo bay. The primary payloads on mission STS-101, the module and ICC contain internal logistics and resupply cargo for restoring full redundancy to the International Space Station power system in preparation for the arrival of the next pressurized module, the Russian-built Zvezda. The payloads will be transferred to Space Shuttle Atlantis after Atlantis rolls out to the pad. Launch of Atlantis on mission STS-101 is scheduled no earlier than April 17, 2000

KSC-00pp0370

NASA Image and Video Library

2000-03-21

KENNEDY SPACE CENTER, FLA. -- The doors of the payload canister open in the Payload Changeout Room (PCR) at Launch Pad 39A to reveal the SPACEHAB Double Module (bottom) and Integrated Cargo Carrier (ICC). Part of the Rotating Service Structure, the PCR is an environmentally controlled facility supporting cargo delivery to the pad and vertical installation in the orbiter cargo bay. The primary payloads on mission STS-101, the module and ICC contain internal logistics and resupply cargo for restoring full redundancy to the International Space Station power system in preparation for the arrival of the next pressurized module, the Russian-built Zvezda. The payloads will be transferred to Space Shuttle Atlantis after Atlantis rolls out to the pad. Launch of Atlantis on mission STS-101 is scheduled no earlier than April 17, 2000

Manned space flight nuclear system safety. Volume 4: Space shuttle nuclear system transportation. Part 1: Space shuttle nuclear safety

NASA Technical Reports Server (NTRS)

1972-01-01

An analysis of the nuclear safety aspects (design and operational considerations) in the transport of nuclear payloads to and from earth orbit by the space shuttle is presented. Three representative nuclear payloads used in the study were: (1) the zirconium hydride reactor Brayton power module, (2) the large isotope Brayton power system and (3) small isotopic heat sources which can be a part of an upper stage or part of a logistics module. Reference data on the space shuttle and nuclear payloads are presented in an appendix. Safety oriented design and operational requirements were identified to integrate the nuclear payloads in the shuttle mission. Contingency situations were discussed and operations and design features were recommended to minimize the nuclear hazards. The study indicates the safety, design and operational advantages in the use of a nuclear payload transfer module. The transfer module can provide many of the safety related support functions (blast and fragmentation protection, environmental control, payload ejection) minimizing the direct impact on the shuttle.

GOES-R Encapsulation

NASA Image and Video Library

2016-10-21

Team members with United Launch Alliance (ULA) monitor the progress as the two halves of the payload fairing close around the Geostationary Operational Environmental Satellite (GOES-R) inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a ULA Atlas V rocket in November.

Applicability of the Remote Mobile Emplacement Package (RMEP) design as a mobility aid for proposed post-84 Mars missions, phase O

NASA Technical Reports Server (NTRS)

1978-01-01

The results of study to determine the applicability of the Remote Mobile Emplacement Package (RMEP) design concept as a mobility aid for the proposed post-'84 Mars missions are presented. The RMEP wheel and mobility subsystem parameters: wheel tire size, weight, stowed volume, and environmental effects; obstacle negotiation; reliability and wear; motor and drive train; and electrical power demand were reviewed. Results indicated that: (1) the basic RMEP wheel design would be satisfactory, with additional attention to heating, side loading, tread wear and ultraviolet radiation protection; (2) motor and drive train power requirements on Mars would be less than on Earth; and (3) the mobility electrical power requirements would be small enough to offer the option of operating the Mars mini rover untethered. Payload power required for certain sampling functions would preclude the use of battery power for these missions. Hazard avoidance and reverse direction maneuvers are discussed. Limited examination of vehicle payload integration and thermal design was made, pending establishment of a baseline vehicle/payload design.

Probe design

NASA Technical Reports Server (NTRS)

Cowan, W.

1974-01-01

Outer planetary probe designs consider mission characteristics, structural configuration, delivery mode, scientific payload, environmental extremes, mass properties, and the launch vehicle and spacecraft interface.

KSC00pp0086

NASA Image and Video Library

2000-01-17

One of two new payload transporters for Kennedy Space Center sits on the dock at Port Canaveral. In the background is a cruise ship docked at the Port. The transporters were shipped by barge from their manufacturer, the KAMAG Company of Ulm, Germany. They are used to carry spacecraft and International Space Station elements from payload facilities to and from the launch pads and orbiter hangars. Each transporter is 65 feet long and 22 feet wide and has 24 tires divided between its two axles. The transporter travels 10 miles per hour unloaded, 5 miles per hour when loaded; it weighs up to 172,000 pounds when the canister with payloads rides atop. The transporters will be outfitted with four subsystems for monitoring the environment inside the canister during the payload moves: the Electrical Power System, Environmental Control System, Instrumentation and Communications System, and the Fluids and Gases System. Engineers and technicians are being trained on the transporter's operation and maintenance. The new transporters are replacing the 20-year-old existing Payload Canister Transporter system

KSC-00pp0085

NASA Image and Video Library

2000-01-17

One of two new payload transporters for Kennedy Space Center sits on the dock at Port Canaveral. In the background is a cruise ship docked at the Port. The transporters were shipped by barge from their manufacturer, the KAMAG Company of Ulm, Germany. They are used to carry spacecraft and International Space Station elements from payload facilities to and from the launch pads and orbiter hangars. Each transporter is 65 feet long and 22 feet wide and has 24 tires divided between its two axles. The transporter travels 10 miles per hour unloaded, 5 miles per hour when loaded; it weighs up to 172,000 pounds when the canister with payloads rides atop. The transporters will be outfitted with four subsystems for monitoring the environment inside the canister during the payload moves: the Electrical Power System, Environmental Control System, Instrumentation and Communications System, and the Fluids and Gases System. Engineers and technicians are being trained on the transporter's operation and maintenance. The new transporters are replacing the 20-year-old existing Payload Canister Transporter system

KSC-00pp0086

NASA Image and Video Library

2000-01-17

One of two new payload transporters for Kennedy Space Center sits on the dock at Port Canaveral. In the background is a cruise ship docked at the Port. The transporters were shipped by barge from their manufacturer, the KAMAG Company of Ulm, Germany. They are used to carry spacecraft and International Space Station elements from payload facilities to and from the launch pads and orbiter hangars. Each transporter is 65 feet long and 22 feet wide and has 24 tires divided between its two axles. The transporter travels 10 miles per hour unloaded, 5 miles per hour when loaded; it weighs up to 172,000 pounds when the canister with payloads rides atop. The transporters will be outfitted with four subsystems for monitoring the environment inside the canister during the payload moves: the Electrical Power System, Environmental Control System, Instrumentation and Communications System, and the Fluids and Gases System. Engineers and technicians are being trained on the transporter's operation and maintenance. The new transporters are replacing the 20-year-old existing Payload Canister Transporter system

KSC-00pp0084

NASA Image and Video Library

2000-01-17

One of two new payload transporters for Kennedy Space Center arrives at Port Canaveral. In the background is a cruise ship docked at the Port. The transporters were shipped by barge from their manufacturer, the KAMAG Company of Ulm, Germany. They are used to carry spacecraft and International Space Station elements from payload facilities to and from the launch pads and orbiter hangars. Each transporter is 65 feet long and 22 feet wide and has 24 tires divided between its two axles. The transporter travels 10 miles per hour unloaded, 5 miles per hour when loaded; it weighs up to 172,000 pounds when the canister with payloads rides atop. The transporters will be outfitted with four subsystems for monitoring the environment inside the canister during the payload moves: the Electrical Power System, Environmental Control System, Instrumentation and Communications System, and the Fluids and Gases System. Engineers and technicians are being trained on the transporter's operation and maintenance. The new transporters are replacing the 20-year-old existing Payload Canister Transporter system

KSC00pp0084

NASA Image and Video Library

2000-01-17

One of two new payload transporters for Kennedy Space Center arrives at Port Canaveral. In the background is a cruise ship docked at the Port. The transporters were shipped by barge from their manufacturer, the KAMAG Company of Ulm, Germany. They are used to carry spacecraft and International Space Station elements from payload facilities to and from the launch pads and orbiter hangars. Each transporter is 65 feet long and 22 feet wide and has 24 tires divided between its two axles. The transporter travels 10 miles per hour unloaded, 5 miles per hour when loaded; it weighs up to 172,000 pounds when the canister with payloads rides atop. The transporters will be outfitted with four subsystems for monitoring the environment inside the canister during the payload moves: the Electrical Power System, Environmental Control System, Instrumentation and Communications System, and the Fluids and Gases System. Engineers and technicians are being trained on the transporter's operation and maintenance. The new transporters are replacing the 20-year-old existing Payload Canister Transporter system

KSC00pp0085

NASA Image and Video Library

2000-01-17

One of two new payload transporters for Kennedy Space Center sits on the dock at Port Canaveral. In the background is a cruise ship docked at the Port. The transporters were shipped by barge from their manufacturer, the KAMAG Company of Ulm, Germany. They are used to carry spacecraft and International Space Station elements from payload facilities to and from the launch pads and orbiter hangars. Each transporter is 65 feet long and 22 feet wide and has 24 tires divided between its two axles. The transporter travels 10 miles per hour unloaded, 5 miles per hour when loaded; it weighs up to 172,000 pounds when the canister with payloads rides atop. The transporters will be outfitted with four subsystems for monitoring the environment inside the canister during the payload moves: the Electrical Power System, Environmental Control System, Instrumentation and Communications System, and the Fluids and Gases System. Engineers and technicians are being trained on the transporter's operation and maintenance. The new transporters are replacing the 20-year-old existing Payload Canister Transporter system

A study to define an in-flight dynamics measurement and data applications program for space shuttle payloads

NASA Technical Reports Server (NTRS)

Rader, W. P.; Barrett, S.; Payne, K. R.

1975-01-01

Data measurement and interpretation techniques were defined for application to the first few space shuttle flights, so that the dynamic environment could be sufficiently well established to be used to reduce the cost of future payloads through more efficient design and environmental test techniques. It was concluded that: (1) initial payloads must be given comprehensive instrumentation coverage to obtain detailed definition of acoustics, vibration, and interface loads, (2) analytical models of selected initial payloads must be developed and verified by modal surveys and flight measurements, (3) acoustic tests should be performed on initial payloads to establish realistic test criteria for components and experiments in order to minimize unrealistic failures and retest requirements, (4) permanent data banks should be set up to establish statistical confidence in the data to be used, (5) a more unified design/test specification philosophy is needed, (6) additional work is needed to establish a practical testing technique for simulation of vehicle transients.

Considerations Affecting Satellite and Space Probe Research with Emphasis on the "Scout" as a Launch Vehicle

NASA Technical Reports Server (NTRS)

Posner, Jack (Editor)

1961-01-01

This report reviews a number of the factors which influence space flight experiments. Included are discussions of payload considerations, payload design and packaging, environmental tests, launch facilities, tracking and telemetry requirements, data acquisition, processing and analysis procedures, communication of information, and project management. Particular emphasis is placed on the "Scout" as a launching vehicle. The document includes a description of the geometry of the "Scout" as well as its flight capabilities and limitations. Although oriented toward the "Scout" vehicle and its payload capabilities, the information presented is sufficiently general to be equally applicable to most space vehicle systems.

KSC-07pd0360

NASA Image and Video Library

2007-02-12

KENNEDY SPACE CENTER, FLA. -- In the payload changeout room (PCR) on Launch Pad 39A, the opening doors of the canister reveal the S3/S4 integrated truss inside. The PCR 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 truss is the payload for Space Shuttle Atlantis on mission STS-117 to the International Space Station. The Atlantis crew will install the new truss segment, retract a set of solar arrays and unfold a new set on the starboard side of the station. Launch is targeted for March 15. Photo credit: NASA/Jack Pfaller

KSC-07pd0358

NASA Image and Video Library

2007-02-12

KENNEDY SPACE CENTER, FLA. -- In the payload changeout room (PCR) on Launch Pad 39A, workers prepare to open the canister containing the S3/S4 integrated truss. The PCR 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 truss is the payload for Space Shuttle Atlantis on mission STS-117 to the International Space Station. The Atlantis crew will install the new truss segment, retract a set of solar arrays and unfold a new set on the starboard side of the station. Launch is targeted for March 15. Photo credit: NASA/Jack Pfaller

GOES-R Encapsulation

NASA Image and Video Library

2016-10-21

Team members with United Launch Alliance (ULA) monitor the progress as the two halves of the payload fairing begin to close around the Geostationary Operational Environmental Satellite (GOES-R) inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a ULA Atlas V rocket in November.

KSC-00pp0690

NASA Image and Video Library

2000-05-29

Research scientist Oscar Monje records data associated with ground testing for the first International Space Station plant experiment, scheduled to fly in October 2001. The payload process testing is one of many studies being performed at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

KSC00pp0690

NASA Image and Video Library

2000-05-29

Research scientist Oscar Monje records data associated with ground testing for the first International Space Station plant experiment, scheduled to fly in October 2001. The payload process testing is one of many studies being performed at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

KSC-08pd1013

NASA Image and Video Library

2008-04-24

CAPE CANAVERAL, Fla. -- In the Vertical Integration Facility at NASA's Kennedy Space Center, workers on either side monitor the progress of the payload canister as it is raised to a vertical position. The canister contains the Japanese Experiment Module -Pressurized Module, which will be transported to Launch Pad 39A for space shuttle Discovery’s STS-124 mission. At the pad, the payload will be transferred from the canister into the payload changeout room on the rotating service structure. The changeout room is the enclosed, environmentally controlled portion of the service structure that supports cargo delivery to the pad and subsequent vertical installation into an orbiter's payload bay. On the mission, the STS-124 crew will transport the JEM as well as the Japanese Remote Manipulator System to the International Space Station. The launch of Discovery is targeted for May 31. Photo credit: NASA/Jim Grossmann

KSC-08pd1009

NASA Image and Video Library

2008-04-24

CAPE CANAVERAL, Fla. -- In the Vertical Integration Facility at NASA's Kennedy Space Center, technicians monitor the rotation of the payload canister to a vertical position. The canister contains the Japanese Experiment Module -Pressurized Module. The canister will be transported to Launch Pad 39A for space shuttle Discovery’s STS-124 mission. At the pad, the payload will be transferred from the canister into the payload changeout room on the rotating service structure. The changeout room is the enclosed, environmentally controlled portion of the service structure that supports cargo delivery to the pad and subsequent vertical installation into an orbiter's payload bay. On the mission, the STS-124 crew will transport the JEM as well as the Japanese Remote Manipulator System to the International Space Station. The launch of Discovery is targeted for May 31. Photo credit: NASA/Jim Grossmann

KSC-07pd0349

NASA Image and Video Library

2007-02-12

KENNEDY SPACE CENTER, FLA. -- The payload canister on its transporter sits beneath the payload changeout room on the rotating service structure (RSS) on Launch Pad 39A. The canister contains the S3/S4 integrated truss for mission STS-117 to the International Space Station aboard Space Shuttle Atlantis. Once inside the PCR, the S3/S4 arrays will be transferred into Space Shuttle Atlantis' payload bay after the vehicle has rolled out to the pad. The changeout room is the enclosed, environmentally controlled portion of the RSS that supports cargo delivery to the pad and subsequent vertical installation into the orbiter payload bay. The Atlantis crew will install the new truss segment, retract a set of solar arrays and unfold a new set on the starboard side of the station. Launch is targeted for March 15. Photo credit: NASA/Kim Shiflett

KSC-07pd0348

NASA Image and Video Library

2007-02-12

KENNEDY SPACE CENTER, FLA. -- The payload canister on its transporter arrives on Launch Pad 39A, stopping beneath the payload changeout room on the rotating service structure (RSS). The canister contains the S3/S4 integrated truss for mission STS-117 to the International Space Station aboard Space Shuttle Atlantis. Once inside the PCR, the S3/S4 arrays will be transferred into Space Shuttle Atlantis' payload bay after the vehicle has rolled out to the pad. The changeout room is the enclosed, environmentally controlled portion of the RSS that supports cargo delivery to the pad and subsequent vertical installation into the orbiter payload bay.The Atlantis crew will install the new truss segment, retract a set of solar arrays and unfold a new set on the starboard side of the station. Launch is targeted for March 15. Photo credit: NASA/Kim Shiflett

KSC-08pd1012

NASA Image and Video Library

2008-04-24

CAPE CANAVERAL, Fla. -- In the Vertical Integration Facility at NASA's Kennedy Space Center, the payload canister containing the Japanese Experiment Module -Pressurized Module is being raised to a vertical position. The canister contains the Japanese Experiment Module -Pressurized Module, which will be transported to Launch Pad 39A for space shuttle Discovery’s STS-124 mission. At the pad, the payload will be transferred from the canister into the payload changeout room on the rotating service structure. The changeout room is the enclosed, environmentally controlled portion of the service structure that supports cargo delivery to the pad and subsequent vertical installation into an orbiter's payload bay. On the mission, the STS-124 crew will transport the JEM as well as the Japanese Remote Manipulator System to the International Space Station. The launch of Discovery is targeted for May 31. Photo credit: NASA/Jim Grossmann

KSC-00pp0368

NASA Image and Video Library

2000-03-21

KENNEDY SPACE CENTER, FLA. -- At Launch Pad 39A, the payload canister with the SPACEHAB Double Module and Integrated Cargo Carrier (ICC) inside is lifted up the Rotating Service Structure (RSS) toward the Payload Changeout Room, an environmentally controlled facility supporting cargo delivery to the pad and vertical installation in the orbiter cargo bay. At right of the RSS is the Fixed Service Structure, topped by the 80-foot-tall fiberglass lightning mast. The primary payload on mission STS-101, the module and ICC contain internal logistics and resupply cargo for restoring full redundancy to the International Space Station power system in preparation for the arrival of the next pressurized module, the Russian-built Zvezda. The payloads will be transferred to Space Shuttle Atlantis after Atlantis rolls out to the pad. Launch of Atlantis on mission STS-101 is scheduled no earlier than April 17, 2000

KSC00pp0368

NASA Image and Video Library

2000-03-21

KENNEDY SPACE CENTER, FLA. -- At Launch Pad 39A, the payload canister with the SPACEHAB Double Module and Integrated Cargo Carrier (ICC) inside is lifted up the Rotating Service Structure (RSS) toward the Payload Changeout Room, an environmentally controlled facility supporting cargo delivery to the pad and vertical installation in the orbiter cargo bay. At right of the RSS is the Fixed Service Structure, topped by the 80-foot-tall fiberglass lightning mast. The primary payload on mission STS-101, the module and ICC contain internal logistics and resupply cargo for restoring full redundancy to the International Space Station power system in preparation for the arrival of the next pressurized module, the Russian-built Zvezda. The payloads will be transferred to Space Shuttle Atlantis after Atlantis rolls out to the pad. Launch of Atlantis on mission STS-101 is scheduled no earlier than April 17, 2000

KSC-08pd1014

NASA Image and Video Library

2008-04-24

CAPE CANAVERAL, Fla. -- In the Vertical Integration Facility at NASA's Kennedy Space Center, the payload canister containing the Japanese Experiment Module -Pressurized Module is suspended vertically after rotation from the horizontal. The canister contains the Japanese Experiment Module -Pressurized Module, which will be transported to Launch Pad 39A for space shuttle Discovery’s STS-124 mission. At the pad, the payload will be transferred from the canister into the payload changeout room on the rotating service structure. The changeout room is the enclosed, environmentally controlled portion of the service structure that supports cargo delivery to the pad and subsequent vertical installation into an orbiter's payload bay. On the mission, the STS-124 crew will transport the JEM as well as the Japanese Remote Manipulator System to the International Space Station. The launch of Discovery is targeted for May 31. Photo credit: NASA/Jim Grossmann

Common aperture multispectral spotter camera: Spectro XR

NASA Astrophysics Data System (ADS)

Petrushevsky, Vladimir; Freiman, Dov; Diamant, Idan; Giladi, Shira; Leibovich, Maor

2017-10-01

The Spectro XRTM is an advanced color/NIR/SWIR/MWIR 16'' payload recently developed by Elbit Systems / ELOP. The payload's primary sensor is a spotter camera with common 7'' aperture. The sensor suite includes also MWIR zoom, EO zoom, laser designator or rangefinder, laser pointer / illuminator and laser spot tracker. Rigid structure, vibration damping and 4-axes gimbals enable high level of line-of-sight stabilization. The payload's list of features include multi-target video tracker, precise boresight, strap-on IMU, embedded moving map, geodetic calculations suite, and image fusion. The paper describes main technical characteristics of the spotter camera. Visible-quality, all-metal front catadioptric telescope maintains optical performance in wide range of environmental conditions. High-efficiency coatings separate the incoming light into EO, SWIR and MWIR band channels. Both EO and SWIR bands have dual FOV and 3 spectral filters each. Several variants of focal plane array formats are supported. The common aperture design facilitates superior DRI performance in EO and SWIR, in comparison to the conventionally configured payloads. Special spectral calibration and color correction extend the effective range of color imaging. An advanced CMOS FPA and low F-number of the optics facilitate low light performance. SWIR band provides further atmospheric penetration, as well as see-spot capability at especially long ranges, due to asynchronous pulse detection. MWIR band has good sharpness in the entire field-of-view and (with full HD FPA) delivers amount of detail far exceeding one of VGA-equipped FLIRs. The Spectro XR offers level of performance typically associated with larger and heavier payloads.

Adding Liquid Payloads Effects to the 6-DOF Trajectory of Spinning Projectiles

DTIC Science & Technology

2010-03-01

Adding Liquid Payloads Effects to the 6-DOF Trajectory of Spinning Projectiles by Gene R. Cooper ARL-TR-5118 March 2010...Liquid Payloads Effects to the 6-DOF Trajectory of Spinning Projectiles Gene R. Cooper Weapons and Materials Research Directorate, ARL...September 2007 4. TITLE AND SUBTITLE Adding Liquid Payloads Effects to the 6-DOF Trajectory of Spinning Projectiles 5a. CONTRACT NUMBER 5b. GRANT

Trajectory Prediction of Spin-Stabilized Projectiles With a Steady Liquid Payload

DTIC Science & Technology

2011-11-01

analysis assumes the effect of a liquid payload is similar to the Magnus effect . Spectral analysis used to numerically compute liquid-fill induced...the internal motion of a liquid payload can induce destabilizing moments on the projectile. This report creates a method to include the effect of... effect , liquid payload moments are added to the applied loads on the projectile. These loads are computed by solving the linearized Navier-Stokes

KSC00pp1730

NASA Image and Video Library

2000-11-14

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 39B, the payload transport canister waits at the base of the Rotating Service Structure (RSS) with the P6 integrated truss segment inside. The canister will be lifted up to the payload changeout room (PCR) where the P6 will be removed for transfer to Space Shuttle Endeavour’s payload bay. The PCR is the enclosed, environmentally controlled portion of the RSS that supports payload delivery at the pad and subsequent vertical installation in the orbiter 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-00pp1730

NASA Image and Video Library

2000-11-14

KENNEDY SPACE CENTER, FLA. -- On Launch Pad 39B, the payload transport canister waits at the base of the Rotating Service Structure (RSS) with the P6 integrated truss segment inside. The canister will be lifted up to the payload changeout room (PCR) where the P6 will be removed for transfer to Space Shuttle Endeavour’s payload bay. The PCR is the enclosed, environmentally controlled portion of the RSS that supports payload delivery at the pad and subsequent vertical installation in the orbiter 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

Payload Fuel Energy Efficiency as a Metric for Aviation Environmental Performance

DOT National Transportation Integrated Search

2008-09-14

Aviation provides productivity in the form of transporting passengers and cargo long distances in a shorter period of time than is available via land or sea. Given the recent rise in fuel prices and environmental concerns, a consistent metric is need...

Shuttle payload vibroacoustic test plan evaluation. Free flyer payload applications and sortie payload parametric variations

NASA Technical Reports Server (NTRS)

Stahle, C. V.; Gongloff, H. R.

1977-01-01

A preliminary assessment of vibroacoustic test plan optimization for free flyer STS payloads is presented and the effects on alternate test plans for Spacelab sortie payloads number of missions are also examined. The component vibration failure probability and the number of components in the housekeeping subassemblies are provided. Decision models are used to evaluate the cost effectiveness of seven alternate test plans using protoflight hardware.

Automated space processing payloads study. Volume 2, book 2: Technical report, appendices A through E. [instrument packages and space shuttles

NASA Technical Reports Server (NTRS)

1975-01-01

Experiment hardware and operational requirements for space shuttle experiments are discussed along with payload and system concepts. Appendixes are included in which experiment data sheets, chamber environmental control and monitoring, method for collection and storage of electrophoretically-separated samples, preliminary thermal evaluation of electromagnetic levitation facilities L1, L2, and L3, and applicable industrial automation equipment are discussed.

KSC00pp0698

NASA Image and Video Library

2000-05-22

Research technician Lisa Ruffa works with a wheat sample that is part of ground testing for the first International Space Station plant experiment, scheduled to fly in October 2001. The payload process testing is one of many studies being performed at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

KSC00pp0691

NASA Image and Video Library

2000-05-29

Research scientist Gary Stutte displays a wheat sample that is part of ground testing for the first International Space Station plant experiment, scheduled to fly in October 2001. The payload process testing is one of many studies being performed at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

KSC-00pp0691

NASA Image and Video Library

2000-05-29

Research scientist Gary Stutte displays a wheat sample that is part of ground testing for the first International Space Station plant experiment, scheduled to fly in October 2001. The payload process testing is one of many studies being performed at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

KSC-00pp0698

NASA Image and Video Library

2000-05-22

Research technician Lisa Ruffa works with a wheat sample that is part of ground testing for the first International Space Station plant experiment, scheduled to fly in October 2001. The payload process testing is one of many studies being performed at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

KSC00pp0689

NASA Image and Video Library

2000-05-22

Research technician Lisa Ruffa works with a wheat sample that is part of ground testing for the first International Space Station plant experiment, scheduled to fly in October 2001. The payload process testing is one of many studies being performed at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

KSC-00pp0689

NASA Image and Video Library

2000-05-22

Research technician Lisa Ruffa works with a wheat sample that is part of ground testing for the first International Space Station plant experiment, scheduled to fly in October 2001. The payload process testing is one of many studies being performed at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

KSC-08pd2772

NASA Image and Video Library

2008-09-20

CAPE CANAVERAL, Fla. - In the Canister Rotation Facility at NASA's Kennedy Space Center, workers check cable fittings that will lift the payload canister to a vertical position for the trip to Launch Pad 39A. The canister’s cargo consists of four carriers holding various equipment for the STS-125 mission aboard space shuttle Atlantis to service NASA’s Hubble Space Telescope. At the pad, the cargo will be moved into the Payload Changeout Room. 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 shuttle’s payload bay. Launch of Atlantis is targeted for Oct. 10. Photo credit: NASA/Jack Pfaller

An estimate of the outgassing of space payloads, their internal pressures, contaminations and gaseous influences on the environment

NASA Technical Reports Server (NTRS)

Scialdone, J. J.

1985-01-01

Experimentally measured outgassing as a function of time is presented for 14 space systems including several spacecraft instruments, spacecraft, the shuttle bay, and a spent solid fuel motor. The weights, volumes, and some of the scientific functions of the instruments involved are indicated. The methods used to obtain the data are briefly described. General indications on how to use the data to obtain the internal pressure versus time for a payload, its self-contamination, the gaseous flow in its vicinity, the column densities in its field of view, and other environmental parameters which are dependent on the outgassing of a payload are provided.

KSC-07pd0361

NASA Image and Video Library

2007-02-12

KENNEDY SPACE CENTER, FLA. -- In the payload changeout room (PCR) on Launch Pad 39A, the doors of the canister are opened to reveal the S3/S4 integrated truss inside. The PCR 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 truss is the payload for Space Shuttle Atlantis on mission STS-117 to the International Space Station. The Atlantis crew will install the new truss segment, retract a set of solar arrays and unfold a new set on the starboard side of the station. Launch is targeted for March 15. Photo credit: NASA/Jack Pfaller

KSC-07pd0362

NASA Image and Video Library

2007-02-12

KENNEDY SPACE CENTER, FLA. -- In the payload changeout room (PCR) on Launch Pad 39A, the doors of the canister are opened to reveal the S3/S4 integrated truss inside. The PCR 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 truss is the payload for Space Shuttle Atlantis on mission STS-117 to the International Space Station. The Atlantis crew will install the new truss segment, retract a set of solar arrays and unfold a new set on the starboard side of the station. Launch is targeted for March 15. Photo credit: NASA/Jack Pfaller

KSC-07pd0359

NASA Image and Video Library

2007-02-12

KENNEDY SPACE CENTER, FLA. -- In the payload changeout room (PCR) on Launch Pad 39A, a worker prepares the mechanism to open the doors of the canister containing the S3/S4 integrated truss. The PCR 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 truss is the payload for Space Shuttle Atlantis on mission STS-117 to the International Space Station. The Atlantis crew will install the new truss segment, retract a set of solar arrays and unfold a new set on the starboard side of the station. Launch is targeted for March 15. Photo credit: NASA/Jack Pfaller

KSC-07pd0351

NASA Image and Video Library

2007-02-12

KENNEDY SPACE CENTER, FLA. -- With umbilical lines still attached, the payload canister is lifted up to the payload changeout room on the rotating service structure (RSS) on Launch Pad 39A The canister contains the S3/S4 integrated truss for mission STS-117 to the International Space Station aboard Space Shuttle Atlantis. Once inside the PCR, the S3/S4 arrays will be transferred into Space Shuttle Atlantis' payload bay after the vehicle has rolled out to the pad. The changeout room is the enclosed, environmentally controlled portion of the RSS that supports cargo delivery to the pad and subsequent vertical installation into the orbiter payload bay. The Atlantis crew will install the new truss segment, retract a set of solar arrays and unfold a new set on the starboard side of the station. Launch is targeted for March 15. Photo credit: NASA/Kim Shiflett

KSC-07pd0352

NASA Image and Video Library

2007-02-12

KENNEDY SPACE CENTER, FLA. -- With umbilical lines still attached, the payload canister is lifted up to the payload changeout room on the rotating service structure (RSS) on Launch Pad 39A The canister contains the S3/S4 integrated truss for mission STS-117 to the International Space Station aboard Space Shuttle Atlantis. Once inside the PCR, the S3/S4 arrays will be transferred into Space Shuttle Atlantis' payload bay after the vehicle has rolled out to the pad. The changeout room is the enclosed, environmentally controlled portion of the RSS that supports cargo delivery to the pad and subsequent vertical installation into the orbiter payload bay. The Atlantis crew will install the new truss segment, retract a set of solar arrays and unfold a new set on the starboard side of the station. Launch is targeted for March 15. Photo credit: NASA/Kim Shiflett

KSC-07pd0350

NASA Image and Video Library

2007-02-12

KENNEDY SPACE CENTER, FLA. -- With umbilical lines still attached, the payload canister is lifted up to the payload changeout room on the rotating service structure (RSS) on Launch Pad 39A The canister contains the S3/S4 integrated truss for mission STS-117 to the International Space Station aboard Space Shuttle Atlantis. Once inside the PCR, the S3/S4 arrays will be transferred into Space Shuttle Atlantis' payload bay after the vehicle has rolled out to the pad. The changeout room is the enclosed, environmentally controlled portion of the RSS that supports cargo delivery to the pad and subsequent vertical installation into the orbiter payload bay. The Atlantis crew will install the new truss segment, retract a set of solar arrays and unfold a new set on the starboard side of the station. Launch is targeted for March 15. Photo credit: NASA/Kim Shiflett

STS-91 AMS-01 payload moved from MPPF to SSPF

NASA Technical Reports Server (NTRS)

1998-01-01

The alpha-magnetic spectrometer (AMS-1) is lifted in KSC's MultiPayload Processing Facility in preparation for a move to the Space Station Processing Facility via the Payload Environmental Transportation System. The STS-91 payload arrived at KSC in January and is scheduled to be flown on the 9th and final Mir docking mission, scheduled for launch in May. The objectives of the AMS-1 investigation are to search for anti-matter and dark matter in space and to study astrophysics. 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. After docking with the Russian Space Station Mir, Mission Specialist Andrew Thomas, Ph.D., will join the STS-91 crew and return to Earth aboard Discovery.

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

KSC-00pp1732

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 that supports payload delivery at the pad and subsequent vertical installation in the orbiter payload bay. Attached to the canister are the red umbilical lines that maintain the controlled environment inside. 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

KSC00pp1732

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 that supports payload delivery at the pad and subsequent vertical installation in the orbiter payload bay. Attached to the canister are the red umbilical lines that maintain the controlled environment inside. 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

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.

The Neutron Star Interior Composition Explorer (NICER): Design and Development

NASA Technical Reports Server (NTRS)

Gendreau, Keith C.; Arzoumanian, Zaven; Adkins, Phillip W.; Albert, Cheryl L.; Anders, John F.; Aylward, Andrew T.; Baker, Charles L.; Balsamo, Erin R.; Bamford, William A.; Benegalrao, Suyog S.;

The Neutron star Interior Composition Explorer (NICER): design and development

NASA Astrophysics Data System (ADS)

Gendreau, Keith C.; Arzoumanian, Zaven; Adkins, Phillip W.; Albert, Cheryl L.; Anders, John F.; Aylward, Andrew T.; Baker, Charles L.; Balsamo, Erin R.; Bamford, William A.; Benegalrao, Suyog S.; Berry, Daniel L.; Bhalwani, Shiraz; Black, J. Kevin; Blaurock, Carl; Bronke, Ginger M.; Brown, Gary L.; Budinoff, Jason G.; Cantwell, Jeffrey D.; Cazeau, Thoniel; Chen, Philip T.; Clement, Thomas G.; Colangelo, Andrew T.; Coleman, Jerry S.; Coopersmith, Jonathan D.; Dehaven, William E.; Doty, John P.; Egan, Mark D.; Enoto, Teruaki; Fan, Terry W.; Ferro, Deneen M.; Foster, Richard; Galassi, Nicholas M.; Gallo, Luis D.; Green, Chris M.; Grosh, Dave; Ha, Kong Q.; Hasouneh, Monther A.; Heefner, Kristofer B.; Hestnes, Phyllis; Hoge, Lisa J.; Jacobs, Tawanda M.; Jørgensen, John L.; Kaiser, Michael A.; Kellogg, James W.; Kenyon, Steven J.; Koenecke, Richard G.; Kozon, Robert P.; LaMarr, Beverly; Lambertson, Mike D.; Larson, Anne M.; Lentine, Steven; Lewis, Jesse H.; Lilly, Michael G.; Liu, Kuochia Alice; Malonis, Andrew; Manthripragada, Sridhar S.; Markwardt, Craig B.; Matonak, Bryan D.; Mcginnis, Isaac E.; Miller, Roger L.; Mitchell, Alissa L.; Mitchell, Jason W.; Mohammed, Jelila S.; Monroe, Charles A.; Montt de Garcia, Kristina M.; Mulé, Peter D.; Nagao, Louis T.; Ngo, Son N.; Norris, Eric D.; Norwood, Dwight A.; Novotka, Joseph; Okajima, Takashi; Olsen, Lawrence G.; Onyeachu, Chimaobi O.; Orosco, Henry Y.; Peterson, Jacqualine R.; Pevear, Kristina N.; Pham, Karen K.; Pollard, Sue E.; Pope, John S.; Powers, Daniel F.; Powers, Charles E.; Price, Samuel R.; Prigozhin, Gregory Y.; Ramirez, Julian B.; Reid, Winston J.; Remillard, Ronald A.; Rogstad, Eric M.; Rosecrans, Glenn P.; Rowe, John N.; Sager, Jennifer A.; Sanders, Claude A.; Savadkin, Bruce; Saylor, Maxine R.; Schaeffer, Alexander F.; Schweiss, Nancy S.; Semper, Sean R.; Serlemitsos, Peter J.; Shackelford, Larry V.; Soong, Yang; Struebel, Jonathan; Vezie, Michael L.; Villasenor, Joel S.; Winternitz, Luke B.; Wofford, George I.; Wright, Michael R.; Yang, Mike Y.; Yu, Wayne H.

2016-07-01

During 2014 and 2015, NASA's Neutron star Interior Composition Explorer (NICER) mission proceeded success- fully through Phase C, Design and Development. An X-ray (0.2-12 keV) astrophysics payload destined for the International Space Station, NICER is manifested for launch in early 2017 on the Commercial Resupply Services SpaceX-11 flight. Its scientific objectives are to investigate the internal structure, dynamics, and energetics of neutron stars, the densest objects in the universe. During Phase C, flight components including optics, detectors, the optical bench, pointing actuators, electronics, and others were subjected to environmental testing and integrated to form the flight payload. A custom-built facility was used to co-align and integrate the X-ray "con- centrator" optics and silicon-drift detectors. Ground calibration provided robust performance measures of the optical (at NASA's Goddard Space Flight Center) and detector (at the Massachusetts Institute of Technology) subsystems, while comprehensive functional tests prior to payload-level environmental testing met all instrument performance requirements. We describe here the implementation of NICER's major subsystems, summarize their performance and calibration, and outline the component-level testing that was successfully applied.

Research experiments at Hangar L

NASA Technical Reports Server (NTRS)

2000-01-01

Research technician Lisa Ruffa works with a wheat sample that is part of ground testing for the first International Space Station plant experiment, scheduled to fly in October 2001. The payload process testing is one of many studies being performed at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship.

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.

Stratospheric platforms: a novel technological support for Earth observation and remote sensing applications

NASA Astrophysics Data System (ADS)

Dovis, Fabio; Lo Presti, Letizia; Magli, Enrico; Mulassano, Paolo; Olmo, Gabriella

2001-12-01

The international community agrees that the new technology based on the use of Unmanned Air Vehicles High Altitude Very long Endurance (UAV-HAVE) could play an important role for the development of remote sensing and telecommunication applications. A UAV-HAVE vehicle can be described as a low- cost flying infrastructure (compared with satellites) optimized for long endurance operations at an altitude of about 20 km. Due to such features, its role is similar to satellites, with the major advantages of being less expensive, more flexible, movable on demand, and suitable for a larger class of applications. According to this background, Politecnico di Torino is involved as coordinator in an important project named HeliNet, that represent one of the main activities in Europe in the field of stratospheric platforms, and is concerned with the development of a network of UAV-HAVE aircraft. A key point of this project is the feasibility study for the provision of several services, namely traffic monitoring, environmental surveillance, broadband communications and navigation. This paper reports preliminary results on the HeliNet imaging system and its remote sensing applications. In fact, many environmental surveillance services (e.g. regional public services for agriculture, hydrology, fire protection, and more) require very high-resolution imaging, and can be offered at a lower cost if operated by a shared platform. The philosophy behind the HeliNet project seems to be particularly suitable to manage such missions. In particular, we present a system- level study of possible imaging payloads to be mounted on- board of a stratospheric platform to collect Earth observation data. Firstly, we address optical payloads such as multispectral and/or hyperspectral ones, which are a very short-term objective of the project. Secondly, as an example of mid-term on-board payload, we examine the possibility to carry on the platform a light-SAR system. For both types of payload, we show how intelligent processing algorithms for environmental data can be run on-board in real-time, in order to make data analysis and transmission more effective, and designed to match the constrains imposed by a UAV-HAVE platform. The results of the study lead to the conclusion that the stratospheric technology seems to be a competitive infrastructure (with respect to the satellites) in the remote sensing scenarios described above.

Design guide for low cost standardized payloads, volume 1

NASA Technical Reports Server (NTRS)

1972-01-01

Concept point designs of low cost and refurbishable spacecraft, subsystems, and modules revealed payload program savings up to 50 percent. The general relationship of payload approaches to program costs; cost reductions from low cost standardized payloads; cost effective application of payload reliability, MMD, repair, and refurbishment; and implementation of standardization for future spacecraft are discussed. Shuttle interfaces and support equipment for future payloads are also considered

Project UM-HAUL: A self-unloading reusable lunar lander

NASA Technical Reports Server (NTRS)

1991-01-01

The establishment of a lunar base is technologically and financially challenging. Given the necessary resources and political support, it can be done. In addition to the geopolitical obstacles, however, there are logistical problems involved in establishing such bases that can only be overcome with the acquisition of a significant transportation and communications network in the Earth-Moon spatial region. Considering the significant number of payloads that will be required in this process, the mass-specific cost of launching these payloads, and the added risk and cost of human presence in space, it is clearly desirable to automate major parts of such an operation. One very costly and time-consuming factor in this picture is the delivery of payloads to the Moon. Foreseeable payloads would include atmospheric modules, inflatable habitat kits, energy and oxygen plant elements, ground vehicles, laboratory modules, crew supplies, etc. The duration of high-risk human presence on the Moon could be greatly reduced if all such payloads were delivered to the prospective base site in advance of crew arrival. In this view, the idea of a 'Self-Unloading Reusable Lunar Lander' (SURLL) arises naturally. The general scenario depicts the lander being brought to low lunar orbit (LLO) from Earth atop a generic Orbital Transfer Vehicle (OTV). From LLO, the lander shuttles payloads down to the lunar surface, where, by means of some resident, detachable unloading device, it deploys the payloads and returns to orbit. The general goal is for the system to perform with maximum payload capability, automation, and reliability, while also minimizing environmental hazards, servicing needs, and mission costs. Our response to this demand is UM-HAUL, or the UnManned Heavy pAyload Unloader and Lander. The complete study includes a system description, along with a preliminary cost analysis and a design status assessment.

Project UM-HAUL: A self-unloading reusable lunar lander

NASA Astrophysics Data System (ADS)

The establishment of a lunar base is technologically and financially challenging. Given the necessary resources and political support, it can be done. In addition to the geopolitical obstacles, however, there are logistical problems involved in establishing such bases that can only be overcome with the acquisition of a significant transportation and communications network in the Earth-Moon spatial region. Considering the significant number of payloads that will be required in this process, the mass-specific cost of launching these payloads, and the added risk and cost of human presence in space, it is clearly desirable to automate major parts of such an operation. One very costly and time-consuming factor in this picture is the delivery of payloads to the Moon. Foreseeable payloads would include atmospheric modules, inflatable habitat kits, energy and oxygen plant elements, ground vehicles, laboratory modules, crew supplies, etc. The duration of high-risk human presence on the Moon could be greatly reduced if all such payloads were delivered to the prospective base site in advance of crew arrival. In this view, the idea of a 'Self-Unloading Reusable Lunar Lander' (SURLL) arises naturally. The general scenario depicts the lander being brought to low lunar orbit (LLO) from Earth atop a generic Orbital Transfer Vehicle (OTV). From LLO, the lander shuttles payloads down to the lunar surface, where, by means of some resident, detachable unloading device, it deploys the payloads and returns to orbit. The general goal is for the system to perform with maximum payload capability, automation, and reliability, while also minimizing environmental hazards, servicing needs, and mission costs. Our response to this demand is UM-HAUL, or the UnManned Heavy pAyload Unloader and Lander. The complete study includes a system description, along with a preliminary cost analysis and a design status assessment.

Space shuttle I-tube radiator testing at Johnson Space Center, May 1976, volume 1

NASA Technical Reports Server (NTRS)

Scheps, P. B.

1976-01-01

During the two weeks of thermal vacuum testing a representative forward panel was successfully operated in a variety of simulated environmental conditions. Performance limits for both high and low load operations were established. Confidence in the stable operation of the panel throughout its typical operating range was verified by the testing, and design studies were conducted to analyze the effects of the payload bay door, and the panel deployment angle, on performance.

ISS and Shuttle Payload Research Development and Processing

NASA Technical Reports Server (NTRS)

Calhoun, Kyle A.

2010-01-01

NASA's ISS and Spacecraft Processing Directorate (UB) is charged with the performance of payload development for research originating through NASA, ISS international partners, and the National Laboratory. The Payload Development sector of the Directorate takes biological research approved for on orbit experimentation from its infancy stage and finds a way to integrate and implement that research into a payload on either a Shuttle sortie or Space Station increment. From solicitation and selection, to definition, to verification, to integration and finally to operations and analysis, Payload Development is there every step of the way. My specific work as an intern this summer has consisted of investigating data received by separate flight and ground control Advanced Biological Research Systems (ABRS) units for Advanced Plant Experiments (APEX) and Cambium research. By correlation and analysis of this data and specific logbook information I have been working to explain changes in environmental conditions on both the flight and ground control unit. I have then, compiled all of that information into a form that can be presentable to the Principal Investigator (PI). This compilation allows that PI scientist to support their findings and add merit to their research. It also allows us, as the Payload Developers, to further inspect the ABRS unit and its performance

Draft environmental impact statement for the Galileo Mission (Tier 2)

NASA Technical Reports Server (NTRS)

1988-01-01

This Draft Environmental Impact Statement (DEIS) addresses the environmental impacts which may be caused by the preparation and operation of the Galileo spacecraft, including its planned launch on the Space Transportation System (STS) Shuttle and the alternative of canceling further work on the mission. The launch configuration will use the STS/Inertial Upper Stage (IUS)/Payload Assist Module-Special (PAM-S) combination. The Tier 1 EIS included a delay alternative which considered the Titan 4 launch vehicle as an alternative booster stage for launch in 1991 or later. However, the U.S. Air Force, which procures the Titan 4 for NASA, could not provide a Titan 4 vehicle for the 1991 launch opportunity because of high priority Department of Defense requirements. The only expected environmental effects of the proposed action are associated with normal Shuttle launch operations. These impacts are limited largely to the near-field at the launch pad, except for temporary stratospheric ozone effects during launch and occasional sonic boom effects near the landing site. These effects have been judged insufficient to preclude Shuttle launches. In the event of: (1) an accident during launch, or (2) reentry of the spacecraft from earth orbit, there are potential adverse health and environmental effects associated with the possible release of plutonium dioxide from the spacecraft's radioisotope thermoelectric generators (RTG).

Zero-gravity cloud physics laboratory: Candidate experiments definition and preliminary concept studies

NASA Technical Reports Server (NTRS)

Eaton, L. R.; Greco, R. V.; Hollinden, A. B.

1973-01-01

The candidate definition studies on the zero-g cloud physics laboratory are covered. This laboratory will be an independent self-contained shuttle sortie payload. Several critical technology areas have been identified and studied to assure proper consideration in terms of engineering requirements for the final design. Areas include chambers, gas and particle generators, environmental controls, motion controls, change controls, observational techniques, and composition controls. This unique laboratory will allow studies to be performed without mechanical, aerodynamics, electrical, or other type techniques to support the object under study. This report also covers the candidate experiment definitions, chambers and experiment classes, laboratory concepts and plans, special supporting studies, early flight opportunities and payload planning data for overall shuttle payload requirements assessments.

KSC-00pp0373

NASA Image and Video Library

2000-03-21

KENNEDY SPACE CENTER, FLA. -- Workers in the Payload Changeout Room (PCR) at Launch Pad 39A check out the SPACEHAB Double Module before moving into the PCR. Part of the Rotating Service Structure, the PCR is an environmentally controlled facility supporting cargo delivery to the pad and vertical installation in the orbiter cargo bay. The primary payloads on mission STS-101, the module and ICC contain internal logistics and resupply cargo for restoring full redundancy to the International Space Station power system in preparation for the arrival of the next pressurized module, the Russian-built Zvezda. The payloads will be transferred to Space Shuttle Atlantis after Atlantis rolls out to the pad. Launch of Atlantis on mission STS-101 is scheduled no earlier than April 17, 2000

KSC00pp0373

NASA Image and Video Library

2000-03-21

KENNEDY SPACE CENTER, FLA. -- Workers in the Payload Changeout Room (PCR) at Launch Pad 39A check out the SPACEHAB Double Module before moving into the PCR. Part of the Rotating Service Structure, the PCR is an environmentally controlled facility supporting cargo delivery to the pad and vertical installation in the orbiter cargo bay. The primary payloads on mission STS-101, the module and ICC contain internal logistics and resupply cargo for restoring full redundancy to the International Space Station power system in preparation for the arrival of the next pressurized module, the Russian-built Zvezda. The payloads will be transferred to Space Shuttle Atlantis after Atlantis rolls out to the pad. Launch of Atlantis on mission STS-101 is scheduled no earlier than April 17, 2000

JPSS-1 Spacecraft Mate to Payload Attach Fittings

NASA Image and Video Library

2017-10-19

NOAA's Joint Polar Satellite System-1, or JPSS-1, remains wrapped in a protective covering after removal from its shipping container at the Astrotech Processing Facility at Vandenberg Air Force Base in California. Technicians confirm that the spacecraft is secured onto a payload attach fitting. JPSS-1 will liftoff aboard a United Launch Alliance Delta II rocket from Vandenberg's Space Launch Complex-2. JPSS-1 is the first in a series of four next-generation environmental satellites in a collaborative program between NOAA and NASA.

JPSS-1 Spacecraft Mate to Payload Attach Fittings

NASA Image and Video Library

2017-10-19

NOAA's Joint Polar Satellite System-1, or JPSS-1, remains wrapped in a protective covering after removal from its shipping container at the Astrotech Processing Facility at Vandenberg Air Force Base in California. Technicians prepare the spacecraft for its move to a payload attach fitting. JPSS-1 will liftoff aboard a United Launch Alliance Delta II rocket from Vandenberg's Space Launch Complex-2. JPSS-1 is the first in a series of four next-generation environmental satellites in a collaborative program between NOAA and NASA.

JPSS-1 Spacecraft Mate to Payload Attach Fittings

NASA Image and Video Library

2017-10-19

NOAA's Joint Polar Satellite System-1, or JPSS-1, remains wrapped in a protective covering after removal from its shipping container at the Astrotech Processing Facility at Vandenberg Air Force Base in California. Technicians help secure the spacecraft onto a payload attach fitting. JPSS-1 will liftoff aboard a United Launch Alliance Delta II rocket from Vandenberg's Space Launch Complex-2. JPSS-1 is the first in a series of four next-generation environmental satellites in a collaborative program between NOAA and NASA.

JPSS-1 Spacecraft Mate to Payload Attach Fittings

NASA Image and Video Library

2017-10-19

NOAA's Joint Polar Satellite System-1, or JPSS-1, remains wrapped in a protective covering after removal from its shipping container at the Astrotech Processing Facility at Vandenberg Air Force Base in California. The spacecraft is being prepared for its move to a payload attach fitting. JPSS-1 will liftoff aboard a United Launch Alliance Delta II rocket from Vandenberg's Space Launch Complex-2. JPSS-1 is the first in a series of four next-generation environmental satellites in a collaborative program between NOAA and NASA.

KSC00pp0697

NASA Image and Video Library

2000-05-01

Researchers work with wheat samples that are part of ground testing for the first International Space Station plant experiment, scheduled to fly in October 2001. From left are research scientist Oscar Monje and research technicians Lisa Ruffa and Ignacio Eraso. The payload process testing they are performing is one of many studies at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

KSC-00pp0697

NASA Image and Video Library

2000-05-01

Researchers work with wheat samples that are part of ground testing for the first International Space Station plant experiment, scheduled to fly in October 2001. From left are research scientist Oscar Monje and research technicians Lisa Ruffa and Ignacio Eraso. The payload process testing they are performing is one of many studies at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

JPSS-1 Spacecraft Mate to Payload Attach Fittings

NASA Image and Video Library

2017-10-19

NOAA's Joint Polar Satellite System-1, or JPSS-1, remains wrapped in a protective covering after removal from its shipping container at the Astrotech Processing Facility at Vandenberg Air Force Base in California. Technicians assist as a crane lowers the spacecraft toward a payload attach fitting. JPSS-1 will liftoff aboard a United Launch Alliance Delta II rocket from Vandenberg's Space Launch Complex-2. JPSS-1 is the first in a series of four next-generation environmental satellites in a collaborative program between NOAA and NASA.

On-Board Software Payload Platform over RTEMS and LEON3FT Processing Units

NASA Astrophysics Data System (ADS)

Martins, Rodolfo; Ribeiro, Pedro; Furano, Gianluca; Costa Pinto, Joao; Habinc, Sandi

2013-08-01

Under ESA and Inmarsat ARTES 8 Alphabus/Alphasat specific programme a technology demonstration payload (TDP) was developed. The payload called TDP8 is an Environment Effects Facility to monitor the GEO radiation environment and its effects on electronic components and sensors. This paper will discuss the on-board software payload platform approach developed since then and based on the TDP8 validation activities.

Dynamic modelling of a double-pendulum gantry crane system incorporating payload

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

Ismail, R. M. T. Raja; Ahmad, M. A.; Ramli, M. S.

The natural sway of crane payloads is detrimental to safe and efficient operation. Under certain conditions, the problem is complicated when the payloads create a double pendulum effect. This paper presents dynamic modelling of a double-pendulum gantry crane system based on closed-form equations of motion. The Lagrangian method is used to derive the dynamic model of the system. A dynamic model of the system incorporating payload is developed and the effects of payload on the response of the system are discussed. Extensive results that validate the theoretical derivation are presented in the time and frequency domains.

Rapid Ascent Simulation at NASA-MSFC

NASA Technical Reports Server (NTRS)

Sisco, Jimmy D.

2004-01-01

The Environmental Test Facility (ETF), located at NASA-Marshall Space Flight Center, Huntsville, Alabama, has provided thermal vacuum testing for several major programs since the 1960's. The ETF consists of over 13 thermal vacuum chambers sized and configured to handle the majority of test payloads. The majority of tests require a hard vacuum with heating and cryogenics. NASA's Return-to-Flight program requested testing to simulate a launch from the ground to flight using vacuum, heating and cryogenics. This paper describes an effective method for simulating a launch.

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

KSC00pp0372

NASA Image and Video Library

2000-03-21

KENNEDY SPACE CENTER, FLA. -- A closeup shows the Integrated Cargo Carrier (top) and SPACEHAB Double Module (below) ready to be moved into the Payload Changeout Room (PCR) at Launch Pad 39A. Part of the Rotating Service Structure, the PCR is an environmentally controlled facility supporting cargo delivery to the pad and vertical installation in the orbiter cargo bay. The primary payloads on mission STS-101, the module and ICC contain internal logistics and resupply cargo for restoring full redundancy to the International Space Station power system in preparation for the arrival of the next pressurized module, the Russian-built Zvezda. The payloads will be transferred to Space Shuttle Atlantis after Atlantis rolls out to the pad. Launch of Atlantis on mission STS-101 is scheduled no earlier than April 17, 2000

KSC-00pp0372

NASA Image and Video Library

2000-03-21

KENNEDY SPACE CENTER, FLA. -- A closeup shows the Integrated Cargo Carrier (top) and SPACEHAB Double Module (below) ready to be moved into the Payload Changeout Room (PCR) at Launch Pad 39A. Part of the Rotating Service Structure, the PCR is an environmentally controlled facility supporting cargo delivery to the pad and vertical installation in the orbiter cargo bay. The primary payloads on mission STS-101, the module and ICC contain internal logistics and resupply cargo for restoring full redundancy to the International Space Station power system in preparation for the arrival of the next pressurized module, the Russian-built Zvezda. The payloads will be transferred to Space Shuttle Atlantis after Atlantis rolls out to the pad. Launch of Atlantis on mission STS-101 is scheduled no earlier than April 17, 2000

Stability of Pharmaceuticals in Space

NASA Technical Reports Server (NTRS)

Nguyen, Y-Uyen

2009-01-01

Stability testing is a tool used to access shelf life and effects of storage conditions for pharmaceutical formulations. Early research from the International Space Station (ISS) revealed that some medications may have degraded while in space. This potential loss of medication efficacy would be very dangerous to Crew health. The aim of this research project, Stability of Pharmacotherapeutic Compounds, is to study how the stability of pharmaceutical compounds is affected by environmental conditions in space. Four identical pharmaceutical payload kits containing medications in different dosage forms (liquid for injection, tablet, capsule, ointment and suppository) were transported to the ISS aboard a Space Shuttle. One of the four kits was stored on that Shuttle and the other three were stored on the ISS for return to Earth at various time intervals aboard a pre-designated Shuttle flight. The Pharmacotherapeutics laboratory used stability test as defined by the United States Pharmacopeia (USP), to access the degree of degradation to the Payload kit medications that may have occurred during space flight. Once these medications returned, the results of stability test performed on them were compared to those from the matching ground controls stored on Earth. Analyses of the results obtained from physical and chemical stability assessments on these payload medications will provide researchers additional tools to promote safe and efficacious medications for space exploration.

KSC-2009-1486

NASA Image and Video Library

2009-01-12

VANDENBERG AIR FORCE BASE, Calif. – In Building 1610 at Vandenberg Air Force Base in California, the United Launch Alliance direct mate adapter, or DMA, is installed on the NOAA-N Prime's payload attach fitting underneath the spacecraft. The DMA is needed to install the payload canister around the spacecraft for the journey to the launch pad. NOAA-N Prime is the latest polar-orbiting operational environmental weather satellite developed by NASA for the National Oceanic and Atmospheric Administration. Launch of NOAA-N Prime is scheduled for Feb. 4. Photo credit: NASA/Doug Kolkow, VAFB

KSC-2009-1487

NASA Image and Video Library

2009-01-12

VANDENBERG AIR FORCE BASE, Calif. – In Building 1610 at Vandenberg Air Force Base in California, the United Launch Alliance direct mate adapter, or DMA, is installed on the NOAA-N Prime's payload attach fitting underneath the spacecraft. The DMA is needed to install the payload canister around the spacecraft for the journey to the launch pad. NOAA-N Prime is the latest polar-orbiting operational environmental weather satellite developed by NASA for the National Oceanic and Atmospheric Administration. Launch of NOAA-N Prime is scheduled for Feb. 4. Photo credit: NASA/Doug Kolkow, VAFB

Research experiments at Hangar L

NASA Technical Reports Server (NTRS)

2000-01-01

Researchers work with wheat samples that are part of ground testing for the first International Space Station plant experiment, scheduled to fly in October 2001. From left are research scientist Oscar Monje and research technicians Lisa Ruffa and Ignacio Eraso. The payload process testing they are performing is one of many studies at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship.

Dynamics Simulation Model for Space Tethers

NASA Technical Reports Server (NTRS)

Levin, E. M.; Pearson, J.; Oldson, J. C.

2006-01-01

This document describes the development of an accurate model for the dynamics of the Momentum Exchange Electrodynamic Reboost (MXER) system. The MXER is a rotating tether about 100-km long in elliptical Earth orbit designed to catch payloads in low Earth orbit and throw them to geosynchronous orbit or to Earth escape. To ensure successful rendezvous between the MXER tip catcher and a payload, a high-fidelity model of the system dynamics is required. The model developed here quantifies the major environmental perturbations, and can predict the MXER tip position to within meters over one orbit.

JPSS-1 Spacecraft Mate to Payload Attach Fittings

NASA Image and Video Library

2017-10-19

NOAA's Joint Polar Satellite System-1, or JPSS-1, remains wrapped in a protective covering after removal from its shipping container at the Astrotech Processing Facility at Vandenberg Air Force Base in California. Technicians assist as a crane lifts the spacecraft up for its move to a payload attach fitting. JPSS-1 will liftoff aboard a United Launch Alliance Delta II rocket from Vandenberg's Space Launch Complex-2. JPSS-1 is the first in a series of four next-generation environmental satellites in a collaborative program between NOAA and NASA.

JPSS-1 Spacecraft Mate to Payload Attach Fittings

NASA Image and Video Library

2017-10-19

NOAA's Joint Polar Satellite System-1, or JPSS-1, remains wrapped in a protective covering after removal from its shipping container at the Astrotech Processing Facility at Vandenberg Air Force Base in California. A crane is attached to the spacecraft to prepare for its move to a payload attach fitting. JPSS-1 will liftoff aboard a United Launch Alliance Delta II rocket from Vandenberg's Space Launch Complex-2. JPSS-1 is the first in a series of four next-generation environmental satellites in a collaborative program between NOAA and NASA.

JPSS-1 Spacecraft Mate to Payload Attach Fittings

NASA Image and Video Library

2017-10-19

NOAA's Joint Polar Satellite System-1, or JPSS-1, remains wrapped in a protective covering after removal from its shipping container at the Astrotech Processing Facility at Vandenberg Air Force Base in California. Technicians assist as a crane lifts and moves the spacecraft to a payload attach fitting. JPSS-1 will liftoff aboard a United Launch Alliance Delta II rocket from Vandenberg's Space Launch Complex-2. JPSS-1 is the first in a series of four next-generation environmental satellites in a collaborative program between NOAA and NASA.

Russian BAR/EXPERT experiment

NASA Image and Video Library

2009-08-28

ISS020-E-035016 (27 Aug. 2009) --- Russian cosmonaut Gennady Padalka, Expedition 20 commander, uses the Russian BAR/EXPERT science payload to take various environmental measurements in the Zvezda Service Module of the International Space Station.

Russian BAR/EXPERT experiment

NASA Image and Video Library

2009-08-28

ISS020-E-035022 (27 Aug. 2009) --- Russian cosmonaut Roman Romanenko, Expedition 20 flight engineer, uses the Russian BAR/EXPERT science payload to take various environmental measurements in the Zvezda Service Module of the International Space Station.

Russian BAR/EXPERT experiment

NASA Image and Video Library

2009-08-28

ISS020-E-035017 (27 Aug. 2009) --- Russian cosmonaut Gennady Padalka, Expedition 20 commander, uses the Russian BAR/EXPERT science payload to take various environmental measurements in the Zvezda Service Module of the International Space Station.

Skylab program payload integration. Skylab film environmental effects

NASA Technical Reports Server (NTRS)

1975-01-01

The effects of the Skylab environments on the 22 types of film used for data recording on Skylab were evaluated. Environmental histories and sensitometric curves for 114 rolls of film used for this evaluation are presented. Photographic parameters evaluated in detail were film fogging of black and white films, changes in maximum density of color film, latent image fading, and changes in film sensitivity. Other photographic and film physical anomalies such as electrostatic exposure, emulsion cracking, and reciprocity failure were also documented. Results based upon comparison of film sensitometric data for flight film with ground control film and ground test film are presented independently for each film type. The study showed that photographic film fulfilled the requirements of the Skylab applications in which it was used. Environmental film degradation, although present on almost every roll, did not preclude recording sufficient data to meet experiment requirements for all film, except film type SC-5. Specific conclusions are provided in the areas of further analyses, tests, and developments.

KSC-98pc1185

NASA Image and Video Library

1998-09-30

KENNEDY SPACE CENTER, FLA. -- Inside the Payload Changeout Room (PCR) in the Rotating Service Structure (RSS) at Launch Pad 39-B, technicians in clean suits move the payloads for mission STS-95 to the payload bay of Space Shuttle Discovery. At the top of the RSS is the Spacehab module; below it are the Spartan solar-observing deployable spacecraft, the Hubble Space Telescope Orbiting Systems Test Platform (HOST), and the International Extreme Ultraviolet Hitchhiker (IEH-3). The PCR is an environmentally controlled facility with seals around the mating surface that fit against the orbiter or payload canister and permit the payload bay or canister doors to be opened and cargo removed without exposing it to outside air and contaminants. Payloads are installed vertically in the orbiter using the extendable payload ground handling mechanism. Fixed and extendable work platforms provide work access in the PCR. The SPACEHAB single module involves experiments on space flight and the aging process. Spartan is a solar physics spacecraft designed to perform remote sensing of the hot outer layers of the sun's atmosphere or corona. HOST carries four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an Earth-orbiting environment. IEH-3 comprises several experiments that will study the Jovian planetary system, hot stars, planetary and reflection nebulae, other stellar objects and their environments through remote observation of EUV/FUV emissions; study spacecraft interactions, Shuttle glow, thruster firings, and contamination; and measure the solar constant and identify variations in the value during a solar cycle. Mission STS-95 is scheduled to launch Oct. 29, 1998

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.

Payload analysis for space shuttle applications (study 2.2). Volume 3: Payload system operations analysis (task 2.2.1). [payload system operations analysis for shuttles and space tugs

NASA Technical Reports Server (NTRS)

1972-01-01

The technical and cost analysis that was performed for the payload system operations analysis is presented. The technical analysis consists of the operations for the payload/shuttle and payload/tug, and the spacecraft analysis which includes sortie, automated, and large observatory type payloads. The cost analysis includes the costing tradeoffs of the various payload design concepts and traffic models. The overall objectives of this effort were to identify payload design and operational concepts for the shuttle which will result in low cost design, and to examine the low cost design concepts to identify applicable design guidelines. The operations analysis examined several past and current NASA and DoD satellite programs to establish a shuttle operations model. From this model the analysis examined the payload/shuttle flow and determined facility concepts necessary for effective payload/shuttle ground operations. The study of the payload/tug operations was an examination of the various flight timelines for missions requiring the tug.

Computational Fluid Dynamics Uncertainty Analysis for Payload Fairing Spacecraft Environmental Control Systems

NASA Technical Reports Server (NTRS)

Groves, Curtis; Ilie, Marcel; Schallhorn, Paul

2014-01-01

Spacecraft components may be damaged due to airflow produced by Environmental Control Systems (ECS). There are uncertainties and errors associated with using Computational Fluid Dynamics (CFD) to predict the flow field around a spacecraft from the ECS System. This paper describes an approach to estimate the uncertainty in using CFD to predict the airflow speeds around an encapsulated spacecraft.

CHARGE-2 rocket observations of vehicle charging and charge neutralization

NASA Astrophysics Data System (ADS)

Banks, P. M.; Gilchrist, B. E.; Neubert, T.; Myers, N.; Raitt, W. J.; Williamson, P. R.; Fraser-Smith, A. C.; Sasaki, S.

Observations of electrical charging and other phenomena have been made in the ionosphere with the CHARGE-2 tethered rocket system. In this experiment, two electrically connected payloads with a variety of plasma instruments measured effects associated with operation of a 1 keV, 40 mA electron gun and a 450-volt dc power supply. During electron beam operations, it was found that both mother and daughter payloads reached high positive potentials as a consequence of the restricted electron current collecting area of the payloads. During neutral gas thruster firings, the payload potentials were dramatically reduced, indicating that electrical discharges could effectively ground each payload to plasma potential. Other thruster-related effects were also seen, including substantial reductions of return current-associated electrical noise at HF and VLF and large increases in 3914 A light in the plasma sheath.

Athena Mars rover science investigation

NASA Astrophysics Data System (ADS)

Squyres, Steven W.; Arvidson, Raymond E.; Baumgartner, Eric T.; Bell, James F.; Christensen, Philip R.; Gorevan, Stephen; Herkenhoff, Kenneth E.; Klingelhöfer, Göstar; Madsen, Morten Bo; Morris, Richard V.; Rieder, Rudolf; Romero, Raul A.

2003-12-01

Each Mars Exploration Rover carries an integrated suite of scientific instruments and tools called the Athena science payload. The primary objective of the Athena science investigation is to explore two sites on the Martian surface where water may once have been present, and to assess past environmental conditions at those sites and their suitability for life. The remote sensing portion of the payload uses a mast called the Pancam Mast Assembly (PMA) that provides pointing for two instruments: the Panoramic Camera (Pancam), and the Miniature Thermal Emission Spectrometer (Mini-TES). Pancam provides high-resolution, color, stereo imaging, while Mini-TES provides spectral cubes at mid-infrared wavelengths. For in-situ study, a five degree-of-freedom arm called the Instrument Deployment Device (IDD) carries four more tools: a Microscopic Imager (MI) for close-up imaging, an Alpha Particle X-Ray Spectrometer (APXS) for elemental chemistry, a Mössbauer Spectrometer (MB) for the mineralogy of Fe-bearing materials, and a Rock Abrasion Tool (RAT) for removing dusty and weathered surfaces and exposing fresh rock underneath. The payload also includes magnets that allow the instruments to study the composition of magnetic Martian materials. All of the Athena instruments have undergone extensive calibration, both individually and using a set of geologic reference materials that are being measured with all the instruments. Using a MER-like rover and payload in a number of field settings, we have devised operations processes that will enable us to use the MER rovers to formulate and test scientific hypotheses concerning past environmental conditions and habitability at the landing sites.

Athena Mars rover science investigation

USGS Publications Warehouse

Squyres, S. W.; Arvidson, R. E.; Baumgartner, E.T.; Bell, J.F.; Christensen, P.R.; Gorevan, S.; Herkenhoff, K. E.; Klingelhofer, G.; Madsen, M.B.; Morris, R.V.; Rieder, R.; Romero, R.A.

2003-01-01

Each Mars Exploration Rover carries an integrated suite of scientific instruments and tools called the Athena science payload. The primary objective of the Athena science investigation is to explore two sites on the Martian surface where water may once have been present, and to assess past environmental conditions at those sites and their suitability for life. The remote sensing portion of the payload uses a mast called the Pancam Mast Assembly (PMA) that provides pointing for two instruments: the Panoramic Camera (Pancam), and the Miniature Thermal Emission Spectrometer (Mini-TES). Pancam provides high-resolution, color, stereo imaging, while Mini-TES provides spectral cubes at mid-infrared wavelengths. For in-situ study, a five degree-of-freedom arm called the Instrument Deployment Device (IDD) carries four more tools: a Microscopic Imager (MI) for close-up imaging, an Alpha Particle X-Ray Spectrometer (APXS) for elemental chemistry, a Mo??ssbauer Spectrometer (MB) for the mineralogy of Fe-bearing materials, and a Rock Abrasion Tool (RAT) for removing dusty and weathered surfaces and exposing fresh rock underneath. The payload also includes magnets that allow the instruments to study the composition of magnetic Martian materials. All of the Athena instruments have undergone extensive calibration, both individually and using a set of geologic reference materials that are being measured with all the instruments. Using a MER-like rover and payload in a number of field settings, we have devised operations processes that will enable us to use the MER rovers to formulate and test scientific hypotheses concerning past environmental conditions and habitability at the landing sites. Copyright 2003 by the American Geophysical Union.

Plant Science in Reduced Gravity: Lessons Learned

NASA Technical Reports Server (NTRS)

Stutte, Gary W.; Monje, Oscar; Wheeler, Raymond M.

2012-01-01

The effect of gravity on the growth and development of plants has been the subject of scientific investigation for over a century. The results obtained in space to test specific hypotheses on gravitropism, gene expression, seed formation, or growth rate are affected by both the primary effect of the microgravity and secondary effects of the spaceflight environment. The secondary effects of the spaceflight environment include physical effects arising from physical changes, such as the absence of buoyancy driven convective mixing, altered behavior of liquids and gases, and the environmental conditions in the spacecraft atmosphere. Thus, the design of biological experiments (e.g. cells, plants, animals, etc.) conducted in microgravity must account for changes in the physical forces, as well as the environmental conditions, imposed by the specific spaceflight vehicle and experimental hardware. In addition, researchers must become familiar with other aspects of spaceflight experiments: payload integration with hardware developers, safety documentation and crew procedures, and the logistics of conducting flight and ground controls. This report reviews the physical and environmental factors that directly and indirectly affect the results of plant science experiments in microgravity and is intended to serve as a guide in the design and implementation plant experiments in space.

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

Database of proposed payloads and instruments for SEI missions

NASA Technical Reports Server (NTRS)

Barlow, N. G.

1992-01-01

A database of all payloads and instruments proposed for lunar and Mars missions was compiled by the author for the Exploration Programs Office at NASA's Johnson Sapce Center. The database is an outgrowth of the document produced by C. J. Budney et al. at the Jet Propulsion Laboratory in 1991. The present database consists not only of payloads proposed for human exploratory missions of the Moon and Mars, but also experiments selected or proposed for robotic precursor missions such as Lunar Scout, Mars Observer, and MESUR. The database consists of two parts: a written payload description and a matrix that provides a breakdown of payload components. Each payload description consists of the following information: (1) the rationale for why the instrument or payload package is being proposed for operation on the Moon or Mars; (2) a description of how the instrument works; (3) a breakdown of the payload, providing detailed information about the mass, volume, power requirements, and data rates for the constituent pieces of the experiment; (4) estimates of the power consumption and data rate; (5) how the data will be returned to Earth and distributed to the scientific community; (6) any constraints on the location or conditions under which the instrument can or cannot operate; (7) what type of crew interaction (if any) is needed; (8) how the payload is to be delivered to the lunar or martian surface (along with alternative delivery options); (9) how long the instrument or payload package will take to set up; (10) what type of maintenance needs are anticipated for the experiment; (11) stage of development for the instrument and environmental conditions under which the instrument has been tested; (12) an interface required by the instrument with the lander, a rover, an outpost, etc.; (13) information about how often the experiment will need to be resupplied with parts or consumables, if it is to be resupplied; (14) the name and affiliation of a contact person for the experiment; and (15) references where further information about the experiment can be found.

Development of a Remote Sensing and Microgravity Student GAS Payload

NASA Technical Reports Server (NTRS)

Branly, Rolando; Ritter, Joe; Friedfeld, Robert; Ackerman, Eric; Carruthers, Carl; Faranda, Jon

1999-01-01

The G-781 Terrestrial and Atmospheric Multi-Spectral Explorer payload (TAMSE) is the result of an educational partnership between Broward and Brevard Community Colleges with the Association of Small Payload Researchers (ASPR) and the Florida Space Institute, University of Central Florida. The effort focuses on flying nine experiments, including three earth viewing remote sensing experiments, three microgravity experiments involving crystal growth, and three radiation measurement experiments. The G-781 science team, composed of both student and faculty members, has been working on this payload since 1995. The dream of flying the first Florida educational GAS experiment led to the flight of a passive Radiation dosimetry experiment on STS-91 (ASPR-GraDEx-I), which will be reflown as part of TAMSE. This project has lead to the development of a mature space science program within the schools. Many students have been positively touched by direct involvement with NASA and the GAS program as well as with other flight programs e.g. the KC-135 flight program. Several students have changed majors, and selected physics, engineering, and other science career paths as a result of the experience. The importance of interdisciplinary training is fundamental to this payload and to the teaching of the natural sciences. These innovative student oriented projects will payoff not only in new science data, but also in accomplishing training for the next generation of environmental and space scientists. The details the TAMSE payload design are presented in this paper.

The Lunar Crater Observation and Sensing Satellite (LCROSS) Payload Development and Performance in Flight

NASA Astrophysics Data System (ADS)

Ennico, Kimberly; Shirley, Mark; Colaprete, Anthony; Osetinsky, Leonid

2012-05-01

The primary objective of the Lunar Crater Observation and Sensing Satellite (LCROSS) was to confirm the presence or absence of water ice in a permanently shadowed region (PSR) at a lunar pole. LCROSS was classified as a NASA Class D mission. Its payload, the subject of this article, was designed, built, tested and operated to support a condensed schedule, risk tolerant mission approach, a new paradigm for NASA science missions. All nine science instruments, most of them ruggedized commercial-off-the-shelf (COTS), successfully collected data during all in-flight calibration campaigns, and most importantly, during the final descent to the lunar surface on October 9, 2009, after 112 days in space. LCROSS demonstrated that COTS instruments and designs with simple interfaces, can provide high-quality science at low-cost and in short development time frames. Building upfront into the payload design, flexibility, redundancy where possible even with the science measurement approach, and large margins, played important roles for this new type of payload. The environmental and calibration approach adopted by the LCROSS team, compared to existing standard programs, is discussed. The description, capabilities, calibration and in-flight performance of each instrument are summarized. Finally, this paper goes into depth about specific areas where the instruments worked differently than expected and how the flexibility of the payload team, the knowledge of instrument priority and science trades, and proactive margin maintenance, led to a successful science measurement by the LCROSS payload's instrument complement.

Evaluation philosophy for shuttle launched payloads

NASA Technical Reports Server (NTRS)

Heuser, R. E.

1975-01-01

Some approaches to space-shuttle payload evaluation are examined. Issues considered include subsystem replacement in low-cost modular spacecraft (LCMS), validation of spacelab payloads, the use of standard components in shuttle-era spacecraft, effects of shuttle-induced environments on payloads, and crew safety. The LCMS is described, and goals are discussed for its evaluation program. Concepts regarding how the evaluation should proceed are considered.

Predicting the payload capability of cable logging systems including the effect of partial suspension

Treesearch

Gary D. Falk

1981-01-01

A systematic procedure for predicting the payload capability of running, live, and standing skylines is presented. Three hand-held calculator programs are used to predict payload capability that includes the effect of partial suspension. The programs allow for predictions for downhill yarding and for yarding away from the yarder. The equations and basic principles...

Meteorological and Remote Sensing Applications of High Altitude Unmanned Aerial Vehicles

NASA Technical Reports Server (NTRS)

Schoenung, S. M.; Wegener, S. S.

1999-01-01

Unmanned aerial vehicles (UAVs) are maturing in performance and becoming available for routine use in environmental applications including weather reconnaissance and remote sensing. This paper presents a discussion of UAV characteristics and unique features compared with other measurement platforms. A summary of potential remote sensing applications is provided, along with details for four types of tropical cyclone missions. Capabilities of platforms developed under NASA's Environmental Research Aircraft and Sensor Technology (ERAST) program are reviewed, including the Altus, Perseus, and solar- powered Pathfinder, all of which have flown to over 57,000 ft (17 km). In many scientific missions, the science objectives drive the experimental design, thus defining the sensor payload, aircraft performance, and operational requirements. Some examples of science missions and the requisite UAV / payload system are given. A discussion of technology developments needed to fully mature UAV systems for routine operational use is included, along with remarks on future science and commercial UAV business opportunities.

KSC-98pc1183

NASA Image and Video Library

1998-09-30

KENNEDY SPACE CENTER, FLA. -- Inside the Payload Changeout Room (PCR) in the Rotating Service Structure (RSS) at Launch Pad 39-B, technicians in clean suits and tethers prepare to move the payloads for mission STS-95 through the open doors of the payload bay (right) of Space Shuttle Discovery. At the top of the RSS is the Spacehab module; below it are the Spartan solar-observing deployable spacecraft, the Hubble Space Telescope Orbiting Systems Test Platform (HOST), and International Extreme Ultraviolet Hitchhiker (IEH-3). The PCR is an environmentally controlled facility with seals around the mating surface that fit against the orbiter or payload canister and permit the payload bay or canister doors to be opened and cargo removed without exposing it to outside air and contaminants. Payloads are installed vertically in the orbiter using the extendable payload ground handling mechanism. Fixed and extendable work platforms provide work access in the PCR. The SPACEHAB single module involves experiments on space flight and the aging process. Spartan is a solar physics spacecraft designed to perform remote sensing of the hot outer layers of the sun's atmosphere or corona. HOST carries four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an Earth-orbiting environment. IEH-3 comprises several experiments that will study the Jovian planetary system, hot stars, planetary and reflection nebulae, other stellar objects and their environments through remote observation of EUV/FUV emissions; study spacecraft interactions, Shuttle glow, thruster firings, and contamination; and measure the solar constant and identify variations in the value during a solar cycle. Mission STS-95 is scheduled to launch Oct. 29, 1998

KSC-98pc1184

NASA Image and Video Library

1998-09-30

KENNEDY SPACE CENTER,FLA. -- Inside the Payload Changeout Room (PCR) in the Rotating Service Structure (RSS) at Launch Pad 39-B, technicians in clean suits and tethers prepare to move the payloads for mission STS-95 through the open doors of the payload bay (left) of Space Shuttle Discovery. At the top of the RSS is the Spacehab module; below it are the Spartan solar-observing deployable spacecraft, the Hubble Space Telescope Orbiting Systems Test Platform (HOST), and the International Extreme Ultraviolet Hitchhiker (IEH-3). The PCR is an environmentally controlled facility with seals around the mating surface that fit against the orbiter or payload canister and permit the payload bay or canister doors to be opened and cargo removed without exposing it to outside air and contaminants. Payloads are installed vertically in the orbiter using the extendable payload ground handling mechanism. Fixed and extendable work platforms provide work access in the PCR. The SPACEHAB single module involves experiments on space flight and the aging process. Spartan is a solar physics spacecraft designed to perform remote sensing of the hot outer layers of the sun's atmosphere or corona. HOST carries four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an Earth-orbiting environment. IEH-3 comprises several experiments that will study the Jovian planetary system, hot stars, planetary and reflection nebulae, other stellar objects and their environments through remote observation of EUV/FUV emissions; study spacecraft interactions, Shuttle glow, thruster firings, and contamination; and measure the solar constant and identify variations in the value during a solar cycle. Mission STS-95 is scheduled to launch Oct. 29, 1998

Development of thermal control methods for specialized components and scientific instruments at very low temperatures (follow-on)

NASA Technical Reports Server (NTRS)

Wright, J. P.; Wilson, D. E.

1976-01-01

Many payloads currently proposed to be flown by the space shuttle system require long-duration cooling in the 3 to 200 K temperature range. Common requirements also exist for certain DOD payloads. Parametric design and optimization studies are reported for multistage and diode heat pipe radiator systems designed to operate in this temperature range. Also optimized are ground test systems for two long-life passive thermal control concepts operating under specified space environmental conditions. The ground test systems evaluated are ultimately intended to evolve into flight test qualification prototypes for early shuttle flights.

Generalized environmental control and life support system computer program (G189A) configuration control. [computer subroutine libraries for shuttle orbiter analyses

NASA Technical Reports Server (NTRS)

Blakely, R. L.

1973-01-01

A G189A simulation of the shuttle orbiter EC/lSS was prepared and used to study payload support capabilities. Two master program libraries of the G189A computer program were prepared for the NASA/JSC computer system. Several new component subroutines were added to the G189A program library and many existing subroutines were revised to improve their capabilities. A number of special analyses were performed in support of a NASA/JSC shuttle orbiter EC/LSS payload support capability study.

Environmental protection requirements for scout/shuttle auxiliary stages

NASA Technical Reports Server (NTRS)

Qualls, G. L.; Kress, S. S.; Storey, W. W.; Ransdell, P. N.

1980-01-01

The requirements for enabling the Scout upper stages to endure the expected temperature, mechanical shock, acoustical and mechanical vibration environments during a specified shuttle mission were determined. The study consisted of: determining a shuttle mission trajectory for a 545 kilogram (1200 pound) Scout payload; compilation of shuttle environmental conditions; determining of Scout upper stages environments in shuttle missions; compilation of Scout upper stages environmental qualification criteria and comparison to shuttle mission expected environments; and recommendations for enabling Scout upper stages to endure the exptected shuttle mission environments.

KSC-98pc376

NASA Image and Video Library

1998-03-18

KENNEDY SPACE CENTER, FLA. -- The alpha-magnetic spectrometer (AMS-1) is lifted in KSC’s MultiPayload Processing Facility in preparation for a move to the Space Station Processing Facility via the Payload Environmental Transportation System. The STS-91 payload arrived at KSC in January and is scheduled to be flown on the 9th and final Mir docking mission, scheduled for launch in May. The objectives of the AMS-1 investigation are to search for anti-matter and dark matter in space and to study astrophysics. 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. After docking with the Russian Space Station Mir, Mission Specialist Andrew Thomas, Ph.D., will join the STS-91 crew and return to Earth aboard Discovery

KSC-98pc375

NASA Image and Video Library

1998-03-18

KENNEDY SPACE CENTER, FLA. -- The alpha-magnetic spectrometer (AMS-1) is lifted in KSC’s MultiPayload Processing Facility in preparation for a move to the Space Station Processing Facility via the Payload Environmental Transportation System. The STS-91 payload arrived at KSC in January and is scheduled to be flown on the 9th and final Mir docking mission, scheduled for launch in May. The objectives of the AMS-1 investigation are to search for anti-matter and dark matter in space and to study astrophysics. 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. After docking with the Russian Space Station Mir, Mission Specialist Andrew Thomas, Ph.D., will join the STS-91 crew and return to Earth aboard Discovery

Environmental monitoring of the orbiter payload bay and Orbiter Processing Facilities

NASA Technical Reports Server (NTRS)

Bartelson, D. W.; Johnson, A. M.

1985-01-01

Contamination control in the Orbiter Processing Facility (OPF) is studied. The clean level required in the OPF is generally clean, which means no residue, dirt, debris, or other extraneous contamination; various methods of maintaining this level of cleanliness are described. The monitoring and controlling of the temperature, relative humidity, and air quality in the OPF are examined. Additional modifications to the OPF to improve contamination control are discussed. The methods used to maintain the payload changeout room at a level of visually clean, no particulates are to be detected by the unaided eye, are described. The payload bay (PLB) must sustain the cleanliness level required for the specific Orbiter's mission; the three levels of clean are defined as: (1) standard, (2) sensitive, and (3) high sensitive. The cleaning and inspection verification required to achieve the desired cleanliness level on a variety of PLB surface types are examined.

Estimation of payload loads using rigid body interface accelerations. [in structural design of launch vehicle systems

NASA Technical Reports Server (NTRS)

Chen, J. C.; Garba, J. A.; Wada, B. K.

1978-01-01

In the design/analysis process of a payload structural system, the accelerations at the payload/launch vehicle interface obtained from a system analysis using a rigid payload are often used as the input forcing function to the elastic payload to obtain structural design loads. Such an analysis is at best an approximation since the elastic coupling effects are neglected. This paper develops a method wherein the launch vehicle/rigid payload interface accelerations are modified to account for the payload elasticity. The advantage of the proposed method, which is exact to the extent that the physical system can be described by a truncated set of generalized coordinates, is that the complete design/analysis process can be performed within the organization responsible for the payload design. The method requires the updating of the system normal modes to account for payload changes, but does not require a complete transient solution using the composite system model. An application to a real complex structure, the Viking Spacecraft System, is given.

Conceptual design study. Science and Applications Space Platform (SASP). Final briefing

NASA Technical Reports Server (NTRS)

1980-01-01

The modularity, shape, and size of the recommended platform concept offers a low investment, early option to demonstrate the system; flexibility to conservative growth; adaptability to great variety of multi or dedicated payload groups; and good dispersion and viewing freedom for payloads. Platform configuration effectively supports 80 to 85% of the NASA/OSS and OSTA payloads. The subsystem approaches recommended are based on cost effective distribution of functions.

Space shuttle engineering and operations support. Isolation between the S-band quad antenna and the S-band payload antenna. Engineering systems analysis

NASA Technical Reports Server (NTRS)

Lindsey, J. F.

1976-01-01

The isolation between the upper S-band quad antenna and the S-band payload antenna on the shuttle orbiter is calculated using a combination of plane surface and curved surface theories along with worst case values. A minimum value of 60 db isolation is predicted based on recent antenna pattern data, antenna locations on the orbiter, curvature effects, dielectric covering effects and edge effects of the payload bay. The calculated value of 60 db is significantly greater than the baseline value of 40 db. Use of the new value will result in the design of smaller, lighter weight and less expensive filters for S-band transponder and the S-band payload interrogator.

Vertical dynamics of a single-span beam subjected to moving mass-suspended payload system with variable speeds

NASA Astrophysics Data System (ADS)

He, Wei

2018-03-01

This paper presents the vertical dynamics of a simply supported Euler-Bernoulli beam subjected to a moving mass-suspended payload system of variable velocities. A planar theoretical model of the moving mass-suspended payload system of variable speeds is developed based on several assumptions: the rope is massless and rigid, and its length keeps constant; the stiffness of the gantry beam is much greater than the supporting beam, and the gantry beam can be treated as a mass particle traveling along the supporting beam; the supporting beam is assumed as a simply supported Bernoulli-Euler beam. The model can be degenerated to consider two classical cases-the moving mass case and the moving payload case. The proposed model is verified using both numerical and experimental methods. To further investigate the effect of possible influential factors, numerical examples are conducted covering a range of parameters, such as variable speeds (acceleration or deceleration), mass ratios of the payload to the total moving load, and the pendulum lengths. The effect of beam flexibility on swing response of the payload is also investigated. It is shown that the effect of a variable speed is significant for the deflections of the beam. The accelerating movement tends to induce larger beam deflections, while the decelerating movement smaller ones. For accelerating or decelerating movements, the moving mass model may underestimate the deflections of the beam compared with the presented model; while for uniform motion, both the moving mass model and the moving mass-payload model lead to same beam responses. Furthermore, it is observed that the swing response of the payload is not sensitive to the stiffness of the beam for operational cases of a moving crane, thus a simple moving payload model can be employed in the swing control of the payload.

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.

Environmental qualification testing of payload G-534, the Pool Boiling Experiment

NASA Technical Reports Server (NTRS)

Sexton, J. Andrew

1992-01-01

Payload G-534, the prototype Pool Boiling Experiment (PBE), is scheduled to fly on the STS-47 mission in September 1992. This paper describes the purpose of the experiment and the environmental qualification testing program that was used to prove the integrity of the hardware. Component and box level vibration and thermal cycling tests were performed to give an early level of confidence in the hardware designs. At the system level, vibration, thermal extreme soaks, and thermal vacuum cycling tests were performed to qualify the complete design for the expected shuttle environment. The system level vibration testing included three axis sine sweeps and random inputs. The system level hot and cold soak tests demonstrated the hardware's capability to operate over a wide range of temperatures and gave wider latitude in determining which shuttle thermal attitudes were compatible with the experiment. The system level thermal vacuum cycling tests demonstrated the hardware's capability to operate in a convection free environment. A unique environmental chamber was designed and fabricated by the PBE team and allowed most of the environmental testing to be performed within the hardware build laboratory. The completion of the test program gave the project team high confidence in the hardware's ability to function as designed during flight.

Field refurbishment of recoverable sounding rocket payloads.

NASA Technical Reports Server (NTRS)

Needleman, H. C.; Tackett, C. D.

1973-01-01

Sounding rocket payload field refurbishment has been shown to be an effective means for obtaining additional scientific data with substantial time and monetary savings. In a recent campaign three successful missions were flown using two payloads. Field refurbished hardware from two previously flown and recovered payloads were field integrated to form a third payload. Although this operational method may result in compromises in the refurbished system, it allows for quick turn around when the mission requires it. This paper describes the recent success of this approach with the Dudley Observatory Nike-Apache micrometeorite collection experiments launched from Kiruna, Sweden, in October 1972.

KSC-99pp1288

NASA Image and Video Library

1999-11-05

KENNEDY SPACE CENTER, FLA. -- At Launch Pad 39B, the payload canister for Space Shuttle Discovery, for mission STS-103, is lifted up the Rotating Service Structure. The hoses attached to the canister provide airconditioning until the canister is mated to the environmentally controlled Payload Changeout Room and the payload bay doors are open. Installation of the payload into Discovery is slated for Friday, Nov. 12. The mission is a "call-up" due to the need to replace portions of the pointing system, the gyros, which have begun to fail on the Hubble Space Telescope. Although Hubble is operating normally and conducting its scientific observations, only three of its six gyroscopes are working properly. The gyroscopes allow the telescope to point at stars, galaxies and planets. The STS-103 crew will also be replacing a Fine Guidance Sensor and an older computer with a new enhanced model, an older data tape recorder with a solid-state digital recorder, a failed spare transmitter with a new one, and degraded insulation on the telescope with new thermal insulation. The crew will also install a Battery Voltage/Temperature Improvement Kit to protect the spacecraft batteries from overcharging and overheating when the telescope goes into a safe mode

Fuel Consumption of Tractor-Trailer Trucks as Affected by Speed Limit and Payload Weight

DOT National Transportation Integrated Search

1975-11-01

The effect of speed limit and payload weight on fuel consumption was determined in tests of tractor-trailer rigs. Two virtually identical vehicles were used, one loaded with a 28,000 lb payload and the other carrying 42,000 lbs; each was driven over ...

Study to evaluate the effect of EVA on payload systems. Volume 1: Executive summary. [project planning of space missions employing extravehicular activity as a means of cost reduction

NASA Technical Reports Server (NTRS)

Patrick, J. W.; Kraly, E. F.

1975-01-01

Programmatic benefits to payloads are examined which can result from the routine use of extravehicular activity (EVA) during space missions. Design and operations costs were compared for 13 representative baseline payloads to the costs of those payloads adapted for EVA operations. The EVA-oriented concepts developed in the study were derived from these baseline concepts and maintained mission and program objectives as well as basic configurations. This permitted isolation of cost saving factors associated specifically with incorporation of EVA in a variety of payload designs and operations. The study results were extrapolated to a total of 74 payload programs. Using appropriate complexity and learning factors, net EVA savings were extrapolated to over $551M for NASA and U.S. civil payloads for routine operations. Adding DOD and ESRO payloads increases the net estimated savings of $776M. Planned maintenance by EVA indicated an estimated $168M savings due to elimination of automated service equipment. Contingency problems of payloads were also analyzed to establish expected failure rates for shuttle payloads. The failure information resulted in an estimated potential for EVA savings of $1.9 B.

Design and evaluation of a payload to support plant growth onboard COMET 1

NASA Technical Reports Server (NTRS)

Hoehn, A.; Kliss, M. H.; Luttges, M. W.; Robinson, M. C.; Stodieck, L. S.

1992-01-01

The paper describes the design and the operation principles of the Plant Module for Autonomous Space Support (P-MASS), designed to provide life support for a variety of plants, algae, and bacteria in low earth orbit during the maiden flight of COMET-1, scheduled for 1993. During flight (scheduled to continue for 30 days), both color video images and collected environmental data (including light intensity, temperature, relative humidity, CO2 and O2 concentrations, soil moisture, and nutrients released) will be downlinked to earth several times a day. These data will also be stored within the payload and retrieved from it after reentry and recovery.

The space shuttle payload planning working groups. Volume 4: Life sciences

NASA Technical Reports Server (NTRS)

1973-01-01

The findings of the Life Sciences working group of the space shuttle payload planning activity are presented. The objectives of the Life Sciences investigations are: (1) to continue the research directed at understanding the origin of life and the search for extraterrestrial evidence of life, (2) biomedical research to understand mechanisms and provide criteria for support of manned flight, (3) technology development for life support, protective systems, and work aids for providing environmental control, and (4) to study basic biological functions at all levels or organization influenced by gravity, radiation, and circadian rhythms. Examples of candidate experimental schedules and the experimental package functional requirements are included.

Draft Environmental Impact Statement for the Ulysses Mission (Tier 2)

NASA Technical Reports Server (NTRS)

1990-01-01

This Draft Environmental Impact Statement (DEIS) addresses the environmental impacts which may be caused by the preparation and operation of the Ulysses spacecraft, including its planned launch on the Space Transportation System (STS) Shuttle and the alternative of canceling further work on the mission. The launch configuration will use the STS/Inertial Upper Stage (IUS)/Payload Assist Module-Special(PAM-S) combination. The Tier 1 EIS included a delay alternative which considered the Titan 4 launch vehicle as an alternative booster stage for launch in 1991 or later. However, the U.S. Air Force, which procures the Titan 4 for NASA, could not provide a Titan 4 vehicle for the 1991 launch opportunity because of high priority Department of Defense requirements. The only expected environmental effects of the proposed action are associated with normal Shuttle launch operations. These impacts are limited largely to the near-field at the launch pad, except for temporary stratospheric ozone effects during launch and occasional sonic boom effects near the landing site. These effects have been judged insufficient to preclude Shuttle launches. In the event of (1) an accident during launch, or (2) reentry of the spacecraft from earth orbit, there are potential adverse health and environmental effects associated with the possible release of plutonium dioxide from the spacecraft's radioisotope thermoelectric generators (RTG). The potential effects considered in this EIS include risks of air and water quality impacts, local land area contamination, adverse health and safety impacts, the disturbance of biotic resources, impacts on wetland areas or areas containing historical sites, and socioeconomic impacts. Intensive analysis of the possible accidents associated with the proposed action are underway and preliminary results indicate small health or environmental risks. The results of a Final Safety Analysis Report will be available for inclusion into the final EIS.

A Monte Carlo Analysis for Collision Risk Assessment on Vega Launcher Payloads and LARES Satellite

NASA Astrophysics Data System (ADS)

Sindoni, G.; Ciufolini, I.; Battie, F.

2016-03-01

This work has been developed in the framework of the LARES mission of the Italian Space Agency (ASI). The LARES satellite has been built to test, with high accuracy, the frame-dragging effect predicted by the theory of General Relativity, specifically the Lense-Thirring drag of its node. LARES was the main payload in the qualification flight of the European Space Agency launcher VEGA. A concern arose about the possibility of an impact between the eight secondary payloads among themselves, with LARES and with the last stage of the launcher (AVUM). An impact would have caused failure on the payloads and the production of debris in violation of the space debris mitigation measures established internationally. As an additional contribution, this study allowed the effect of the payload release on the final manoeuvers of the AVUM to be understood.

NASA/ESA CV-990 Spacelab Simulation (ASSESS 2)

NASA Technical Reports Server (NTRS)

1977-01-01

Cost effective techniques for addressing management and operational activities on Spacelab were identified and analyzed during a ten day NASA-ESA cooperative mission with payload and flight responsibilities handled by the organization assigned for early Spacelabs. Topics discussed include: (1) management concepts and interface relationships; (2) experiment selection; (3) hardware development; (4) payload integration and checkout; (5) selection and training of mission specialists and payload specialists; (6) mission control center/payload operations control center interactions with ground and flight problems; (7) real time interaction during flight between principal investigators and the mission specialist/payload specialist flight crew; and (8) retrieval of scientific data and its analysis.

Sounding rocket thermal analysis techniques applied to GAS payloads. [Get Away Special payloads (STS)

NASA Technical Reports Server (NTRS)

Wing, L. D.

1979-01-01

Simplified analytical techniques of sounding rocket programs are suggested as a means of bringing the cost of thermal analysis of the Get Away Special (GAS) payloads within acceptable bounds. Particular attention is given to two methods adapted from sounding rocket technology - a method in which the container and payload are assumed to be divided in half vertically by a thermal plane of symmetry, and a method which considers the container and its payload to be an analogous one-dimensional unit having the real or correct container top surface area for radiative heat transfer and a fictitious mass and geometry which model the average thermal effects.

NICER: Mission Overview and Status

NASA Astrophysics Data System (ADS)

Arzoumanian, Zaven; Gendreau, Keith C.

2016-04-01

NASA's Neutron star Interior Composition Explorer (NICER) mission will explore the structure, dynamics, and energetics of neutron stars through soft X-ray (0.2-12 keV) timing and spectroscopy. An external attached payload on the International Space Station (ISS), NICER is manifested on the Commercial Resupply Services SpaceX-11 flight, with launch scheduled for late 2016. The NICER payload is currently in final integration and environmental testing. Ground calibration has provided robust performance measures of the optical and detector subsystems, demonstrating that the instrument meets or surpasses its effective area, timing resolution, energy resolution, etc., requirements. We briefly describe the NICER hardware, its continuing testing, operations and environment on ISS, and the objectives of NICER's prime mission—including precise radius measurements for a handful of neutron stars to constrain the equation of state of cold, ultra-dense matter. Other contributions at this meeting address specific scientific investigations that are enabled by NICER, for neutron stars in their diverse manifestations as well as for broader X-ray astrophysics through a brief, approved Guest Observer program beginning in 2018.

Payload crew activity planning integration. Task 2: Inflight operations and training for payloads

NASA Technical Reports Server (NTRS)

Hitz, F. R.

1976-01-01

The primary objectives of the Payload Crew Activity Planning Integration task were to: (1) Determine feasible, cost-effective payload crew activity planning integration methods. (2) Develop an implementation plan and guidelines for payload crew activity plan (CAP) integration between the JSC Orbiter planners and the Payload Centers. Subtask objectives and study activities were defined as: (1) Determine Crew Activity Planning Interfaces. (2) Determine Crew Activity Plan Type and Content. (3) Evaluate Automated Scheduling Tools. (4) Develop a draft Implementation Plan for Crew Activity Planning Integration. The basic guidelines were to develop a plan applicable to the Shuttle operations timeframe, utilize existing center resources and expertise as much as possible, and minimize unnecessary data exchange not directly productive in the development of the end-product timelines.

Planning and Scheduling of Payloads of AstroSat During Initial and Normal Phase Observations

NASA Astrophysics Data System (ADS)

Pandiyan, R.; Subbarao, S. V.; Nagamani, T.; Rao, Chaitra; Rao, N. Hari Prasad; Joglekar, Harish; Kumar, Naresh; Dumpa, Surya Ratna Prakash; Chauhan, Anshu; Dakshayani, B. P.

2017-06-01

On 28th September 2015, India launched its first astronomical space observatory AstroSat, successfully. AstroSat carried five astronomy payloads, namely, (i) Cadmium Zinc Telluride Imager (CZTI), (ii) Large Area X-ray Proportional Counter (LAXPC), (iii) Soft X-ray Telescope (SXT), (iv) Ultra Violet Imaging Telescope (UVIT) and (v) Scanning Sky Monitor (SSM) and therefore, has the capability to observe celestial objects in multi-wavelength. Four of the payloads are co-aligned along the positive roll axis of the spacecraft and the remaining one is placed along the positive yaw axis direction. All the payloads are sensitive to bright objects and specifically, require avoiding bright Sun within a safe zone of their bore axes in orbit. Further, there are other operational constraints both from spacecraft side and payloads side which are to be strictly enforced during operations. Even on-orbit spacecraft manoeuvres are constrained to about two of the axes in order to avoid bright Sun within this safe zone and a special constrained manoeuvre is exercised during manoeuvres. The planning and scheduling of the payloads during the Performance Verification (PV) phase was carried out in semi-autonomous/manual mode and a complete automation is exercised for normal phase/Guaranteed Time Observation (GuTO) operations. The process is found to be labour intensive and several operational software tools, encompassing spacecraft sub-systems, on-orbit, domain and environmental constraints, were built-in and interacted with the scheduling tool for appropriate decision-making and science scheduling. The procedural details of the complex scheduling of a multi-wavelength astronomy space observatory and their working in PV phase and in normal/GuTO phases are presented in this paper.

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.

Designing an Alternate Mission Operations Control Room

NASA Technical Reports Server (NTRS)

Montgomery, Patty; Reeves, A. Scott

2014-01-01

The Huntsville Operations Support Center (HOSC) is a multi-project facility that is responsible for 24x7 real-time International Space Station (ISS) payload operations management, integration, and control and has the capability to support small satellite projects and will provide real-time support for SLS launches. The HOSC is a service-oriented/ highly available operations center for ISS payloads-directly supporting science teams across the world responsible for the payloads. The HOSC is required to endure an annual 2-day power outage event for facility preventive maintenance and safety inspection of the core electro-mechanical systems. While complete system shut-downs are against the grain of a highly available sub-system, the entire facility must be powered down for a weekend for environmental and safety purposes. The consequence of this ground system outage is far reaching: any science performed on ISS during this outage weekend is lost. Engineering efforts were focused to maximize the ISS investment by engineering a suitable solution capable of continuing HOSC services while supporting safety requirements. The HOSC Power Outage Contingency (HPOC) System is a physically diversified compliment of systems capable of providing identified real-time services for the duration of a planned power outage condition from an alternate control room. HPOC was designed to maintain ISS payload operations for approximately three continuous days during planned HOSC power outages and support a local Payload Operations Team, International Partners, as well as remote users from the alternate control room located in another building.

Water Capture Device Signal Integration Board

NASA Technical Reports Server (NTRS)

Chamberlin, Kathryn J.; Hartnett, Andrew J.

2018-01-01

I am a junior in electrical engineering at Arizona State University, and this is my second internship at Johnson Space Center. I am an intern in the Command and Data Handling Branch of Avionics Division (EV2), my previous internship was also in EV2. During my previous internship I was assigned to the Water Capture Device payload, where I designed a prototype circuit board for the electronics system of the payload. For this internship, I have come back to the Water Capture Device project to further the work on the electronics design I completed previously. The Water Capture Device is an experimental payload to test the functionality of two different phase separators aboard the International Space Station (ISS). A phase separator sits downstream of a condensing heat exchanger (CHX) and separates the water from the air particles for environmental control on the ISS. With changing CHX technology, new phase separators are required. The goal of the project is to develop a test bed for the two phase separators to determine the best solution.

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.

Mars MetNet Mission - Martian Atmospheric Observational Post Network

NASA Astrophysics Data System (ADS)

Harri, Ari-Matti; Aleksashkin, Sergey; Arruego, Ignacio; Schmidt, Walter; Ponomarenko, Andrey; Apestigue, Victor; Genzer, Maria; Vazquez, Luis; Uspensky, Mikhail; Haukka, Harri

2016-04-01

A new kind of planetary exploration mission for Mars is under development 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). The scientific payload of the Mars MetNet Precursor [1] mission is divided into three categories: Atmospheric instruments, Optical devices and Composition and structure devices. Each of the payload instruments will provide significant insights in to the Martian atmospheric behavior. The key technologies of the MetNet Lander have been qualified and the electrical qualification model (EQM) of the payload bay has been built and successfully tested. MetNet Lander The MetNet landing vehicles are 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. Strawman Scientific Payload The strawman payload of the two MNL precursor models includes the following instruments: Atmospheric instruments: • MetBaro Pressure device • MetHumi Humidity device • MetTemp Temperature sensors Optical devices: • PanCam Panoramic • MetSIS Solar irradiance sensor with OWLS optical wireless system for data transfer • DS Dust sensor Composition and Structure Devices: • Tri-axial magnetometer MOURA • Tri-axial System Accelerometer 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. MetNet Mission payload instruments are specially designed to operate under very low power conditions. MNL flexible solar panels provides a total of approximately 0.7-0.8 W of electric power during the daylight time. As the provided power output is insufficient to operate all instruments simultaneously they are activated sequentially according to a specially designed cyclogram table which adapts itself to the different environmental constraints. Mission Status Full Qualification Model (QM) of the MetNet landing unit with the Precursor Mission payload is currently under functional tests. In the near future the QM unit will be exposed to environmental tests with qualification levels including vibrations, thermal balance, thermal cycling and mechanical impact shock. One complete flight unit of the entry, descent and landing systems (EDLS) has been manufactured and tested with acceptance levels. Another flight-like EDLS has been exposed to most of the qualification tests, and hence it may be used for flight after refurbishments. Accordingly two flight-capable EDLS systems exist. The eventual goal is to create a network of atmospheric observational posts around the Martian surface. Even if the MetNet mission is focused on the atmospheric science, the mission payload will also include additional kinds of geophysical instrumentation. The next step in the MetNet Precursor Mission is the demonstration of the technical robustness and scientific capabilities of the MetNet type of landing vehicle. Definition of the Precursor Mission and discussions on launch opportunities are currently under way. The baseline program development funding exists for the next five years. Flight unit manufacture of the payload bay takes about 18 months, and it will be commenced after the Precursor Mission has been defined. References [1] http://metnet.fmi.fi

Mars MetNet Mission Status

NASA Astrophysics Data System (ADS)

Harri, Ari-Matti; Aleksashkin, Sergei; Arruego, Ignacio; Schmidt, Walter; Genzer, Maria; Vazquez, Luis; Haukka, Harri

2015-04-01

New kind of planetary exploration mission for Mars is under development 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). The scientific payload of the Mars MetNet Precursor [1] mission is divided into three categories: Atmospheric instruments, Optical devices and Composition and structure devices. Each of the payload instruments will provide significant insights in to the Martian atmospheric behavior. The key technologies of the MetNet Lander have been qualified and the electrical qualification model (EQM) of the payload bay has been built and successfully tested. 1. MetNet Lander The MetNet landing vehicles are 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. 2. Scientific Payload The payload of the two MNL precursor models includes the following instruments: Atmospheric instruments: 1. MetBaro Pressure device 2. MetHumi Humidity device 3. MetTemp Temperature sensors Optical devices: 1. PanCam Panoramic 2. MetSIS Solar irradiance sensor with OWLS optical wireless system for data transfer 3. DS Dust sensor 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. MetNet Mission payload instruments are specially designed to operate in very low power conditions. MNL flexible solar panels provides a total of approximately 0.7-0.8 W of electric power during the daylight time. As the provided power output is insufficient to operate all instruments simultaneously they are activated sequentially according to a specially designed cyclogram table which adapts itself to the different environmental constraints. 3. Mission Status Full Qualification Model (QM) of the MetNet landing unit with the Precursor Mission payload is currently under functional tests. In near future the QM unit will be exposed to environmental tests with qualification levels including vibrations, thermal balance, thermal cycling and mechanical impact shock. One complete flight unit of the entry, descent and landing systems (EDLS) has been manufactured and tested with acceptance levels. Another flight-like EDLS has been exposed to most of the qualification tests, and hence it may be used for flight after refurbishments. Accordingly two flight-capable EDLS systems exist. The eventual goal is to create a network of atmospheric observational posts around the Martian surface. Even if the MetNet mission is focused on the atmospheric science, the mission payload will also include additional kinds of geophysical instrumentation. The next step in the MetNet Precursor Mission to demonstrate the technical robustness and scientific capabilities of the MetNet type of landing vehicle. Definition of the Precursor Mission and discussions on launch opportunities are currently under way. The baseline program development funding exists for the next five years. Flight unit manufacture of the payload bay takes about 18 months, and it will be commenced after the Precursor Mission has been defined. References [1] http://metnet.fmi.fi

Low energy stage study. Volume 1: Executive summary. [propulsion system configurations for orbital launching of space shuttle payloads

NASA Technical Reports Server (NTRS)

1978-01-01

Cost effective approaches for placing automated payloads into circular and elliptical orbits using energy requirements significantly lower than that provided by the smallest, currently planned shuttle upper stage, SSUS-D, were investigated. Launch costs were derived using both NASA existing/planned launch approaches as well as new propulsion concepts meeting low-energy regime requirements. Candidate new propulsion approaches considered were solid (tandem, cluster, and controlled), solid/liquid combinations and all-liquid stages. Results show that the most economical way to deliver the 129 low energy payloads is basically with a new modular, short liquid bipropellant stage system for the large majority of the payloads. For the remainder of the payloads, use the shuttle with integral OMS and the Scout form for a few specialized payloads until the Shuttle becomes operational.

Orbital transfer and release of tethered payloads. Continuation of investigation of electrodynamic stabilization and control of long orbiting tethers Martinez-Sanchez, Manuel

NASA Technical Reports Server (NTRS)

Colombo, G.; Grossi, M. D.; Arnold, D.

1983-01-01

The effect of reeling operations on the orbital altitude of the tether system and the development of control laws to minimize tether rebound upon payload release were studied. The use of the tether for LEO/GEO payload orbital transfer was also investigated. It was concluded that (1) reeling operations can contribute a significant amount of energy to the orbit of the system and should be considered in orbit calculations and predictions, (2) deployment of payloads, even very large payloads, using tethers is a practical and fully stable operation, (3) tether augmented LEO/GEO transfer operations yield useful payload gains under the practical constraint of fixed size OTV's, and (4) orbit to orbit satellite retrieval is limited by useful revisit times to orbital inclinations of less than forty-five degrees.

Spacelab operations planning. [ground handling, launch, flight and experiments

NASA Technical Reports Server (NTRS)

Lee, T. J.

1976-01-01

The paper reviews NASA planning in the fields of ground, launch and flight operations and experiment integration to effectively operate Spacelab. Payload mission planning is discussed taking consideration of orbital analysis and the mission of a multiuser payload which may be either single or multidiscipline. Payload analytical integration - as active process of analyses to ensure that the experiment payload is compatible to the mission objectives and profile ground and flight operations and that the resource demands upon Spacelab can be satisfied - is considered. Software integration is touched upon and the major integration levels in ground operational processing of Spacelab and its experimental payloads are examined. Flight operations, encompassing the operation of the Space Transportation System and the payload, are discussed as are the initial Spacelab missions. Charts and diagrams are presented illustrating the various planning areas.

Lessons learned from evaluating launch-site processing problems of Space Shuttle payloads

NASA Technical Reports Server (NTRS)

Flores, Carlos A.; Heuser, Robert E.; Sales, Johnny R.; Smith, Anthony M.

1992-01-01

The authors discuss a trend analysis program that is being conducted on the problem reports written during the processing of Space Shuttle payloads at Kennedy Space Center. The program is aimed at developing lessons learned that can both improve the effectiveness of the current payload processing cycles as well as help to guide the processing strategies for Space Station Freedom. The payload processing reports from STS 26R and STS 41 are used. A two-tier evaluation activity is described, and some typical results from the tier one analyses are presented.

Performance estimates for space shuttle vehicles using a hydrogen or a methane fueled turboramjet powered first stage

NASA Technical Reports Server (NTRS)

Knip, G., Jr.; Eisenberg, J. D.

1972-01-01

Two- and three-stage (second stage expendable) shuttle vehicles, both having a hydrogen-fueled, turboramjet-powered first stage, are compared with a two-stage, VTOHL, all-rocket shuttle in terms of payload fraction, inert weight, development cost, operating cost, and total cost. All of the vehicles place 22,680 kilograms of payload into a 500-kilometer orbit. The upper stage(s) uses hydrogen-oxygen rockets. The effect on payload fraction and vehicle inert weight of methane and methane-FLOX as a fuel-propellant combination for the three-stage vehicle is indicated. Compared with a rocket first stage for a two-stage shuttle, an airbreathing first stage results in a higher payload fraction and a lower operating cost, but a higher total cost. The effect on cost of program size and first-stage flyback is indicated. The addition of an expendable rocket second stage (three-stage vehicle) improves the payload fraction but is unattractive economically.

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.

General Environmental Verification Specification

NASA Technical Reports Server (NTRS)

Milne, J. Scott, Jr.; Kaufman, Daniel S.

2003-01-01

The NASA Goddard Space Flight Center s General Environmental Verification Specification (GEVS) for STS and ELV Payloads, Subsystems, and Components is currently being revised based on lessons learned from GSFC engineering and flight assurance. The GEVS has been used by Goddard flight projects for the past 17 years as a baseline from which to tailor their environmental test programs. A summary of the requirements and updates are presented along with the rationale behind the changes. The major test areas covered by the GEVS include mechanical, thermal, and EMC, as well as more general requirements for planning, tracking of the verification programs.

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.

Earth Science

NASA Image and Video Library

1994-04-12

The Atlas-1 (AC-77) that will loft the Geostationary Operational Environmental Satellite-J (GOES-J) next-generation advanced technology weather satellite into space sits poised for takeoff during final countdown operations at Cape Canaveral Air Station, Kennedy Space Center (KSC). GOES-J is atop the expendable launch vehicle inside the rocket's payload fairing.

Twenty-Second Annual NASA Supply and Equipment Management Conference

NASA Technical Reports Server (NTRS)

1989-01-01

The status of actions from the 1988 conference is reviewed. Environmental safety issues, definitions, and regulations; contract transition, payload logistics transition, and safety and support equipment; supply products and services, bar code technology, and inventory accuracy; equipment management workshop topics; and contract property workshop topics are outlined.

76 FR 12787 - Office of Commercial Space Transportation; Notice of Availability of the Final Environmental...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-03-08

... scenarios (land, air, and sea). The Pegasus launch vehicle falls within the parameters of the small-payload... quality; biological resources (including fish, wildlife, and plants); compatible land use; Department of Transportation Section 4(f) resources; hazardous materials, pollution prevention, and solid waste; historical...

A neural network-based input shaping for swing suppression of an overhead crane under payload hoisting and mass variations

NASA Astrophysics Data System (ADS)

Ramli, Liyana; Mohamed, Z.; Jaafar, H. I.

2018-07-01

This paper proposes an improved input shaping for minimising payload swing of an overhead crane with payload hoisting and payload mass variations. A real time unity magnitude zero vibration (UMZV) shaper is designed by using an artificial neural network trained by particle swarm optimisation. The proposed technique could predict and directly update the shaper's parameters in real time to handle the effects of time-varying parameters during the crane operation with hoisting. To evaluate the performances of the proposed method, experiments are conducted on a laboratory overhead crane with a payload hoisting, different payload masses and two different crane motions. The superiority of the proposed method is confirmed by reductions of at least 38.9% and 91.3% in the overall and residual swing responses, respectively over a UMZV shaper designed using an average operating frequency and a robust shaper namely Zero Vibration Derivative-Derivative (ZVDD). The proposed method also demonstrates a significant residual swing suppression as compared to a ZVDD shaper designed based on varying frequency. In addition, the significant reductions are achieved with a less shaper duration resulting in a satisfactory speed of response. It is envisaged that the proposed method can be used for designing effective input shapers for payload swing suppression of a crane with time-varying parameters and for a crane that employ finite actuation states.

Parametric evaluation of the cost effectiveness of Shuttle payload vibroacoustic test plans

NASA Technical Reports Server (NTRS)

Stahle, C. V.; Gongloff, H. R.; Keegan, W. B.; Young, J. P.

1978-01-01

Consideration is given to alternate vibroacoustic test plans for sortie and free flyer Shuttle payloads. Statistical decision models for nine test plans provide a viable method of evaluating the cost effectiveness of alternate vibroacoustic test plans and the associated test levels. The methodology is a major step toward the development of a useful tool for the quantitative tailoring of vibroacoustic test programs to sortie and free flyer payloads. A broader application of the methodology is now possible by the use of the OCTAVE computer code.

PASP Plus: An experiment to measure space-environment effects on photovoltaic power subsystems

NASA Technical Reports Server (NTRS)

Guidice, Donald A.

1992-01-01

The Photovoltaic Array Space Power Plus Diagnostic experiment (PASP Plus) was accepted as part of the APEX Mission payload aboard a Pegastar satellite to be orbited by a Pegasus launch vehicle in late 1992. The mission's elliptical orbit will allow us to investigate both space plasma and space radiation effects. PASP Plus will have eleven types of solar arrays and a full complement of environmental and interactions diagnostic sensors. Measurements of space-plasma interactions on the various solar arrays will be made at large negative voltages (to investigate arcing parameters) and at large positive voltages (to investigate leakage currents) by biasing the arrays to various levels up to -500 and +500 volts. The long-term deterioration in solar array performance caused by exposure to space radiation will also be investigated; radiation dosage will be measured by an electron/proton dosimeter included in the environmental sensor complement. Experimental results from PASP Plus will help establish cause-and-effect relationships and lead to improved design guidelines and test standards for new-technology solar arrays.

The Demonstration and Science Experiments (DSX) Mission

NASA Astrophysics Data System (ADS)

McCollough, J. P., II; Johnston, W. R.; Starks, M. J.; Albert, J.

2015-12-01

In 2016, the Air Force Research Laboratory will launch its Demonstration and Science Experiments mission to investigate wave-particle interactions and the particle and space environment in medium Earth orbit (MEO). The DSX spacecraft includes three experiment packages. The Wave Particle Interaction Experiment (WPIx) will perform active and passive investigations involving VLF waves and their interaction with plasma and energetic electrons in MEO. The Space Weather Experiment (SWx) includes five particle instruments to survey the MEO electron and proton environment. The Space Environmental Effects Experiment (SFx) will investigate effects of the MEO environment on electronics and materials. We will describe the capabilities of the DSX science payloads, science plans, and opportunities for collaborative studies such as conjunction observations and far-field measurements.

Environmental Impact Analysis Process. Preliminary Draft Environmental Impact Statement. Construction and Operation of Space Launch Complex 7. Volume 2. Appendices.

DTIC Science & Technology

1989-03-15

non -point source pollution managementprograms, and implement controls to improve water quality. Controls should be implemented for any project...Businesses or other for- Vandenberg AFB, and the launching of on the proposed information collection profit, non -profit institutions Ithe Titan Centaur. In...communications. The Titan Centaur launch vehicle is a modified Titan 34D designed to deliver a payload of up to U 32,000 pounds directly into polar orbit from VAFB

New NRO Eastern Processing Facility at Cape Canaveral Air Force Station Florida. Environmental Assessment:

DTIC Science & Technology

2005-08-31

to the launch complex is considered a hazardous operation. Transportation of fueled payloads will comply with AFSPCMAN 91 - 710 , Range Safety User...April. 45th Space Wing (SW). 1996b. Hazardous Materials Response Plan 32- 3 , Volume I, March. 45th Space Wing (SW). 2001. Integrated Natural...control number. 1. REPORT DATE 31 AUG 2005 2. REPORT TYPE 3 . DATES COVERED 00-00-2005 to 00-00-2005 4. TITLE AND SUBTITLE Final Environmental

Stability of Formulations Contained in the Pharmaceutical Payload Aboard Space Missions

NASA Technical Reports Server (NTRS)

Putcha, Lakshmi; Du, Brian; Daniels, Vernie; Boyd, Jason L.; Crady, Camille; Satterfield, Rick

2008-01-01

Efficacious pharmaceuticals with adequate shelf life are essential for successful space medical operations in support of space exploration missions. Physical and environmental factors unique to space missions such as vibration, G forces and ionizing radiation may adversely affect stability of pharmaceuticals intended for standard care of astronauts aboard space missions. Stable pharmaceuticals, therefore, are of paramount importance for assuring health and wellness of astronauts in space. Preliminary examination of stability of formulations from Shuttle and International Space Station (ISS) medical kits revealed that some of these medications showed physical and chemical degradation after flight raising concern of reduced therapeutic effectiveness with these medications in space. A research payload experiment was conducted with a select set of formulations stowed aboard a shuttle flight and on ISS. The payload consisted of four identical pharmaceutical kits containing 31 medications in different dosage forms that were transported to the International Space Station (ISS) aboard the Space Shuttle, STS 121. One of the four kits was stored on the shuttle and the other three were stored on the ISS for return to Earth at six months intervals on a pre-designated Shuttle flight for each kit; the shuttle kit was returned to Earth on the same flight. Standard stability indicating physical and chemical parameters were measured for all pharmaceuticals returned from the shuttle and from the first ISS increment payload along with ground-based matching controls. Results were compared between shuttle, ISS and ground controls. Evaluation of data from the three paradigms indicates that some of the formulations exhibited significant degradation in space compared to respective ground controls; a few formulations were unstable both on the ground and in space. An increase in the number of pharmaceuticals from ISS failing USP standards was noticed compared to those from the shuttle flight. A comprehensive evaluation of results is in progress.

Integrated payload and mission planning, phase 3. Volume 3: Ground real-time mission operations

NASA Technical Reports Server (NTRS)

White, W. J.

1977-01-01

The payloads tentatively planned to fly on the first two Spacelab missions were analyzed to examine the cost relationships of providing mission operations support from onboard vs the ground-based Payload Operations Control Center (POCC). The quantitative results indicate that use of a POCC, with data processing capability, to support real-time mission operations is the most cost effective case.

The Hotel Payload, plans for the period 2003-2006

NASA Astrophysics Data System (ADS)

Hansen, Gudmund; Mikalsen, Per-Arne

2003-08-01

The cost and complexity of scientific experiments, carried by traditional sounding rocket payloads, are increasing. At the same time the scientific environment faces declining funding for this basic research. In order to meet the invitation from the science community, Andøya Rocket Range runs a programme for developing a sounding rocket payload, in order to achieve an inexpensive and cost-effective tool for atmosphere research and educational training. The Hotel Payload is a new technological payload concept in the sounding rocket family. By means of standardized mechanical structures and electronics, flexibility in data collection and transmission, roomy vehicles are affordable to most of the scientific research environments as well as for educational training. A complete vehicle - ready for installation of scientific experiments - is offered to the scientists to a fixed price. The fixed price service also includes launch services. This paper describes the Hotel Payload concept and its technology. In addition the three year plan for the development project is discussed. The opportunity of using the Hotel Payload as a platform for a collaborative triangle between research, education and industry is also discussed.

Antibody Drug Conjugates: Application of Quantitative Pharmacology in Modality Design and Target Selection.

PubMed

Sadekar, S; Figueroa, I; Tabrizi, M

2015-07-01

Antibody drug conjugates (ADCs) are a multi-component modality comprising of an antibody targeting a cell-specific antigen, a potent drug/payload, and a linker that can be processed within cellular compartments to release payload upon internalization. Numerous ADCs are being evaluated in both research and clinical settings within the academic and pharmaceutical industry due to their ability to selectively deliver potent payloads. Hence, there is a clear need to incorporate quantitative approaches during early stages of drug development for effective modality design and target selection. In this review, we describe a quantitative approach and framework for evaluation of the interplay between drug- and systems-dependent properties (i.e., target expression, density, localization, turnover, and affinity) in order to deliver a sufficient amount of a potent payload into the relevant target cells. As discussed, theoretical approaches with particular considerations given to various key properties for the target and modality suggest that delivery of the payload into particular effect cells to be more sensitive to antigen concentrations for targets with slow turnover rates as compared to those with faster internalization rates. Further assessments also suggest that increasing doses beyond the threshold of the target capacity (a function of target internalization and expression) may not impact the maximum amount of payload delivered to the intended effect cells. This article will explore the important application of quantitative sciences in selection of the target and design of ADC modalities.

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

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.

Spacelab Life Sciences-2 ARC payload - An overview

NASA Technical Reports Server (NTRS)

Savage, P. D., Jr.; Dalton, B.; Hogan, R.; Leon, H.

1988-01-01

The effects of microgravity on the anatomy and physiology of rodent and primate systems will be investigated on the Spacelab Life Sciences 2 (SLS-2) mission. Here, the payload being developed at NASA Ames Research Center (ARC) is described and illustrated with drawings. The ARC payload will build upon the success of previous missions. Experiments includes asssessment of rodent cardiovascular and vestibular system responses, primate thermoregulation and metabolic responses.

Assessment of the Influence of the RaD-X Balloon Payload on the Onboard Radiation Detectors

NASA Technical Reports Server (NTRS)

Gronoff, Guilluame; Mertens, Christopher J.; Norman, Ryan B.; Straume, Tore; Lusby, Terry C.

2016-01-01

The NASA Radiation Dosimetry Experiment (RaD-X) stratospheric balloon flight mission, launched on 25 September 2015, provided dosimetric measurements above the Pfotzer maximum. The goal of taking these measurements is to improve aviation radiation models by providing a characterization of cosmic ray primaries, which are the source of radiation exposure at aviation altitudes. The RaD-X science payload consists of four instruments. The main science instrument is a tissue-equivalent proportional counter (TEPC). The other instruments consisted of three solid state silicon dosimeters: Liulin, Teledyne total ionizing dose (TID) and RaySure detectors. The instruments were housed in an aluminum structure protected by a foam cover. The structure partially shielded the detectors from cosmic rays but also created secondary particles, modifying the ambient radiation environment observed by the instruments. Therefore, it is necessary to account for the influence of the payload structure on the measured doses. In this paper, we present the results of modeling the effect of the balloon payload on the radiation detector measurements using a Geant-4 (GEometry ANd Tracking) application. Payload structure correction factors derived for the TEPC, Liulin, and TID instruments are provided as a function of altitude. Overall, the payload corrections are no more than a 7% effect on the radiation environment measurements.

STS-66 Official Crew insignia

NASA Technical Reports Server (NTRS)

1994-01-01

Designed by the crew members, the STS-66 emblem depicts the Space Shuttle Atlantis launching into Earth orbit to study global environmental change. The payload for the Atmospheric Laboratory for Applications and Science (ATLAS-3) and complimentary experiments are part of a continuing study of the atmosphere and the Sun's influence on it. The Space Shuttle is trailed by gold plumes representing the astronaut symbol and is superimposed over the Earth, much of which is visible from the flight's high inclination orbit. Sensitive instruments aboard the ATLAS pallet in the Shuttle payload bay and on the free-flying Cryogenic Infrared Spectrometers and Telescopes for the Atmospheric-Shuttle Pallet Satellite (CHRISTA-SPAS) will gaze down on Earth and toward the Sun, illustrated by the stylized sunrise and visible spectrum.

KSC-03pp0147

NASA Image and Video Library

2003-01-16

KENNEDY SPACE CENTER, FLA. -- STS-107 Payload Commander Michael Anderson gets help with his launch and entry suit from the Closeout Crew in the White Room. The environmentally controlled chamber is mated to Space Shuttle Columbia for entry into the Shuttle. Behind him is Pilot William "Willie" McCool. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. The payload on Space Shuttle Columbia includes FREESTAR (Fast Reaction Experiments Enabling Science, Technology, Applications and Research) and the SHI Research Double Module (SHI/RDM), known as SPACEHAB. Experiments on the module range from material sciences to life sciences. Liftoff is scheduled for 10:39 a.m. EST.

Space Shuttle Projects

NASA Image and Video Library

1994-09-13

Designed by the mission crew members, the STS-66 emblem depicts the Space Shuttle Atlantis launching into Earth orbit to study global environmental change. The payload for the Atmospheric Laboratory for Applications and Science (ATLAS-3) and complementary experiments were part of a continuing study of the atmosphere and the Sun's influence on it. The Space Shuttle is trailed by gold plumes representing the astronaut symbol and is superimposed over Earth, much of which is visible from the flight's high inclination orbit. Sensitive instruments aboard the ATLAS pallet in the Shuttle payload bay and on the free-flying Cryogenic Infrared Spectrometers and Telescopes for the Atmospheric-Shuttle Pallet Satellite (CHRISTA-SPAS) that gazed down on Earth and toward the Sun, are illustrated by the stylized sunrise and visible spectrum.

STS-26 Discovery, OV-103, OASIS equipment is mounted in payload bay (PLB)

NASA Image and Video Library

1988-04-18

S88-37764 (18 April 1988) --- OASIS, instrumentation which will record the environment experienced by Discovery during the STS-26 Space Shuttle mission, is lowered into position for attachment to the orbiter's aft port sill. Instrumentation sensors in the payload bay which are connected to the tape recorder module will document a variety of environmental measurements during various phases of the flight including temperature, pressure, vibration, sounds, acceleration, stress, and strain. OASIS will also record data during the Flight Readiness Firing. NASA is flying OASIS aboard Discovery in support of the Inertial Upper Stage (IUS) program office of the Air Force Space Division. The system was developed by Lockheed under a NASA contract, funded by the Air Force.

ERTS-1 - Teaching us a new way to see.

NASA Technical Reports Server (NTRS)

Mercanti, E. P.

1973-01-01

The ERTS-1 payload is discussed, giving attention to three television cameras, which view the same area in three different spectral bands. The payload includes also a multispectral scanner subsystem and a data collection system which collects information from some 150 remote, unattended, instrumented ground platforms. Many government agencies use ERTS-1 data as integral parts of their ongoing programs. Through its EROS program, the Interior Department represents the largest single recipient and user agency of data obtained from NASA aircraft and spacecraft designed to gather repetitive information related to a wide variety of earth-science and natural-resources disciplines. Questions of environmental impact are considered together with applications in agriculture, forestry, marine resources, geography, and the survey of water resources.

GOES-R Lift to Stand

NASA Image and Video Library

2016-08-23

The GOES-R spacecraft is secured on its work stand inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA Geostationary Operational Environmental Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Uncrating and Move to Vertical

NASA Image and Video Library

2016-08-23

The GOES-R spacecraft stands vertically inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA Geostationary Operational Environmental Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

Hermod: optical payload technology demonstrator flying on PROBA-V: overview of the payload development, testing and results after 1 year in orbit exploitation

NASA Astrophysics Data System (ADS)

Hernandez, S.; Blasco, J.; Henriksen, V.; Samuelsson, H.; Navasquillo, O.; Grimsgaard, M.; Mellab, K.

2017-11-01

Proba-V is the third mission of ESA's Programme for In-orbit Technology Demonstration (IOD), based on a small, high performance satellite platform and a compact payload. Besides, the main satellite instrument aiming at Vegetation imaging, Proba-V embarks five technological payloads providing early flight opportunities for novel instruments and space technologies. Successfully launched by the ESA VEGA launcher in May 2013, it has now completed its commissioning and the full calibration of platform, main instrument and additional payloads and is, since last October, fully operational. The High dEnsity space foRM cOnnector Demonstration or HERMOD is the last payload selected to fly on Proba-V. The payload objective is to validate through an actual launch and in orbit high-density optical fibre cable assembly, cumulate space heritage for fibre optics transmission and evaluate possible degradation induced by the space environment compared to on-ground tests. The future applications of this technology are for intrasatellite optical communications in view of mass reduction, the electrical grounding simplification and to increase the transmission rate. The project has been supported under an ESA GSTP contract. T&G Elektro (Norway) developed and tested the different optical cable assembly to be validated in the payload. The electrooptic modules, control, power and mechanical interfaces have been developed by DAS Photonics (Spain). The payload contains four optical channels to be studied through the experiment, two assemblies with MTP/PC connectors and two assemblies with MPO/APC connectors. Optical data is transmitted in the four independent channels using two optoelectronic conversion modules (SIOS) working at 100Mbps including 2 full duplex channels each. A FPGA is used to generate, receive and compare the different binary patterns. The number of errors (if any) and Bit Error Rate (BER) is sent to the satellite TM interface. HERMOD successfully went through all mechanical and environmental tests before the integration in a very limited time. The telemetry data is currently sent to ground on daily basis. All the channels have survived the launch and no BER has been measured with the exception of channel 2, currently recording a BER of 3.06*10-16, that exhibits from time to time a burst of errors due to synchronizing issues of the initial data frame. It is expected to observe during the operating life of the payload the first errors within the channel 4 which was designed on purpose with reduced power margin. This paper will present the full overview of the HERMOD technology demonstrator including the development, testing, validation activity, integration, commissioning and 1 year in-orbit exploitation results.

Payload vibration isolation in a microgravity environment

NASA Technical Reports Server (NTRS)

Alexander, Richard M.

1990-01-01

Many in-space research experiments require the microgravity environment attainable near the center of mass of the Space Station. Disturbances to the structure surrounding an experiment may lead to vibration levels that will degrade the microgravity environment and undermine the experiment's validity. In-flight disturbances will include vibration transmission from nearby equipment and excitation from crew activity. Isolation of these vibration-sensitive experiments is required. Analytical and experimental work accomplished to develop a payload (experiment) isolation system for use in space is described. The isolation scheme allows the payload to float freely within a prescribed boundary while being kept centered with forces generated by small jets of air. The vibration criterion was a maximum payload acceleration of 10 micro-g's (9.81x10(exp -5)m/s(exp 2), independent of frequency. An experimental setup, composed of a cart supported by air bearings on a flat granite slab, was designed and constructed to simulate the microgravity environment in the horizontal plane. Experimental results demonstrate that the air jet control system can effectively manage payload oscillatory response. An analytical model was developed and verified by comparing predicted and measured payload response. The mathematical model, which includes payload dynamics, control logic, and air jet forces, is used to investigate payload response to disturbances likely to be present in the Space Station.

CH-TRU Waste Content Codes (CH-TRUCON)

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

Washington TRU Solutions LLC

2007-08-15

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container.more » Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).« less

CH-TRU Waste Content Codes (CH-TRUCON)

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

Washington TRU Solutions LLC

2007-06-15

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container.more » Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).« less

CH-TRU Waste Content Codes (CH-TRUCON)

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

Washington TRU Solutions LLC

2007-09-20

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container.more » Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).« less

CH-TRU Waste Content Codes (CH-TRUCON)

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

Washington TRU Solutions LLC

2006-06-20

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container.more » Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).« less

CH-TRU Waste Content Codes (CH-TRUCON)

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

Washington TRU Solutions LLC

2006-01-18

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container.more » Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).« less

CH-TRU Waste Content Codes (CH-TRUCON)

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

Washington TRU Solutions LLC

2006-08-15

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container.more » Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).« less

CH-TRU Waste Content Codes (CH-TRUCON)

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

Washington TRU Solutions LLC

2006-12-20

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container.more » Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).« less

CH-TRU Waste Content Codes (CH-TRUCON)

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

Washington TRU Solutions LLC

2007-02-15

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container.more » Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).« less

CH-TRU Waste Content Codes (CH-TRUCON)

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

Washington TRU Solutions LLC

2006-09-15

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container.more » Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).« less

CH-TRU Waste Content Codes

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

Washington TRU Solutions LLC

2008-01-16

The CH-TRU Waste Content Codes (CH-TRUCON) document describes the inventory of the U.S. Department of Energy (DOE) CH-TRU waste within the transportation parameters specified by the Contact-Handled Transuranic Waste Authorized Methods for Payload Control (CH-TRAMPAC). The CH-TRAMPAC defines the allowable payload for the Transuranic Package Transporter-II (TRUPACT-II) and HalfPACT packagings. This document is a catalog of TRUPACT-II and HalfPACT authorized contents and a description of the methods utilized to demonstrate compliance with the CH-TRAMPAC. A summary of currently approved content codes by site is presented in Table 1. The CH-TRAMPAC describes "shipping categories" that are assigned to each payload container.more » Multiple shipping categories may be assigned to a single content code. A summary of approved content codes and corresponding shipping categories is provided in Table 2, which consists of Tables 2A, 2B, and 2C. Table 2A provides a summary of approved content codes and corresponding shipping categories for the "General Case," which reflects the assumption of a 60-day shipping period as described in the CH-TRAMPAC and Appendix 3.4 of the CH-TRU Payload Appendices. For shipments to be completed within an approximately 1,000-mile radius, a shorter shipping period of 20 days is applicable as described in the CH-TRAMPAC and Appendix 3.5 of the CH-TRU Payload Appendices. For shipments to WIPP from Los Alamos National Laboratory (LANL), Nevada Test Site, and Rocky Flats Environmental Technology Site, a 20-day shipping period is applicable. Table 2B provides a summary of approved content codes and corresponding shipping categories for "Close-Proximity Shipments" (20-day shipping period). For shipments implementing the controls specified in the CH-TRAMPAC and Appendix 3.6 of the CH-TRU Payload Appendices, a 10-day shipping period is applicable. Table 2C provides a summary of approved content codes and corresponding shipping categories for "Controlled Shipments" (10-day shipping period).« less

GEP, A Geophysical and Environemental integrated payload for ExoMars

NASA Astrophysics Data System (ADS)

Spohn, T.; Lognonne, P.; Dehant, V.; Giardini, D.; Friis-Christensen, E.; Calcutt, S.; GEP Team

The goal of the GEP proposed onboard the ExoMars mission is to provide the first complete set of geophysical and environmental data of Mars. A full mass of 20 kg is envisaged, enabling a payload of about 5 kg serviced by common integrated subsystems. GEP will first monitor the present Martian climate and meteorology by providing a unique monitoring on potential hazards for future human exploration missions (radiations, atmospheric electricity, dust) and on atmospheric parameters (wind, pressure, temperature, humidity). Such a long term monitoring has never been performed since the Viking landers. GEP will then provide, for the first time, a complete geophysical monitoring of Mars. It will search for remote and regional seismic activity, will measure the heat flux of the planets, will monitor the rotation of Mars and will study the magnetic field at the surface and finally will constrain the subsurface in the vicinity of the ExoMars landing site and the deep interior. By providing these new geophysical data and associated constraints on the interior and on the actual geologic activity of the surface, GEP will provide a major step in our understanding of the geological evolution of the planet and the habitability conditions during the first billion years, enabling a full understanding of the surface and mineralogical observations performed by the Pasteur payload onboard the ExoMars rover and by the payload onboard the MSL NASA 2009 mission.

Balloonborne lidar payloads for remote sensing

NASA Astrophysics Data System (ADS)

Shepherd, O.; Aurilio, G.; Hurd, A. G.; Rappaport, S. A.; Reidy, W. P.; Rieder, R. J.; Bedo, D. E.; Swirbalus, R. A.

1994-02-01

A series of lidar experiments has been conducted using the Atmospheric Balloonborne Lidar Experiment payload (ABLE). These experiments included the measurement of atmospheric Rayleigh and Mie backscatter from near space (approximately 30 km) and Raman backscatter measurements of atmospheric constituents as a function of altitude. The ABLE payload consisted of a frequency-tripled Nd:YAG laser transmitter, a 50 cm receiver telescope, and filtered photodetectors in various focal plane configurations. The payload for lidar pointing, thermal control, data handling, and remote control of the lidar system. Comparison of ABLE performance with that of a space lidar shows significant performance advantages and cost effectiveness for balloonborne lidar systems.

Lightning Effects in the Payload Changeout Room

NASA Technical Reports Server (NTRS)

Thomas, Garland L.; Fisher, Franklin A.; Collier, Richard S.; Medelius, Pedro J.

1997-01-01

Analytical and empirical studies have been performed to provide better understanding of the electromagnetic environment inside the Payload Changeout Room and Orbiter payload bay resulting from lightning strikes to the launch pad lightning protection system. The analytical studies consisted of physical and mathematical modeling of the pad structure and the Payload Changeout Room. Empirical testing was performed using a lightning simulator to simulate controlled (8 kA) lightning strikes to the catenary wire lightning protection system. In addition to the analyses and testing listed above, an analysis of the configuration with the vehicle present was conducted, in lieu of testing, by the Finite Difference, Time Domain method.

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.

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.

Integrated operations payloads/fleet analysis study extension report

NASA Technical Reports Server (NTRS)

1971-01-01

An analysis of the factors affecting the cost effectiveness of space shuttle operations is presented. The subjects discussed are: (1)payload data bank, (2) program risk analysis, (3)navigation satellite program, and (4) reusable launch systems.

An approximate solution to improve computational efficiency of impedance-type payload load prediction

NASA Technical Reports Server (NTRS)

White, C. W.

1981-01-01

The computational efficiency of the impedance type loads prediction method was studied. Three goals were addressed: devise a method to make the impedance method operate more efficiently in the computer; assess the accuracy and convenience of the method for determining the effect of design changes; and investigate the use of the method to identify design changes for reduction of payload loads. The method is suitable for calculation of dynamic response in either the frequency or time domain. It is concluded that: the choice of an orthogonal coordinate system will allow the impedance method to operate more efficiently in the computer; the approximate mode impedance technique is adequate for determining the effect of design changes, and is applicable for both statically determinate and statically indeterminate payload attachments; and beneficial design changes to reduce payload loads can be identified by the combined application of impedance techniques and energy distribution review techniques.

Simulating flight boundary conditions for orbiter payload modal survey

NASA Technical Reports Server (NTRS)

Chung, Y. T.; Sernaker, M. L.; Peebles, J. H.

1993-01-01

An approach to simulate the characteristics of the payload/orbiter interfaces for the payload modal survey was developed. The flexure designed for this approach is required to provide adequate stiffness separation in the free and constrained interface degrees of freedom to closely resemble the flight boundary condition. Payloads will behave linearly and demonstrate similar modal effective mass distribution and load path as the flight if the flexure fixture is used for the payload modal survey. The potential non-linearities caused by the trunnion slippage during the conventional fixed base modal survey may be eliminated. Consequently, the effort to correlate the test and analysis models can be significantly reduced. An example is given to illustrate the selection and the sensitivity of the flexure stiffness. The advantages of using flexure fixtures for the modal survey and for the analytical model verification are also demonstrated.

Optimal design and experimental analyses of a new micro-vibration control payload-platform

NASA Astrophysics Data System (ADS)

Sun, Xiaoqing; Yang, Bintang; Zhao, Long; Sun, Xiaofen

2016-07-01

This paper presents a new payload-platform, for precision devices, which possesses the capability of isolating the complex space micro-vibration in low frequency range below 5 Hz. The novel payload-platform equipped with smart material actuators is investigated and designed through optimization strategy based on the minimum energy loss rate, for the aim of achieving high drive efficiency and reducing the effect of the magnetic circuit nonlinearity. Then, the dynamic model of the driving element is established by using the Lagrange method and the performance of the designed payload-platform is further discussed through the combination of the controlled auto regressive moving average (CARMA) model with modified generalized prediction control (MGPC) algorithm. Finally, an experimental prototype is developed and tested. The experimental results demonstrate that the payload-platform has an impressive potential of micro-vibration isolation.

Space station needs, attributes, and architectural options study. Volume 1: Missions and requirements

NASA Technical Reports Server (NTRS)

1983-01-01

Science and applications, NOAA environmental observation, commercial resource observations, commercial space processing, commercial communications, national security, technology development, and GEO servicing are addressed. Approach to time phasing of mission requirements, system sizing summary, time-phased user mission payload support, space station facility requirements, and integrated time-phased system requirements are also addressed.

Progress in supersonic cruise aircraft technology

NASA Technical Reports Server (NTRS)

Driver, C.

1978-01-01

The supersonic cruise aircraft research program identified significant improvements in the technology areas of propulsion, aerodynamics, structures, takeoff and landing procedures, and advanced configuration concepts. Application of these technology areas to a commercial aircraft is discussed. An advanced SST family of aircraft which may be environmentally acceptable, have flexible range-payload capability, and be economically viable is projected.

GOES-R Uncrating and Move to Vertical

NASA Image and Video Library

2016-08-23

Team members remove a protective plastic covering from the GOES-R spacecraft inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA Geostationary Operational Environmental Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Uncrating and Move to Vertical

NASA Image and Video Library

2016-08-23

The shipping container is lifted off the GOES-R spacecraft inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA Geostationary Operational Environmental Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Lift to Stand

NASA Image and Video Library

2016-08-23

An overhead crane moves the GOES-R spacecraft toward its work stand inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA Geostationary Operational Environmental Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Uncrating and Move to Vertical

NASA Image and Video Library

2016-08-23

The GOES-R spacecraft is revealed following its uncrating inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA Geostationary Operational Environmental Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

65. DETAIL OF ASSISTANT LAUNCH CONTROLLER AND LAUNCH CONTROLLER PANELS ...

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

65. DETAIL OF ASSISTANT LAUNCH CONTROLLER AND LAUNCH CONTROLLER PANELS LOCATED NEAR CENTER OF SLC-3E CONTROL ROOM. NOTE 30-CHANNEL COMMUNICATIONS PANELS. PAYLOAD ENVIRONMENTAL CONTROL AND MONITORING PANELS (LEFT) AND LAUNCH OPERATORS PANEL (RIGHT) IN BACKGROUND. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Operations Building, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

KSC-2009-1369

NASA Image and Video Library

2008-11-04

VANDENBERG AIR FORCE BASE, Calif. – The latest polar-orbiting operational environmental weather satellite developed by NASA for the National Oceanic and Atmospheric Administration, called NOAA-N Prime, is moved into a NASA payload processing facility to be prepared for a Feb. 4 launch. NOAA-N Prime, built by Lockheed Martin, is similar to NOAA-N launched on May 20, 2005.

Reusable Reentry Satellite (RRS): Thermal control trade study

NASA Technical Reports Server (NTRS)

Wallace, Clark

1990-01-01

The design and assessment work performed in defining the on-orbit Thermal Control Subsystem (TCS) requirements for the Reusable Reentry Satellite (RRS) is discussed. Specifically, it describes the hardware and design measures necessary for maintaining the Payload Module (PM) Environmental Control Life Support System (ECLSS) heat exchanger, the hydrazine propellant, and PM water supply within their required temperature limits.

An Innovative Unmanned System for Advanced Environmental Monitoring: Design and Development

NASA Astrophysics Data System (ADS)

Marsella, Ennio; Giordano, Laura; Evangelista, Lorenza; Iengo, Antonio; di Filippo, Alessandro; Coppola, Aniello

2015-04-01

The paper summarizes the design and development of a new technology and tools for real-time coordination and control of unmanned vehicles for advanced environmental monitoring. A new Unmanned System has been developed at Institute for Coastal Marine Environmental - National Research Council (Italy), in the framework of two National Operational Programs (PON): Technological Platform for Geophysical and Environmental Marine Survey-PITAM and Integrated Systems and Technologies for Geophysical and Environmental Monitoring in coastal-marine areas-STIGEAC. In particular, the system includes one Unmanned Aerial Vehicle (UAV) and two Unmanned Marine Vehicles (UMV). Major innovations concern the implementation of a new architecture to control each drone and/or to allow the cooperation between heterogeneous vehicles, the integration of distributed sensing techniques and real-time image processing capabilities. Part of the research in these projects involves, therefore, an architecture, where the ground operator can communicate with the Unmanned Vehicles at various levels of abstraction using pointing devices and video viewing. In detail, a Ground Control Station (GCS) has been design and developed to allow the government in security of the drones within a distance up to twenty kilometers for air explorations and within ten nautical miles for marine activities. The Ground Control Station has the following features: 1. hardware / software system for the definition of the mission profiles; 3. autonomous and semi-autonomous control system by remote control (joystick or other) for the UAV and UMVs; 4. integrated control system with comprehensive visualization capabilities, monitoring and archiving of real-time data acquired from scientific payload; 5. open structure to future additions of systems, sensors and / or additional vehicles. In detail, the UAV architecture is a dual-rotor, with an endurance ranging from 55 to 200 minutes, depending on payload weight (maximum 26 kg) and wind conditions, and a capability to survey an area of up to 5x5 square kilometers. The UAV payload consists of three different types of sensors: a laser scanner, a thermal-camera and an integrated camera reflex with gimbal. The laser scanner has 10 mm survey-grade accuracy and a field of view up to 330°. The thermal-camera has a resolution 640x480 pixels and a thermal sensitivity <20 mK (at 30 °C), while the reflex is a 22.3 Megapixel full-frame sensor. In addition to the common applications, such as generating mapping, charting, and geodesy products, the system allows performing real-time survey and monitoring of different natural risk under dangerous condition. The system is, also, address to environmental risk monitoring and prevention, industrial activity and emergency interventions related to environmental crises (i.e. oil spills).

KSC-03PP-0149

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. -- STS-107 Payload Specialist Ilan Ramon, who represents the Israel Space Agency, chats with the Closeout Crew in the White Room before entering Columbia. The environmentally controlled chamber is mated to Space Shuttle Columbia for entry into the Shuttle. Ramon is the first Israeli astronaut to fly in the Shuttle. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. The payload on Space Shuttle Columbia includes FREESTAR (Fast Reaction Experiments Enabling Science, Technology, Applications and Research) and the SHI Research Double Module (SHI/RDM), known as SPACEHAB. Experiments on the module range from material sciences to life sciences. Liftoff is scheduled for 10:39 a.m. EST.

KSC-03pp0149

NASA Image and Video Library

2003-01-16

KENNEDY SPACE CENTER, FLA. -- STS-107 Payload Specialist Ilan Ramon, who represents the Israel Space Agency, chats with the Closeout Crew in the White Room before entering Columbia. The environmentally controlled chamber is mated to Space Shuttle Columbia for entry into the Shuttle. Ramon is the first Israeli astronaut to fly in the Shuttle. STS-107 is a mission devoted to research and will include more than 80 experiments that will study Earth and space science, advanced technology development, and astronaut health and safety. The payload on Space Shuttle Columbia includes FREESTAR (Fast Reaction Experiments Enabling Science, Technology, Applications and Research) and the SHI Research Double Module (SHI/RDM), known as SPACEHAB. Experiments on the module range from material sciences to life sciences. Liftoff is scheduled for 10:39 a.m. EST.

Impact of low gravity on water electrolysis operation

NASA Technical Reports Server (NTRS)

Powell, F. T.; Schubert, F. H.; Lee, M. G.

1989-01-01

Advanced space missions will require oxygen and hydrogen utilities for several important operations including the following: (1) propulsion; (2) electrical power generation and storage; (3) environmental control and life support; (4) extravehicular activity; (5) in-space manufacturing and (6) in-space science activities. An experiment suited to a Space Shuttle standard middeck payload has been designed for the Static Feed Water Electrolysis technology which has been viewed as being capable of efficient, reliable oxygen and hydrogen generation with few subsystem components. The program included: end use design requirements, phenomena to be studied, Space Shuttle Orbiter experiment constraints, experiment design and data requirements, and test hardware requirements. The objectives are to obtain scientific and engineering data for future research and development and to focus on demonstrating and monitoring for safety of a standard middeck payload.

Space Shuttle utilization characteristics with special emphasis on payload design, economy of operation and effective space exploitation

NASA Technical Reports Server (NTRS)

Turner, D. N.

1981-01-01

The reusable manned Space Shuttle has made new and innovative payload planning a reality and opened the door to a variety of payload concepts formerly unavailable in routine space operations. In order to define the payload characteristics and program strategies, current Shuttle-oriented programs are presented: NASA's Space Telescope, the Long Duration Exposure Facility, the West German Shuttle Pallet Satellite, and the Goddard Space Flight Center's Multimission Modular Spacecraft. Commonality of spacecraft design and adaptation for specific mission roles minimizes payload program development and STS integration costs. Commonality of airborne support equipment assures the possibility of multiple program space operations with the Shuttle. On-orbit maintenance and repair was suggested for the module and system levels. Program savings from 13 to over 50% were found obtainable by the Shuttle over expendable launch systems, and savings from 17 to 45% were achievable by introducing reuse into the Shuttle-oriented programs.

Plasma observations of the active mother-daughter payload MAIMIK in the lower thermosphere

NASA Astrophysics Data System (ADS)

Friedrich, M.; Torkar, K. M.; Troim, J.; Maehlum, B. N.

1991-03-01

Observations during the re-entry into the denser atmosphere of a mother-daughter payload equipped with a powerful electron gun are reported. The behavior of the payload potential, the flux of returning electrons and the propagation of an HF signal differed drastically at heights below approx. 130 km from what was observed in the F-region; in particular, the payload potential remained well below the accelerator voltage. A 10 MHz signal transmitted between daughter and mother showed variations both in phase and amplitude, whereas no such signatures were seen earlier in the flight when the two bodies were closer to each other. The most likely explanation is based on an increase in plasma density near the payloads in denser regions of the atmosphere. The dynamics of the effects are discussed in terms of ion plasma waves, although no firm conclusions can be drawn.

Science aspects of a 1980 flyby of Comet Encke with a Pioneer spacecraft

NASA Technical Reports Server (NTRS)

Jaffe, L. D.; Elachi, C.; Giffin, C. E.; Huntress, W.; Newburn, R. L.; Parker, R. H.; Taylor, F. W.; Thorpe, T. E.

1974-01-01

Results are presented of an investigation of the feasibility of a 1980 flyby of Comet Encke using a Pioneer class spacecraft. Specific areas studied include: science objectives and rationale; science observables; effects of encounter velocity; science encounter and targeting requirements; selection and description of science instruments; definition of a candidate science payload; engineering characteristics of suggested payload; value of a separable probe; science instruments for a separable probe; science payload integration problems; and science operations profile.

Vibration isolation and dual-stage actuation pointing system for space precision payloads

NASA Astrophysics Data System (ADS)

Kong, Yongfang; Huang, Hai

2018-02-01

Pointing and stability requirements for future space missions are becoming more and more stringent. This work follows the pointing control method which consists of a traditional spacecraft attitude control system and a payload active pointing loop, further proposing a vibration isolation and dual-stage actuation pointing system for space precision payloads based on a soft Stewart platform. Central to the concept is using the dual-stage actuator instead of the traditional voice coil motor single-stage actuator to improve the payload active pointing capability. Based on a specified payload, the corresponding platform was designed to be installed between the spacecraft bus and the payload. The performance of the proposed system is demonstrated by preliminary closed-loop control investigations in simulations. With the ordinary spacecraft bus, the line-of-sight pointing accuracy can be controlled to below a few milliarcseconds in tip and tilt. Meanwhile, utilizing the voice coil motor with the softening spring in parallel, which is a portion of the dual-stage actuator, the system effectively achieves low-frequency motion transmission and high-frequency vibration isolation along the other four degree-of-freedom directions.

The BIMDA shuttle flight mission: a low cost microgravity payload.

PubMed

Holemans, J; Cassanto, J M; Moller, T W; Cassanto, V A; Rose, A; Luttges, M; Morrison, D; Todd, P; Stewart, R; Korszun, R Z; Deardorff, G

1991-01-01

This paper presents the design, operation and experiment protocol of the Bioserve sponsored flights of the ITA Materials Dispersion Apparatus Payload (BIMDA) flown on the Space Shuttle on STS-37. The BIMDA payload represents a joint effort between ITA (Instrumentation Technology Associates, Inc.) and Bioserve Space Technologies, a NASA Center for the Commercial Development of Space, to investigate the methods and commercial potential of biomedical and fluid science applications in the microgravity environment of space. The BIMDA payload, flown in a Refrigerator/Incubator Module (R/IM) in the Orbiter middeck, consists of three different devices designed to mix fluids in space; four Materials Dispersion Apparatus (MDA) Minilabs developed by ITA, six Cell Syringes, and six Bioprocessing Modules both developed by NASA JSC and Bioserve. The BIMDA design and operation reflect user needs for late access prior to launch (<24 h) and early access after landing (<2 h). The environment for the payload is temperature controlled by the R/IM. The astronaut crew operates the payload and documents its operation. The temperature of the payload is recorded automatically during flight. The flight of the BIMDA payload is the first of two development flights of the MDA on the Space Shuttle. Future commercial flights of ITA's Materials Dispersion Apparatus on the Shuttle will be sponsored by NASA's Office of Commercial Programs and will take place over the next three years. Experiments for the BIMDA payload include research into the following areas: protein crystal growth, thin film membrane casting, collagen formation, fibrin clot formation, seed germination, enzymatic catalysis, zeolite crystallization, studies of mixing effects of lymphocyte functions, and solute diffusion and transport.

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

NASA Technical Reports Server (NTRS)

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

2014-01-01

With an increase in 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 real-time 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 Video 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. This paper describes the logistics and lessons learned in upgrading a control center capability in the middle of complex real-time operations. Combining the efficiencies of controller interaction and new technology infusion were prime drivers for this upgrade to handle the increased utilization of science research on ISS. The success of this project could not jeopardize the current operations while these facility upgrades occurred.

NASA LeRC's Acoustic Fill Effect Test Program and Results

NASA Technical Reports Server (NTRS)

Hughes, William O.; Mcnelis, Mark E.; Manning, Jerome E.

1994-01-01

NASA Lewis Research Center, in conjunction with General Dynamics Space Systems Division, has performed a test program to investigate the acoustic fill effect for an unblanketed payload fairing for a variety of payload simulators. This paper will discuss this test program and fill factor test data, and make comparisons with theoretical predictions. This paper will also address the NASA acoustic fill effect standard which was verified from the test data analysis.

KSC-98pc270

NASA Image and Video Library

1998-02-05

KENNEDY SPACE CENTER, FLA. -- The STS-90 Neurolab payload is lowered into its payload canister in KSC's Operations and Checkout Building. Investigations during the Neurolab mission will focus on the effects of microgravity on the nervous system. Specifically, experiments will study the adaptation of the vestibular system, the central nervous system, and the pathways that control the ability to sense location in the absence of gravity, as well as the effect of microgravity on a developing nervous system. The crew of STS-90, slated for launch in April, will include Commander Richard Searfoss, Pilot Scott Altman, Mission Specialists Richard Linnehan, Dafydd (Dave) Williams, M.D., and Kathryn (Kay) Hire, and Payload Specialists Jay Buckey, M.D., and James Pawelczyk, Ph.D

KSC-98pc269

NASA Image and Video Library

1998-02-05

KENNEDY SPACE CENTER, FLA. -- The STS-90 Neurolab payload is lowered into its payload canister in KSC's Operations and Checkout Building. Investigations during the Neurolab mission will focus on the effects of microgravity on the nervous system. Specifically, experiments will study the adaptation of the vestibular system, the central nervous system, and the pathways that control the ability to sense location in the absence of gravity, as well as the effect of microgravity on a developing nervous system. The crew of STS-90, slated for launch in April, will include Commander Richard Searfoss, Pilot Scott Altman, Mission Specialists Richard Linnehan, Dafydd (Dave) Williams, M.D., and Kathryn (Kay) Hire, and Payload Specialists Jay Buckey, M.D., and James Pawelczyk, Ph.D

Shuttle payload minimum cost vibroacoustic tests

NASA Technical Reports Server (NTRS)

Stahle, C. V.; Gongloff, H. R.; Young, J. P.; Keegan, W. B.

1977-01-01

This paper is directed toward the development of the methodology needed to evaluate cost effective vibroacoustic test plans for Shuttle Spacelab payloads. Statistical decision theory is used to quantitatively evaluate seven alternate test plans by deriving optimum test levels and the expected cost for each multiple mission payload considered. The results indicate that minimum costs can vary by as much as $6 million for the various test plans. The lowest cost approach eliminates component testing and maintains flight vibration reliability by performing subassembly tests at a relatively high acoustic level. Test plans using system testing or combinations of component and assembly level testing are attractive alternatives. Component testing alone is shown not to be cost effective.

Mars MetNet Mission - Martian Atmospheric Observational Post Network

NASA Astrophysics Data System (ADS)

Hari, Ari-Matti; Haukka, Harri; Aleksashkin, Sergey; Arruego, Ignacio; Schmidt, Walter; Genzer, Maria; Vazquez, Luis; Siikonen, Timo; Palin, Matti

2017-04-01

A new kind of planetary exploration mission for Mars is under development 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). The scientific payload of the Mars MetNet Precursor [1] mission is divided into three categories: Atmospheric instruments, Optical devices and Composition and structure devices. Each of the payload instruments will provide significant insights in to the Martian atmospheric behavior. The key technologies of the MetNet Lander have been qualified and the electrical qualification model (EQM) of the payload bay has been built and successfully tested. 1. MetNet Lander The MetNet landing vehicles are 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. 2. Strawman Scientific Payload The strawman payload of the two MNL precursor models includes the following instruments: Atmospheric instruments: - MetBaro Pressure device - MetHumi Humidity device - MetTemp Temperature sensors Optical devices: - PanCam Panoramic - MetSIS Solar irradiance sensor with OWLS optical wireless system for data transfer - DS Dust sensor Composition and Structure Devices: Tri-axial magnetometer MOURA Tri-axial System Accelerometer 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. MetNet Mission payload instruments are specially designed to operate under very low power conditions. MNL flexible solar panels provides a total of approximately 0.7-0.8 W of electric power during the daylight time. As the provided power output is insufficient to operate all instruments simultaneously they are activated sequentially according to a specially designed cyclogram table which adapts itself to the different environmental constraints. 3. Mission Status he eventual goal is to create a network of atmospheric observational posts around the Martian surface. Even if the MetNet mission is focused on the atmospheric science, the mission payload will also include additional kinds of geophysical instrumentation. The next step is the MetNet Precursor Mission that will demonstrate the technical robustness and scientific capabilities of the MetNet type of landing vehicle. Definition of the Precursor Mission and discussions on launch opportunities are currently under way. The first MetNet Science Payload Precursors have already been successfully completed, e,g, the REMS/MSL and DREAMS/Exomars-2016. The next MetNet Payload Precursors will be METEO/Exomars-2018 and MEDA/Mars-2020. The baseline program development funding exists for the next seven years. Flight unit manufacture of the payload bay takes about 18 months, and it will be commenced after the Precursor Mission has been defined. References [1] http://metnet.fmi.fi

High-Rate Communications Outage Recorder Operations for Optimal Payload and Science Telemetry Management Onboard the International Space Station

NASA Technical Reports Server (NTRS)

Shell, Michael T.; McElyea, Richard M. (Technical Monitor)

2002-01-01

All International Space Station (ISS) Ku-band telemetry transmits through the High-Rate Communications Outage Recorder (HCOR). The HCOR provides the recording and playback capability for all payload, science, and International Partner data streams transmitting through NASA's Ku-band antenna system. The HCOR is a solid-state memory recorder that provides recording capability to record all eight ISS high-rate data during ISS Loss-of-Signal periods. NASA payloads in the Destiny module are prime users of the HCOR; however, NASDA and ESA will also utilize the HCOR for data capture and playback of their high data rate links from the Kibo and Columbus modules. Marshall Space Flight Center's Payload Operations Integration Center manages the HCOR for nominal functions, including system configurations and playback operations. The purpose of this paper is to present the nominal operations plan for the HCOR and the plans for handling contingency operations affecting payload operations. In addition, the paper will address HCOR operation limitations and the expected effects on payload operations. The HCOR is manifested for ISS delivery on flight 9A with the HCOR backup manifested on flight 11A. The HCOR replaces the Medium-Rate Communications Outage Recorder (MCOR), which has supported payloads since flight 5A.1.

Using Life-Cycle Human Factors Engineering to Avoid $2.4 Million in Costs: Lessons Learned from NASA's Requirements Verification Process for Space Payloads

NASA Technical Reports Server (NTRS)

Carr, Daniel; Ellenberger, Rich

2008-01-01

The Human Factors Implementation Team (HFIT) process has been used to verify human factors requirements for NASA International Space Station (ISS) payloads since 2003, resulting in $2.4 million in avoided costs. This cost benefit has been realized by greatly reducing the need to process time-consuming formal waivers (exceptions) for individual requirements violations. The HFIT team, which includes astronauts and their technical staff, acts as the single source for human factors requirements integration of payloads. HFIT has the authority to provide inputs during early design phases, thus eliminating many potential requirements violations in a cost-effective manner. In those instances where it is not economically or technically feasible to meet the precise metric of a given requirement, HFIT can work with the payload engineers to develop common sense solutions and formally document that the resulting payload design does not materially affect the astronaut s ability to operate and interact with the payload. The HFIT process is fully ISO 9000 compliant and works concurrently with NASA s formal systems engineering work flow. Due to its success with payloads, the HFIT process is being adapted and extended to ISS systems hardware. Key aspects of this process are also being considered for NASA's Space Shuttle replacement, the Crew Exploration Vehicle.

Mobile Geochemistry Instrument Package Facility (MGIPF) for In Situ Mineralogical and Chemical Analysis of Planetary Surface Material

NASA Astrophysics Data System (ADS)

Klingelhöfer, G.; Romstedt, J.; Henkel, H.; Michaelis, H.; Brückner, J.; D'Uston, C.

A first order requirement for any spacecraft mission to land on a solid planetary or moon surface is instrumentation for in-situ mineralogical and chemical analysis 2 Such analysis provide data needed for primary classification and characterization of surface materials present We will discuss a mobile instrument package we have developed for in-situ investigations under harsh environmental conditions like on Mercury or Mars This Geochemistry Instrument Package Facility is a compact box also called payload cab containing three small advanced geochemistry mineralogy instruments the chemical spectrometer APXS the mineralogical M o ssbauer spectrometer MIMOS II 3 and a textural imager close-up camera The payload cab is equipped with two actuating arms with two degrees of freedom permitting precision placement of all instruments at a chosen sample This payload cab is the central part of the small rover Nanokhod which has the size of a shoebox 1 The Nanokhod rover is a tethered system with a typical operational range of sim 100 m Of course the payload cab itself can be attached by means of its arms to any deployment device of any other rover or deployment device 1 Andre Schiele Jens Romstedt Chris Lee Sabine Klinkner Rudi Rieder Ralf Gellert G o star Klingelh o fer Bodo Bernhardt Harald Michaelis The new NANOKHOD Engineeering model for extreme cold environments 8th International symposium on Artificial Intelligence Robotics and Automation in Space 5 - 9 September 2005

GOES-R ITAR Photos for Media Day

NASA Image and Video Library

2016-09-26

The Geostationary Operational Environmental Satellite (GOES-R) is undergoing final launch preparations prior to fueling inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Uncrating and Move to Vertical

NASA Image and Video Library

2016-08-23

The GOES-R spacecraft is inspected after being uncrated and raised to vertical inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA Geostationary Operational Environmental Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Rotation to Vertical

NASA Image and Video Library

2016-09-15

The Geostationary Operational Environmental Satellite (GOES-R) is lifted to the vertical position on an “up-ender” inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Uncrating and Move to Vertical

NASA Image and Video Library

2016-08-23

Team members monitor progress as the GOES-R spacecraft is lifted from horizontal to vertical inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA Geostationary Operational Environmental Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Uncrating and Move to Vertical

NASA Image and Video Library

2016-08-23

Team members monitor progress as the GOES-R spacecraft is raised to vertical inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA Geostationary Operational Environmental Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Fairing Inspection

NASA Image and Video Library

2016-09-26

Team members with United Launch Alliance (ULA) inspect the first half of the fairing for the Geostationary Operational Environmental Satellite (GOES-R) inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a ULA Atlas V rocket in November.

GOES-R Rotation to Vertical

NASA Image and Video Library

2016-09-15

The Geostationary Operational Environmental Satellite (GOES-R) is raised to the vertical position on an “up-ender” inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Lift to Stand

NASA Image and Video Library

2016-08-23

Team members monitor progress as an overhead crane lowers the GOES-R spacecraft into its work stand inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA Geostationary Operational Environmental Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Lift to Stand

NASA Image and Video Library

2016-08-23

Team members monitor progress as an overhead crane lowers the GOES-R spacecraft toward its work stand inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA Geostationary Operational Environmental Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Lift to Stand

NASA Image and Video Library

2016-08-23

An overhead crane lifts the GOES-R spacecraft to move it into its work stand inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA Geostationary Operational Environmental Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Lift to Stand

NASA Image and Video Library

2016-08-23

An overhead crane is positioned to move the GOES-R spacecraft into its work stand inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA Geostationary Operational Environmental Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Rotation to Vertical

NASA Image and Video Library

2016-09-15

The Geostationary Operational Environmental Satellite (GOES-R) has been secured in the vertical position on an “up-ender” inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Rotation to Vertical

NASA Image and Video Library

2016-09-15

Team members are securing the Geostationary Operational Environmental Satellite (GOES-R) in the vertical position on an “up-ender” inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

77 FR 21619 - Office of Commercial Space Transportation; Notice of Intent To Prepare an Environmental Impact...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-04-10

... rocket propellant-1 or refined petroleum-1 (RP-1), as propellants to carry payloads into orbit. The... tank with a maximum propellant (RP-1 and LOX) load of approximately 6,900 gallons. As part of the... processing-hangar, a launch pad and stand with its associated flame duct, propellant storage and handling...

Integrated orbital servicing and payloads study. Volume 2: Technical and cost analysis

NASA Technical Reports Server (NTRS)

1975-01-01

The details and background used in the investigation of orbital servicing and payloads are presented. Topics discussed include review of previous models, application of servicing to communications satellites, assessment of spacecraft servicing, cost of servicing, and launch vehicle effects on spacecraft.

Evaluation of space environmental effects on metals and optical thin films on EOIM-3

NASA Technical Reports Server (NTRS)

Vaughn, Jason A.; Linton, Roger C.; Finckenor, Miria M.; Kamenetzky, Rachel R.

1995-01-01

Metals and optical thin films exposed to the space environment on the Third Flight of the Evaluation of Oxygen Interactions with Materials (EOIM-3) payload, onboard Space Shuttle mission STS-46 were evaluated. The materials effects described in this paper include the effects of space exposure on various pure metals, optical thin films, and optical thin film metals. The changes induced by exposure to the space environment in the material properties were evaluated using bidirectional reflectance distribution function (BRDF), specular reflectance (250 nm to 2500 nm), ESCA, VUV reflectance (120 nm to 200 nm), ellipsometry, FTIR and optical properties. Using these analysis techniques gold optically thin film metal mirrors with nickel undercoats were observed to darken due to nickel diffusion through the gold to the surface. Also, thin film nickel mirrors formed nickel oxide due to exposure to both the atmosphere and space.

VANDENBERG AIR FORCE BASE, CALIF. - Workers mate the Pegasus , with its cargo of the SciSat-1 payload to the L-1011 carrier aircraft. The SciSat-1 weighs approximately 330 pounds and after launch will be placed in a 400-mile-high polar orbit to investigate processes that control the distribution of ozone in the upper atmosphere. The data from the satellite will provide Canadian and international scientists with improved measurements relating to global ozone processes and help policymakers assess existing environmental policy and develop protective measures for improving the health of our atmosphere, preventing further ozone depletion. The mission is designed to last two years.

NASA Image and Video Library

2003-08-09

VANDENBERG AIR FORCE BASE, CALIF. - Workers mate the Pegasus , with its cargo of the SciSat-1 payload to the L-1011 carrier aircraft. The SciSat-1 weighs approximately 330 pounds and after launch will be placed in a 400-mile-high polar orbit to investigate processes that control the distribution of ozone in the upper atmosphere. The data from the satellite will provide Canadian and international scientists with improved measurements relating to global ozone processes and help policymakers assess existing environmental policy and develop protective measures for improving the health of our atmosphere, preventing further ozone depletion. The mission is designed to last two years.

VANDENBERG AIR FORCE BASE, CALIF. - The SciSat-1 payload and Pegasus launch vehicle are lifted and mated to the L-1011 carrier aircraft. The SciSat-1 weighs approximately 330 pounds and after launch will be placed in a 400-mile-high polar orbit to investigate processes that control the distribution of ozone in the upper atmosphere. The data from the satellite will provide Canadian and international scientists with improved measurements relating to global ozone processes and help policymakers assess existing environmental policy and develop protective measures for improving the health of our atmosphere, preventing further ozone depletion. The mission is designed to last two years.

NASA Image and Video Library

2003-08-09

VANDENBERG AIR FORCE BASE, CALIF. - The SciSat-1 payload and Pegasus launch vehicle are lifted and mated to the L-1011 carrier aircraft. The SciSat-1 weighs approximately 330 pounds and after launch will be placed in a 400-mile-high polar orbit to investigate processes that control the distribution of ozone in the upper atmosphere. The data from the satellite will provide Canadian and international scientists with improved measurements relating to global ozone processes and help policymakers assess existing environmental policy and develop protective measures for improving the health of our atmosphere, preventing further ozone depletion. The mission is designed to last two years.

Current Closure in the Auroral Ionosphere: Results from the Auroral Current and Electrodynamics Structure Rocket Mission

NASA Technical Reports Server (NTRS)

Kaeppler, S. R.; Kletzing, C. A.; Bounds, S. R.; Gjerloev, J. W.; Anderson, B. J.; Korth, H.; LaBelle, J. W.; Dombrowski, M. P.; Lessard, M.; Pfaff, R. F.;

Current Closure in the Auroral Ionosphere: Results from the Auroral Current and Electrodynamics Structure Rocket Mission

NASA Technical Reports Server (NTRS)

Kaeppler, S. R.; Kletzing, C. A.; Bounds, S. R.; Gjerloev, J. W.; Anderson, B. J.; Korth, H.; LaBelle, J. W.; Dombrowski, M. P.; Lessard, M.; Pfaff, R. F.;

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

IEEE 1393 Spaceborne Fiber Optic Data Bus: A Standard Approach to On-Board Payload Data Handling Networks for the AIAA Space Technology Conference and Exposition "Partnering in the 21th Century"

NASA Technical Reports Server (NTRS)

Andrucyk, Dennis J.; Orlando, Fred J.; Chalfant, Charles H.

1999-01-01

The Spaceborne Fiber Optic Data Bus (SFODB) is the next generation in on-board data handling networks. It will do for high speed payloads what SAE 1773 has done for on-board command and telemetry systems. That is, it will significantly reduce the cost of payload development, integration and test through interface standardization. As defined in IEEE 1393, SFODB is a 1 Gb/s, fiber optic network specifically designed to support the real-time, on-board data handling requirements of remote sensing spacecraft. The network is highly reliable, fault tolerant, and capable of withstanding the rigors of launch and the harsh space environment. SFODB achieves this operational and environmental performance while maintaining the small size, light weight, and low power necessary for spaceborne applications. SFODB was developed jointly by DoD and NASA GSFC to meet the on-board data handling needs of Remote Sensing satellites. This jointly funded project produced a complete set of flight transmitters, receivers and protocol ASICS; a complete Development & Evaluation System; and, the IEEE 1393 standard.

KSC-99pp1289

NASA Image and Video Library

1999-11-05

KENNEDY SPACE CENTER, FLA. -- At Launch Pad 39B, the open doors of the payload canister, inside the environmentally controlled Payload Changeout Room, reveal the Hubble Servicing Mission cargo. At the top is the Orbital Replacement Unit Carrier and at the bottom is the Flight Support System. Installation of the payload into Discovery is slated for Friday, Nov. 12. The mission is a "call-up" due to the need to replace portions of the pointing system, the gyros, which have begun to fail on the Hubble Space Telescope. Although Hubble is operating normally and conducting its scientific observations, only three of its six gyroscopes are working properly. The gyroscopes allow the telescope to point at stars, galaxies and planets. The STS-103 crew will also be replacing a Fine Guidance Sensor and an older computer with a new enhanced model, an older data tape recorder with a solid-state digital recorder, a failed spare transmitter with a new one, and degraded insulation on the telescope with new thermal insulation. The crew will also install a Battery Voltage/Temperature Improvement Kit to protect the spacecraft batteries from overcharging and overheating when the telescope goes into a safe mode

Space Science Payloads Optical Properties Monitor (OPM) Mission Flight Anomalies Thermal Analyses

NASA Technical Reports Server (NTRS)

Schmitz, Craig P.

2001-01-01

The OPM was the first space payload that measured in-situ the optical properties of materials and had data telemetered to ground. The OPM was EVA mounted to the Mir Docking Module for an eight-month stay where flight samples were exposed to the Mir induced and natural environments. The OPM was comprised of three optical instruments; a total hemispherical spectral reflectometer, a vacuum ultraviolet spectrometer, and a total integrated scatterometer. There were also three environmental monitors; an atomic oxygen monitor, solar and infrared radiometers, and two temperature-controlled quartz crystal microbalances (to monitor contamination). Measurements were performed weekly and data telemetered to ground through the Mir data system. This paper will describe the OPM thermal control design and how the thermal math models were used to analyze anomalies which occurred during the space flight mission.

JPSS-1 P-Pod Installation

NASA Image and Video Library

2017-10-31

At Vandenberg Air Force Base in California, a Poly Picosatellite Orbital Deployer, or P-POD, container is installed on the Joint Polar Satellite System-1, or JPSS-1, spacecraft. P-PODS are auxiliary payloads launched aboard NASA expendable launch vehicles carrying up to three small CubeSats. The small cube-shaped satellites are part of NASA’s Educational Launch of Nanosatellite, or ELaNa, missions. The small payloads are designed and built by students from high school-level classes up to college and university students. JPSS is the first in a series of four next-generation environmental satellites in a collaborative program between the NOAA and NASA. Liftoff from Vandenberg's Space Launch Compex-2 atop a United Launch Alliance Delta II rocket is scheduled for 1:47 a.m. PST (4:47 a.m. EST), on Nov. 14, 2017.

JPSS-1 P-Pod Installation

NASA Image and Video Library

2017-10-31

At Vandenberg Air Force Base in California, technicians and engineers prepare to install a Poly Picosatellite Orbital Deployer, or P-POD, container on the Joint Polar Satellite System-1, or JPSS-1, spacecraft. P-PODS are auxiliary payloads launched aboard NASA expendable launch vehicles carrying up to three small CubeSats. The small cube-shaped satellites are part of NASA’s Educational Launch of Nanosatellite, or ELaNa, missions. The small payloads are designed and built by students from high school-level classes up to college and university students. JPSS is the first in a series of four next-generation environmental satellites in a collaborative program between the NOAA and NASA. Liftoff from Vandenberg's Space Launch Compex-2 atop a United Launch Alliance Delta II rocket is scheduled for 1:47 a.m. PST (4:47 a.m. EST), on Nov. 14, 2017.

JPSS-1 P-Pod Installation

NASA Image and Video Library

2017-10-31

At Vandenberg Air Force Base in California, technicians and engineers prepare a Poly Picosatellite Orbital Deployer, or P-POD, container for installation on the Joint Polar Satellite System-1, or JPSS-1, spacecraft. P-PODS are auxiliary payloads launched aboard NASA expendable launch vehicles carrying up to three small CubeSats. The small cube-shaped satellites are part of NASA’s Educational Launch of Nanosatellite, or ELaNa, missions. The small payloads are designed and built by students from high school-level classes up to college and university students. JPSS is the first in a series of four next-generation environmental satellites in a collaborative program between the NOAA and NASA. Liftoff from Vandenberg's Space Launch Compex-2 atop a United Launch Alliance Delta II rocket is scheduled for 1:47 a.m. PST (4:47 a.m. EST), on Nov. 14, 2017.

U.S. mission plans for Spacelab

NASA Technical Reports Server (NTRS)

Sander, M. J.

1982-01-01

Mission configurations, instrumentation, and objectives for Spacelab sorties on board the Shuttle beginning in Sept. 1983 are reviewed. The first two flights will serve to verify the Spacelab systems and will be followed by operational status, including the fifth flight, which will be a reimbursible venture. Scientific investigations in the fields of atmospheric physics and environmental observation, space plasma physics, astronomy and solar physics, materials processing, and life sciences will be performed using the habitable long module, instrument pallets, and/or an instrument igloo mounted in the payload bay. Instrumentation, such as the imaging spectrometric observatory, which was developed in the U.S., will originate in either the U.S. or Europe. Details of the first four Spacelab flights are presented, noting that the OSS-3 through -7 missions will feature the first time that entire NASA payloads have returned to space.

Beyond DNA Sequencing in Space: Current and Future Omics Capabilities of the Biomolecule Sequencer Payload

NASA Technical Reports Server (NTRS)

Wallace, Sarah

2017-01-01

Why do we need a DNA sequencer to support the human exploration of space? (A) Operational environmental monitoring; (1) Identification of contaminating microbes, (2) Infectious disease diagnosis, (3) Reduce down mass (sample return for environmental monitoring, crew health, etc.). (B) Research; (1) Human, (2) Animal, (3) Microbes/Cell lines, (4) Plant. (C) Med Ops; (1) Response to countermeasures, (2) Radiation, (3) Real-time analysis can influence medical intervention. (C) Support astrobiology science investigations; (1) Technology superiorly suited to in situ nucleic acid-based life detection, (2) Functional testing for integration into robotics for extraplanetary exploration mission.

Factors Influencing Solar Electric Propulsion Vehicle Payload Delivery for Outer Planet Missions

NASA Technical Reports Server (NTRS)

Cupples, Michael; Green, Shaun; Coverstone, Victoria

2003-01-01

Systems analyses were performed for missions utilizing solar electric propulsion systems to deliver payloads to outer-planet destinations. A range of mission and systems factors and their affect on the delivery capability of the solar electric propulsion system was examined. The effect of varying the destination, the trip time, the launch vehicle, and gravity-assist boundary conditions was investigated. In addition, the affects of selecting propulsion system and power systems characteristics (including primary array power variation, number of thrusters, thruster throttling mode, and thruster Isp) on delivered payload was examined.

The space shuttle payload planning working groups: Volume 9: Materials processing and space manufacturing

NASA Technical Reports Server (NTRS)

1973-01-01

The findings and recommendations of the Materials Processing and Space Manufacturing group of the space shuttle payload planning activity are presented. The effects of weightlessness on the levitation processes, mixture stability, and control over heat and mass transport in fluids are considered for investigation. The research and development projects include: (1) metallurgical processes, (2) electronic materials, (3) biological applications, and (4)nonmetallic materials and processes. Additional recommendations are provided concerning the allocation of payload space, acceptance of experiments for flight, flight qualification, and private use of the space shuttle.

STS-47 MS Jemison trains in SLJ module at MSFC Payload Crew Training Complex

NASA Technical Reports Server (NTRS)

1992-01-01

STS-47 Endeavour, Orbiter Vehicle (OV) 105, Mission Specialist (MS) Mae C. Jemison, wearing Autogenic Feedback Training System 2 suit, works with the Frog Embryology Experiment in a General Purpose Workstation (GPWS) in the Spacelab Japan (SLJ) module mockup at the Payload Crew Training Complex. The experiment will study the effects of weightlessness on the development of frog eggs fertilized in space. The Payload Crew Training Complex is located at the Marshall Space Flight Center (MSFC) in Huntsville, Alabama. View provided with alternate number 92P-139.

On-Board Software Reference Architecture for Payloads

NASA Astrophysics Data System (ADS)

Bos, Victor; Rugina, Ana; Trcka, Adam

2016-08-01

The goal of the On-board Software Reference Architecture for Payloads (OSRA-P) is to identify an architecture for payload software to harmonize the payload domain, to enable more reuse of common/generic payload software across different payloads and missions and to ease the integration of the payloads with the platform.To investigate the payload domain, recent and current payload instruments of European space missions have been analyzed. This led to a Payload Catalogue describing 12 payload instruments as well as a Capability Matrix listing specific characteristics of each payload. In addition, a functional decomposition of payload software was prepared which contains functionalities typically found in payload systems. The definition of OSRA-P was evaluated by case studies and a dedicated OSRA-P workshop to gather feedback from the payload community.

Autonomous support for microorganism research in space

NASA Technical Reports Server (NTRS)

Fleet, Mary L.; Miller, Mark S.; Shipley, Derek, E.; Smith, Jeff D.

1992-01-01

A preliminary design for performing on orbit, autonomous research on microorganisms and cultured cells/tissues is presented. An understanding of gravity and its effects on cells is crucial for space exploration as well as for terrestrial applications. The payload is designed to be compatible with the Commercial Experiment Transporter (COMET) launch vehicle, an orbiter middeck locker interface, and with Space Station Freedom. Uplink/downlink capabilities and sample return through controlled reentry are available for all carriers. Autonomous testing activities are preprogrammed with in-flight reprogrammability. Sensors for monitoring temperature, pH, light, gravity levels, vibrations, and radiation are provided for environmental regulation and experimental data collection. Additional experimental data acquisition includes optical density measurement, microscopy, video, and film photography. On-board full data storage capabilities are provided. A fluid transfer mechanism is utilized for inoculation, sampling, and nutrient replenishment of experiment cultures. In addition to payload design, representative experiments were developed to ensure scientific objectives remained compatible with hardware capabilities. The project is defined to provide biological data pertinent to extended duration crewed space flight including crew health issues and development of a Controlled Ecological Life Support System (CELSS). In addition, opportunities are opened for investigations leading to commercial applications of space, such as pharmaceutical development, modeling of terrestrial diseases, and material processing.

Autonomous support for microorganism research in space

NASA Technical Reports Server (NTRS)

Luttges, M. W.; Klaus, D. M.; Fleet, M. L.; Miller, M. S.; Shipley, D. E.; Smith, J. D.

1992-01-01

A preliminary design for performing on-orbit, autonomous research on microorganisms and cultured cells/tissues is presented. An understanding of gravity and its effects on cells is crucial for space exploration as well as for terrestrial applications. The payload is designed to be compatible with the COMmercial Experiment Transported (COMET) launch vehicle, an orbiter middeck locker interface, and with Space Station Freedom. Uplink/downlink capabilities and sample return through controlled reentry are available for all carriers. Autonomous testing activities are preprogrammed with inflight reprogrammability. Sensors for monitoring temperature, pH, light, gravity levels, vibration, and radiation are provided for environmental regulation and experimental data collection. Additional experiment data acquisition includes optical density measurement, microscopy, video, and file photography. Onboard full data storage capabilities are provided. A fluid transfer mechanism is utilized for inoculation, sampling, and nutrient replenishment of experiment cultures. In addition to payload design, representative experiments were developed to ensure scientific objectives remained compatible with hardware capabilities. The project is defined to provide biological data pertinent to extended duration crewed space flight including crew health issues and development of a Controlled Ecological Life Support System (CELSS). In addition, opportunities are opened for investigations leading to commercial applications of space, such as pharmaceutical development, modeling of terrestrial diseases, and material processing.

The influence of various test plans on mission reliability. [for Shuttle Spacelab payloads

NASA Technical Reports Server (NTRS)

Stahle, C. V.; Gongloff, H. R.; Young, J. P.; Keegan, W. B.

1977-01-01

Methods have been developed for the evaluation of cost effective vibroacoustic test plans for Shuttle Spacelab payloads. The shock and vibration environments of components have been statistically represented, and statistical decision theory has been used to evaluate the cost effectiveness of five basic test plans with structural test options for two of the plans. Component, subassembly, and payload testing have been performed for each plan along with calculations of optimum test levels and expected costs. The tests have been ranked according to both minimizing expected project costs and vibroacoustic reliability. It was found that optimum costs may vary up to $6 million with the lowest plan eliminating component testing and maintaining flight vibration reliability via subassembly tests at high acoustic levels.

KSC-98pc343

NASA Image and Video Library

1998-03-09

KENNEDY SPACE CENTER, FLA. -- The STS-90 Neurolab payload and four Getaway Specials (GAS) await payload bay door closure in the orbiter Columbia today in Orbiter Processing Facility bay 3. Investigations during the Neurolab mission will focus on the effects of microgravity on the nervous system. Specifically, experiments will study the adaptation of the vestibular system, the central nervous system, and the pathways that control the ability to sense location in the absence of gravity, as well as the effect of microgravity on a developing nervous system. The crew of STS-90, slated for launch in April, will include Commander Richard Searfoss, Pilot Scott Altman, Mission Specialists Richard Linnehan, Dafydd (Dave) Williams, M.D., and Kathryn (Kay) Hire, and Payload Specialists Jay Buckey, M.D., and James Pawelczyk, Ph.D

KSC-98pc149

NASA Image and Video Library

1998-01-09

STS-90 crew members study manuals and drawings for the mission's Neurolab payload during the Crew Equipment Interface Test (CEIT) in Kennedy Space Center's (KSC's) Operations and Checkout Building, where the payload is undergoing processing. The CEIT gives astronauts an opportunity to get a hands-on look at the payloads with which they will be working on-orbit. STS-90 is scheduled to launch aboard the Shuttle Columbia from KSC on April 2. Investigations during the Neurolab mission will focus on the effects of microgravity on the nervous system. Specifically, experiments will study the adaptation of the vestibular system, the central nervous system, and the pathways that control the ability to sense location in the absence of gravity, as well as the effect of microgravity on a developing nervous system

Effect of present technology on airship capabilities

NASA Technical Reports Server (NTRS)

Madden, R. T.

1975-01-01

The effect is presented of updating past airship designs using current materials and propulsion systems to determine new airship performance and productivity capabilities. New materials and power plants permit reductions in the empty weights and increases in the useful load capabilities of past airship designs. The increased useful load capability results in increased productivity for a given range, i.e., either increased payload at the same operating speed or increased operating speed for the same payload weight or combinations of both. Estimated investment costs and operating costs are presented to indicate the significant cost parameters in estimating transportation costs of payloads in cents per ton mile. Investment costs are presented considering production lots of 1, 10 and 100 units. Operating costs are presented considering flight speeds and ranges.

Modular space station phase B extension preliminary system design. Volume 7: Ancillary studies

NASA Technical Reports Server (NTRS)

Jones, A. L.

1972-01-01

Sortie mission analysis and reduced payloads size impact studies are presented. In the sortie mission analysis, a modular space station oriented experiment program to be flown by the space shuttle during the period prior to space station IOC is discussed. Experiments are grouped into experiment packages. Mission payloads are derived by grouping experiment packages and by adding support subsystems and structure. The operational and subsystems analyses of these payloads are described. Requirements, concepts, and shuttle interfaces are integrated. The sortie module/station module commonality and a sortie laboratory concept are described. In the payloads size analysis, the effect on the modular space station concept of reduced diameter and reduced length of the shuttle cargo bay is discussed. Design concepts are presented for reduced sizes of 12 by 60 ft, 14 by 40 ft, and 12 by 40 ft. Comparisons of these concepts with the modular station (14 by 60 ft) are made to show the impact of payload size changes.

Helicopter payload gains utilizing water injection for hot day power augmentation

NASA Technical Reports Server (NTRS)

Stroub, R. H.

1972-01-01

An analytical investigation was undertaken to assess the gains in helicopter mission payload through the use of water injection to produce power augmentation in an altitude-hot day environment. Substantial gains are shown for two representative helicopters, the UH-lH and CH-47B. The UH-lH payload increased 86.7 percent for a 50 n.mi. (92.6 km) radius mission involving two out-of-ground effect (OGE) hover take-offs of 2 minutes each at 5000 ft. (1525 m) 35 C ambient conditions. The CH-47B payload increased 49.5 percent for a 50 n.mi. (92.6 km) radius mission with sling loaded cargo as the outbound payload and a 3000 lb. (1360 kg) internal cargo on the return leg. The mission included two 4 min. OGE hovers at 6000 ft. (1830 m) 35 C. An improvement in take off performance and maximum performance climb also resulted as a consequence of the OGE hover capability and higher maximum power available.

Design and performance evaluation of the imaging payload for a remote sensing satellite

NASA Astrophysics Data System (ADS)

Abolghasemi, Mojtaba; Abbasi-Moghadam, Dariush

2012-11-01

In this paper an analysis method and corresponding analytical tools for design of the experimental imaging payload (IMPL) of a remote sensing satellite (SINA-1) are presented. We begin with top-level customer system performance requirements and constraints and derive the critical system and component parameters, then analyze imaging payload performance until a preliminary design that meets customer requirements. We consider system parameters and components composing the image chain for imaging payload system which includes aperture, focal length, field of view, image plane dimensions, pixel dimensions, detection quantum efficiency, and optical filter requirements. The performance analysis is accomplished by calculating the imaging payload's SNR (signal-to-noise ratio), and imaging resolution. The noise components include photon noise due to signal scene and atmospheric background, cold shield, out-of-band optical filter leakage and electronic noise. System resolution is simulated through cascaded modulation transfer functions (MTFs) and includes effects due to optics, image sampling, and system motion. Calculations results for the SINA-1 satellite are also presented.

Payload Processing for Mice Drawer System

NASA Technical Reports Server (NTRS)

Brown, Judy

2007-01-01

Experimental payloads flown to the International Space Station provide us with valuable research conducted in a microgravity environment not attainable on earth. The Mice Drawer System is an experiment designed by Thales Alenia Space Italia to study the effects of microgravity on mice. It is designed to fly to orbit on the Space Shuttle Utilization Logistics Flight 2 in October 2008, remain onboard the International Space Station for approximately 100 days and then return to earth on a following Shuttle flight. The experiment apparatus will be housed inside a Double Payload Carrier. An engineering model of the Double Payload Carrier was sent to Kennedy Space Center for a fit check inside both Shuttles, and the rack that it will be installed in aboard the International Space Station. The Double Payload Carrier showed a good fit quality inside each vehicle, and Thales Alenia Space Italia will now construct the actual flight model and continue to prepare the Mice Drawer System experiment for launch.

Reinventing the International Space Station Payload Integration Processes and Capabilities

NASA Technical Reports Server (NTRS)

Jones, Rod; Price, Carmen; Copeland, Scott; Geiger, Wade; Geiger, Wade; Rice, Amanda; Lauchner, Adam

2011-01-01

The fundamental ISS payload integration philosophy, processes and capabilities were established in the context of how NASA science programs were conducted and executed in the early 1990 s. Today, with the designation of the United States (US) portion of ISS as a National Lab, the ISS payload customer base is growing to include other government agencies, private and commercial research. The fields of research are becoming more diverse expanding from the NASA centric physical, materials and human research sciences to test beds for exploration and technology demonstration, biology and biotechnology, and as an Earth and Space science platform. This new customer base has a broader more diverse set of expectations and requirements for payload design, verification, integration, test, training, and operations. One size fits all processes are not responsive to this broader customer base. To maintain an organization s effectiveness it must listen to its customers, understand their needs, learn from its mistakes, and foster an environment of continual process improvement. The ISS Payloads office is evolving to meet these new customer expectations.

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.

International Cooperation of Payload Operations on the International Space Station

NASA Technical Reports Server (NTRS)

Melton, Tina; Onken, Jay

2003-01-01

One of the primary goals of the International Space Station (ISS) is to provide an orbiting laboratory to be used to conduct scientific research and commercial products utilizing the unique environment of space. The ISS Program has united multiple nations into a coalition with the objective of developing and outfitting this orbiting laboratory and sharing in the utilization of the resources available. The primary objectives of the real- time integration of ISS payload operations are to ensure safe operations of payloads, to avoid mutual interference between payloads and onboard systems, to monitor the use of integrated station resources and to increase the total effectiveness of ISS. The ISS organizational architecture has provided for the distribution of operations planning and execution functions to the organizations with expertise to perform each function. Each IPP is responsible for the integration and operations of their payloads within their resource allocations and the safety requirements defined by the joint program. Another area of international cooperation is the sharing in the development and on- orbit utilization of unique payload facilities. An example of this cooperation is the Microgravity Science Glovebox. The hardware was developed by ESA and provided to NASA as part of a barter arrangement.

The transition of ground-based space environmental effects testing to the space environment

NASA Technical Reports Server (NTRS)

Zaat, Stephen V.; Schaefer, Glen A.; Wallace, John F.

1991-01-01

The goal of the space flight program at the Center for Commercial Development of Space (CCDS)--Materials for Space Structures is to provide environmentally stable structural materials to support the continued humanization and commercialization of the space frontier. Information on environmental stability will be obtained through space exposure, evaluation, documentation, and subsequent return to the supplier of the candidate material for internal investigation. This program provides engineering and scientific service to space systems development firms and also exposes CCDS development candidate materials to space environments representative of in-flight conditions. The maintenance of a technological edge in space for NASA suggests the immediate search for space materials that maintain their structural integrity and remain environmentally stable. The materials being considered for long-lived space structures are complex, high strength/weight ratio composites. In order for these new candidate materials to qualify for use in space structures, they must undergo strenuous testing to determine their reliability and stability when subjected to the space environment. Ultraviolet radiation, atomic oxygen, debris/micrometeoroids, charged particles radiation, and thermal fatigue all influence the design of space structural materials. The investigation of these environmental interactions is the key purpose of this center. Some of the topics discussed with respect to the above information include: the Space Transportation System, mission planning, spaceborne experiments, and space flight payloads.

In-flight calibration of mesospheric rocket plasma probes.

PubMed

Havnes, Ove; Hartquist, Thomas W; Kassa, Meseret; Morfill, Gregor E

2011-07-01

Many effects and factors can influence the efficiency of a rocket plasma probe. These include payload charging, solar illumination, rocket payload orientation and rotation, and dust impact induced secondary charge production. As a consequence, considerable uncertainties can arise in the determination of the effective cross sections of plasma probes and measured electron and ion densities. We present a new method for calibrating mesospheric rocket plasma probes and obtaining reliable measurements of plasma densities. This method can be used if a payload also carries a probe for measuring the dust charge density. It is based on that a dust probe's effective cross section for measuring the charged component of dust normally is nearly equal to its geometric cross section, and it involves the comparison of variations in the dust charge density measured with the dust detector to the corresponding current variations measured with the electron and/or ion probes. In cases in which the dust charge density is significantly smaller than the electron density, the relation between plasma and dust charge density variations can be simplified and used to infer the effective cross sections of the plasma probes. We illustrate the utility of the method by analysing the data from a specific rocket flight of a payload containing both dust and electron probes.

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.

Space Shuttle UHF Communications Performance Evaluation

NASA Technical Reports Server (NTRS)

Hwu, Shian U.; Loh, Yin-Chung; Kroll, Quin D.; Sham, Catherine C.

2004-01-01

An extension boom is to be installed on the starboard side of the Space Shuttle Orbiter (SSO) payload bay for thermal tile inspection and repairing. As a result, the Space Shuttle payload bay Ultra High Frequency (UHF) antenna will be under the boom. This study is to evaluate the Space Shuttle UHF communication performance for antenna at a suitable new location. To insure the RF coverage performance at proposed new locations, the link margin between the UHF payload bay antenna and Extravehicular Activity (EVA) Astronauts at a range distance of 160 meters from the payload bay antenna was analyzed. The communication performance between Space Shuttle Orbiter and International Space Station (SSO-ISS) during rendezvous was also investigated. The multipath effects from payload bay structures surrounding the payload bay antenna were analyzed. The computer simulation tool based on the Geometrical Theory of Diffraction method (GTD) was used to compute the signal strengths. The total field strength was obtained by summing the direct fields from the antennas and the reflected and diffracted fields from the surrounding structures. The computed signal strengths were compared to the signal strength corresponding to the 0 dB link margin. Based on the results obtained in this study, RF coverage for SSO-EVA and SSO- ISS communication links was determined for the proposed payload bay antenna UHF locations. The RF radiation to the Orbiter Docking System (ODS) pyros, the payload bay avionics, and the Shuttle Remote Manipulator System (SRMS) from the new proposed UHF antenna location was also investigated to ensure the EMC/EMI compliances.

A Rocket-Base Study of Auroral Electrodynamics Within the Current Closure Ionosphere

NASA Technical Reports Server (NTRS)

Kaeppler, Stephen R.; Kletzing, Craig; Bounds, Scott R.; Sigsbee, Kristine M.; Gjerloev, Jesper W.; Anderson, Brian Jay; Korth, Haje; Lessard, Marc; Labelle, James W.; Dombrowski, Micah P.;

Satellite global monitoring of environmental quality

NASA Technical Reports Server (NTRS)

Schiffer, R. A.

1975-01-01

The missions of two NASA satellites for the monitoring of environmental quality are described: Nimbus G, the Air Pollution and Oceanographic Observing Satellite, and the Applications Explorer Mission (AEM) satellite to be used in the Stratospheric Aerosol and Gas Experiment (SAGE). The scientific payload of Nimbus G is described in detail with a discussion of limb infrared monitoring of the stratosphere, the stratospheric and mesospheric sounder, stratospheric aerosol measurement, the solar and backscatter UV spectrometer for ozone mapping, the earth radiation budget experiment, the scanning multichannel microwave radiometer, the coastal zone color scanner and the temperature-humidity infrared radiometer. A brief description is given of the SAGE program and future NASA plans relating to the global monitoring of environmental quality are outlined.

Research experiments at Hangar L

NASA Technical Reports Server (NTRS)

2000-01-01

Visiting scientist Cheryl Frazier monitors a prototype composting machine in Hangar L at the Cape Canaveral Air Force Station. The research she is performing is one of many studies at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship.

GOES-R Rotation to Vertical

NASA Image and Video Library

2016-09-15

Team members assist as the Geostationary Operational Environmental Satellite (GOES-R) is prepared for lifting to the vertical position on an “up-ender” inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Advanced Base Line Imager Installation

NASA Image and Video Library

2016-08-30

Team members prepare the Advanced Base Line Imager, the primary optical instrument, for installation on the Geostationary Operational Environmental Satellite (GOES-R) inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Fairing Inspection

NASA Image and Video Library

2016-09-26

Team members with United Launch Alliance (ULA) inspect an clean the first half of the fairing for the Geostationary Operational Environmental Satellite (GOES-R) inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a ULA Atlas V rocket in November.

GOES-R Lift and Mate

NASA Image and Video Library

2016-11-09

Enclosed in its payload fairing, NOAA's Geostationary Operational Environmental Satellite (GOES-R) is mated to the United Launch Alliance Atlas V Centaur upper stage in the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The satellite will launch aboard the Atlas V rocket in November. GOES-R is the first satellite in a series of next-generation NOAA GOES Satellites.

GOES-R Rotation to Vertical

NASA Image and Video Library

2016-09-15

Team members monitor the progress as the Geostationary Operational Environmental Satellite (GOES-R) is lifted to the vertical position on an “up-ender” inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Advanced Base Line Imager Installation

NASA Image and Video Library

2016-08-30

Team members install the Advanced Base Line Imager, the primary optical instrument, on the Geostationary Operational Environmental Satellite (GOES-R) inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Advanced Base Line Imager Installation

NASA Image and Video Library

2016-08-30

The Advanced Base Line Imager, the primary optical instrument, has been installed on the Geostationary Operational Environmental Satellite (GOES-R) inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Rotation to Vertical

NASA Image and Video Library

2016-09-15

Team members check the Geostationary Operational Environmental Satellite (GOES-R) after it was lifted to the vertical position on an “up-ender” inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Lift and Mate

NASA Image and Video Library

2016-11-09

A crane begins to lift the payload fairing containing NOAA's Geostationary Operational Environmental Satellite (GOES-R) at the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. GOES-R will be mated to the United Launch Alliance Atlas V Centaur upper stage in preparation for launch in November. GOES-R is the first satellite in a series of next-generation NOAA GOES Satellites.

GOES-R Fairing Inspection

NASA Image and Video Library

2016-09-26

Both halves of the fairing for the Geostationary Operational Environmental Satellite (GOES-R) are being inspected and cleaned by United Launch Alliance (ULA) team members inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a ULA Atlas V rocket in November.

KSC-00pp0694

NASA Image and Video Library

2000-05-29

Research assistant Trisha Bruno performs an analysis on potato samples at Hangar L at the Cape Canaveral Air Force Station. The research she is performing is one of many studies at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

KSC-00pp0695

NASA Image and Video Library

2000-05-29

Visiting scientist Cheryl Frazier monitors a prototype composting machine in Hangar L at the Cape Canaveral Air Force Station. The research she is performing is one of many studies at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

KSC00pp0695

NASA Image and Video Library

2000-05-29

Visiting scientist Cheryl Frazier monitors a prototype composting machine in Hangar L at the Cape Canaveral Air Force Station. The research she is performing is one of many studies at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

KSC-00pp0696

NASA Image and Video Library

2000-05-01

Research scientist Greg Goins monitors radish growth under a sulfur-microwave light at Hangar L at the Cape Canaveral Air Force Station. The research he is performing is one of many studies at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardshi

KSC00pp0693

NASA Image and Video Library

2000-05-29

Research assistant Trisha Bruno performs an analysis on potato samples at Hangar L at the Cape Canaveral Air Force Station. The research she is performing is one of many studies at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

KSC00pp0694

NASA Image and Video Library

2000-05-29

Research assistant Trisha Bruno performs an analysis on potato samples at Hangar L at the Cape Canaveral Air Force Station. The research she is performing is one of many studies at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

KSC-00pp0693

NASA Image and Video Library

2000-05-29

Research assistant Trisha Bruno performs an analysis on potato samples at Hangar L at the Cape Canaveral Air Force Station. The research she is performing is one of many studies at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

KSC00pp0696

NASA Image and Video Library

2000-05-01

Research scientist Greg Goins monitors radish growth under a sulfur-microwave light at Hangar L at the Cape Canaveral Air Force Station. The research he is performing is one of many studies at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardshi

KSC00pp0692

NASA Image and Video Library

2000-05-29

Research scientist Vadim Rygalov describes a new low-pressure water-recycling experiment being designed to help simulate plant growth conditions on Mars. The research he is performing is one of many studies at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

KSC-00pp0692

NASA Image and Video Library

2000-05-29

Research scientist Vadim Rygalov describes a new low-pressure water-recycling experiment being designed to help simulate plant growth conditions on Mars. The research he is performing is one of many studies at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship

Research experiments at Hangar L

NASA Technical Reports Server (NTRS)

2000-01-01

Research assistant Trisha Bruno performs an analysis on potato samples at Hangar L at the Cape Canaveral Air Force Station. The research she is performing is one of many studies at the Biological Sciences Branch in the Spaceport Engineering and Technology Directorate at Kennedy Space Center. The branch's operations and research areas include life sciences Space Shuttle payloads, bioregenerative life-support for long-duration spaceflight and environmental/ecological stewardship.

Stratospheric Balloon Platforms for Near Space Access

NASA Astrophysics Data System (ADS)

Dewey, R. G.

2012-12-01

For over five decades, high altitude aerospace balloon platforms have provided a unique vantage point for space and geophysical research by exposing scientific instrument packages and experiments to space-like conditions above 99% of Earth's atmosphere. Reaching altitudes in excess of 30 km for durations ranging from hours to weeks, high altitude balloons offer longer flight durations than both traditional sounding rockets and emerging suborbital reusable launch vehicles. For instruments and experiments requiring access to high altitudes, engineered balloon systems provide a timely, responsive, flexible, and cost-effective vehicle for reaching near space conditions. Moreover, high altitude balloon platforms serve as an early means of testing and validating hardware bound for suborbital or orbital space without imposing space vehicle qualifications and certification requirements on hardware in development. From float altitudes above 30 km visible obscuration of the sky is greatly reduced and telescopes and other sensors function in an orbit-like environment, but in 1g. Down-facing sensors can take long-exposure atmospheric measurements and images of Earth's surface from oblique and nadir perspectives. Payload support subsystems such as telemetry equipment and command, control, and communication (C3) interfaces can also be tested and operationally verified in this space-analog environment. For scientific payloads requiring over-flight of specific areas of interests, such as an active volcano or forest region, advanced mission planning software allows flight trajectories to be accurately modeled. Using both line-of-sight and satellite-based communication systems, payloads can be tracked and controlled throughout the entire mission duration. Under NASA's Flight Opportunities Program, NSC can provide a range of high altitude flight options to support space and geophysical research: High Altitude Shuttle System (HASS) - A balloon-borne semi-autonomous glider carries payloads to high altitude and returns them safely to pre-selected landing sites, supporting quick recovery, refurbishment, and re-flight. Small Balloon System (SBS) - Controls payload interfaces via a standardized avionics system. Using a parachute for recovery, the SBS is well suited for small satellite and spacecraft subsystem developers wanting to raise their Technology Readiness Level (TRL) in an operationally relevant environment. Provides flexibility for scientific payloads requiring externally mounted equipment, such as telescopes and antennas. Nano Balloon System (NBS) - For smaller payloads (~CubeSats) with minimal C3 requirements, the Nano Balloon System (NBS) operates under less restrictive flight regulations with increased operational flexibility. The NBS is well suited for payload providers seeking a quick, simple, and cost effective solution for operating small ~passive payloads in near space. High altitude balloon systems offer the payload provider and experimenter a unique and flexible platform for geophysical and space research. Though new launch vehicles continue to expand access to suborbital and orbital space, recent improvements in high altitude balloon technology and operations provide a cost effective alternative to access space-like conditions.

Space Station accommodation of attached payloads

NASA Technical Reports Server (NTRS)

Browning, Ronald K.; Gervin, Janette C.

1987-01-01

The Attached Payload Accommodation Equipment (APAE), which provides the structure to attach payloads to the Space Station truss assembly, to access Space Station resources, and to orient payloads relative to specified targets, is described. The main subelements of the APAE include a station interface adapter, payload interface adapter, subsystem support module, contamination monitoring system, payload pointing system, and attitude determination system. These components can be combined to provide accommodations for small single payloads, small multiple payloads, large self-supported payloads, carrier-mounted payloads, and articulated payloads. The discussion also covers the power, thermal, and data/communications subsystems and operations.

Integrated operations/payloads/fleet analysis. Volume 2: Payloads

NASA Technical Reports Server (NTRS)

1971-01-01

The payloads for NASA and non-NASA missions of the integrated fleet are analyzed to generate payload data for the capture and cost analyses for the period 1979 to 1990. Most of the effort is on earth satellites, probes, and planetary missions because of the space shuttle's ability to retrieve payloads for repair, overhaul, and maintenance. Four types of payloads are considered: current expendable payload; current reusable payload; low cost expendable payload, (satellite to be used with expendable launch vehicles); and low cost reusable payload (satellite to be used with the space shuttle/space tug system). Payload weight analysis, structural sizing analysis, and the influence of mean mission duration on program cost are also discussed. The payload data were computerized, and printouts of the data for payloads for each program or mission are included.

The HAMMER: High altitude multiple mission environmental researcher

NASA Technical Reports Server (NTRS)

Hayashi, Darren; Zylla, Cara; Amaro, Ernesto; Colin, Phil; Klause, Thomas; Lopez, Bernardo; Williamson, Danna

1991-01-01

At the equator, the ozone layer ranges from 65,000 to 130,000+ feet which is beyond the capabilities of the ER-2, NASA's current high altitude reconnaissance aircraft. The Universities Space Research Association, in cooperation with NASA, is sponsoring an undergraduate program which is geared to designing an aircraft that can study the ozone layer at the equator. This aircraft must be able to satisfy four mission profiles. Mission one is a polar mission which ranges from Chile to the South Pole and back to Chile, a total range of 6000 n. mi. at 100,000 feet with a 2500 lb. payload. The second mission is also a polar mission with a decreased altitude of 70,000 feet and an increased payload of 4000 lb. For the third mission, the aircraft will take-off at NASA Ames, cruise at 100,000 feet carrying a 2500 lb. payload, and land in Puerto Montt, Chile. The final mission requires the aircraft to take-off at NASA Ames, cruise at 100,000 feet with a 1000 lb. payload, make an excursion to 120,000 feet, and land at Howard AFB, Panama. All three missions require that a subsonic Mach number is maintained due to constraints imposed by the air sampling equipment. The aircraft need not be manned for all four missions. Three aircraft configurations were determined to be the most suitable for meeting the above requirements. The performance of each configuration is analyzed to investigate the feasibility of the project requirements. In the event that a requirement can not be obtained within the given constraints, recommendations for proposal modifications are given.

Designing an Alternate Mission Operations Control Room

NASA Technical Reports Server (NTRS)

Montgomery, Patty; Reeves, A. Scott

2014-01-01

The Huntsville Operations Support Center (HOSC) is a multi-project facility that is responsible for 24x7 real-time International Space Station (ISS) payload operations management, integration, and control and has the capability to support small satellite projects and will provide real-time support for SLS launches. The HOSC is a serviceoriented/ highly available operations center for ISS payloads-directly supporting science teams across the world responsible for the payloads. The HOSC is required to endure an annual 2-day power outage event for facility preventive maintenance and safety inspection of the core electro-mechanical systems. While complete system shut-downs are against the grain of a highly available sub-system, the entire facility must be powered down for a weekend for environmental and safety purposes. The consequence of this ground system outage is far reaching: any science performed on ISS during this outage weekend is lost. Engineering efforts were focused to maximize the ISS investment by engineering a suitable solution capable of continuing HOSC services while supporting safety requirements. The HOSC Power Outage Contingency (HPOC) System is a physically diversified compliment of systems capable of providing identified real-time services for the duration of a planned power outage condition from an alternate control room. HPOC was designed to maintain ISS payload operations for approximately three continuous days during planned HOSC power outages and support a local Payload Operations Team, International Partners, as well as remote users from the alternate control room located in another building. This paper presents the HPOC architecture and lessons learned during testing and the planned maiden operational commissioning. Additionally, this paper documents the necessity of an HPOC capability given the unplanned HOSC Facility power outage on April 27th, 2011, as a result of the tornado outbreak that damaged the electrical grid to such a degree that significantly inhibited the Tennessee Valley Authority's ability to transmit electricity throughout the North Alabama region.

Mars MetNet Mission - Martian Atmospheric Observational Post Network

NASA Astrophysics Data System (ADS)

Haukka, Harri; Harri, Ari-Matti; Aleksashkin, Sergey; Arruego, Ignacio; Schmidt, Walter; Genzer, Maria; Vazquez, Luis; Siikonen, Timo; Palin, Matti

2016-10-01

A new kind of planetary exploration mission for Mars is under development 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).The scientific payload of the Mars MetNet Precursor mission is divided into three categories: Atmospheric instruments, Optical devices and Composition and structure devices. Each of the payload instruments will provide significant insights in to the Martian atmospheric behavior.The key technologies of the MetNet Lander have been qualified and the electrical qualification model (EQM) of the payload bay has been built and successfully tested.Full Qualification Model (QM) of the MetNet landing unit with the Precursor Mission payload is currently under functional tests. In the near future the QM unit will be exposed to environmental tests with qualification levels including vibrations, thermal balance, thermal cycling and mechanical impact shock. One complete flight unit of the entry, descent and landing systems (EDLS) has been manufactured and tested with acceptance levels. Another flight-like EDLS has been exposed to most of the qualification tests, and hence it may be used for flight after refurbishments. Accordingly two flight-capable EDLS systems exist. The eventual goal is to create a network of atmospheric observational posts around the Martian surface. The next step in the MetNet Precursor Mission is the demonstration of the technical robustness and scientific capabilities of the MetNet type of landing vehicle. Definition of the Precursor Mission and discussions on launch opportunities are currently under way. The baseline program development funding exists for the next five years. Flight unit manufacture of the payload bay takes about 18 months, and it will be commenced after the Precursor Mission has been defined.

Views of the payload bay of OV-105 taken during the STS-99 mission

NASA Image and Video Library

2000-03-30

STS099-315-031 (11-22 February 2000) --- The Space Shuttle Endeavour orbits Earth with its lengthy SRTM mast at work (out of frame). Part of the SRTM payload is silhouetted in the cargo bay. Airglow effect of Earth's atmosphere makes for interesting light and color display.

Preliminary analysis of an integrated logistics system for OSSA payloads. Volume 2: OSSA integrated logistics support strategy

NASA Technical Reports Server (NTRS)

Palguta, T.; Bradley, W.; Stockton, T.

1988-01-01

The purpose is to outline an Office of Space Science and Applications (OSSA) integrated logistics support strategy that will ensure effective logistics support of OSSA payloads at an affordable life-cycle cost. Program objectives, organizational relationships, and implementation of the logistics strategy are discussed.

Resource planning and scheduling of payload for satellite with particle swarm optimization

NASA Astrophysics Data System (ADS)

Li, Jian; Wang, Cheng

2007-11-01

The resource planning and scheduling technology of payload is a key technology to realize an automated control for earth observing satellite with limited resources on satellite, which is implemented to arrange the works states of various payloads to carry out missions by optimizing the scheme of the resources. The scheduling task is a difficult constraint optimization problem with various and mutative requests and constraints. Based on the analysis of the satellite's functions and the payload's resource constraints, a proactive planning and scheduling strategy based on the availability of consumable and replenishable resources in time-order is introduced along with dividing the planning and scheduling period to several pieces. A particle swarm optimization algorithm is proposed to address the problem with an adaptive mutation operator selection, where the swarm is divided into groups with different probabilities to employ various mutation operators viz., differential evolution, Gaussian and random mutation operators. The probabilities are adjusted adaptively by comparing the effectiveness of the groups to select a proper operator. The simulation results have shown the feasibility and effectiveness of the method.

A feasibility study of a hypersonic real-gas facility

NASA Technical Reports Server (NTRS)

Gully, J. H.; Driga, M. D.; Weldon, W. F.

1987-01-01

A four month feasibility study of a hypersonic real-gas free flight test facility for NASA Langley Research Center (LARC) was performed. The feasibility of using a high-energy electromagnetic launcher (EML) to accelerate complex models (lifting and nonlifting) in the hypersonic, real-gas facility was examined. Issues addressed include: design and performance of the accelerator; design and performance of the power supply; design and operation of the sabot and payload during acceleration and separation; effects of high current, magnetic fields, temperature, and stress on the sabot and payload; and survivability of payload instrumentation during acceleration, flight, and soft catch.

KSC-98pc148

NASA Image and Video Library

1998-01-09

STS-90 crew members check out the inside of the module for the mission's Neurolab payload during the Crew Equipment Interface Test (CEIT) in Kennedy Space Center's (KSC's) Operations and Checkout Building, where the payload is undergoing processing. The CEIT gives astronauts an opportunity to get a hands-on look at the payloads with which they will be working on-orbit. STS-90 is scheduled to launch aboard the Shuttle Columbia from KSC on April 2. Investigations during the Neurolab mission will focus on the effects of microgravity on the nervous system. Specifically, experiments will study the adaptation of the vestibular system, the central nervous system, and the pathways that control the ability to sense location in the absence of gravity, as well as the effect of microgravity on a developing nervous system

KSC-98pc147

NASA Image and Video Library

1998-01-09

STS-90 Payload Specialist James Pawelczyk, Ph.D., holds up a panel as one of the items used during the Crew Equipment Interface Test (CEIT) in Kennedy Space Center's (KSC's) Operations and Checkout Building, where the Neurolab payload is undergoing processing. The CEIT gives astronauts an opportunity to get a hands-on look at the payloads with which they will be working on-orbit. STS-90 is scheduled to launch aboard the Shuttle Columbia from KSC on April 2. Investigations during the Neurolab mission will focus on the effects of microgravity on the nervous system. Specifically, experiments will study the adaptation of the vestibular system, the central nervous system, and the pathways that control the ability to sense location in the absence of gravity, as well as the effect of microgravity on a developing nervous system

KSC-98pc145

NASA Image and Video Library

1998-01-09

STS-90 Payload Specialists James Pawelczyk, Ph.D. (at left), and Jay Buckey Jr., M.D., examine items to be used during the Crew Equipment Interface Test (CEIT) in Kennedy Space Center's (KSC's) Operations and Checkout Building, where the Neurolab payload is undergoing processing. The CEIT gives astronauts an opportunity to get a hands-on look at the payloads with which they will be working on-orbit. STS-90 is scheduled to launch aboard the Shuttle Columbia from KSC on April 2. Investigations during the Neurolab mission will focus on the effects of microgravity on the nervous system. Specifically, experiments will study the adaptation of the vestibular system, the central nervous system, and the pathways that control the ability to sense location in the absence of gravity, as well as the effect of microgravity on a developing nervous system

Relative tracking control of constellation satellites considering inter-satellite link

NASA Astrophysics Data System (ADS)

Fakoor, M.; Amozegary, F.; Bakhtiari, M.; Daneshjou, K.

2017-11-01

In this article, two main issues related to the large-scale relative motion of satellites in the constellation are investigated to establish the Inter Satellite Link (ISL) which means the dynamic and control problems. In the section related to dynamic problems, a detailed and effective analytical solution is initially provided for the problem of satellite relative motion considering perturbations. The direct geometric method utilizing spherical coordinates is employed to achieve this solution. The evaluation of simulation shows that the solution obtained from the geometric method calculates the relative motion of the satellite with high accuracy. Thus, the proposed analytical solution will be applicable and effective. In the section related to control problems, the relative tracking control system between two satellites will be designed in order to establish a communication link between the satellites utilizing analytical solution for relative motion of satellites with respect to the reference trajectory. Sliding mode control approach is employed to develop the relative tracking control system for body to body and payload to payload tracking control. Efficiency of sliding mode control approach is compared with PID and LQR controllers. Two types of payload to payload tracking control considering with and without payload degree of freedom are designed and suitable one for practical ISL applications is introduced. Also, Fuzzy controller is utilized to eliminate the control input in the sliding mode controller.

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.

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.

Payload Safety: Risk and Characteristic-Based Control of Engineered Nanomaterials

NASA Astrophysics Data System (ADS)

Abou, Seraphin Chally; Saad, Maarouf

2013-09-01

In the last decade progress has been made to assist organizations that are developing payloads intended for flight on the International Space Station (ISS) and/or Space Shuttle. Collaboration programs for comprehensive risk assessment have been initiated between the U.S. and the European Union to generate requirements and data needed to comply with payloads safety and to perform risk assessment and controls guidance. Yet, substantial research gaps remain, as do challenges in the translation of these research findings to control for exposure to nanoscale material payloads, and the health effects. Since nanomaterial structures are different from traditional molecules, some standard material properties can change at size of 50nm or less. Changes in material properties at this scale challenge our understanding of hazards posed by nanomaterial payloads in the ISS realistic exposure conditions, and our ability to anticipate, evaluate, and control potential health issues, and safety. The research question addressed in this framework is: what kind of descriptors can be developed for nanomaterial payloads risks assessment? Methods proposed incorporate elements of characteristic- based risk an alysis: (1) to enable characterization of anthropogenic nanomaterials which can result in incidental from natural nanoparticles; and (2) to better understand safety attributes in terms of human health impacts from exposure to varying types of engineered nanomaterials.

Effects of neutral gas release on current collection during the CHARGE-2 rocket experiment

NASA Technical Reports Server (NTRS)

Gilchrist, B. E.; Banks, P. M.; Neubert, T.; Williamson, P. R.; Myers, Neil B.; Raitt, W. John; Sasaki, S.

1990-01-01

Observations of current collection enhancements due to cold nitrogen gas control jet emissions from a highly charged rocket payload in the ionosphere are reported. These observations were made during the second cooperative high altitude rocket gun experiment (CHARGE-2) which was an electrically tethered mother/daughter payload system. The current collection enhancement was observed at the daughter payload located 100 to 400 m away from the mother which was firing an energetic electron beam. The authors interpret these results in terms of an electrical discharge forming in close proximity to the daughter during the short periods of gas emission. The results indicate that it is possible to enhance the electron current collection capability of positively charged vehicles by means of deliberate neutral gas releases into an otherwise undisturbed space plasma. These results can also be compared with recent laboratory observations of hollow cathode plasma contactors operating in the ignited mode. Experimental observations of current collection enhancements due to cold nitrogen gas control jet emissions from a highly charged, isolated daughter payload in the nighttime ionosphere were made. These observations were derived from the second cooperative high altitude rocket gun experiment (CHARGE-2) which was an electrically tethered mother-daughter payload system. The rocket flew from White Sands Missile Range (WSMR) in December, 1985. The rocket achieved an altitude of 261 km and carried a 1 keV electron beam emitting up to 48 mA of current (Myers, et al., 1989a). The mother payload, carried the electron beam source, while the daughter acted as a remote current collection and observation platform and reached a distance of 426 m away from the main payload. Gas emissions at the daughter were due to periodic thruster jet firings to maintain separation velocity between the two payloads.

Materials samples face rigors of space.

PubMed

Flinn, Edward D

2002-07-01

The Materials International Space Station Experiment (MISSE) is described. This project is designed to conduct long duration materials tests on samples attached to the ISS. A batch of 750 material samples were delivered on STS-105 and attached to the ISS airlock. They will be exposed to the space environment for 18 months and are slated to return on STS-114. A second batch of 750 samples is being prepared. The experiment containers were used originally for the Mir Environmental Effects Payload, which tested a variety of substances, including some slated for use on the ISS. Researchers are particularly interested in the effects of atomic oxygen on the samples. Some samples are being tested to determine their use in radiation protection. As part of the MISSE project, ultrathin tether materials are being tested for use on the Propulsive Small Expendable Depoloyer System (ProSEDS), which will use a tether system to change a satellite's orbital altitude.

Expedition Earth and Beyond: Using Crew Earth Observation Imagery from the International Space Station to Facilitate Student-Led Authentic Research

NASA Technical Reports Server (NTRS)

Graff, P. V.; Stefanov, W. L.; Willis, K. J.; Runco, S.

2012-01-01

Student-led authentic research in the classroom helps motivate students in science, technology, engineering, and mathematics (STEM) related subjects. Classrooms benefit from activities that provide rigor, relevance, and a connection to the real world. Those real world connections are enhanced when they involve meaningful connections with NASA resources and scientists. Using the unique platform of the International Space Station (ISS) and Crew Earth Observation (CEO) imagery, the Expedition Earth and Beyond (EEAB) program provides an exciting way to enable classrooms in grades 5-12 to be active participants in NASA exploration, discovery, and the process of science. EEAB was created by the Astromaterials Research and Exploration Science (ARES) Education Program, at the NASA Johnson Space Center. This Earth and planetary science education program has created a framework enabling students to conduct authentic research about Earth and/or planetary comparisons using the captivating CEO images being taken by astronauts onboard the ISS. The CEO payload has been a science payload onboard the ISS since November 2000. ISS crews are trained in scientific observation of geological, oceanographic, environmental, and meteorological phenomena. Scientists on the ground select and periodically update a series of areas to be photographed as part of the CEO science payload.

GOES (Geostationary Operational Environmental Satellite)-Next Overview.

DTIC Science & Technology

1985-09-01

shows the locations and sizes of warm and cold eddies. r * Hydrological services. GOES (and polar orbiter) data are used to produce maps and charts...rationale used to develop specifications for the N next generation of satellites of this series. The payload * instruments of the current satellites are...reviewed in con- junction with the products prepared from their data outputs. The rationale used by the National Weather Service (NWS) in developing

STS-30 Magellan spacecraft processing at Kennedy Space Center (KSC) SAEF-2

NASA Image and Video Library

1988-10-08

S89-25281 (8 Oct 1988) --- The Magellan spacecraft is hoisted from the transport trailer of the Payload Environmental Transportation System (PETS) to the floor of the cleanroom in the SAEF-2 planetary checkout facility at the Kennedy Space Center (KSC). The spacecraft, destined for unprecedented studies of Venusian topographic features, is to be deployed by the crew of NASA's STS-30 mission in April 1989.

GOES-R Lift and Mate

NASA Image and Video Library

2016-11-09

A crane is used to lift the payload fairing containing NOAA's Geostationary Operational Environmental Satellite (GOES-R) at the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. GOES-R will be mated to the United Launch Alliance Atlas V Centaur upper stage in preparation for launch in November. GOES-R is the first satellite in a series of next-generation NOAA GOES Satellites.

GOES-R Rollout from VIF to Pad 41

NASA Image and Video Library

2016-11-18

A United Launch Alliance Atlas V rocket arrives at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. In view is the upper stage and payload fairing containing the Geostationary Operational Environmental Satellite (GOES-R). The launch vehicle will send GOES-R to a geostationary position over the U.S. GOES-R is the first satellite in a series of next-generation NOAA GOES satellites.

GOES-R Lift and Mate

NASA Image and Video Library

2016-11-09

Enclosed in its payload fairing, NOAA's Geostationary Operational Environmental Satellite (GOES-R) is lifted into the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. GOES-R will be mated to the United Launch Alliance Atlas V Centaur upper stage in preparation for launch aboard the rocket in November. GOES-R is the first satellite in a series of next-generation NOAA GOES Satellites.

GOES-R Lift and Mate

NASA Image and Video Library

2016-11-09

Preparations are underway to lift NOAA's Geostationary Operational Environmental Satellite (GOES-R), enclosed in its payload fairing at the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. GOES-R will be mated to the United Launch Alliance Atlas V Centaur upper stage in preparation for launch in November. GOES-R is the first satellite in a series of next-generation NOAA GOES Satellites.

GOES-R Advanced Base Line Imager Installation

NASA Image and Video Library

2016-08-30

Team members assist as a crane lifts the Advanced Base Line Imager, the primary optical instrument, for installation on the Geostationary Operational Environmental Satellite (GOES-R) inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Rotation to Vertical

NASA Image and Video Library

2016-09-15

Team members assist as the Geostationary Operational Environmental Satellite (GOES-R) is raised and prepared for lifting to the vertical position on an “up-ender” inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November

GOES-R Advanced Base Line Imager Installation

NASA Image and Video Library

2016-08-30

Team members assist as a crane moves the Advanced Base Line Imager, the primary optical instruments, for installation on the Geostationary Operational Environmental Satellite (GOES-R) inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Lift and Mate

NASA Image and Video Library

2016-11-09

A crane has been attached to the payload fairing containing NOAA's Geostationary Operational Environmental Satellite (GOES-R) at the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. GOES-R will be mated to the United Launch Alliance Atlas V Centaur upper stage in preparation for launch in November. GOES-R is the first satellite in a series of next-generation NOAA GOES Satellites.

GOES-R Rotation to Vertical

NASA Image and Video Library

2016-09-15

Team members assist as the Geostationary Operational Environmental Satellite (GOES-R) is raised and prepared for lifting to the vertical position on an “up-ender” inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

Alexander Samokutyaev conducts BTKh-14/Bioemulsiya (Bioemulsion) Experiment

NASA Image and Video Library

2011-05-05

ISS027-E-022454 (5 May 2011) --- Russian cosmonaut Alexander Samokutyaev, Expedition 27 flight engineer, uses a glovebox to service the Russian Bioemulsion science payload in the Poisk Mini-Research Module 2 (MRM2) of the International Space Station. The Bioemulsion experiment is attempting to develop faster technologies for obtaining microorganism biomass and biologically active substance biomass for creating highly efficient environmentally pure bacteria, enzymes, and medicinal/pharmaceutical preparations.

KSC-2009-1379

NASA Image and Video Library

2008-11-11

VANDENBERG AIR FORCE BASE, Calif. – The NOAA-N Prime satellite is displayed in the payload processing facility at Vandenberg Air Force Base in California. NOAA-N Prime is the latest polar-orbiting operational environmental weather satellite developed by NASA for the National Oceanic and Atmospheric Administration. It is built by Lockheed Martin and similar to NOAA-N launched on May 20, 2005. Launch of NOAA-N Prime is scheduled for Feb. 4. Photo credit: NASA

KSC-2009-1368

NASA Image and Video Library

2008-11-04

VANDENBERG AIR FORCE BASE, Calif. – The latest polar-orbiting operational environmental weather satellite developed by NASA for the National Oceanic and Atmospheric Administration, called NOAA-N Prime, is offloaded from the trailer at Vandenberg Air Force Base, Calif. The spacecraft will be moved into a NASA payload processing facility and prepared for a Feb. 4 launch. NOAA-N Prime, built by Lockheed Martin, is similar to NOAA-N launched on May 20, 2005.

MSFC Skylab airlock module, volume 1. [systems design and performance

NASA Technical Reports Server (NTRS)

1974-01-01

The history and development of the Skylab Airlock Module and Payload Shroud is presented from initial concept through final design. A summary is given of the Airlock features and systems. System design and performance are presented for the Spent Stage Experiment Support Module, structure and mechanical systems, mass properties, thermal and environmental control systems, EVA/IVA suite system, electrical power system, sequential system, sequential system, and instrumentation system.

VANDENBERG AIR FORCE BASE, CALIF. - The Pegasus transporter, with its cargo of the SciSat-1 payload and Pegasus launch vehicle, moves under the L-1011 carrier aircraft for matting. The SciSat-1 weighs approximately 330 pounds and after launch will be placed in a 400-mile-high polar orbit to investigate processes that control the distribution of ozone in the upper atmosphere. The data from the satellite will provide Canadian and international scientists with improved measurements relating to global ozone processes and help policymakers assess existing environmental policy and develop protective measures for improving the health of our atmosphere, preventing further ozone depletion. The mission is designed to last two years.

NASA Image and Video Library

2003-08-09

VANDENBERG AIR FORCE BASE, CALIF. - The Pegasus transporter, with its cargo of the SciSat-1 payload and Pegasus launch vehicle, moves under the L-1011 carrier aircraft for matting. The SciSat-1 weighs approximately 330 pounds and after launch will be placed in a 400-mile-high polar orbit to investigate processes that control the distribution of ozone in the upper atmosphere. The data from the satellite will provide Canadian and international scientists with improved measurements relating to global ozone processes and help policymakers assess existing environmental policy and develop protective measures for improving the health of our atmosphere, preventing further ozone depletion. The mission is designed to last two years.

VANDENBERG AIR FORCE BASE, CALIF. - The SciSat-1 payload, with fairing installed and attached to its Pegasus launch vehicle, arrives at the pad for mating to the L-1011 carrier aircraft. The SciSat-1 weighs approximately 330 pounds and after launch will be placed in a 400-mile-high polar orbit to investigate processes that control the distribution of ozone in the upper atmosphere. The data from the satellite will provide Canadian and international scientists with improved measurements relating to global ozone processes and help policymakers assess existing environmental policy and develop protective measures for improving the health of our atmosphere, preventing further ozone depletion. The mission is designed to last two years.

NASA Image and Video Library

2003-08-09

VANDENBERG AIR FORCE BASE, CALIF. - The SciSat-1 payload, with fairing installed and attached to its Pegasus launch vehicle, arrives at the pad for mating to the L-1011 carrier aircraft. The SciSat-1 weighs approximately 330 pounds and after launch will be placed in a 400-mile-high polar orbit to investigate processes that control the distribution of ozone in the upper atmosphere. The data from the satellite will provide Canadian and international scientists with improved measurements relating to global ozone processes and help policymakers assess existing environmental policy and develop protective measures for improving the health of our atmosphere, preventing further ozone depletion. The mission is designed to last two years.

Shuttle-Derived Launch Vehicles' Capablities: An Overview

NASA Technical Reports Server (NTRS)

Rothschild, William J.; Bailey, Debra A.; Henderson, Edward M.; Crumbly, Chris

2005-01-01

Shuttle-Derived Launch Vehicle (SDLV) concepts have been developed by a collaborative team comprising the Johnson Space Center, Marshall Space Flight Center, Kennedy Space Center, ATK-Thiokol, Lockheed Martin Space Systems Company, The Boeing Company, and United Space Alliance. The purpose of this study was to provide timely information on a full spectrum of low-risk, cost-effective options for STS-Derived Launch Vehicle concepts to support the definition of crew and cargo launch requirements for the Space Exploration Vision. Since the SDLV options use high-reliability hardware, existing facilities, and proven processes, they can provide relatively low-risk capabilities to launch extremely large payloads to low Earth orbit. This capability to reliably lift very large, high-dollar-value payloads could reduce mission operational risks by minimizing the number of complex on-orbit operations compared to architectures based on multiple smaller launchers. The SDLV options also offer several logical spiral development paths for larger exploration payloads. All of these development paths make practical and cost-effective use of existing Space Shuttle Program (SSP) hardware, infrastructure, and launch and flight operations systems. By utilizing these existing assets, the SDLV project could support the safe and orderly transition of the current SSP through the planned end of life in 2010. The SDLV concept definition work during 2004 focused on three main configuration alternatives: a side-mount heavy lifter (approximately 77 MT payload), an in-line medium lifter (approximately 22 MT Crew Exploration Vehicle payload), and an in-line heavy lifter (greater than 100 MT payload). This paper provides an overview of the configuration, performance capabilities, reliability estimates, concept of operations, and development plans for each of the various SDLV alternatives. While development, production, and operations costs have been estimated for each of the SDLV configuration alternatives, these proprietary data have not been included in this paper.

In-flight calibration of mesospheric rocket plasma probes

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

Havnes, Ove; University Studies Svalbard; Hartquist, Thomas W.

Many effects and factors can influence the efficiency of a rocket plasma probe. These include payload charging, solar illumination, rocket payload orientation and rotation, and dust impact induced secondary charge production. As a consequence, considerable uncertainties can arise in the determination of the effective cross sections of plasma probes and measured electron and ion densities. We present a new method for calibrating mesospheric rocket plasma probes and obtaining reliable measurements of plasma densities. This method can be used if a payload also carries a probe for measuring the dust charge density. It is based on that a dust probe's effectivemore » cross section for measuring the charged component of dust normally is nearly equal to its geometric cross section, and it involves the comparison of variations in the dust charge density measured with the dust detector to the corresponding current variations measured with the electron and/or ion probes. In cases in which the dust charge density is significantly smaller than the electron density, the relation between plasma and dust charge density variations can be simplified and used to infer the effective cross sections of the plasma probes. We illustrate the utility of the method by analysing the data from a specific rocket flight of a payload containing both dust and electron probes.« less

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.

Impact of low cost refurbishable and standard spacecraft upon future NASA space programs. Payload effects follow-on study, appendix

NASA Technical Reports Server (NTRS)

1972-01-01

Mission analysis is discussed, including the consolidation and expansion of mission equipment and experiment characteristics, and determination of simplified shuttle flight schedule. Parametric analysis of standard space hardware and preliminary shuttle/payload constraints analysis are evaluated, along with the cost impact of low cost standard hardware.

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.

ExoMars: Overview of scientific programme

NASA Astrophysics Data System (ADS)

Rodionov, Daniel; Witasse, Olivier; Vago, Jorge L.

The ExoMars Programme is a joint project between the European Space Agency (ESA) and the Russian Federal Space Agency (Roscosmos). The project consists of two missions with launches in 2016 and 2018. The scientific objectives of ExoMars are: begin{itemize} To search for signs of past and present life on Mars. To investigate the water/geochemical environment as a function of depth in the shallow subsurface. To study Martian atmospheric trace gases and their sources. To characterize the surface environment. The 2016 mission will be launched (January 2016) on a Proton rocket. It includes the Trace Gas Orbiter (TGO) and an Entry, descent and landing Demonstrator Module (EDM), both contributed by ESA. The TGO will carry European and Russian scientific instruments for remote observations, while the EDM will have a European payload for in-situ measurements during descent and on the Martian surface. The TGO scientific payload includes:begin{itemize} NOMAD. Suite of 2 Infrared (IR) and 1 Ultraviolet (UV) spectrometer. ACS. Suite of 2 IR echelle-spectrometers (near and middle IR) and 1 Fourier spectrometer. FREND. Neutron spectrometer with a collimation module. CaSSIS. High-resolution camera. The EDM payload includes a set of accelerometers and heat shield sensors (AMELIA), to study the Martian atmosphere and obtain images throughout the EDM’s descent, and an environmental station (DREAMS), to conduct a series of short meteorological observations at the EDM’s landing location. The 2018 mission will land a Rover, provided by ESA, making use of a Descent Module (DM) contributed by Roscosmos. The mission will be launched on a Proton rocket (May 2018). The ExoMars rover will have a nominal lifetime of approximately 6 months. During this period, it will ensure a regional mobility of several kilometres, relying on solar array electrical power. The rover’s Pasteur payload will produce self-consistent sets of measurements capable to provide reliable evidence, for or against, the existence of a range of biosignatures at each search location. Pasteur contains: panoramic instruments (wide-angle and high-resolution cameras, an infrared spectrometer, a ground-penetrating radar, and a neutron detector); contact instruments for studying rocks and collected samples (a close-up imager and an infrared spectrometer in the drill head); a subsurface drill capable of reaching a depth of 2 m to collect specimens; a Sample Preparation and Distribution System (SPDS); and the analytical laboratory, the latter including a visual and infrared imaging spectrometer, a Raman spectrometer, and a Laser-Desorption, Thermal-Volatilisation, Derivatisation, Gas Chromatograph Mass Spectrometer (LD + Der-TV GCMS). After Rover egress, the Surface Platform (SP) will conduct environmental and geophysics experiments for about a Martian year. The SP scientific payload is under selection at the moment.

Effects of the specular Orbiter forward radiators on a typical Spacelab payload thermal environment

NASA Technical Reports Server (NTRS)

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

1981-01-01

Orbiter radiators, having a specular reflection, must be considered when determining the design environment for payloads which can view the forward deployed radiators. Unlike most surfaces on the Orbiter, which reflect energy diffusely, the radiators are covered with a highly specular silverized Teflon material, with high emissivity, and have a concave contour, producing a local concentration of reflected energy towards the region of angle incidence. The combined effects of radiator specularity and geometry were analyzed using the Thermal Radiation Analysis System (TRASYS II), a specialized ray trace program, and a generalized Monte-Carlo-based thermal radiation program. Data given for a 0 deg payload inclination angle at orbital noon at 3.454 m indicate that the maximum total flux and average flux can increase 173% and 63%, respectively, when compared to diffuse radiators.

Control-structure interaction/mirror motion compensation

NASA Technical Reports Server (NTRS)

Mclaren, Mark; Chu, Peter; Price, Xen

1992-01-01

Space Systems/Loral (formerly Ford Aerospace, Space Systems Division) has implemented a rigid-body Mirror Motion Compensation (MMC) scheme for the GOES-I/M spacecraft currently being built for NASA and NOAA. This has resulted in a factor of 15 reduction in pointing error due to rigid-body spacecraft motion induced by the periodic black-body calibration maneuvers required for the instruments. For GOES the spacecraft and the payload mirrors are considered as rigid bodies. The structural flexibility effects are small and are included in the total pointing budget as a separate item. This paper extends the MMC technique to include structural flexibility. For large multi-payload platforms, the structural flexibility effects can be more important in sensor pointing jitter as the result of payload motion. Sensitivity results are included to show the importance of the dynamic model fidelity.

Spacelab Level 4 Programmatic Implementation Assessment Study. Volume 1: Representative payload definition

NASA Technical Reports Server (NTRS)

1978-01-01

Four types of Spacelab payloads were analyzed; these were considered to be representative of the Spacelab traffic model. The payloads were: (1) space processing - a single pallet payload; (2) combined astronomy - a five pallet payload; (3) life sciences - a long module payload; and (4) advanced technology lab - a short module plus train payload.

Communications platform payload definition study, executive summary

NASA Technical Reports Server (NTRS)

Clopp, H. W.; Hawkes, T. A.; Bertles, C. R.; Pontano, B. A.; Kao, T.

1986-01-01

Large geostationary communications platforms have been investigated in a number of studies since 1974 as a possible means to more effectively utilize the geostationary orbital arc and electromagnetic spectrum and to reduce overall satellite communications system costs. This NASA Lewis sponsored study addresses the commercial feasibility of various communications platform payload concepts circa 1998. It defines promising payload concepts, estimates recurring costs and identifies critical technologies needed to permit eventual commercialization. Ten communications service aggregation scenarios describing potential groupings of services were developed for a range of conditions. Payload concepts were defined for four of these scenarios: (1) Land Mobile Satellite Service (LMSS), meet 100% of CONUS plus Canada demand with a single platform; (2) Fixed Satellite Service (FSS) (Trunking + Customer Premises Service (CPS), meet 20% of CONUS demands; (3) FSS (Trunking + video distribution), 10 to 13% of CONUS demand; and (4) FSS (20% of demand) + Inter Satellite Links (ISL) + TDRSS/TDAS Data Distribution.

Interactions measurement payload for Shuttle

NASA Technical Reports Server (NTRS)

Guidice, D. A.; Pike, C. P.

1985-01-01

The Interactions Measurement Payload for Shuttle (IMPS) consisted of engineering experiments to determine the effects of the space environment on projected Air Force space systems. Measurements by IMPS on a polar-orbit Shuttle flight will lead to detailed knowledge of the interaction of the low-altitude polar-auroral environment on materials, equipment and technologies to be used in future large, high-power space systems. The results from the IMPS measurements will provide direct input to MIL-STD design guidelines and test standards that properly account for space-environment effects.

Selected OAST/OSSA space experiment activities in support of Space Station Freedom

NASA Astrophysics Data System (ADS)

Delombard, Richard

The Space Experiments Division at NASA Lewis Research Center is developing technology and science space experiments for the Office of Aeronautics and Space Technology (OAST) and the Office of Space Sciences and Applications (OSSA). Selected precursor experiments and technology development activities supporting the Space Station Freedom (SSF) are presented. The Tank Pressure Control Experiment (TPCE) is an OAST-funded cryogenic fluid dynamics experiment, the objective of which is to determine the effectiveness of jet mixing as a means of equilibrating fluid temperatures and controlling tank pressures, thereby permitting the design of lighter cryogenic tanks. The information from experiments such as this will be utilized in the design and operation of on board cryogenic storage for programs such as SSF. The Thermal Energy Storage Flight Project (TES) is an OAST-funded thermal management experiment involving phase change materials for thermal energy storage. The objective of this project is to develop and fly in-space experiments to characterize void shape and location in phase change materials used in a thermal energy storage configuration representative of an advanced solar dynamic system design. The information from experiments such as this will be utilized in the design of future solar dynamic power systems. The Solar Array Module Plasma Interaction Experiment (SAMPIE) is an OAST-funded experiment to determine the environmental effects of the low earth orbit (LEO) space plasma environment on state-of-the-art solar cell modules biased to high potentials relative to the plasma. Future spacecraft designs and structures will push the operating limits of solar cell arrays and other high voltage systems. SAMPIE will provide key information necessary for optimum module design and construction. The Vibration Isolation Technology (VIT) Advanced Technology Development effort is funded by OSSA to provide technology necessary to maintain a stable microgravity environment for sensitive payloads on board spacecraft. The proof of concept will be demonstrated by laboratory tests and in low-gravity aircraft flights. VIT is expected to be utilized by many SSF microgravity science payloads. The Space Acceleration Measurement System (SAMS) is an OSSA-funded instrument to measure the microgravity acceleration environment for OSSA payloads on the shuttle and SSF.

Selected OAST/OSSA space experiment activities in support of Space Station Freedom

NASA Technical Reports Server (NTRS)

Delombard, Richard

1992-01-01

The Space Experiments Division at NASA Lewis Research Center is developing technology and science space experiments for the Office of Aeronautics and Space Technology (OAST) and the Office of Space Sciences and Applications (OSSA). Selected precursor experiments and technology development activities supporting the Space Station Freedom (SSF) are presented. The Tank Pressure Control Experiment (TPCE) is an OAST-funded cryogenic fluid dynamics experiment, the objective of which is to determine the effectiveness of jet mixing as a means of equilibrating fluid temperatures and controlling tank pressures, thereby permitting the design of lighter cryogenic tanks. The information from experiments such as this will be utilized in the design and operation of on board cryogenic storage for programs such as SSF. The Thermal Energy Storage Flight Project (TES) is an OAST-funded thermal management experiment involving phase change materials for thermal energy storage. The objective of this project is to develop and fly in-space experiments to characterize void shape and location in phase change materials used in a thermal energy storage configuration representative of an advanced solar dynamic system design. The information from experiments such as this will be utilized in the design of future solar dynamic power systems. The Solar Array Module Plasma Interaction Experiment (SAMPIE) is an OAST-funded experiment to determine the environmental effects of the low earth orbit (LEO) space plasma environment on state-of-the-art solar cell modules biased to high potentials relative to the plasma. Future spacecraft designs and structures will push the operating limits of solar cell arrays and other high voltage systems. SAMPIE will provide key information necessary for optimum module design and construction. The Vibration Isolation Technology (VIT) Advanced Technology Development effort is funded by OSSA to provide technology necessary to maintain a stable microgravity environment for sensitive payloads on board spacecraft. The proof of concept will be demonstrated by laboratory tests and in low-gravity aircraft flights. VIT is expected to be utilized by many SSF microgravity science payloads. The Space Acceleration Measurement System (SAMS) is an OSSA-funded instrument to measure the microgravity acceleration environment for OSSA payloads on the shuttle and SSF.

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.

Integrating International Space Station payload operations

NASA Technical Reports Server (NTRS)

Noneman, Steven R.

1996-01-01

The payload operations support for the International Space Station (ISS) payload is reported on, describing payload activity planning, payload operations control, payload data management and overall operations integration. The operations concept employed is based on the distribution of the payload operations responsibility between the researchers and ISS partners. The long duration nature of the ISS mission dictates the geographical distribution of the payload operations activities between the different national centers. The coordination and integration of these operations will be assured by NASA's Payload Operations Integration Center (POIC). The prime objective of the POIC is the achievement of unified operations through communication and collaboration.

Engineering aspect of the Microwave Ionosphere Nonlinear Interaction Experiment (MINIX) with a sounding rocket

NASA Astrophysics Data System (ADS)

Nagatomo, M.; Kaya, N.; Matsumoto, H.

1984-10-01

One type of problem arising in connection with an evaluation of the feasibility of the Solar Power Satellite (SPS) and the definition of suitable SPS designs is related to environmental issues. Questions exist, for instance, regarding the interaction between microwave power and the upper atmosphere. The present investigation is concerned with the Microwave Ionosphere Nonlinear Interaction Experiment (MINIX), which is a space plasma experiment originally devoted to the research of space plasma physics. MINIX is eventually to observe possible effects of a strong microwave field in the ionospheric environment. The scientific requirements of the MINIX are discussed, taking into account functional and experimental conditions. Attention is also given to rocket characteristics, experimental design, the payload, the inflight experiment configuration, and details concerning the conduction of the experiment.

Selection of shuttle payload data processing drivers for the data system new technology study

NASA Technical Reports Server (NTRS)

1976-01-01

An investigation of all payloads in the IBM disciplines and the selection of driver payloads within each discipline are described. The driver payloads were selected on the basis of their data processing requirements. These requirements are measured by a weighting scheme. The total requirements for each discipline are estimated by use of the technology payload model. The driver selection process which was both a payload by payload comparison and a comparison of expected groupings of payloads was examined.

Control system and method for payload control in mobile platform cranes

DOEpatents

Robinett, III, Rush D.; Groom, Kenneth N.; Feddema, John T.; Parker, Gordon G.

2002-01-01

A crane control system and method provides a way to generate crane commands responsive to a desired payload motion to achieve substantially pendulation-free actual payload motion. The control system and method apply a motion compensator to maintain a payload in a defined payload configuration relative to an inertial coordinate frame. The control system and method can further comprise a pendulation damper controller to reduce an amount of pendulation between a sensed payload configuration and the defined payload configuration. The control system and method can further comprise a command shaping filter to filter out a residual payload pendulation frequency from the desired payload motion.

Cargo systems manual: Heat Pipe Performance (HPP) STS-66

NASA Technical Reports Server (NTRS)

Napp, Robert

1994-01-01

The purpose of the cargo systems manual (CSM) is to provide a payload reference document for payload and shuttle flight operations personnel during shuttle mission planning, training, and flight operations. It includes orbiter-to-payload interface information and payload system information (including operationally pertinent payload safety data) that is directly applicable to the Mission Operations Directorate (MOD) role in the payload mission. The primary objectives of the heat pipe performance (HPP) are to obtain quantitative data on the thermal performance of heat pipes in a microgravity environment. This information will increase understanding of the behavior of heat pipes in space and be useful for application to design improvements in heat pipes and associated systems. The purpose of HPP-2 is to establish a complete one-g and zero-g data base for axial groove heat pipes. This data will be used to update and correlate data generated from a heat pipe design computer program called Grooved Analysis Program (GAP). The HPP-2 objectives are to: determine heat transport capacity and conductance for open/closed grooved heat pipes and different Freon volumes (nominal, under, and overcharged) using a uniform heat load; determine heat transport capacity and conductance for single/multiple evaporators using asymmetric heat loads; obtain precise static, spin, and rewicking data points for undercharged pipes; investigate heat flux limits (asymmetric heat loads); and determine effects of positive body force on thermal performance.

Status of robotic mission studies for the Space Exploration Initiative - 1991

NASA Technical Reports Server (NTRS)

Bourke, Roger D.; Dias, William C.; Golombek, Matthew P.; Pivirotto, Donna L.; Sturms, Francis M.; Hubbard, G. S.

1991-01-01

Results of studies of robotic missions to the moon and Mars planned under the U.S. Space Exploration Initiative are summarized. First, an overall strategy for small robotic missions to accomplish the information gathering required by human missions is reviewed, and the principal robotic mission requirements are discussed. The discussion covers the following studies: the Lunar Observer, the Mars Environmental Survey mission, Mars Sample Return missions using microtechnology, and payloads.

Environmental Assessment for the National Museum of the United States Air Force Addition, Wright-Patterson Air Force Base, Ohio

DTIC Science & Technology

2013-02-01

telephone, local computer systems, long-haul communications , and land mobile radio systems (WPAFB 2001). There are over 100 miles of communication cable...10. SPONSOR/MONITOR’S ACRONYM(S) 11 . SPONSOR/MONITOR’S REPORT NUMBER(S) 12. DISTRIBUTION/AVAILABILITY STATEMENT Approved for public release...Air Force technologies and would include unique characteristics in design, propulsion, payload capacity, buman factors, communication , range, speed

Sentinel-3a: commissioning phase results of its optical payload

NASA Astrophysics Data System (ADS)

Nieke, J.; Mavrocordatos, C.

2017-09-01

The Sentinel-3 (S3) is a Global Land and Ocean Mission [1] currently in development as part of the European Commission's Copernicus programme (former: Global Monitoring for Environment and Security (GMES) [2]). The multi-instrument Sentinel-3 mission measures sea-surface topography, sea- and land-surface temperature, ocean colour and land colour to support ocean forecasting systems, as well as environmental and climate monitoring with near-real time data.

GOES-R Lift and Mate

NASA Image and Video Library

2016-11-09

A view from high up inside the Vertical Integration Facility at Space Launch Complex 41 at Cape Canaveral Air Force Station in Florida. A crane lifts the payload fairing containing NOAA's Geostationary Operational Environmental Satellite (GOES-R) for mating to the United Launch Alliance Atlas V Centaur upper stage. The satellite will launch aboard the Atlas V rocket in November. GOES-R is the first satellite in a series of next-generation NOAA GOES Satellites.

The development of a high-capacity instrument module heat transport system, appendixes

NASA Technical Reports Server (NTRS)

1981-01-01

Data sheets provide temperature requirements for 82 individual instruments that are under development or planned for grouping on a space platform or pallet. The scientific objectives of these instrument packages are related to solar physics, space plasma physics, astronomy, high energy astrophysics, resources observations, environmental observations, materials processing, and life sciences. System specifications are given for a high capacity instrument module heat transport system to be used with future payloads.

KSC-2009-1371

NASA Image and Video Library

2008-11-05

VANDENBERG AIR FORCE BASE, Calif. – Inside the payload processing facility at Vandenberg Air Force Base in California, the shipping container for NOAA-N Prime is lifted. NOAA-N Prime is the latest polar-orbiting operational environmental weather satellite developed by NASA for the National Oceanic and Atmospheric Administration. NOAA-N Prime is built by Lockheed Martin and similar to NOAA-N launched on May 20, 2005. Launch of NOAA-N Prime is scheduled for Feb. 4. Photo credit: NASA

KSC-2009-1382

NASA Image and Video Library

2008-11-11

VANDENBERG AIR FORCE BASE, Calif. – Another view of the NOAA-N Prime satellite in the payload processing facility at Vandenberg Air Force Base in California. NOAA-N Prime is the latest polar-orbiting operational environmental weather satellite developed by NASA for the National Oceanic and Atmospheric Administration. It is built by Lockheed Martin and similar to NOAA-N launched on May 20, 2005. Launch of NOAA-N Prime is scheduled for Feb. 4. Photo credit: NASA

KSC-2009-1372

NASA Image and Video Library

2008-11-05

VANDENBERG AIR FORCE BASE, Calif. – Inside the payload processing facility at Vandenberg Air Force Base in California, NOAA-N Prime, the latest polar-orbiting operational environmental weather satellite developed by NASA for the National Oceanic and Atmospheric Administration, is revealed after removal of the shipping container. NOAA-N Prime is built by Lockheed Martin and similar to NOAA-N launched on May 20, 2005. Launch of NOAA-N Prime is scheduled for Feb. 4. Photo credit: NASA

KSC-2009-1388

NASA Image and Video Library

2008-11-12

VANDENBERG AIR FORCE BASE, Calif. – Another view of the NOAA-N Prime satellite in the payload processing facility at Vandenberg Air Force Base in California. NOAA-N Prime is the latest polar-orbiting operational environmental weather satellite developed by NASA for the National Oceanic and Atmospheric Administration. It is built by Lockheed Martin and similar to NOAA-N launched on May 20, 2005. Launch of NOAA-N Prime is scheduled for Feb. 4. Photo credit: NASA/Joe Davila, VAFB

KSC-2009-1381

NASA Image and Video Library

2008-11-11

VANDENBERG AIR FORCE BASE, Calif. – Another view of the NOAA-N Prime satellite in the payload processing facility at Vandenberg Air Force Base in California. NOAA-N Prime is the latest polar-orbiting operational environmental weather satellite developed by NASA for the National Oceanic and Atmospheric Administration. It is built by Lockheed Martin and similar to NOAA-N launched on May 20, 2005. Launch of NOAA-N Prime is scheduled for Feb. 4. Photo credit: NASA

KSC-2009-1380

NASA Image and Video Library

2008-11-11

VANDENBERG AIR FORCE BASE, Calif. – Another view of the NOAA-N Prime satellite in the payload processing facility at Vandenberg Air Force Base in California. NOAA-N Prime is the latest polar-orbiting operational environmental weather satellite developed by NASA for the National Oceanic and Atmospheric Administration. It is built by Lockheed Martin and similar to NOAA-N launched on May 20, 2005. Launch of NOAA-N Prime is scheduled for Feb. 4. Photo credit: NASA

KSC-2009-1370

NASA Image and Video Library

2008-11-05

VANDENBERG AIR FORCE BASE, Calif. – Inside the payload processing facility at Vandenberg Air Force Base in California, workers get ready to remove the shipping container from NOAA-N Prime, the latest polar-orbiting operational environmental weather satellite developed by NASA for the National Oceanic and Atmospheric Administration. NOAA-N Prime is built by Lockheed Martin and similar to NOAA-N launched on May 20, 2005. Launch of NOAA-N Prime is scheduled for Feb. 4. Photo credit: NASA

Final Environmental Impact Statement for the Ulysses Mission (Tier 2)

NASA Technical Reports Server (NTRS)

1990-01-01

This Final (Tier 2) Environmental Impact Statement (FEIS) addresses the environmental impacts which may be caused by implementation of the Ulysses mission, a space flight mission to observe the polar regions of the Sun. The proposed action is completion of preparation and operation of the Ulysses spacecraft, including its planned launch at the earliest available launch opportunity on the Space Transportation System (STS) Shuttle in October 1990 or in the backup opportunity in November 1991. The alternative is canceling further work on the mission. The Tier 1 EIS included a delay alternative which considered the Titan 4 launch vehicle as an alternative booster stage for launch in 1991 or later. This alternative was further evaluated and eliminated from consideration when, in November 1988, the U.S. Air Force, which procures the Titan 4, notified that it could not provide a Titan 4 vehicle for the 1991 launch opportunity because of high priority Department of Defense requirements. The Titan 4 launch vehicle is no longer a feasible alternative to the STS/Inertial Upper Stage (IUS)/Payload Assist Module-Special (PAM-S) for the November 1991 launch opportunity. The only expected environment effects of the proposed action are associated with normal launch vehicle operation and are treated elsewhere. The environmental impacts of normal Shuttle launches were addressed in existing NEPA documentation and are briefly summarized. These impacts are limited largely to the near-field at the launch pad, except for temporary stratospheric ozone effects during launch and occasional sonic boom effects near the landing site. These effects were judged insufficient to preclude Shuttle launches. There could also be environmental impacts associated with the accidental release of radiological material during launch, deployment, or interplanetary trajectory injection of the Ulysses spacecraft. Intensive analysis indicates that the probability of release is small. There are no environmental impacts in the no-action alternative; however, the U.S. Government and the European Space Agency would suffer adverse fiscal and programmatic impacts if this alternative were adopted. The scientific benefits of the mission would be delayed and possibly lost. There could be significant impacts on the ability of the U.S. to negotiate international agreements for cooperative space activities.

14 CFR 415.59 - Information requirements for payload review.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Information requirements for payload review... ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LAUNCH LICENSE Payload Review and Determination § 415.59 Information requirements for payload review. (a) A person requesting review of a particular payload or payload...

14 CFR 431.7 - Payload and payload reentry determinations.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Payload and payload reentry determinations. 431.7 Section 431.7 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... payload reentry determination is required to reenter a payload to Earth on an RLV unless the proposed...

Bi-Axial Solar Array Drive Mechanism: Design, Build and Environmental Testing

NASA Technical Reports Server (NTRS)

Scheidegger, Noemy; Ferris, Mark; Phillips, Nigel

2014-01-01

The development of the Bi-Axial Solar Array Drive Mechanism (BSADM) presented in this paper is a demonstration of SSTL's unique space manufacturing approach that enables performing rapid development cycles for cost-effective products that meet ever-challenging mission requirements: The BSADM is designed to orient a solar array wing towards the sun, using its first rotation axis to track the sun, and its second rotation axis to compensate for the satellite orbit and attitude changes needed for a successful payload operation. The tight development schedule, with manufacture of 7 Flight Models within 1.5 year after kick-off, is offset by the risk-reduction of using qualified key component-families from other proven SSTL mechanisms. This allowed focusing the BSADM design activities on the mechanism features that are unique to the BSADM, and having an Engineering Qualification Model (EQM) built 8 months after kick-off. The EQM is currently undergoing a full environmental qualification test campaign. This paper presents the BSADM design approach that enabled meeting such a challenging schedule, its design particularities, and the ongoing verification activities.

Next generation sensing platforms for extended deployments in large-scale, multidisciplinary, adaptive sampling and observational networks

NASA Astrophysics Data System (ADS)

Cross, J. N.; Meinig, C.; Mordy, C. W.; Lawrence-Slavas, N.; Cokelet, E. D.; Jenkins, R.; Tabisola, H. M.; Stabeno, P. J.

2016-12-01

New autonomous sensors have dramatically increased the resolution and accuracy of oceanographic data collection, enabling rapid sampling over extremely fine scales. Innovative new autonomous platofrms like floats, gliders, drones, and crawling moorings leverage the full potential of these new sensors by extending spatiotemporal reach across varied environments. During 2015 and 2016, The Innovative Technology for Arctic Exploration Program at the Pacific Marine Environmental Laboratory tested several new types of fully autonomous platforms with increased speed, durability, and power and payload capacity designed to deliver cutting-edge ecosystem assessment sensors to remote or inaccessible environments. The Expendable Ice-Tracking (EXIT) gloat developed by the NOAA Pacific Marine Environmental Laboratory (PMEL) is moored near bottom during the ice-free season and released on an autonomous timer beneath the ice during the following winter. The float collects a rapid profile during ascent, and continues to collect critical, poorly-accessible under-ice data until melt, when data is transmitted via satellite. The autonomous Oculus sub-surface glider developed by the University of Washington and PMEL has a large power and payload capacity and an enhanced buoyancy engine. This 'coastal truck' is designed for the rapid water column ascent required by optical imaging systems. The Saildrone is a solar and wind powered ocean unmanned surface vessel (USV) developed by Saildrone, Inc. in partnership with PMEL. This large-payload (200 lbs), fast (1-7 kts), durable (46 kts winds) platform was equipped with 15 sensors designed for ecosystem assessment during 2016, including passive and active acoustic systems specially redesigned for autonomous vehicle deployments. The senors deployed on these platforms achieved rigorous accuracy and precision standards. These innovative platforms provide new sampling capabilities and cost efficiencies in high-resolution sensor deployment, including reconnaissance for annual fisheries and marine mammal surveys; better linkages between sustained observing platforms; and adaptive deployments that can easily target anomalies as they arise.

Autonomous mine detection system (AMDS) neutralization payload module

NASA Astrophysics Data System (ADS)

Majerus, M.; Vanaman, R.; Wright, N.

2010-04-01

The Autonomous Mine Detection System (AMDS) program is developing a landmine and explosive hazards standoff detection, marking, and neutralization system for dismounted soldiers. The AMDS Capabilities Development Document (CDD) has identified the requirement to deploy three payload modules for small robotic platforms: mine detection and marking, explosives detection and marking, and neutralization. This paper addresses the neutralization payload module. There are a number of challenges that must be overcome for the neutralization payload module to be successfully integrated into AMDS. The neutralizer must meet stringent size, weight, and power (SWaP) requirements to be compatible with a small robot. The neutralizer must be effective against a broad threat, to include metal and plastic-cased Anti-Personnel (AP) and Anti-Tank (AT) landmines, explosive devices, and Unexploded Explosive Ordnance (UXO.) It must adapt to a variety of threat concealments, overburdens, and emplacement methods, to include soil, gravel, asphalt, and concrete. A unique neutralization technology is being investigated for adaptation to the AMDS Neutralization Module. This paper will describe review this technology and how the other two payload modules influence its design for minimizing SWaP. Recent modeling and experimental efforts will be included.

Shuttle payload bay thermal environments: Summary and conclusion report for STS Flights 1-5

NASA Technical Reports Server (NTRS)

Fu, J. H.; Graves, G. R.

1987-01-01

The thermal data for the payload bay of the first five shuttle flights is summarized and the engineering evaluation of that data is presented. After a general discussion on mission profiles and vehicle configurations, the thermal design and flight instrumentation systems of the payload bay are described. The thermal flight data sources and a categorization of the data are then presented. A thermal flight data summarization section provides temperature data for the five phases of a typical mission profile. These are: prelaunch, ascent, on-orbit, entry and postlanding. The thermal flight data characterization section encompasses this flight data for flight to flight variations, payload effects, temperature ranges, and other variations. Discussion of the thermal environment prediction models in use by industry and various NASA Centers, and the results predicted by these models, is followed by an evaluation of the correlation between the actual flight data and the results predicted by the models. Finally, the available thermal data are evaluated from the viewpoint of the user concerned with establishing the thermal environment in the payload bay. The data deficiencies are discussed and recommendations for their elimination are presented.

Improving UV Resistance of High Strength Fibers Used In Large Scientific Balloons

NASA Technical Reports Server (NTRS)

Said, M.; Gupta, A.; Seyam, A.; Mock, G.; Theyson, T.

2004-01-01

For the last three decades, NASA has been involved in the development of giant balloons that are capable of lifting heavy payloads of equipment (such as large telescopes and scientific instruments) to the upper atmosphere. While the use of such balloons has led to scientific discoveries, the demand for competitive science payloads and observational programs continues to rise. The NASA Balloon Program Office has entered a new phase of research to develop an Ultra Long Duration Balloon (ULDB) that will lift payloads of up to 3,600 kg to altitudes of up to 40 km. The flight duration is targeted to ranges between 30 to 100 days. Attaining these target durations requires the development of a super-pressure balloon design. The use of textile structures have already been established in these missions in the form of high strength tendons essential for the super pressure pumpkin design. Unfortunately, high strength fibers lose significant strength upon exposure to Ultra Violet (UV) radiation. Such UV degradation poses a serious challenge for the development of the ULDB. To improve the mission performance of the ULDB, new methods for protecting the tendons from the environmental effects need to be developed. NASA and NC State University College of Textiles are undertaking a research program to address these issues. Four tracks have been identified to prepare finishes that are believed to enhance the resistance of high strength fibers to UV. These tracks are: (a) self-polymerizing, (b) diffusion application, (c) polymer-filled with 30-40% UV absorber, and (d) combination of dyeing plus surface application. Four high performance fibers have been selected for this research investigation. These are Vectran (trademark), Spectra (trademark), Kevlar (trademark) and, PBO (Zylon (trademark)). This work will address the current progress of evaluating the performance of the UV finishes. This will be accomplished by comparing the tensile properties (strength, breaking elongation, modulus, etc) of untreated, unexposed to UV fibers; untreated exposed to UV fibers; and treated exposed to UV fibers.

Functional activity of plasmid DNA after entry into the atmosphere of earth investigated by a new biomarker stability assay for ballistic spaceflight experiments.

PubMed

Thiel, Cora S; Tauber, Svantje; Schütte, Andreas; Schmitz, Burkhard; Nuesse, Harald; Moeller, Ralf; Ullrich, Oliver

2014-01-01

Sounding rockets represent an excellent platform for testing the influence of space conditions during the passage of Earth's atmosphere and re-entry on biological, physical and chemical experiments for astrobiological purposes. We designed a robust functionality biomarker assay to analyze the biological effects of suborbital spaceflights prevailing during ballistic rocket flights. During the TEXUS-49 rocket mission in March 2011, artificial plasmid DNA carrying a fluorescent marker (enhanced green fluorescent protein: EGFP) and an antibiotic resistance cassette (kanamycin/neomycin) was attached on different positions of rocket exterior; (i) circular every 90 degree on the outer surface concentrical of the payload, (ii) in the grooves of screw heads located in between the surface application sites, and (iii) on the surface of the bottom side of the payload. Temperature measurements showed two major peaks at 118 and 130 °C during the 780 seconds lasting flight on the inside of the recovery module, while outer gas temperatures of more than 1000 °C were estimated on the sample application locations. Directly after retrieval and return transport of the payload, the plasmid DNA samples were recovered. Subsequent analyses showed that DNA could be recovered from all application sites with a maximum of 53% in the grooves of the screw heads. We could further show that up to 35% of DNA retained its full biological function, i.e., mediating antibiotic resistance in bacteria and fluorescent marker expression in eukaryotic cells. These experiments show that our plasmid DNA biomarker assay is suitable to characterize the environmental conditions affecting DNA during an atmospheric transit and the re-entry and constitute the first report of the stability of DNA during hypervelocity atmospheric transit indicating that sounding rocket flights can be used to model the high-speed atmospheric entry of organics-laden artificial meteorites.

Functional Activity of Plasmid DNA after Entry into the Atmosphere of Earth Investigated by a New Biomarker Stability Assay for Ballistic Spaceflight Experiments

PubMed Central

Thiel, Cora S.; Tauber, Svantje; Schütte, Andreas; Schmitz, Burkhard; Nuesse, Harald; Moeller, Ralf; Ullrich, Oliver

2014-01-01

Sounding rockets represent an excellent platform for testing the influence of space conditions during the passage of Earth's atmosphere and re-entry on biological, physical and chemical experiments for astrobiological purposes. We designed a robust functionality biomarker assay to analyze the biological effects of suborbital spaceflights prevailing during ballistic rocket flights. During the TEXUS-49 rocket mission in March 2011, artificial plasmid DNA carrying a fluorescent marker (enhanced green fluorescent protein: EGFP) and an antibiotic resistance cassette (kanamycin/neomycin) was attached on different positions of rocket exterior; (i) circular every 90 degree on the outer surface concentrical of the payload, (ii) in the grooves of screw heads located in between the surface application sites, and (iii) on the surface of the bottom side of the payload. Temperature measurements showed two major peaks at 118 and 130°C during the 780 seconds lasting flight on the inside of the recovery module, while outer gas temperatures of more than 1000°C were estimated on the sample application locations. Directly after retrieval and return transport of the payload, the plasmid DNA samples were recovered. Subsequent analyses showed that DNA could be recovered from all application sites with a maximum of 53% in the grooves of the screw heads. We could further show that up to 35% of DNA retained its full biological function, i.e., mediating antibiotic resistance in bacteria and fluorescent marker expression in eukariotic cells. These experiments show that our plasmid DNA biomarker assay is suitable to characterize the environmental conditions affecting DNA during an atmospheric transit and the re-entry and constitute the first report of the stability of DNA during hypervelocity atmospheric transit indicating that sounding rocket flights can be used to model the high-speed atmospheric entry of organics-laden artificial meteorites. PMID:25426925

KSC-98pc146

NASA Image and Video Library

1998-01-09

STS-90 Mission Specialist Dafydd "Dave" Rhys Williams, M.D., with the Canadian Space Agency, and back-up Payload Specialist Chiaki Mukai, M.D., Ph.D., with the National Space Development Agency of Japan, examine items to be used during the Crew Equipment Interface Test (CEIT) in Kennedy Space Center's (KSC's) Operations and Checkout Building, where the Neurolab payload is undergoing processing. The CEIT gives astronauts an opportunity to get a hands-on look at the payloads with which they will be working on-orbit. STS-90 is scheduled to launch aboard the Shuttle Columbia from KSC on April 2. Investigations during the Neurolab mission will focus on the effects of microgravity on the nervous system. Specifically, experiments will study the adaptation of the vestibular system, the central nervous system, and the pathways that control the ability to sense location in the absence of gravity, as well as the effect of microgravity on a developing nervous system

KSC-98pc316

NASA Image and Video Library

1998-02-26

Members of the STS-90 crew participate in the Crew Equipment Interface Test (CEIT) in Kennedy Space Center's Orbiter Processing Facility Bay 3. The CEIT gives astronauts an opportunity to get a hands-on look at the payloads with which they will be working on-orbit. Investigations during the STS-90 Neurolab mission will focus on the effects of microgravity on the nervous system. Specifically, experiments will study the adaptation of the vestibular system, the central nervous system, and the pathways that control the ability to sense location in the absence of gravity, as well as the effect of microgravity on a developing nervous system. The crew of STS-90, slated for launch in April, are, left to right, Pilot Scott Altman; Payload Specialist James Pawelczyk, Ph.D.; Commander Richard Searfoss; Mission Specialists Dafydd (Dave) Williams, M.D., and Kathryn (Kay) Hire; Payload Specialist Jay Buckey, M.D.; and Mission Specialist Richard Linnehan

14 CFR 415.57 - Payload review.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Payload review. 415.57 Section 415.57... TRANSPORTATION LICENSING LAUNCH LICENSE Payload Review and Determination § 415.57 Payload review. (a) Timing. A payload review may be conducted as part of a license application review or may be requested by a payload...

Express Payload Project - A new method for rapid access to Space Station Freedom

NASA Technical Reports Server (NTRS)

Uhran, Mark L.; Timm, Marc G.

1993-01-01

The deployment and permanent operation of Space Station Freedom will enable researchers to enter a new era in the 21st century, in which continuous on-orbit experimentation and observation become routine. In support of this objective, the Space Station Freedom Program Office has initiated the Express Payload Project. The fundamental project goal is to reduce the marginal cost associated with small payload development, integration, and operation. This is to be accomplished by developing small payload accommodations hardware and a new streamlined small payload integration process. Standardization of small payload interfaces, certification of small payload containers, and increased payload developer responsibility for mission success are key aspects of the Express Payload Project. As the project progresses, the principles will be applied to both pressurized payloads flown inside the station laboratories and unpressurized payloads attached to the station external structures. The increased access to space afforded by Space Station Freedom and the Express Payload Project has the potential to significantly expand the scope, magnitude, and success of future research in the microgravity environment.

New Heights with High-Altitude Balloon Launches for Effective Student Learning and Environmental Awareness

NASA Astrophysics Data System (ADS)

Voss, H. D.; Dailey, J. F.; Takehara, D.; Krueger, J. M.

2009-12-01

Over a seven-year period Taylor University, an undergraduate liberal art school, has successfully launched and recovered over 200 sophisticated student payloads to altitudes between 20-33 km (100% success with rapid recovery) with flight times between 2 to 6 hrs. All of the payloads included two GPS tracking systems, cameras and monitors, a 110 kbit down link, an uplink command capability for educational experiments (K-12 and undergrad). Launches were conducted during the day and night, with multiple balloons, with up to 10 payloads for experiments, and under varying weather and upper atmospheric conditions. The many launches in a short period of time allowed the payload bus design to evolve toward increased performance, reliability, standardization, simplicity, and modularity for low-cost launch services. Through NSF and NASA grants, the program has expanded leading to over 50 universities trained at workshops to implement high altitude balloon launches in the classroom. A spin-off company (StraoStar Systems LLC) now sells the high-altitude balloon system and facilitates networking between schools. This high-altitude balloon program helps to advance knowledge and understanding across disciplines by giving students and faculty rapid and low-cost access to earth/ecology remote sensing from high altitude, insitu and limb atmospheric measurements, near-space stratosphere measurements, and IR/UV/cosmic ray access to the heavens. This new capability is possible by exposing students to recent advances in MEMS technology, nanotechnology, wireless telecommunication systems, GPS, DSPs and other microchip miniaturizations to build < 4 kg payloads. The high-altitude balloon program provides an engaging laboratory, gives challenging field experiences, reaches students from diverse backgrounds, encourages collaboration among science faculty, and provides quantitative assessment of the learning outcomes. Furthermore this program has generated many front page news reports along with significant TV coverage because of its connection to hands-on learning for students and adults of all ages, connection to understanding climate change and ways to mitigate global warming, and the excitement of taking measurements in a much uncharted region of our atmosphere. Teaching the scientific method or learning cycle (theory, research, instrumentation, operations, data analysis, and presentation) is a significant pedagogical building block that stimulates and retains students and prepares them well for graduate school and professional careers. Students obtain a personal ownership of their education when they engage in state-of-the-art balloon launch capability into the "unknown" with real-time data (50 Kb) with command interaction. The scientific method comes alive with creativity, problem solving, fun, and multidisciplinary hands-on team work. More students in basic science (and liberal arts) and public have an awareness of the environment, atmosphere, space, and heavens by direct probing and remote sensing from "New Heights" (over 98% of atmosphere at 30 km altitude).

Satellite situation report, volume 33, number 4

NASA Technical Reports Server (NTRS)

1993-01-01

The Satellite Situation Report is a listing of those satellites (objects) currently in orbit and those which have previously orbited the Earth. Some objects are too small or too far from the Earth's surface to be detected; therefore, the Satellite Situation Report does not include all manmade objects orbiting the Earth. Generally, satellites are classified as follows: (1) Payloads may contain one or more functioning or nonfunctioning experiments. Usually only the owners of the satellites know if the experiments are functioning, and there is no one source which indicates the operational status of all payloads and/or experiments. Payloads are normally the first listed in the Satellite Situation Report, i.e., 1982 087A, unless there are multiple payloads for the launch. In which case, the first objects cataloged are usually all payloads, unless a subsequent payload is later identified after objects other than payloads have been cataloged. (2) Platforms are used to support a payload while it is being placed into orbit. A platform may remain in orbit long after its purpose is served, usually longer than rocket bodies. It is usually the first object identified in the Satellite Situation Report listing after the payload(s), i.e., 1982 087B (when a platform is not used, the first object after the payload(s) is usually the rocket body). (3) Rocket bodies are used to place the payload and platform (if one is used) into orbit. Some launches may have more than one rocket body because of the payload weight or the type of orbit or experiment. Most rocket bodies decay within a short time after the payload (and platform) have achieved orbit. Rocket bodies are usually the third object listed in the Satellite Situation Report after the payload(s), i.e., 1982 087C. (4) Debris in orbit occurs when parts (nose cone shrouds, lens or hatch covers) are separated from the payload, when rocket bodies or payloads disintegrate or explode, or when objects are placed into free space from manned orbiting spacecraft during operations. Debris is detected by its size and distance from the Earth. Debris objects are the last objects after payload(s), platform, and rocket body(s) listed in the Satellite Situation Report, i.e., 1982 087D, 1982 087E, 1982 087F.

KSC-08pd3323

NASA Image and Video Library

2008-10-22

CAPE CANAVERAL, Fla. - In the Payload Changeout Room, or PCR, on Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers use the payload ground-handling mechanism to transfer space shuttle Endeavour's STS-126 mission payload from the payload canister. The payload is the Multi-Purpose Logistics Module Leonardo and the Lightweight Multi-Purpose Experiment Support Structure Carrier. The payload later will be installed in Endeavour's payload bay. Endeavour is targeted for launch on Nov. 14. Photo credit: NASA/Kim Shiflett

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.

STS-87 Payload Specialist Kadenyuk in white room

NASA Technical Reports Server (NTRS)

1997-01-01

STS-87 Payload Specialist Leonid Kadenyuk of the National Space Agency of Ukraine is assisted with final preparations before launch in the white room at Launch Pad 39B by Danny Wyatt, NASA quality assurance specialist, at left; Dave Law, USA mechanical technician, facing Kadenyuk; and Travis Thompson, USA orbiter vehicle closeout chief, at right. STS-87 is the fourth flight of the United States Microgravity Payload and Spartan-201. The 16- day mission will include the Collaborative Ukrainian Experiment (CUE), a collection of 10 plant space biology experiments that will fly in Columbias middeck and will feature an educational component that involves evaluating the effects of microgravity on Brassica rapa seedlings.

NASA Headquarters/Kennedy Space Center: Organization and Small Spacecraft Launch Services

NASA Technical Reports Server (NTRS)

Sierra, Albert; Beddel, Darren

1999-01-01

The objectives of the Kennedy Space Center's (KSC) Expendable Launch Vehicles (ELV) Program are to provide safe, reliable, cost effective ELV launches, maximize customer satisfaction, and perform advanced payload processing capability development. Details are given on the ELV program organization, products and services, foreign launch vehicle policy, how to get a NASA launch service, and some of the recent NASA payloads.

Advanced Plant Habitat Test Harvest

NASA Image and Video Library

2017-08-24

John "JC" Carver, a payload integration engineer with NASA Kennedy Space Center's Test and Operations Support Contract, harvests half the Arabidopsis thaliana plants inside the growth chamber of the Advanced Plant Habitat (APH) Flight Unit No. 1. The harvest is part of an ongoing verification test of the APH unit, which is located inside the International Space Station Environmental Simulator in Kennedy's Space Station Processing Facility. The APH undergoing testing at Kennedy is identical to one on the station and uses red, green and broad-spectrum white LED lights to grow plants in an environmentally controlled chamber. The seeds grown during the verification test will be grown on the station to help scientists understand how these plants adapt to spaceflight.

GOES-S Spacecraft Mate to PLA

NASA Image and Video Library

2018-02-05

In a clean room at Astrotech Space Operations in Titusville, Florida, technicians and engineers monitor progress as NOAA's Geostationary Operational Environmental Satellite-S, or GOES-S, is mated to its payload attach fitting. It soon will be moved to Space Launch Complex 41 at Cape Canaveral Air Force Station for mounting atop the Atlas V rocket that will boost the satellite to orbit. GOES-S is the second in a series of four advanced geostationary weather satellites that will significantly improve the detection and observation of environmental phenomena that directly affect public safety, protection of property and the nation's economic health and prosperity. GOES-S is slated to launch March 1, 2018 aboard a United Launch Alliance Atlas V rocket.

GOES-S Encapsulation

NASA Image and Video Library

2018-02-07

In a clean room at Astrotech Space Operations in Titusville, Florida, technicians and engineers monitor progress as NOAA's Geostationary Operational Environmental Satellite-S, or GOES-S, is encapsulated in its payload fairing. It soon will be moved to Space Launch Complex 41 at Cape Canaveral Air Force Station for mounting atop the Atlas V rocket that will boost the satellite to orbit. GOES-S is the second in a series of four advanced geostationary weather satellites that will significantly improve the detection and observation of environmental phenomena that directly affect public safety, protection of property and the nation's economic health and prosperity. GOES-S is slated to launch March 1, 2018 aboard a United Launch Alliance Atlas V rocket.

Commonalities and Differences in Functional Safety Systems Between ISS Payloads and Industrial Applications

NASA Astrophysics Data System (ADS)

Malyshev, Mikhail; Kreimer, Johannes

2013-09-01

Safety analyses for electrical, electronic and/or programmable electronic (E/E/EP) safety-related systems used in payload applications on-board the International Space Station (ISS) are often based on failure modes, effects and criticality analysis (FMECA). For industrial applications of E/E/EP safety-related systems, comparable strategies exist and are defined in the IEC-61508 standard. This standard defines some quantitative criteria based on potential failure modes (for example, Safe Failure Fraction). These criteria can be calculated for an E/E/EP system or components to assess their compliance to requirements of a particular Safety Integrity Level (SIL). The standard defines several SILs depending on how much risk has to be mitigated by a safety-critical system. When a FMECA is available for an ISS payload or its subsystem, it may be possible to calculate the same or similar parameters as defined in the 61508 standard. One example of a payload that has a dedicated functional safety subsystem is the Electromagnetic Levitator (EML). This payload for the ISS is planned to be operated on-board starting 2014. The EML is a high-temperature materials processing facility. The dedicated subsystem "Hazard Control Electronics" (HCE) is implemented to ensure compliance to failure tolerance in limiting samples processing parameters to maintain generation of the potentially toxic by-products to safe limits in line with the requirements applied to the payloads by the ISS Program. The objective of this paper is to assess the implementation of the HCE in the EML against criteria for functional safety systems in the IEC-61508 standard and to evaluate commonalities and differences with respect to safety requirements levied on ISS Payloads. An attempt is made to assess a possibility of using commercially available components and systems certified for compliance to industrial functional safety standards in ISS payloads.

Integrated payload and mission planning, phase 3. Volume 1: Integrated payload and mission planning process evaluation

NASA Technical Reports Server (NTRS)

Sapp, T. P.; Davin, D. E.

1977-01-01

The integrated payload and mission planning process for STS payloads was defined, and discrete tasks which evaluate performance and support initial implementation of this process were conducted. The scope of activity was limited to NASA and NASA-related payload missions only. The integrated payload and mission planning process was defined in detail, including all related interfaces and scheduling requirements. Related to the payload mission planning process, a methodology for assessing early Spacelab mission manager assignment schedules was defined.

Consort 1 sounding rocket flight

NASA Technical Reports Server (NTRS)

Wessling, Francis C.; Maybee, George W.

1989-01-01

This paper describes a payload of six experiments developed for a 7-min microgravity flight aboard a sounding rocket Consort 1, in order to investigate the effects of low gravity on certain material processes. The experiments in question were designed to test the effect of microgravity on the demixing of aqueous polymer two-phase systems, the electrodeposition process, the production of elastomer-modified epoxy resins, the foam formation process and the characteristics of foam, the material dispersion, and metal sintering. The apparatuses designed for these experiments are examined, and the rocket-payload integration and operations are discussed.

Evolutionary space platform concept study. Volume 2, part A: SASP special emphasis trade studies

NASA Technical Reports Server (NTRS)

1982-01-01

Efforts are in progress to define an approach to provide a simple and cost effective solution to the problem of long duration space flight. This approach involves a Space Platform in low Earth orbit, which can be tended by the Space Shuttle and which will provide, for extended periods of time, stability, utilities and access for a variety of replaceable payloads. The feasibility of an evolutionary space system which would cost effectively support unmanned payloads in groups, using a Space Platform which provides centralized basic subsystems is addressed.

Space evaluation of optical modulators for microwave photonic on-board applications

NASA Astrophysics Data System (ADS)

Le Kernec, A.; Sotom, M.; Bénazet, B.; Barbero, J.; Peñate, L.; Maignan, M.; Esquivias, I.; Lopez, F.; Karafolas, N.

2017-11-01

Since several years, perspectives and assets offered by photonic technologies compared with their traditional RF counterparts (mass and volume reduction, transparency to RF frequency, RF isolation), make them particularly attractive for space applications [1] and, in particular, telecommunication satellites [2]. However, the development of photonic payload concepts have concurrently risen and made the problem of the ability of optoelectronic components to withstand space environment more and more pressing. Indeed, photonic components used in such photonic payloads architectures come from terrestrial networks applications in order to benefit from research and development in this field. This paper presents some results obtained in the frame of an ESA-funded project, carried out by Thales Alenia Space France, as prime contractor, and Alter Technology Group Spain (ATG) and Universidad Politecnica de Madrid (UPM), as subcontractors, one objective of which was to assess commercial high frequency optical intensity modulators for space use through a functional and environmental test campaign. Their potential applications in microwave photonic sub-systems of telecom satellite payloads are identified and related requirements are presented. Optical modulator technologies are reviewed and compared through, but not limited to, a specific figure of merit, taking into account two key features of these components : optical insertion loss and RF half-wave voltage. Some conclusions on these different technologies are given, on the basis of the test results, and their suitability for the targeted applications and environment is highlighted.

Payload Operations Support Team Tools

NASA Technical Reports Server (NTRS)

Askew, Bill; Barry, Matthew; Burrows, Gary; Casey, Mike; Charles, Joe; Downing, Nicholas; Jain, Monika; Leopold, Rebecca; Luty, Roger; McDill, David;

Modular Countermine Payload for Small Robots

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

Herman Herman; Doug Few; Roelof Versteeg

2010-04-01

Payloads for small robotic platforms have historically been designed and implemented as platform and task specific solutions. A consequence of this approach is that payloads cannot be deployed on different robotic platforms without substantial re-engineering efforts. To address this issue, we developed a modular countermine payload that is designed from the ground-up to be platform agnostic. The payload consists of the multi-mission payload controller unit (PCU) coupled with the configurable mission specific threat detection, navigation and marking payloads. The multi-mission PCU has all the common electronics to control and interface to all the payloads. It also contains the embedded processormore » that can be used to run the navigational and control software. The PCU has a very flexible robot interface which can be configured to interface to various robot platforms. The threat detection payload consists of a two axis sweeping arm and the detector. The navigation payload consists of several perception sensors that are used for terrain mapping, obstacle detection and navigation. Finally, the marking payload consists of a dual-color paint marking system. Through the multi-mission PCU, all these payloads are packaged in a platform agnostic way to allow deployment on multiple robotic platforms, including Talon and Packbot.« less

Modular countermine payload for small robots

NASA Astrophysics Data System (ADS)

Herman, Herman; Few, Doug; Versteeg, Roelof; Valois, Jean-Sebastien; McMahill, Jeff; Licitra, Michael; Henciak, Edward

2010-04-01

Payloads for small robotic platforms have historically been designed and implemented as platform and task specific solutions. A consequence of this approach is that payloads cannot be deployed on different robotic platforms without substantial re-engineering efforts. To address this issue, we developed a modular countermine payload that is designed from the ground-up to be platform agnostic. The payload consists of the multi-mission payload controller unit (PCU) coupled with the configurable mission specific threat detection, navigation and marking payloads. The multi-mission PCU has all the common electronics to control and interface to all the payloads. It also contains the embedded processor that can be used to run the navigational and control software. The PCU has a very flexible robot interface which can be configured to interface to various robot platforms. The threat detection payload consists of a two axis sweeping arm and the detector. The navigation payload consists of several perception sensors that are used for terrain mapping, obstacle detection and navigation. Finally, the marking payload consists of a dual-color paint marking system. Through the multimission PCU, all these payloads are packaged in a platform agnostic way to allow deployment on multiple robotic platforms, including Talon and Packbot.