Facteurs prédictifs de l’échec de traitement antituberculeux en Guinée Conakry

PubMed Central

Nimagan, Souleymane; Bopaka, Regis Gothard; Diallo, Mamadou Mouctar; Diallo, Boubacar Djelo; Diallo, Mamadou Bailo; Sow, Oumou Younoussa

2015-01-01

La tuberculose est un véritable problème de santé publique. C'est une maladie guérissable et cette guérison passe par une bonne prise en charge thérapeutique. Il arrive parfois on assiste à l’échec thérapeutique, d'où l'intérêt de notre étude portant sur les facteurs prédictifs de ses échecs. Dans l'espace d'une année sur 1300 cas de tuberculose toute forme confondue, 700 cas de tuberculose pulmonaire à microscopie positive ont été répertorié dont 100 cas transférés. La tranche d’âge de 15-25 ans a été la plus touchée avec un sexe-ratio de 2 en faveur des hommes et 41,66% de nos malades ont été les ouvriers suivis de 20,83% des commerçants. La majorité de nos patients provenait de Conakry soit 99, 5%. Sur 600 patients suivis les nouveaux cas représentaient 83,33% et l’échec thérapeutique représentait 12 cas soit 2%. L'interruption du traitement représente le principal facteur de l’échec. Les facteurs qui ont influencé la régularité des malades au traitement ont été multiples. Des facteurs liés à l'organisation du système de santé, la rupture des médicaments antituberculeux, l’éducation sanitaire insuffisante, les contraintes de la supervision du traitement, l'implication insuffisante et la vente des médicaments par le personnel de santé. Des facteurs liés aux patients eux-mêmes, la crainte de perte d'emploi, les contraintes financières. Les renforcements de l'organisation du système sanitaire et l’éducation thérapeutiques pourront réduire le taux d’échec du traitement antituberculeux. L'amélioration de la qualité de la prise en charge des malades en situation d’échec devrait passer par une culture systématique des expectorations avec antibiogramme. PMID:26889327

Evaluating the Performance of the NASA LaRC CMF Motion Base Safety Devices

NASA Technical Reports Server (NTRS)

Gupton, Lawrence E.; Bryant, Richard B., Jr.; Carrelli, David J.

2006-01-01

This paper describes the initial measured performance results of the previously documented NASA Langley Research Center (LaRC) Cockpit Motion Facility (CMF) motion base hardware safety devices. These safety systems are required to prevent excessive accelerations that could injure personnel and damage simulator cockpits or the motion base structure. Excessive accelerations may be caused by erroneous commands or hardware failures driving an actuator to the end of its travel at high velocity, stepping a servo valve, or instantly reversing servo direction. Such commands may result from single order failures of electrical or hydraulic components within the control system itself, or from aggressive or improper cueing commands from the host simulation computer. The safety systems must mitigate these high acceleration events while minimizing the negative performance impacts. The system accomplishes this by controlling the rate of change of valve signals to limit excessive commanded accelerations. It also aids hydraulic cushion performance by limiting valve command authority as the actuator approaches its end of travel. The design takes advantage of inherent motion base hydraulic characteristics to implement all safety features using hardware only solutions.

Lessons Learned from the Crew Health Care System (CHeCS) Rack 1 Environmental Control and Life Support (ECLS) Design

NASA Technical Reports Server (NTRS)

Williams, David E.

2006-01-01

This paper will provide an overview of the International Space Station (ISS) Environmental Control and Life Support (ECLS) design of the Crew Health Care System (CHeCS) Rack 1 and it will document some of the lessons that have been learned to date for the ECLS equipment in this rack.

Only in Canada: A Study of National Market Potential for Christian Higher Education Canada (CHEC) Institutions

ERIC Educational Resources Information Center

Hiebert, Al

2011-01-01

In July 2007 Ipsos Reid delivered to Christian Higher Education Canada (CHEC) a report entitled "Christian Post-Secondary Education in Canada, Phase 3: Defining the Market". This article is a selective summary of the full 353-page report. It tabulates and analyzes findings from 1,000 phone interviews and 6,689 online surveys from six…

Fincke unbolts the front panel of the CHeCS Rack for inspection and cleaning during Expedition 9

NASA Image and Video Library

2004-09-16

ISS009-E-23061 (16 September 2004) --- Astronaut Edward M. (Mike) Fincke, Expedition 9 NASA ISS science officer and flight engineer, uses a drill to unfasten a panel on the CHeCS Rack in the Destiny laboratory of the International Space Station (ISS). Fincke was about to perform an inspection of the Avionics Air Assembly.

Novitskiy participates in a CHeCS medical contingency drill in the U.S. Laboratory

NASA Image and Video Library

2012-11-26

ISS034-E-005260 (26 Nov. 2012) --- Russian cosmonaut Oleg Novitskiy, Expedition 34 flight engineer, participates in a Crew Health Care System (CHeCS) medical contingency drill in the Destiny laboratory of the International Space Station. This drill gives crew members the opportunity to work as a team in resolving a simulated medical emergency onboard the space station.

Shkaplerov participates in a CHeCS Medical Contingency Drill in the U.S. Laboratory

NASA Image and Video Library

2011-12-16

ISS030-E-012600 (16 Dec. 2011) --- Russian cosmonaut Anton Shkaplerov, Expedition 30 flight engineer, participates in a Crew Health Care System (CHeCS) medical contingency drill in the Destiny laboratory of the International Space Station. This drill gives crew members the opportunity to work as a team in resolving a simulated medical emergency onboard the space station.

Novitskiy participates in a CHeCS medical contingency drill in the U.S. Laboratory

NASA Image and Video Library

2012-11-26

ISS034-E-005266 (26 Nov. 2012) --- Russian cosmonaut Oleg Novitskiy, Expedition 34 flight engineer, participates in a Crew Health Care System (CHeCS) medical contingency drill in the Destiny laboratory of the International Space Station. This drill gives crew members the opportunity to work as a team in resolving a simulated medical emergency onboard the space station.

Health Maintenance System (HMS) Hardware Research, Design, and Collaboration

NASA Technical Reports Server (NTRS)

Gonzalez, Stefanie M.

2010-01-01

The Space Life Sciences division (SLSD) concentrates on optimizing a crew member's health. Developments are translated into innovative engineering solutions, research growth, and community awareness. This internship incorporates all those areas by targeting various projects. The main project focuses on integrating clinical and biomedical engineering principles to design, develop, and test new medical kits scheduled for launch in the Spring of 2011. Additionally, items will be tagged with Radio Frequency Interference Devices (RFID) to keep track of the inventory. The tags will then be tested to optimize Radio Frequency feed and feed placement. Research growth will occur with ground based experiments designed to measure calcium encrusted deposits in the International Space Station (ISS). The tests will assess the urine calcium levels with Portable Clinical Blood Analyzer (PCBA) technology. If effective then a model for urine calcium will be developed and expanded to microgravity environments. To support collaboration amongst the subdivisions of SLSD the architecture of the Crew Healthcare Systems (CHeCS) SharePoint site has been redesigned for maximum efficiency. Community collaboration has also been established with the University of Southern California, Dept. of Aeronautical Engineering and the Food and Drug Administration (FDA). Hardware disbursements will transpire within these communities to support planetary surface exploration and to serve as an educational tool demonstrating how ground based medicine influenced the technological development of space hardware.

Space Station requirements for in-flight exercise countermeasures

NASA Technical Reports Server (NTRS)

Hayes, Judith C.; Harris, Bernard A.

1990-01-01

In an effort to retard the deleterious effects of space adaptation, NASA has defined requirements for an Exercise Countermeasure Facility (ECF) within the Space Station Crew Health Care System (CHeCS). The application of exercise as a countermeasure to spaceflight-induced deconditioning has been utilized in the past by both the United States and the Soviet space programs. The ECF will provide exercise hardware, physiological monitoring capabilities, and an interactive motivational display system. ECF operations and data will be coupled through the Space Station Freedom Data Management System for monitoring of inflight training and testing from ground control, thus allowing for real-time evaluation of crewmember performance and modification of exercise prescriptions. Finally, the objective of the ECF is to monitor and control the exercise of crewmembers for the maintenance of an operational level of fitness to ensure mission success.

Ivanishin participates in a CHeCS Medical Contingency Drill in the U.S. Laboratory

NASA Image and Video Library

2011-12-16

ISS030-E-012604 (16 Dec. 2011) --- Russian cosmonauts Anatoly Ivanishin (foreground) and Anton Shkaplerov, both Expedition 30 flight engineers, participate in a Crew Health Care System (CHeCS) medical contingency drill in the Destiny laboratory of the International Space Station. This drill gives crew members the opportunity to work as a team in resolving a simulated medical emergency onboard the space station.

Novitskiy and Tarelkin both participate in a CHeCS medical contingency drill in the U.S. Laboratory

NASA Image and Video Library

2012-11-26

ISS034-E-005261 (26 Nov. 2012) --- Russian cosmonauts Oleg Novitskiy (left) and Evgeny Tarelkin, both Expedition 34 flight engineers, participate in a Crew Health Care System (CHeCS) medical contingency drill in the Destiny laboratory of the International Space Station. This drill gives crew members the opportunity to work as a team in resolving a simulated medical emergency onboard the space station.

Space Station Environmental Health System water quality monitoring

NASA Technical Reports Server (NTRS)

Vincze, Johanna E.; Sauer, Richard L.

1990-01-01

One of the unique aspects of the Space Station is that it will be a totally encapsulated environment and the air and water supplies will be reclaimed for reuse. The Environmental Health System, a subsystem of CHeCS (Crew Health Care System), must monitor the air and water on board the Space Station Freedom to verify that the quality is adequate for crew safety. Specifically, the Water Quality Subsystem will analyze the potable and hygiene water supplies regularly for organic, inorganic, particulate, and microbial contamination. The equipment selected to perform these analyses will be commercially available instruments which will be converted for use on board the Space Station Freedom. Therefore, the commercial hardware will be analyzed to identify the gravity dependent functions and modified to eliminate them. The selection, analysis, and conversion of the off-the-shelf equipment for monitoring the Space Station reclaimed water creates a challenging project for the Water Quality engineers and scientists.

Hardware Evolution of Control Electronics

NASA Technical Reports Server (NTRS)

Gwaltney, David; Steincamp, Jim; Corder, Eric; King, Ken; Ferguson, M. I.; Dutton, Ken

2003-01-01

The evolution of closed-loop motor speed controllers implemented on the JPL FPTA2 is presented. The response of evolved controller to sinusoidal commands, controller reconfiguration for fault tolerance,and hardware evolution are described.

Mission Management Computer and Sequencing Hardware for RLV-TD HEX-01 Mission

NASA Astrophysics Data System (ADS)

Gupta, Sukrat; Raj, Remya; Mathew, Asha Mary; Koshy, Anna Priya; Paramasivam, R.; Mookiah, T.

2017-12-01

Reusable Launch Vehicle-Technology Demonstrator Hypersonic Experiment (RLV-TD HEX-01) mission posed some unique challenges in the design and development of avionics hardware. This work presents the details of mission critical avionics hardware mainly Mission Management Computer (MMC) and sequencing hardware. The Navigation, Guidance and Control (NGC) chain for RLV-TD is dual redundant with cross-strapped Remote Terminals (RTs) interfaced through MIL-STD-1553B bus. MMC is Bus Controller on the 1553 bus, which does the function of GPS aided navigation, guidance, digital autopilot and sequencing for the RLV-TD launch vehicle in different periodicities (10, 20, 500 ms). Digital autopilot execution in MMC with a periodicity of 10 ms (in ascent phase) is introduced for the first time and successfully demonstrated in the flight. MMC is built around Intel i960 processor and has inbuilt fault tolerance features like ECC for memories. Fault Detection and Isolation schemes are implemented to isolate the failed MMC. The sequencing hardware comprises Stage Processing System (SPS) and Command Execution Module (CEM). SPS is `RT' on the 1553 bus which receives the sequencing and control related commands from MMCs and posts to downstream modules after proper error handling for final execution. SPS is designed as a high reliability system by incorporating various fault tolerance and fault detection features. CEM is a relay based module for sequence command execution.

Expedition 21 Commander De Winne poses for a photo with a MSL FLSS

NASA Image and Video Library

2009-10-14

ISS021-E-018952 (14 Oct. 2009) --- European Space Agency astronaut Frank De Winne, Expedition 21 commander, is pictured with Materials Science Laboratory (MSL) hardware in the Kibo laboratory of the International Space Station.

Architecture for Control of the K9 Rover

NASA Technical Reports Server (NTRS)

Bresina, John L.; Bualat, maria; Fair, Michael; Wright, Anne; Washington, Richard

2006-01-01

Software featuring a multilevel architecture is used to control the hardware on the K9 Rover, which is a mobile robot used in research on robots for scientific exploration and autonomous operation in general. The software consists of five types of modules: Device Drivers - These modules, at the lowest level of the architecture, directly control motors, cameras, data buses, and other hardware devices. Resource Managers - Each of these modules controls several device drivers. Resource managers can be commanded by either a remote operator or the pilot or conditional-executive modules described below. Behaviors and Data Processors - These modules perform computations for such functions as planning paths, avoiding obstacles, visual tracking, and stereoscopy. These modules can be commanded only by the pilot. Pilot - The pilot receives a possibly complex command from the remote operator or the conditional executive, then decomposes the command into (1) more-specific commands to the resource managers and (2) requests for information from the behaviors and data processors. Conditional Executive - This highest-level module interprets a command plan sent by the remote operator, determines whether resources required for execution of the plan are available, monitors execution, and, if necessary, selects an alternate branch of the plan.

Apollo experience report: Battery subsystem

NASA Technical Reports Server (NTRS)

Trout, J. B.

1972-01-01

Experience with the Apollo command service module and lunar module batteries is discussed. Significant hardware development concepts and hardware test results are summarized, and the operational performance of batteries on the Apollo 7 to 13 missions is discussed in terms of performance data, mission constraints, and basic hardware design and capability. Also, the flight performance of the Apollo battery charger is discussed. Inflight data are presented.

Robotics control using isolated word recognition of voice input

NASA Technical Reports Server (NTRS)

Weiner, J. M.

1977-01-01

A speech input/output system is presented that can be used to communicate with a task oriented system. Human speech commands and synthesized voice output extend conventional information exchange capabilities between man and machine by utilizing audio input and output channels. The speech input facility is comprised of a hardware feature extractor and a microprocessor implemented isolated word or phrase recognition system. The recognizer offers a medium sized (100 commands), syntactically constrained vocabulary, and exhibits close to real time performance. The major portion of the recognition processing required is accomplished through software, minimizing the complexity of the hardware feature extractor.

Autonomous Visual Tracking of Stationary Targets Using Small Unmanned Aerial Vehicles

DTIC Science & Technology

2004-06-01

59 Figure 43. Commanded and Actual Yaw Rates during Simulation ..................................60 Figure 44. Setup for Hardware In Loop Simulation...System with AVDS Figure 44. Setup for Hardware In Loop Simulation with AVDS and PerceptiVU 2. Test Conditions Simulations were conducted for the

Accouchements sur utérus cicatriciel en République Démocratique du Congo: épreuve utérine et facteurs déterminants de l’issue

PubMed Central

Momat, Félix Kitenge wa; Zalagile, Pierre Akilimali; Mukalenge, Faustin Chenge; Luboya, Oscar Numbi; Kalala, Cléophas Tshibangu; Mashinda, Désiré; Grangé, Gilles; Mukuku, Olivier; Kaj, Fanny Malonga; Lubamba, Chamy Cham; Bwama, Joseph Bagambe; Mukoko, Célestin Kayembe; Kakoma, Jean Baptiste; Kalungwe, Justin Kizonde

2017-01-01

Introduction L'objectif était d'identifier les principaux facteurs de risque associés à un échec d'épreuve utérine et définir un score prédictif d'accouchement sur utérus cicatriciel en République Démocratique du Congo. Méthodes Étude multicentrique, transversale et analytique des patientes porteuses d'un utérus cicatriciel sur la période du 1er janvier au 31 décembre 2013 dans quatre maternités de la République Démocratique du Congo (RDC). Un modèle de régression logistique a été construit pour identifier les facteurs associés à l'échec de l'épreuve utérine. De ce modèle, un score prédictif a été construit pour prédire l'échec de l'épreuve utérine dans les maternités de la RDC. La courbe ROC a été utilisée pour évaluer la capacité du score construit à identifier les patientes à risque de connaitre un échec de l'épreuve utérine. Le cut off point du score prédictif a été déterminé en fonction de la sensibilité et spécificité optimale via l'index de Youden. Tous les tests ont été réalisés au seuil de signification α=0,05. Résultats Deux types de facteurs explicatifs de l'échec de l'épreuve utérine ont été retenus. Il s'agit d'un facteur sociodémographique (âge maternel) et de trois facteurs obstétricaux (hauteur utérine, présentation du fœtus et rupture prématurée des membranes). Le score de prédiction a été défini pour prédire l'échec de l'épreuve utérine. La construction de ce score s'est basée sur quatre éléments : l'âge maternel, l'état de la poche des eaux à l'admission, la hauteur utérine et la présentation fœtale. Le score minimal est de 4 et le score maximal est de 16. Le seuil est de 7. Un Score total supérieur ou égal à 7 traduit un risque d'échec de l'épreuve utérine. Conclusion L'utilisation de ce score prédictif chez les patientes pourra améliorer la qualité dans les indications de la voie haute, l'augmentation des taux de césariennes prophylactiques ainsi que la meilleure sélection des patientes soumises à l'épreuve utérine. Ceci pourra également contribuer à la réduction de la morbi-mortalité fœto-maternelle liée à la gestion de l'accouchement sur utérus cicatriciels. PMID:28819492

A natural command language for C/3/I applications

NASA Astrophysics Data System (ADS)

Mergler, J. P.

1980-03-01

The article discusses the development of a natural command language and a control and analysis console designed to simplify the task of the operator in field of Command, Control, Communications, and Intelligence. The console is based on a DEC LSI-11 microcomputer, supported by 16-K words of memory and a serial interface component. Discussion covers the language, which utilizes English and a natural syntax, and how it is integrated with the hardware. It is concluded that results have demonstrated the effectiveness of this natural command language.

Aircrew Training Devices: Utility and Utilization of Advanced Instructional Features (Phase II-Air Training Command, Military Airlift Command, and Strategic Air Command [and] Phase III-Electronic Warfare Trainers).

ERIC Educational Resources Information Center

Polzella, Donald J.; Hubbard, David C.

This document consists of an interim report and a final report which describe the second and third phases of a project designed to determine the utility and utilization of sophisticated hardware and software capabilities known as advanced instructional features (AIFs). Used with an aircrew training device (ATD), AIFs permit a simulator instructor…

Wheel slide protection control using a command map and Smith predictor for the pneumatic brake system of a railway vehicle

NASA Astrophysics Data System (ADS)

Lee, Nam-Jin; Kang, Chul-Goo

2016-10-01

In railway vehicles, excessive sliding or wheel locking can occur while braking because of a temporarily degraded adhesion between the wheel and the rail caused by the contaminated or wet surface of the rail. It can damage the wheel tread and affect the performance of the brake system and the safety of the railway vehicle. To safeguard the wheelset from these phenomena, almost all railway vehicles are equipped with wheel slide protection (WSP) systems. In this study, a new WSP algorithm is proposed. The features of the proposed algorithm are the use of the target sliding speed, the determination of a command for WSP valves using command maps, and compensation for the time delay in pneumatic brake systems using the Smith predictor. The proposed WSP algorithm was verified using experiments with a hardware-in-the-loop simulation system including the hardware of the pneumatic brake system.

Langley Storage facility which houses remains of Apollo 204 craft

NASA Technical Reports Server (NTRS)

1990-01-01

The Apollo 204 command module is seen in storage at Langley Research Center in Virginia. The command module, damaged in the 1967 Apollo fire, its heat shield, booster protective cover and 81 cartons of related hardware and investigative data occupy 3,300 cubic feet of Langley's storage space. Astronauts Virgil I. Grissom, Roger B. Chaffee and Edward H. White II perished in the Apollo 204 spacecraft fire on Jan. 27, 1967 on Launch Complex 34, Cape Canaveral. The hardware has been stored at Langley since 1967. PLEASE NOTE UPDATE: In early May of 1990, NASA announced plans to move the hardware and related data to permanent storage at the site of all the Challenger debris in an abandoned missile silo at Cape Canaveral Air Force Station (CCAFS), Florida. However, at month's end, NASA announced it had decided to keep the capsule at Langley for an indefinite period of time.

Langley Storage facility which houses remains of Apollo 204 craft

NASA Technical Reports Server (NTRS)

1990-01-01

The Apollo 204 command module is seen in storage at Langley Research Center in Virginia. The command module, damaged in the 1967 Apollo fire, its heat shield, booster protective cover and 81 cartons of related hardware and investigative data occupy 3,300 cubic feet of warehouse storage space. Astronauts Virgil I. Grissom, Roger B. Chaffee and Edward H. White II perished in the Apollo 204 spacecraft fire on Jan. 27, 1967 on Launch Complex 34 at Cape Canaveral. The hardware has been stored at Langley since 1967. PLEASE NOTE UPDATE: In early May of 1990, NASA announced plans to move the hardware and related data to permanent storage with the Challenger debris in an abandoned missile silo at Cape Canaveral Air Force Station (CCAFS), Florida. However, at month's end, NASA announced it had decided to keep the capsule at Langley for an indefinite period of time.

Apollo experience report: Command and service module sequential events control subsystem

NASA Technical Reports Server (NTRS)

Johnson, G. W.

1975-01-01

The Apollo command and service module sequential events control subsystem is described, with particular emphasis on the major systems and component problems and solutions. The subsystem requirements, design, and development and the test and flight history of the hardware are discussed. Recommendations to avoid similar problems on future programs are outlined.

Apollo Experience Report: Command and Service Module Reaction Control Systems

NASA Technical Reports Server (NTRS)

Taeuber, Ralph J.; Weary, Dwayne P.

1973-01-01

The reaction control systems of the Apollo command and service module were developed and modified between July 1961 and July 1969. The successful development of these systems, as part of the Apollo Program, was the result of extensive testing, retesting, and modifications of the hardware to ensure system capability and intrasystem compatibility.

Development of display design and command usage guidelines for Spacelab experiment computer applications

NASA Technical Reports Server (NTRS)

Dodson, D. W.; Shields, N. L., Jr.

1979-01-01

Individual Spacelab experiments are responsible for developing their CRT display formats and interactive command scenarios for payload crew monitoring and control of experiment operations via the Spacelab Data Display System (DDS). In order to enhance crew training and flight operations, it was important to establish some standardization of the crew/experiment interface among different experiments by providing standard methods and techniques for data presentation and experiment commanding via the DDS. In order to establish optimum usage guidelines for the Spacelab DDS, the capabilities and limitations of the hardware and Experiment Computer Operating System design had to be considered. Since the operating system software and hardware design had already been established, the Display and Command Usage Guidelines were constrained to the capabilities of the existing system design. Empirical evaluations were conducted on a DDS simulator to determine optimum operator/system interface utilization of the system capabilities. Display parameters such as information location, display density, data organization, status presentation and dynamic update effects were evaluated in terms of response times and error rates.

Automated Sequence Processor: Something Old, Something New

NASA Technical Reports Server (NTRS)

Streiffert, Barbara; Schrock, Mitchell; Fisher, Forest; Himes, Terry

2012-01-01

High productivity required for operations teams to meet schedules Risk must be minimized. Scripting used to automate processes. Scripts perform essential operations functions. Automated Sequence Processor (ASP) was a grass-roots task built to automate the command uplink process System engineering task for ASP revitalization organized. ASP is a set of approximately 200 scripts written in Perl, C Shell, AWK and other scripting languages.. ASP processes/checks/packages non-interactive commands automatically.. Non-interactive commands are guaranteed to be safe and have been checked by hardware or software simulators.. ASP checks that commands are non-interactive.. ASP processes the commands through a command. simulator and then packages them if there are no errors.. ASP must be active 24 hours/day, 7 days/week..

MicroShell Minimalist Shell for Xilinx Microprocessors

NASA Technical Reports Server (NTRS)

Werne, Thomas A.

2011-01-01

MicroShell is a lightweight shell environment for engineers and software developers working with embedded microprocessors in Xilinx FPGAs. (MicroShell has also been successfully ported to run on ARM Cortex-M1 microprocessors in Actel ProASIC3 FPGAs, but without project-integration support.) Micro Shell decreases the time spent performing initial tests of field-programmable gate array (FPGA) designs, simplifies running customizable one-time-only experiments, and provides a familiar-feeling command-line interface. The program comes with a collection of useful functions and enables the designer to add an unlimited number of custom commands, which are callable from the command-line. The commands are parameterizable (using the C-based command-line parameter idiom), so the designer can use one function to exercise hardware with different values. Also, since many hardware peripherals instantiated in FPGAs have reasonably simple register-mapped I/O interfaces, the engineer can edit and view hardware parameter settings at any time without stopping the processor. MicroShell comes with a set of support scripts that interface seamlessly with Xilinx's EDK tool. Adding an instance of MicroShell to a project is as simple as marking a check box in a library configuration dialog box and specifying a software project directory. The support scripts then examine the hardware design, build design-specific functions, conditionally include processor-specific functions, and complete the compilation process. For code-size constrained designs, most of the stock functionality can be excluded from the compiled library. When all of the configurable options are removed from the binary, MicroShell has an unoptimized memory footprint of about 4.8 kB and a size-optimized footprint of about 2.3 kB. Since MicroShell allows unfettered access to all processor-accessible memory locations, it is possible to perform live patching on a running system. This can be useful, for instance, if a bug is discovered in a routine but the system cannot be rebooted: Shell allows a skilled operator to directly edit the binary executable in memory. With some forethought, MicroShell code can be located in a different memory location from custom code, permitting the custom functionality to be overwritten at any time without stopping the controlling shell.

Human factors in the Naval Air Systems Command: Computer based training

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

Seamster, T.L.; Snyder, C.E.; Terranova, M.

1988-01-01

Military standards applied to the private sector contracts have a substantial effect on the quality of Computer Based Training (CBT) systems procured for the Naval Air Systems Command. This study evaluated standards regulating the following areas in CBT development and procurement: interactive training systems, cognitive task analysis, and CBT hardware. The objective was to develop some high-level recommendations for evolving standards that will govern the next generation of CBT systems. One of the key recommendations is that there be an integration of the instructional systems development, the human factors engineering, and the software development standards. Recommendations were also made formore » task analysis and CBT hardware standards. (9 refs., 3 figs.)« less

Network command processing system overview

NASA Technical Reports Server (NTRS)

Nam, Yon-Woo; Murphy, Lisa D.

1993-01-01

The Network Command Processing System (NCPS) developed for the National Aeronautics and Space Administration (NASA) Ground Network (GN) stations is a spacecraft command system utilizing a MULTIBUS I/68030 microprocessor. This system was developed and implemented at ground stations worldwide to provide a Project Operations Control Center (POCC) with command capability for support of spacecraft operations such as the LANDSAT, Shuttle, Tracking and Data Relay Satellite, and Nimbus-7. The NCPS consolidates multiple modulation schemes for supporting various manned/unmanned orbital platforms. The NCPS interacts with the POCC and a local operator to process configuration requests, generate modulated uplink sequences, and inform users of the ground command link status. This paper presents the system functional description, hardware description, and the software design.

Movable Ground Based Recovery System for Reuseable Space Flight Hardware

NASA Technical Reports Server (NTRS)

Sarver, George L. (Inventor)

2013-01-01

A reusable space flight launch system is configured to eliminate complex descent and landing systems from the space flight hardware and move them to maneuverable ground based systems. Precision landing of the reusable space flight hardware is enabled using a simple, light weight aerodynamic device on board the flight hardware such as a parachute, and one or more translating ground based vehicles such as a hovercraft that include active speed, orientation and directional control. The ground based vehicle maneuvers itself into position beneath the descending flight hardware, matching its speed and direction and captures the flight hardware. The ground based vehicle will contain propulsion, command and GN&C functionality as well as space flight hardware landing cushioning and retaining hardware. The ground based vehicle propulsion system enables longitudinal and transverse maneuverability independent of its physical heading.

PromISS 4 hardware set up in the MSG during Expedition 12

NASA Image and Video Library

2006-01-18

ISS012-E-16184 (18 Jan. 2006) --- Astronaut William S. (Bill) McArthur, Jr., Expedition 12 commander and NASA space station science officer, sets up the Protein Crystal Growth Monitoring by Digital Holographic Microscope (PromISS) experiment hardware inside the Microgravity Science Glovebox (MSG) facility in the Destiny laboratory on the International Space Station.

Lower Total Cost of Ownership of ONE-NET by Using Thin-Client Desktop Deployment and Virtualization-Based Server Technology

DTIC Science & Technology

2010-09-01

NNWC) was used to calculate major cost components—labor, hardware, software , and transport, while a VMware tool was used to calculate power and...cooling costs for both solutions. In addition, VMware provided a cost estimate for the upfront hardware and software licensing costs needed to support...cost per seat (CPS) model developed by Naval Network Warfare Command (NNWC) was used to calculate major cost components—labor, hardware, software , and

Steamer II: Steamer prototype component inventory and user interface commands. Technical report, 1988-1989

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

Dickieson, J.L.; Thode, W.F.; Newbury, K.

1988-12-01

Over the last several years, Navy Personnel Research and Development has produced a prototype simulation of a 1200-psi steam plant. This simulation, called Steamer, is installed on an expensive Symbolics minicomputer at the Surface Warfare Officers School, Pacific Coronado, California. The fundamental research goal of the Steamer prototype system was to evaluate the potential of, what was then, new artificial intelligence (AI) hardware and software technology for supporting the construction of computer-based training systems using graphic representations of complex, dynamic systems. The area of propulsion engineering was chosen for a number of reasons. This document describes the Steamer prototype systemmore » components and user interface commands and establishes a starting point for designing, developing, and implementing Steamer II. Careful examination of the actual program code produced an inventory that describes the hardware, system software, application software, and documentation for the Steamer prototype system. Exercising all menu options systematically produced an inventory of all Steamer prototype user interface commands.« less

Using FastX on the Peregrine System | High-Performance Computing | NREL

Science.gov Websites

with full 3D hardware acceleration. The traditional method of displaying graphics applications to a remote X server (indirect rendering) supports 3D hardware acceleration, but this approach causes all of the OpenGL commands and 3D data to be sent over the network to be rendered on the client machine. With

Virtual Frame Buffer Interface Program

NASA Technical Reports Server (NTRS)

Wolfe, Thomas L.

1990-01-01

Virtual Frame Buffer Interface program makes all frame buffers appear as generic frame buffer with specified set of characteristics, allowing programmers to write codes that run unmodified on all supported hardware. Converts generic commands to actual device commands. Consists of definition of capabilities and FORTRAN subroutines called by application programs. Developed in FORTRAN 77 for DEC VAX 11/780 or DEC VAX 11/750 computer under VMS 4.X.

Installing the new PCE (Proximity Communications Equipment) hardware

NASA Image and Video Library

2005-06-29

ISS011-E-09799 (27 June 2005) --- Cosmonaut Sergei K. Krikalev, Expedition 11 commander representing Russia's Federal Space Agency, works with the new Proximity Communications Equipment (PCE) hardware of the ASN-M satellite navigation system for the European Automated Transfer Vehicle (ATV) “Jules Verne” in the Zvezda Service Module of the International Space Station. The ATV is scheduled to arrive at the Station next year.

MSRR-1 Commissioning

NASA Image and Video Library

2009-11-02

ISS021-E-018978 (2 Nov. 2009) --- European Space Agency astronaut Frank De Winne, Expedition 21 commander, works with Materials Science Laboratory (MSL) hardware in the Destiny laboratory of the International Space Station.

Guidance system operations plan for manned CM earth orbital missions using program Skylark 1. Section 2: Data links

NASA Technical Reports Server (NTRS)

Hamilton, M. H.

1972-01-01

A computer program to define the digital uplink and downlink for use in manned command module orbital missions is presented. The subjects discussed are: (1) digital uplink to command module, (2) CMC digital downlink, (3) downlist formats, (4) description of telemetered qualities, (5) flagbits, and (6) effects of Fresh Start (V36) and Hardware Restart on flagword and channel bits.

Testing the newly installed PCE (Proximity Communications Equipment) hardware

NASA Image and Video Library

2005-06-29

ISS011-E-09816 (28 June 2005) --- Cosmonaut Sergei K. Krikalev, Expedition 11 commander representing Russia's Federal Space Agency, tests the newly installed Proximity Communications Equipment (PCE) hardware of the ASN-M satellite navigation system for the European Automated Transfer Vehicle (ATV) “Jules Verne” in the Zvezda Service Module of the International Space Station. The ATV is scheduled to arrive at the Station next year.

Testing the newly installed PCE (Proximity Communications Equipment) hardware

NASA Image and Video Library

2005-06-28

ISS011-E-09812 (28 June 2005) --- Cosmonaut Sergei K. Krikalev, Expedition 11 commander representing Russia's Federal Space Agency, tests the newly installed Proximity Communications Equipment (PCE) hardware of the ASN-M satellite navigation system for the European Automated Transfer Vehicle (ATV) “Jules Verne” in the Zvezda Service Module of the international space station. The ATV is scheduled to arrive at the station next year.

Burbank works at the MSG

NASA Image and Video Library

2012-01-10

ISS030-E-030125 (10 Jan. 2012) --- NASA astronaut Dan Burbank, Expedition 30 commander, works on the Selectable Optical Diagnostics Instrument C Colloid (SODI-COLLOID) hardware in the Microgravity Science Glovebox in the International Space Station?s Destiny laboratory. Burbank is supporting ground-commanded operations by exchanging out some disks. COLLOID is part of ESA?s triple experiment series for advancement in liquids, diffusion measurements in petroleum reservoirs and the study on growth and properties of advanced photonic materials within colloidal solutions. The commander is currently joined by five other Expedition 30 astronauts and cosmonauts, all flight engineers, aboard the orbital outpost.

Centralized Planning for Multiple Exploratory Robots

NASA Technical Reports Server (NTRS)

Estlin, Tara; Rabideau, Gregg; Chien, Steve; Barrett, Anthony

2005-01-01

A computer program automatically generates plans for a group of robotic vehicles (rovers) engaged in geological exploration of terrain. The program rapidly generates multiple command sequences that can be executed simultaneously by the rovers. Starting from a set of high-level goals, the program creates a sequence of commands for each rover while respecting hardware constraints and limitations on resources of each rover and of hardware (e.g., a radio communication terminal) shared by all the rovers. First, a separate model of each rover is loaded into a centralized planning subprogram. The centralized planning software uses the models of the rovers plus an iterative repair algorithm to resolve conflicts posed by demands for resources and by constraints associated with the all the rovers and the shared hardware. During repair, heuristics are used to make planning decisions that will result in solutions that will be better and will be found faster than would otherwise be possible. In particular, techniques from prior solutions of the multiple-traveling- salesmen problem are used as heuristics to generate plans in which the paths taken by the rovers to assigned scientific targets are shorter than they would otherwise be.

An automatic speech recognition system with speaker-independent identification support

NASA Astrophysics Data System (ADS)

Caranica, Alexandru; Burileanu, Corneliu

2015-02-01

The novelty of this work relies on the application of an open source research software toolkit (CMU Sphinx) to train, build and evaluate a speech recognition system, with speaker-independent support, for voice-controlled hardware applications. Moreover, we propose to use the trained acoustic model to successfully decode offline voice commands on embedded hardware, such as an ARMv6 low-cost SoC, Raspberry PI. This type of single-board computer, mainly used for educational and research activities, can serve as a proof-of-concept software and hardware stack for low cost voice automation systems.

Mir 22 and STS-81 crew work with gyrodyne

NASA Image and Video Library

1997-02-04

STS081-301-031 (12-22 Jan 1997) --- Shortly after docking of the Space Shuttle Atlantis and Russia's Mir Space Station, crew members from the respective spacecraft begin to transfer hardware from the Spacehab Double Module (DM) onto the Mir complex. Here, cosmonaut Valeri G. Korzun, Mir-22 commander, along with astronauts Michael A. Baker, commander, and Brent W. Jett, Jr., pilot, unstow a gyrodyne, device for attitude control, transfer to Mir.

Balloon-Supported Loran Antenna, New Hardware for Tethered Balloons, and Payloads Used in BAMM Flights.

DTIC Science & Technology

1980-02-28

containing a command receiver, batteries, and a differential- pressure switch , all located immediately below the confluence point, with long leads and a...should break free, or during normal deflation at take- down. Purpose of the differential- pressure switch was to momentarily open the valves if the...otherwise was completely different. A differential- pressure switch of the type formerly used in the command package, but without the long pressure

Yurchikhin with Cryogem-03 hardware in Zvezda

NASA Image and Video Library

2007-04-01

ISS014-E-19148 (April 2007) --- Cosmonaut Fyodor N. Yurchikhin, Expedition 15 commander representing Russia's Federal Space Agency, works with a Cryogem-03 refrigerator in the Zvezda Service Module of the International Space Station.

CDR Frank De Winne during MSRR Commissioning Activities

NASA Image and Video Library

2009-10-14

ISS021-E-006202 (14 Oct. 2009) --- European Space Agency astronaut Frank De Winne, Expedition 21 commander, works with Materials Science Laboratory (MSL) hardware in the Destiny laboratory of the International Space Station.

CDR Frank De Winne during MSRR Commissioning Activities

NASA Image and Video Library

2009-10-14

ISS021-E-006219 (14 Oct. 2009) --- European Space Agency astronaut Frank De Winne, Expedition 21 commander, works with Materials Science Laboratory (MSL) hardware in the Destiny laboratory of the International Space Station.

CDR Frank De Winne during MSRR Commissioning Activities

NASA Image and Video Library

2009-10-14

ISS021-E-006209 (14 Oct. 2009) --- European Space Agency astronaut Frank De Winne, Expedition 21 commander, works with Materials Science Laboratory (MSL) hardware in the Destiny laboratory of the International Space Station.

CDR Frank De Winne during MSRR Commissioning Activities

NASA Image and Video Library

2009-10-14

ISS021-E-006180 (14 Oct. 2009) --- European Space Agency astronaut Frank De Winne, Expedition 21 commander, works with Materials Science Laboratory (MSL) hardware in the Destiny laboratory of the International Space Station.

CDR Frank De Winne during MSRR Commissioning Activities

NASA Image and Video Library

2009-10-14

ISS021-E-006196 (14 Oct. 2009) --- European Space Agency astronaut Frank De Winne, Expedition 21 commander, works with Materials Science Laboratory (MSL) hardware in the Destiny laboratory of the International Space Station.

Lunar Reconnaissance Orbiter (LRO) Command and Data Handling Flight Electronics Subsystem

NASA Technical Reports Server (NTRS)

Nguyen, Quang; Yuknis, William; Haghani, Noosha; Pursley, Scott; Haddad, Omar

2012-01-01

A document describes a high-performance, modular, and state-of-the-art Command and Data Handling (C&DH) system developed for use on the Lunar Reconnaissance Orbiter (LRO) mission. This system implements a complete hardware C&DH subsystem in a single chassis enclosure that includes a processor card, 48 Gbytes of solid-state recorder memory, data buses including MIL-STD-1553B, custom RS-422, SpaceWire, analog collection, switched power services, and interfaces to the Ka-Band and S-Band RF communications systems. The C&DH team capitalized on extensive experience with hardware and software with PCI bus design, SpaceWire networking, Actel FPGA design, digital flight design techniques, and the use of VxWorks for the real-time operating system. The resulting hardware architecture was implemented to meet the LRO mission requirements. The C&DH comprises an enclosure, a backplane, a low-voltage power converter, a single-board computer, a communications interface board, four data storage boards, a housekeeping and digital input/output board, and an analog data acquisition board. The interfaces between the C&DH and the instruments and avionics are connected through a SpaceWire network, a MIL-STD-1553 bus, and a combination of synchronous and asynchronous serial data transfers over RS-422 and LVDS (low-voltage differential-signaling) electrical interfaces. The C&DH acts as the spacecraft data system with an instrument data manager providing all software and internal bus scheduling, ingestion of science data, distribution of commands, and performing science operations in real time.

Occupational variation in incidence of bladder cancer: a comparison of population-representative cohorts from Nordic countries and Canada.

PubMed

Hadkhale, Kishor; MacLeod, Jill; Demers, Paul A; Martinsen, Jan Ivar; Weiderpass, Elisabete; Kjaerheim, Kristina; Lynge, Elsebeth; Sparen, Pär; Tryggvadottir, Laufey; Anne Harris, M; Tjepkema, Michael; Peters, Paul A; Pukkala, Eero

2017-08-04

The objective of this study was to compare occupational variation of the risk of bladder cancer in the Nordic countries and Canada. In the Nordic Occupational Cancer study (NOCCA), 73 653 bladder cancer cases were observed during follow-up of 141.6 million person-years. In the Canadian Census Health and Environment Cohort (CanCHEC), 8170 cases were observed during the follow-up of 36.7 million person-years. Standardised incidence ratios with 95% CI were estimated for 53 occupations in the NOCCA cohort and HR with 95% CIs were estimated for 42 occupations in the CanCHEC. Elevated risks of bladder cancer were observed among hairdressers, printers, sales workers, plumbers, painters, miners and laundry workers. Teachers and agricultural workers had reduced risk of bladder cancer in both cohorts. Chimney-sweeps, tobacco workers and waiters had about 1.5-fold risk in the Nordic countries; no risk estimates for these categories were given from the CanCHEC cohort. We observed different occupational patterns in risk of bladder cancer in Nordic countries and Canada. The only occupation with similarly increased risk was observed among sales workers. Differences in smoking across occupational groups may explain some, but not all, of this variation. © Article author(s) (or their employer(s) unless otherwise stated in the text of the article) 2017. All rights reserved. No commercial use is permitted unless otherwise expressly granted.

Hybrid Brain-Computer Interface Techniques for Improved Classification Accuracy and Increased Number of Commands: A Review.

PubMed

Hong, Keum-Shik; Khan, Muhammad Jawad

2017-01-01

In this article, non-invasive hybrid brain-computer interface (hBCI) technologies for improving classification accuracy and increasing the number of commands are reviewed. Hybridization combining more than two modalities is a new trend in brain imaging and prosthesis control. Electroencephalography (EEG), due to its easy use and fast temporal resolution, is most widely utilized in combination with other brain/non-brain signal acquisition modalities, for instance, functional near infrared spectroscopy (fNIRS), electromyography (EMG), electrooculography (EOG), and eye tracker. Three main purposes of hybridization are to increase the number of control commands, improve classification accuracy and reduce the signal detection time. Currently, such combinations of EEG + fNIRS and EEG + EOG are most commonly employed. Four principal components (i.e., hardware, paradigm, classifiers, and features) relevant to accuracy improvement are discussed. In the case of brain signals, motor imagination/movement tasks are combined with cognitive tasks to increase active brain-computer interface (BCI) accuracy. Active and reactive tasks sometimes are combined: motor imagination with steady-state evoked visual potentials (SSVEP) and motor imagination with P300. In the case of reactive tasks, SSVEP is most widely combined with P300 to increase the number of commands. Passive BCIs, however, are rare. After discussing the hardware and strategies involved in the development of hBCI, the second part examines the approaches used to increase the number of control commands and to enhance classification accuracy. The future prospects and the extension of hBCI in real-time applications for daily life scenarios are provided.

Hybrid Brain–Computer Interface Techniques for Improved Classification Accuracy and Increased Number of Commands: A Review

PubMed Central

Hong, Keum-Shik; Khan, Muhammad Jawad

2017-01-01

In this article, non-invasive hybrid brain–computer interface (hBCI) technologies for improving classification accuracy and increasing the number of commands are reviewed. Hybridization combining more than two modalities is a new trend in brain imaging and prosthesis control. Electroencephalography (EEG), due to its easy use and fast temporal resolution, is most widely utilized in combination with other brain/non-brain signal acquisition modalities, for instance, functional near infrared spectroscopy (fNIRS), electromyography (EMG), electrooculography (EOG), and eye tracker. Three main purposes of hybridization are to increase the number of control commands, improve classification accuracy and reduce the signal detection time. Currently, such combinations of EEG + fNIRS and EEG + EOG are most commonly employed. Four principal components (i.e., hardware, paradigm, classifiers, and features) relevant to accuracy improvement are discussed. In the case of brain signals, motor imagination/movement tasks are combined with cognitive tasks to increase active brain–computer interface (BCI) accuracy. Active and reactive tasks sometimes are combined: motor imagination with steady-state evoked visual potentials (SSVEP) and motor imagination with P300. In the case of reactive tasks, SSVEP is most widely combined with P300 to increase the number of commands. Passive BCIs, however, are rare. After discussing the hardware and strategies involved in the development of hBCI, the second part examines the approaches used to increase the number of control commands and to enhance classification accuracy. The future prospects and the extension of hBCI in real-time applications for daily life scenarios are provided. PMID:28790910

Laboratory process control using natural language commands from a personal computer

NASA Technical Reports Server (NTRS)

Will, Herbert A.; Mackin, Michael A.

1989-01-01

PC software is described which provides flexible natural language process control capability with an IBM PC or compatible machine. Hardware requirements include the PC, and suitable hardware interfaces to all controlled devices. Software required includes the Microsoft Disk Operating System (MS-DOS) operating system, a PC-based FORTRAN-77 compiler, and user-written device drivers. Instructions for use of the software are given as well as a description of an application of the system.

Scavenge/remove an AAA (Avionics Air Assembly) filter

NASA Image and Video Library

2009-08-25

ISS020-E-033979 (25 Aug. 2009) --- NASA astronaut Michael Barratt, Expedition 20 flight engineer, works with the Crew Health Care System (CHeCS) rack in the Kibo laboratory of the International Space Station.

Command/response protocols and concurrent software

NASA Technical Reports Server (NTRS)

Bynum, W. L.

1987-01-01

A version of the program to control the parallel jaw gripper is documented. The parallel jaw end-effector hardware and the Intel 8031 processor that is used to control the end-effector are briefly described. A general overview of the controller program is given and a complete description of the program's structure and design are contained. There are three appendices: a memory map of the on-chip RAM, a cross-reference listing of the self-scheduling routines, and a summary of the top-level and monitor commands.

Field Programmable Gate Array Failure Rate Estimation Guidelines for Launch Vehicle Fault Tree Models

NASA Technical Reports Server (NTRS)

Al Hassan, Mohammad; Britton, Paul; Hatfield, Glen Spencer; Novack, Steven D.

2017-01-01

Today's launch vehicles complex electronic and avionics systems heavily utilize Field Programmable Gate Array (FPGA) integrated circuits (IC) for their superb speed and reconfiguration capabilities. Consequently, FPGAs are prevalent ICs in communication protocols such as MILSTD- 1553B and in control signal commands such as in solenoid valve actuations. This paper will identify reliability concerns and high level guidelines to estimate FPGA total failure rates in a launch vehicle application. The paper will discuss hardware, hardware description language, and radiation induced failures. The hardware contribution of the approach accounts for physical failures of the IC. The hardware description language portion will discuss the high level FPGA programming languages and software/code reliability growth. The radiation portion will discuss FPGA susceptibility to space environment radiation.

Automated Activation and Deactivation of a System Under Test

NASA Technical Reports Server (NTRS)

Poff, Mark A.

2006-01-01

The MPLM Automated Activation/Deactivation application (MPLM means Multi-Purpose Logistic Module) was created with a three-fold purpose in mind: 1. To reduce the possibility of human error in issuing commands to, or interpreting telemetry from, the MPLM power, computer, and environmental control systems; 2. To reduce the amount of test time required for the repetitive activation/deactivation processes; and 3. To reduce the number of on-console personnel required for activation/ deactivation. All of these have been demonstrated with the release of the software. While some degree of automated end-item commanding had previously been performed for space-station hardware in the test environment, none approached the functionality and flexibility of this application. For MPLM activation, it provides mouse-click selection of the hardware complement to be activated, activates the desired hardware and verifies proper feedbacks, and alerts the user when telemetry indicates an error condition or manual intervention is required. For MPLM deactivation, the product senses which end items are active and deactivates them in the proper sequence. For historical purposes, an on-line log is maintained of commands issued and telemetry points monitored. The benefits of the MPLM Automated Activation/ Deactivation application were demonstrated with its first use in December 2002, when it flawlessly performed MPLM activation in 8 minutes (versus as much as 2.4 hours for previous manual activations), and performed MPLM deactivation in 3 minutes (versus 66 minutes for previous manual deactivations). The number of test team members required has dropped from eight to four, and in actuality the software can be operated by a sole (knowledgeable) system engineer.

Microprogramming for real-time data acquisition

NASA Technical Reports Server (NTRS)

Patella, F. J.

1977-01-01

Transmit microcode trap logic is conditioned by preset clock. Measurement request or issuance of command is controlled by set of software-initialized polling tables. Receive microcode trap logic is conditioned by transmit/receive hardware when response is returned on data bus.

Burbank uses the Neurospat hardware in the Columbus Module

NASA Image and Video Library

2012-03-15

ISS030-E-177227 (15 March 2012) --- NASA astronaut Dan Burbank, Expedition 30 commander, uses Neurospat hardware to perform a science session with the European Space Agency PASSAGES experiment in the Columbus laboratory of the International Space Station. PASSAGES is designed to test how astronauts interpret visual information in weightlessness. It aims at studying the effects of microgravity on the use of the 'Eye-Height' strategy for estimating allowed actions in an environment, and whether this could possibly decrease after a long exposure to weightlessness.

Burbank uses the Neurospat hardware in the Columbus Module

NASA Image and Video Library

2012-03-15

ISS030-E-177225 (15 March 2012) --- NASA astronaut Dan Burbank, Expedition 30 commander, uses Neurospat hardware to perform a science session with the European Space Agency PASSAGES experiment in the Columbus laboratory of the International Space Station. PASSAGES is designed to test how astronauts interpret visual information in weightlessness. It aims at studying the effects of microgravity on the use of the 'Eye-Height' strategy for estimating allowed actions in an environment, and whether this could possibly decrease after a long exposure to weightlessness.

A memory-mapped output interface: Omega navigation output data from the JOLT (TM) microcomputer

NASA Technical Reports Server (NTRS)

Lilley, R. W.

1976-01-01

A hardware interface which allows both digital and analog data output from the JOLT microcomputer is described in the context of a software-based Omega Navigation receiver. The interface hardware described is designed for output of six (or eight with simple extensions) bits of binary output in response to a memory store command from the microcomputer. The interface was produced in breadboard form and is operational as an evaluation aid for the software Omega receiver.

Apollo Guidance, Navigation, and Control (GNC) Hardware Overview

NASA Technical Reports Server (NTRS)

Interbartolo, Michael

2009-01-01

This viewgraph presentation reviews basic guidance, navigation and control (GNC) concepts, examines the Command and Service Module (CSM) and Lunar Module (LM) GNC organization and discusses the primary GNC and the CSM Stabilization and Control System (SCS), as well as other CSM-specific hardware. The LM Abort Guidance System (AGS), Control Electronics System (CES) and other LM-specific hardware are also addressed. Three subsystems exist on each vehicle: the computer subsystem (CSS), the inertial subsystem (ISS) and the optical subsystem (OSS). The CSS and ISS are almost identical between CSM and LM and each is designed to operate independently. CSM SCS hardware are highlighted, including translation control, rotation controls, gyro assemblies, a gyro display coupler and flight director attitude indicators. The LM AGS hardware are also highlighted and include the abort electronics assembly and the abort sensor assembly; while the LM CES hardware includes the attitude controller assembly, thrust/translation controller assemblies and the ascent engine arming assemble. Other common hardware including the Orbital Rate Display - Earth and Lunar (ORDEAL) and the Crewman Optical Alignment Sight (COAS), a docking aid, are also highlighted.

Instrumentation Hardware Abstraction Language (IHAL) Handbook

DTIC Science & Technology

2017-01-01

1-1 1.1 The Range Commanders Council (RCC) and IHAL ....................................................... 1-1 1.2 Problem Description ...1-5 1.3.1 IHAL as a Description Language...Figure 2-6. Generic IHAL Device Schema Diagram ............................................................. 2-7 Figure 2-7. Device Description Schema

Krikalev with TVIS hardware in Zvezda

NASA Image and Video Library

2005-09-07

ISS011-E-12601 (7 September 2005) --- Cosmonaut Sergei K. Krikalev, Expedition 11 commander representing Russia's Federal Space Agency, works with the Treadmill Vibration Isolation System (TVIS) during In-Flight Maintenance (IFM) in the Zvezda Service Module of the International Space Station.

Krikalev with TVIS hardware in Zvezda

NASA Image and Video Library

2005-09-07

ISS011-E-12494 (7 September 2005) --- Cosmonaut Sergei K. Krikalev, Expedition 11 commander representing Russia's Federal Space Agency, works with the Treadmill Vibration Isolation System (TVIS) during In-Flight Maintenance (IFM) in the Zvezda Service Module of the International Space Station.

Preliminary Advanced Colloids Experiment

NASA Image and Video Library

2011-09-29

ISS029-E-011867 (29 Sept. 2011) --- NASA astronaut Mike Fossum, Expedition 29 commander, works with the Light Microscopy Module (LMM) control box in the Destiny laboratory of the International Space Station in preparation for another session with the Preliminary Advanced Colloids Experiment (PACE) hardware.

Field Programmable Gate Array Reliability Analysis Guidelines for Launch Vehicle Reliability Block Diagrams

NASA Technical Reports Server (NTRS)

Al Hassan, Mohammad; Britton, Paul; Hatfield, Glen Spencer; Novack, Steven D.

2017-01-01

Field Programmable Gate Arrays (FPGAs) integrated circuits (IC) are one of the key electronic components in today's sophisticated launch and space vehicle complex avionic systems, largely due to their superb reprogrammable and reconfigurable capabilities combined with relatively low non-recurring engineering costs (NRE) and short design cycle. Consequently, FPGAs are prevalent ICs in communication protocols and control signal commands. This paper will identify reliability concerns and high level guidelines to estimate FPGA total failure rates in a launch vehicle application. The paper will discuss hardware, hardware description language, and radiation induced failures. The hardware contribution of the approach accounts for physical failures of the IC. The hardware description language portion will discuss the high level FPGA programming languages and software/code reliability growth. The radiation portion will discuss FPGA susceptibility to space environment radiation.

Swanson in

NASA Image and Video Library

2014-06-11

ISS040-E-010261 (11 June 2014) --- NASA astronaut Steve Swanson, Expedition 40 commander, works with the Multi-user Drop Combustion Apparatus (MDCA) at a workstation in the Harmony node of the International Space Station. The MDCA contains hardware and software to conduct unique droplet combustion experiments in space.

Swanson in

NASA Image and Video Library

2014-06-11

ISS040-E-010258 (11 June 2014) --- NASA astronaut Steve Swanson, Expedition 40 commander, works with the Multi-user Drop Combustion Apparatus (MDCA) at a workstation in the Harmony node of the International Space Station. The MDCA contains hardware and software to conduct unique droplet combustion experiments in space.

Usachev with IRED hardware in Node 1/Unity module

NASA Image and Video Library

2001-04-07

ISS002-E-5508 (7 April 2001) --- Cosmonaut Yury V. Usachev, Expedition Two commander, wears a harness while conducting resistance exercises in the Unity Node 1 on the International Space Station (ISS). The image was recorded with a digital still camera.

KSC-03pd1112

NASA Image and Video Library

2003-04-09

KENNEDY SPACE CENTER, FLA. -- Eric Baker, a United Space Alliance project engineer at Kennedy Space Center, (right) works at the Lufkin Command Center to track hazardous tank finds. KSC workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

KSC-03pd1111

NASA Image and Video Library

2003-04-09

KENNEDY SPACE CENTER, FLA. -- Jeff Angermeier, assigned to lead the ground operations at the Lufkin Command Center, points out a town near the Columbia debris field. KSC workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

Lightning around the Apollo 15 stack prior to launch

NASA Image and Video Library

1971-07-25

S89-41564 (25 July 1971) --- Lightning streaks through the sky around the Apollo 15 stack of hardware prior to the Apollo 15 launch. The huge 363-feet tall Apollo 15 (Spacecraft 112/Lunar Module 10/Saturn 510) space vehicle is scheduled to launch from Pad A, Launch Complex 39, at 9:34:00:79 p.m. (EDT) on July 26, 1971. The prime crewmembers for the Apollo 15 mission are astronauts David R. Scott, commander; James B. Irwin, lunar module pilot; and Alfred M. Worden, command module pilot.

Advanced Command Destruct System (ACDS) Enhanced Flight Termination System (EFTS)

NASA Technical Reports Server (NTRS)

Tow, David

2009-01-01

NASA Dryden started working towards a single vehicle enhanced flight termination system (EFTS) in January 2008. NASA and AFFTC combined their efforts to work towards final operating capability for multiple vehicle and multiple missions simultaneously, to be completed by the end of 2011. Initially, the system was developed to support one vehicle and one frequency per mission for unmanned aerial vehicles (UAVs) at NASA Dryden. By May 2008 95% of design and hardware builds were completed, however, NASA Dryden's change of software safety scope and requirements caused delays after May 2008. This presentation reviews the initial and final operating capabilities for the Advanced Command Destruct System (ACDS), including command controller and configuration software development. A requirements summary is also provided.

Immunological failure of first-line and switch to second-line antiretroviral therapy among HIV-infected persons in Tanzania: analysis of routinely collected national data

PubMed Central

Vanobberghen, Fiona M; Kilama, Bonita; Wringe, Alison; Ramadhani, Angela; Zaba, Basia; Mmbando, Donan; Todd, Jim

2015-01-01

Objectives Rates of first-line treatment failure and switches to second-line therapy are key indicators for national HIV programmes. We assessed immunological treatment failure defined by WHO criteria in the Tanzanian national HIV programme. Methods We included adults initiating first-line therapy in 2004–2011 with a pre-treatment CD4 count, and ≥6-months of follow-up. We assessed subhazard ratios (SHR) for immunological treatment failure, and subsequent switch to second-line therapy, using competing risks methods to account for deaths. Results Of 121 308 adults, 7% experienced immunological treatment failure, and 2% died without observed immunological treatment failure, over a median 1.7 years. The 6-year cumulative probability of immunological treatment failure was 19.0% (95% CI 18.5, 19.7) and of death, 5.1% (4.8, 5.4). Immunological treatment failure predictors included earlier year of treatment initiation (P < 0.001), initiation in lower level facilities (SHR = 2.23 [2.03, 2.45] for dispensaries vs. hospitals), being male (1.27 [1.19, 1.33]) and initiation at low or high CD4 counts (for example, 1.78 [1.65, 1.92] and 5.33 [4.65, 6.10] for <50 and ≥500 vs. 200–349 cells/mm3, respectively). Of 7382 participants in the time-to-switch analysis, 6% switched and 5% died before switching. Four years after immunological treatment failure, the cumulative probability of switching was 7.3% (6.6, 8.0) and of death, 6.8% (6.0, 7.6). Those who immunologically failed in dispensaries, health centres and government facilities were least likely to switch. Conclusions Immunological treatment failure rates and unmet need for second-line therapy are high in Tanzania; virological monitoring, at least for persons with immunological treatment failure, is required to minimise unnecessary switches to second-line therapy. Lower level government health facilities need more support to reduce treatment failure rates and improve second-line therapy uptake to sustain the benefits of increased coverage. Objectifs Les taux d’échec du traitement de 1ère ligne et les passages au traitement de 2nde ligne sont des indicateurs clés pour les programmes nationaux VIH. Nous avons évalué l’échec immunologique du traitement selon les critères de l’OMS dans le programme national VIH tanzanien. Méthodes Nous avons inclus les adultes entreprenant une thérapie de 1ère ligne entre 2004 et 2011 avec une numération des CD4 prétraitement disponible et un suivi ≥6 mois. Nous avons évalué les rapports en dessous du risque pour l’échec immunologique du traitement et le passage subséquent à la thérapie de 2nde ligne, en utilisant les méthodes de risques concurrents pour tenir compte des décès. Résultats Sur 121.308 adultes, 7% ont connu un échec immunologique du traitement et 2% sont décédés sans observation d’échec immunologique du traitement, sur une médiane de 1,7 ans. La probabilité cumulée d’échec immunologique du traitement sur six ans était de 19,0% (IC95%: 18,5 à 19,7) et 5,1% (4,8 à 5,4) de décès. Les prédicteurs d’échecs immunologiques du traitement comprenaient: l'instauration précoce du traitement (p <0,001), l'initiation dans les établissements de niveau inférieur (SHR = 2,23 [2,03 à 2,45] pour les dispensaires versus les hôpitaux), le sexe masculin (1,27 [1,19 à 1,33]) et l'initiation du traitement à des taux de CD4 faibles ou élevés (par exemple, 1,78 [1,65 à 1,92] et 5,33 [4,65 à 6,10] pour des taux <50 et ≥500 versus des taux compris entre 200 et 349 cellules/mm3, respectivement). Sur 7.382 participants à l'analyse sur le moment du changement de traitement, 6% ont changé de traitement et 5% sont décédés avant le changement. Quatre ans après l’échec immunologique du traitement, la probabilité cumulative du changement de traitement était de 7,3% (6,6 à 8,0) et de 6,8% (6,0 à 7,6) pour les décès. Ceux qui ont connu un échec immunologique dans les dispensaires, les centres de santé et les établissements gouvernementaux étaient les moins susceptibles de changer de traitement. Conclusions Les taux d’échecs immunologiques du traitement et les besoins non satisfaits pour le traitement de 2nde ligne sont élevés en Tanzanie. La surveillance virologique, au moins pour les personnes avec un échec immunologique de traitement, est nécessaire pour minimiser les passages inutiles au traitement de 2nde ligne. Les établissements de santé gouvernementaux de niveau inférieur ont besoin de plus de support pour réduire les taux d’échec de traitement et pour améliorer l'adoption de la thérapie de 2nde ligne afin de maintenir les avantages d'une couverture accrue. Objetivos Las tasas de fallo de la terapia de primera línea y los cambios a la terapia de segunda línea son indicadores claves para los programas nacionales de VIH. Hemos evaluado los fallos en el tratamiento inmunológico definidos según criterios de la OMS dentro del programa nacional para VIH en Tanzania. Métodos Hemos incluido adultos que iniciaban la terapia de primera línea entre el 2004-2011 con un conteo de CD4 antes de recibir el tratamiento, y tras ≥6 meses de seguimiento. Hemos evaluado los subíndices de riesgo del fallo inmunológico en el tratamiento, y el cambio subsecuente a la segunda línea de tratamiento, utilizando análisis de riesgo competitivo para explicar las muertes. Resultados De 121,308 adultos, un 7% experimentó fallo inmunológico, y un 2% murió sin observarse un fallo inmunológico en el tratamiento, a lo largo de una mediana de 1.7 años. La probabilidad acumulada a lo largo de seis años de fallo terapéutico inmunológico era del 19.0% (IC 95% 18.5, 19.7) y de muerte del 5.1% (4.8,5.4). Los vaticinadores de fallo terapéutico inmunológico incluían haber empezado el tratamiento un año antes (p<0.001), haberlo iniciado en centros de menor nivel (SHR=2.23 [2.03,2.45] para dispensarios versus hospitales), ser ombre (1.27 [1.19,1.33]) e iniciar con conteos de CD$ bajos o altos (por ejemplo, 1.78 [1.65,1.92] y 5.33 [4.65,6.10] para <50 y ≥500 versus 200-349 células/mm3, respectivamente). De 7,382 participantes en el análisis de tiempo-hasta-el-cambio, un 6% cambió y un 5% murió antes del cambio. Cuatro años después del fallo terapéutico inmunológico, la probabilidad acumulativa de cambiar era del 7.3% (6.6,8.0) y de muerte, del 6.8% (6.0,7.6). Aquellos que tuvieron un fallo terapéutico inmunológico en los dispensarios, centros sanitarios y centros gubernamentales tenían una menor probabilidad de cambiar. Conclusiones Las tasas de fallo terapéutico inmunológico y una necesidad de segunda línea de tratamiento no resuelta son altas en Tanzania; la monitorización virológica, al menos en el caso de personas con fallo terapéutico inmunológico, es necesaria para minimizar los cambios innecesarios a la segunda línea de tratamiento. Los centros sanitarios gubernamentales de menor nivel requieren de más apoyo para reducir las tasas de fallo terapéutico y mejorar la aceptación de la segunda línea de tratamiento asegurando la continuidad de los beneficios de una mayor cobertura. PMID:25779383

CIR

NASA Image and Video Library

2014-06-11

ISS040-E-010496 (11 June 2014) --- NASA astronaut Steve Swanson, Expedition 40 commander, works with the Multi-user Drop Combustion Apparatus (MDCA) inside the Combustion Integrated Rack (CIR) in the Destiny laboratory of the International Space Station. The MDCA contains hardware and software to conduct unique droplet combustion experiments in space.

CIR

NASA Image and Video Library

2014-06-11

ISS040-E-010502 (11 June 2014) --- NASA astronaut Steve Swanson, Expedition 40 commander, works with the Multi-user Drop Combustion Apparatus (MDCA) inside the Combustion Integrated Rack (CIR) in the Destiny laboratory of the International Space Station. The MDCA contains hardware and software to conduct unique droplet combustion experiments in space.

Usachev with IRED hardware in Node 1/Unity module

NASA Image and Video Library

2001-04-07

ISS002-E-5507 (07 April 2001) --- Cosmonaut Yury V. Usachev, Expedition Two mission commander, wears a harness while conducting resistance exercises in the Node 1 / Unity module of the International Space Station (ISS). This image was recorded with a digital still camera.

Kennedy Space Center's Command and Control System - "Toasters to Rocket Ships"

NASA Technical Reports Server (NTRS)

Lougheed, Kirk; Mako, Cheryle

2011-01-01

This slide presentation reviews the history of the development of the command and control system at Kennedy Space Center. From a system that could be brought to Florida in the trunk of a car in the 1950's. Including the development of larger and more complex launch vehicles with the Apollo program where human launch controllers managed the launch process with a hardware only system that required a dedicated human interface to perform every function until the Apollo vehicle lifted off from the pad. Through the development of the digital computer that interfaced with ground launch processing systems with the Space Shuttle program. Finally, showing the future control room being developed to control the missions to return to the moon and Mars, which will maximize the use of Commercial-Off-The Shelf (COTS) hardware and software which was standards based and not tied to a single vendor. The system is designed to be flexible and adaptable to support the requirements of future spacecraft and launch vehicles.

An avionics scenario and command model description for Space Generic Open Avionics Architecture (SGOAA)

NASA Technical Reports Server (NTRS)

Stovall, John R.; Wray, Richard B.

1994-01-01

This paper presents a description of a model for a space vehicle operational scenario and the commands for avionics. This model will be used in developing a dynamic architecture simulation model using the Statemate CASE tool for validation of the Space Generic Open Avionics Architecture (SGOAA). The SGOAA has been proposed as an avionics architecture standard to NASA through its Strategic Avionics Technology Working Group (SATWG) and has been accepted by the Society of Automotive Engineers (SAE) for conversion into an SAE Avionics Standard. This architecture was developed for the Flight Data Systems Division (FDSD) of the NASA Johnson Space Center (JSC) by the Lockheed Engineering and Sciences Company (LESC), Houston, Texas. This SGOAA includes a generic system architecture for the entities in spacecraft avionics, a generic processing external and internal hardware architecture, and a nine class model of interfaces. The SGOAA is both scalable and recursive and can be applied to any hierarchical level of hardware/software processing systems.

Apollo experience report: Guidance and control systems. Engineering simulation program

NASA Technical Reports Server (NTRS)

Gilbert, D. W.

1973-01-01

The Apollo Program experience from early 1962 to July 1969 with respect to the engineering-simulation support and the problems encountered is summarized in this report. Engineering simulation in support of the Apollo guidance and control system is discussed in terms of design analysis and verification, certification of hardware in closed-loop operation, verification of hardware/software compatibility, and verification of both software and procedures for each mission. The magnitude, time, and cost of the engineering simulations are described with respect to hardware availability, NASA and contractor facilities (for verification of the command module, the lunar module, and the primary guidance, navigation, and control system), and scheduling and planning considerations. Recommendations are made regarding implementation of similar, large-scale simulations for future programs.

The NASA Spacecraft Transponding Modem

NASA Technical Reports Server (NTRS)

Berner, Jeff B.; Kayalar, Selahattin; Perret, Jonathan D.

2000-01-01

A new deep space transponder is being developed by the Jet Propulsion Laboratory for NASA. The Spacecraft Transponding Modem (STM) implements the standard transponder functions and the channel service functions that have previously resided in spacecraft Command/Data Subsystems. The STM uses custom ASICs, MMICs, and MCMs to reduce the active device parts count to 70, mass to I kg, and volume to 524 cc. The first STMs will be flown on missions launching in the 2003 time frame. The STM tracks an X-band uplink signal and provides both X-band and Ka-band downlinks, either coherent or non-coherent with the uplink. A NASA standard Command Detector Unit is integrated into the STM, along with a codeblock processor and a hardware command decoder. The decoded command codeblocks are output to the spacecraft command/data subsystem. Virtual Channel 0 (VC-0) (hardware) commands are processed and output as critical controller (CRC) commands. Downlink telemetry is received from the spacecraft data subsystem as telemetry frames. The STM provides the following downlink coding options: the standard CCSDS (7-1/2) convolutional coding, ReedSolomon coding with interleave depths one and five, (15-1/6) convolutional coding, and Turbo coding with rates 1/3 and 1/6. The downlink symbol rates can be linearly ramped to match the G/T curve of the receiving station, providing up to a 1 dB increase in data return. Data rates range from 5 bits per second (bps) to 24 Mbps, with three modulation modes provided: modulated subcarrier (3 different frequencies provided), biphase-L modulated direct on carrier, and Offset QPSK. Also, the capability to generate one of four non-harmonically related telemetry beacon tones is provided, to allow for a simple spacecraft status monitoring scheme for cruise phases of missions. Three ranging modes are provided: standard turn around ranging, regenerative pseudo-noise (PN) ranging, and Differential One-way Ranging (DOR) tones. The regenerative ranging provides the capability of increasing the ground received ranging SNR by up to 30 dB. Two different avionics interfaces to the command/data subsystem's data bus are provided: a MIL STD 1553B bus or an industry standard PCI interface. Digital interfaces provide the capability to control antenna selection (e.g., switching between high gain and low gain antennas) and antenna pointing (for future steered Ka-band antennas).

A Wireless Local Area Network Command and Control System for Explosive Ordnance Disposal Incident Response

DTIC Science & Technology

2001-09-01

43 4. GPS ......................................................................................................44 E. POWER SUPPLY HARDWARE...44 Figure 5.6 Earthmate GPS Receiver ........................................................................................45...and 5Watts at 25 Ft Effective Range Minimum range of wireless link is 5 miles. Positional awareness System requires GPS input to determine

Man+Machine+Master Plan.

ERIC Educational Resources Information Center

Atwood, E. Barrett, Jr.

1982-01-01

Computer hardware and software alone do not improve a financial management system. They are only the tools that carry out commands. College business offices and related administrative functions must commit effort to improving the overall system. Available from Peat, Marwick, Mitchell & Co., 345 Park Avenue, New York, NY 10154. (MSE)

Innovation for integrated command environments

NASA Astrophysics Data System (ADS)

Perry, Amie A.; McKneely, Jennifer A.

2000-11-01

Command environments have rarely been able to easily accommodate rapid changes in technology and mission. Yet, command personnel, by their selection criteria, experience, and very nature, tend to be extremely adaptive and flexible, and able to learn new missions and address new challenges fairly easily. Instead, the hardware and software components of the systems do no provide the needed flexibility and scalability for command personnel. How do we solve this problem? In order to even dream of keeping pace with a rapidly changing world, we must begin to think differently about the command environment and its systems. What is the correct definition of the integrated command environment system? What types of tasks must be performed in this environment, and how might they change in the next five to twenty-five years? How should the command environment be developed, maintained, and evolved to provide needed flexibility and scalability? The issues and concepts to be considered as new Integrated Command/Control Environments (ICEs) are designed following a human-centered process. A futuristic model, the Dream Integrated Command Environment (DICE) will be described which demonstrates specific ICE innovations. The major paradigm shift required to be able to think differently about this problem is to center the DICE around the command personnel from its inception. Conference participants may not agree with every concept or idea presented, but will hopefully come away with a clear understanding that to radically improve future systems, designers must focus on the end users.

Effects of cationic hydroxyethyl cellulose on glucose tolerance and obesity

USDA-ARS?s Scientific Manuscript database

Cholestyramine is a cationic polymer prescribed to lower cholesterol in humans. We investigated the effects of cationic hydroxyethyl cellulose (cHEC) on weight loss and metabolic disorders associated with obesity using both hamster and diet-induced obese mouse models. Golden Syrian hamsters and ob...

Re-Engineering of the Hubble Space Telescope (HST) to Reduce Operational Costs

NASA Technical Reports Server (NTRS)

Garvis, Michael; Dougherty, Andrew; Whittier, Wallace

1996-01-01

Satellite telemetry processing onboard the Hubble Space Telescope (HST) is carried out using dedicated software and hardware. The current ground system is expensive to operate and maintain. The mandate to reduce satellite ground system operations and maintenance costs by the year 2000 led NASA to upgrade the command and control systems in order to improve the data processing capabilities, reduce operator experience levels and increase system standardization. As a result, a command and control system product development team was formed to redesign and develop the HST ground system. The command and control system ground system development consists of six elements. The results of the prototyping phase carried out for the following of these elements are presented: the front end processor; middleware, and the graphical user interface.

Managing the Risk of Command File Errors

NASA Technical Reports Server (NTRS)

Meshkat, Leila; Bryant, Larry W.

2013-01-01

Command File Error (CFE), as defined by the Jet Propulsion Laboratory's (JPL) Mission Operations Assurance (MOA) is, regardless of the consequence on the spacecraft, either: an error in a command file sent to the spacecraft, an error in the process for developing and delivering a command file to the spacecraft, or the omission of a command file that should have been sent to the spacecraft. The risk consequence of a CFE can be mission ending and thus a concern to space exploration projects during their mission operations. A CFE during space mission operations is often the symptom of some kind of imbalance or inadequacy within the system that comprises the hardware & software used for command generation and the human experts involved in this endeavour. As we move into an era of enhanced collaboration with other NASA centers and commercial partners, these systems become more and more complex and hence it is all the more important to formally model and analyze CFEs in order to manage the risk of CFEs. Here we will provide a summary of the ongoing efforts at JPL in this area and also explain some more recent developments in the area of developing quantitative models for the purpose of managing CFE's.

Burbank works on the EPIC in the Node 2

NASA Image and Video Library

2012-02-28

ISS030-E-114433 (29 Feb. 2012) --- In the International Space Station?s Destiny laboratory, NASA astronaut Dan Burbank, Expedition 30 commander, upgrades Multiplexer/Demultiplexer (MDM) computers and Portable Computer System (PCS) laptops and installs the Enhanced Processor & Integrated Communications (EPIC) hardware in the Payload 1 (PL-1) MDM.

Development and Command-Control Tools for Many-Robot Systems

DTIC Science & Technology

2005-01-01

been components such as pressure sensors and accelerometers for the automobile market. In fact, robots of any size have yet to appear in our daily...34 mode, so that the target hardware is neither reprogrammable nor rechargable. The goal of this paper is to propose some generic tools that the

OpenPET Hardware, Firmware, Software, and Board Design Files

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

Abu-Nimeh, Faisal; Choong, Woon-Sengq; Moses, William W.

OpenPET is an open source, flexible, high-performance, and modular data acquisition system for a variety of applications. The OpenPET electronics are capable of reading analog voltage or current signals from a wide variety of sensors. The electronics boards make extensive use of field programmable gate arrays (FPGAs) to provide flexibility and scalability. Firmware and software for the FPGAs and computer are used to control and acquire data from the system. The command and control flow is similar to the data flow, however, the commands are initiated from the computer similar to a tree topology (i.e., from top-to-bottom). Each node inmore » the tree discovers its parent and children, and all addresses are configured accordingly. A user (or a script) initiates a command from the computer. This command will be translated and encoded to the corresponding child (e.g., SB, MB, DB, etc.). Consecutively, each node will pass the command to its corresponding child(ren) by looking at the destination address. Finally, once the command reaches its desired destination(s) the corresponding node(s) execute(s) the command and send(s) a reply, if required. All the firmware, software, and the electronics board design files are distributed through the OpenPET website (http://openpet.lbl.gov).« less

Mir 22 and STS-81 crew work with gyrodyne

NASA Image and Video Library

1997-02-04

STS081-301-032 (12-22 Jan. 1997) --- Shortly after the docking of the Space Shuttle Atlantis and Russia's Mir Space Station, crewmembers from the respective spacecraft begin to transfer hardware from the Spacehab Double Module (DM) onto the Mir complex. In this scene, cosmonaut Valeri G. Korzun (second left) Mir-22 commander, along with astronauts Michael A. Baker (second right) commander, and Brent W. Jett, Jr., pilot, unstow a gyrodyne, a device used for attitude control, for transfer to Mir. Astronaut Marsha S. Ivins looks over a lengthy inventory of supplies to be transferred.

International Space Station Payload Operations Integration Center (POIC) Overview

NASA Technical Reports Server (NTRS)

Ijames, Gayleen N.

2012-01-01

Objectives and Goals: Maintain and operate the POIC and support integrated Space Station command and control functions. Provide software and hardware systems to support ISS payloads and Shuttle for the POIF cadre, Payload Developers and International Partners. Provide design, development, independent verification &validation, configuration, operational product/system deliveries and maintenance of those systems for telemetry, commanding, database and planning. Provide Backup Control Center for MCC-H in case of shutdown. Provide certified personnel and systems to support 24x7 facility operations per ISS Program. Payloads CoFR Implementation Plan (SSP 52054) and MSFC Payload Operations CoFR Implementation Plan (POIF-1006).

Compliance control with embedded neural elements

NASA Technical Reports Server (NTRS)

Venkataraman, S. T.; Gulati, S.

1992-01-01

The authors discuss a control approach that embeds the neural elements within a model-based compliant control architecture for robotic tasks that involve contact with unstructured environments. Compliance control experiments have been performed on actual robotics hardware to demonstrate the performance of contact control schemes with neural elements. System parameters were identified under the assumption that environment dynamics have a fixed nonlinear structure. A robotics research arm, placed in contact with a single degree-of-freedom electromechanical environment dynamics emulator, was commanded to move through a desired trajectory. The command was implemented by using a compliant control strategy.

Apollo experience report: Command and service module communications subsystem

NASA Technical Reports Server (NTRS)

Lattier, E. E., Jr.

1974-01-01

The development of spacecraft communications hardware from design to operation is described. Programs, requirements, specifications, and design approaches for a variety of functions (such as voice, telemetry, television, and antennas) are reviewed. Equipment environmental problems such as vibration, extreme temperature variation, and zero gravity are discussed. A review of the development of managerial techniques used in refining the roles of prime and subcontractors is included. The hardware test program is described in detail as it progressed from breadboard design to manned flight system evaluations. Finally, a series of actions is recommended to managers of similar projects to facilitate administration.

Intelligent systems and advanced user interfaces for design, operation, and maintenance of command management systems

NASA Technical Reports Server (NTRS)

Potter, William J.; Mitchell, Christine M.

1993-01-01

Historically, command management systems (CMS) have been large and expensive spacecraft-specific software systems that were costly to build, operate, and maintain. Current and emerging hardware, software, and user interface technologies may offer an opportunity to facilitate the initial formulation and design of a spacecraft-specific CMS as well as to develop a more generic CMS system. New technologies, in addition to a core CMS common to a range of spacecraft, may facilitate the training and enhance the efficiency of CMS operations. Current mission operations center (MOC) hardware and software include Unix workstations, the C/C++ programming languages, and an X window interface. This configuration provides the power and flexibility to support sophisticated and intelligent user interfaces that exploit state-of-the-art technologies in human-machine interaction, artificial intelligence, and software engineering. One of the goals of this research is to explore the extent to which technologies developed in the research laboratory can be productively applied in a complex system such as spacecraft command management. Initial examination of some of these issues in CMS design and operation suggests that application of technologies such as intelligent planning, case-based reasoning, human-machine systems design and analysis tools (e.g., operator and designer models), and human-computer interaction tools (e.g., graphics, visualization, and animation) may provide significant savings in the design, operation, and maintenance of the CMS for a specific spacecraft as well as continuity for CMS design and development across spacecraft. The first six months of this research saw a broad investigation by Georgia Tech researchers into the function, design, and operation of current and planned command management systems at Goddard Space Flight Center. As the first step, the researchers attempted to understand the current and anticipated horizons of command management systems at Goddard. Preliminary results are given on CMS commonalities and causes of low re-use, and methods are proposed to facilitate increased re-use.

Independent Orbiter Assessment (IOA): Analysis of the guidance, navigation, and control subsystem

NASA Technical Reports Server (NTRS)

Trahan, W. H.; Odonnell, R. A.; Pietz, K. C.; Hiott, J. M.

1986-01-01

The results of the Independent Orbiter Assessment (IOA) of the Failure Modes and Effects Analysis (FMEA) and Critical Items List (CIL) is presented. The IOA approach features a top-down analysis of the hardware to determine failure modes, criticality, and potential critical items. To preserve independence, this analysis was accomplished without reliance upon the results contained within the NASA FMEA/CIL documentation. The independent analysis results corresponding to the Orbiter Guidance, Navigation, and Control (GNC) Subsystem hardware are documented. The function of the GNC hardware is to respond to guidance, navigation, and control software commands to effect vehicle control and to provide sensor and controller data to GNC software. Some of the GNC hardware for which failure modes analysis was performed includes: hand controllers; Rudder Pedal Transducer Assembly (RPTA); Speed Brake Thrust Controller (SBTC); Inertial Measurement Unit (IMU); Star Tracker (ST); Crew Optical Alignment Site (COAS); Air Data Transducer Assembly (ADTA); Rate Gyro Assemblies; Accelerometer Assembly (AA); Aerosurface Servo Amplifier (ASA); and Ascent Thrust Vector Control (ATVC). The IOA analysis process utilized available GNC hardware drawings, workbooks, specifications, schematics, and systems briefs for defining hardware assemblies, components, and circuits. Each hardware item was evaluated and analyzed for possible failure modes and effects. Criticality was assigned based upon the severity of the effect for each failure mode.

Small Explorer project: Submillimeter Wave Astronomy Satellite (SWAS). Mission operations and data analysis plan

NASA Technical Reports Server (NTRS)

Melnick, Gary J.

1990-01-01

The Mission Operations and Data Analysis Plan is presented for the Submillimeter Wave Astronomy Satellite (SWAS) Project. It defines organizational responsibilities, discusses target selection and navigation, specifies instrument command and data requirements, defines data reduction and analysis hardware and software requirements, and discusses mission operations center staffing requirements.

Some research advances in computer graphics that will enhance applications to engineering design

NASA Technical Reports Server (NTRS)

Allan, J. J., III

1975-01-01

Research in man/machine interactions and graphics hardware/software that will enhance applications to engineering design was described. Research aspects of executive systems, command languages, and networking used in the computer applications laboratory are mentioned. Finally, a few areas where little or no research is being done were identified.

Hardware-in-the-Loop Rendezvous Tests of a Novel Actuators Command Concept

NASA Astrophysics Data System (ADS)

Gomes dos Santos, Willer; Marconi Rocco, Evandro; Boge, Toralf; Benninghoff, Heike; Rems, Florian

2016-12-01

Integration, test and validation results, in a real-time environment, of a novel concept for spacecraft control are presented in this paper. The proposed method commands simultaneously a group of actuators optimizing a given set of objective functions based on a multiobjective optimization technique. Since close proximity maneuvers play an important role in orbital servicing missions, the entire GNC system has been integrated and tested at a hardware-in-the-loop (HIL) rendezvous and docking simulator known as European Proximity Operations Simulator (EPOS). During the test campaign at EPOS facility, a visual camera has been used to provide the necessary measurements for calculating the relative position with respect to the target satellite during closed-loop simulations. In addition, two different configurations of spacecraft control have been considered in this paper: a thruster reaction control system and a mixed actuators mode which includes thrusters, reaction wheels, and magnetic torqrods. At EPOS, results of HIL closed-loop tests have demonstrated that a safe and stable rendezvous approach can be achieved with the proposed GNC loop.

Hardware platform for multiple mobile robots

NASA Astrophysics Data System (ADS)

Parzhuber, Otto; Dolinsky, D.

2004-12-01

This work is concerned with software and communications architectures that might facilitate the operation of several mobile robots. The vehicles should be remotely piloted or tele-operated via a wireless link between the operator and the vehicles. The wireless link will carry control commands from the operator to the vehicle, telemetry data from the vehicle back to the operator and frequently also a real-time video stream from an on board camera. For autonomous driving the link will carry commands and data between the vehicles. For this purpose we have developed a hardware platform which consists of a powerful microprocessor, different sensors, stereo- camera and Wireless Local Area Network (WLAN) for communication. The adoption of IEEE802.11 standard for the physical and access layer protocols allow a straightforward integration with the internet protocols TCP/IP. For the inspection of the environment the robots are equipped with a wide variety of sensors like ultrasonic, infrared proximity sensors and a small inertial measurement unit. Stereo cameras give the feasibility of the detection of obstacles, measurement of distance and creation of a map of the room.

SOCIAL - APOLLO-SOYUZ TEST PROJECT (ASTP) - DISNEY WORLD - FL

NASA Image and Video Library

1975-02-10

S75-24052 (8-10 Feb. 1975) --- A space-suited Mickey Mouse character welcomes the prime crewmen of the Apollo-Soyuz Test Project mission to Florida?s Disney World near Orlando. The crewmen made a side-trip to Disney World during a three-day inspection tour of NASA's Kennedy Space Center. The crewmen were at KSC to look over launch facilities and flight hardware. Receiving the jovial Disney World welcome are, left to right, cosmonaut Valeriy N. Kubasov, engineer on the Soviet crew; astronaut Donald K. Slayton, docking module pilot of the American crew; astronaut Vance D. Brand, command module pilot of the American crew; cosmonaut Aleksey A. Leonov, commander of the Soviet crew; astronaut Thomas P. Stafford, commander of the American crew; and cosmonaut Vladimir A. Shatalov, Chief of Cosmonaut Training for the USSR.

Human factors in command and control for the Los Angeles Fire Department.

PubMed

Harper, W R

1974-03-01

Ergonomics owes much of its operations and systems heritage to military research. Since public safety systems such as police, fire departments and civil defence organisations are quasi-military in nature, one may reasonably use the findings from military ergonomics research to extrapolate design data for use in a decision-making system. This article discusses a case study concerning Human Factors in command and control for the Los Angeles Fire Department. The case involved transfer from a manual dispatch system involving three geographic areas of metropolitan Los Angeles to one central computer-aided command and control system. Comments are made on console mock-ups, environmental factors in the Control Centre placement of the consoles. Because of extreme delays in procurement of the recommended hardware it is doubtful that empirical testing of the ergonomics aspect of the system will take place.

Universal programming interface with concurrent access

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

Alferov, Oleg

2004-10-07

There exist a number of devices with a positioning nature of operation, such as mechanical linear stages, temperature controllers, or filterwheels with discrete state, and most of them have different programming interfaces. The Universal Positioner software suggests the way to handle all of them is with a single approach, whereby a particular hardware driver is created from the template and by translating the actual commands used by the hardware to and from the universal programming interface. The software contains the universal API module itself, the demo simulation of hardware, and the front-end programs to help developers write their own softwaremore » drivers along with example drivers for actual hardware controllers. The software allows user application programs to call devices simultaneously without race conditions (multitasking and concurrent access). The template suggested in this package permits developers to integrate various devices easily into their applications using the same API. The drivers can be stacked; i.e., they can call each other via the same interface.« less

The Course of Educational Change: Challenge and Opportunity

ERIC Educational Resources Information Center

Shulman, Lee

2014-01-01

Lee Shulman's keynote address from the Catholic Higher Education Collaborative (CHEC) Conference on Catholic School Financing, University of Notre Dame, September 23, 2013 is presented in this article. He reflects back on serving as the convener of the group's first meeting, at the Carnegie Foundation in California. In this keynote…

KSC-03pd1110

NASA Image and Video Library

2003-04-09

KENNEDY SPACE CENTER, FLA. -- NASA Kennedy Space Center engineer Lamar Russell, who is serving as team lead for debris siting reports outside of Texas, points out to his Lufkin Command Center team a location targeted for a grid search. Kennedy Space Center workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

Spacelab data management subsystem phase B study

NASA Technical Reports Server (NTRS)

1974-01-01

The Spacelab data management system is described. The data management subsystem (DMS) integrates the avionics equipment into an operational system by providing the computations, logic, signal flow, and interfaces needed to effectively command, control, monitor, and check out the experiment and subsystem hardware. Also, the DMS collects/retrieves experiment data and other information by recording and by command of the data relay link to ground. The major elements of the DMS are the computer subsystem, data acquisition and distribution subsystem, controls and display subsystem, onboard checkout subsystem, and software. The results of the DMS portion of the Spacelab Phase B Concept Definition Study are analyzed.

BIRD: A general interface for sparse distributed memory simulators

NASA Technical Reports Server (NTRS)

Rogers, David

1990-01-01

Kanerva's sparse distributed memory (SDM) has now been implemented for at least six different computers, including SUN3 workstations, the Apple Macintosh, and the Connection Machine. A common interface for input of commands would both aid testing of programs on a broad range of computer architectures and assist users in transferring results from research environments to applications. A common interface also allows secondary programs to generate command sequences for a sparse distributed memory, which may then be executed on the appropriate hardware. The BIRD program is an attempt to create such an interface. Simplifying access to different simulators should assist developers in finding appropriate uses for SDM.

Battlefield awareness computers: the engine of battlefield digitization

NASA Astrophysics Data System (ADS)

Ho, Jackson; Chamseddine, Ahmad

1997-06-01

To modernize the army for the 21st century, the U.S. Army Digitization Office (ADO) initiated in 1995 the Force XXI Battle Command Brigade-and-Below (FBCB2) Applique program which became a centerpiece in the U.S. Army's master plan to win future information wars. The Applique team led by TRW fielded a 'tactical Internet' for Brigade and below command to demonstrate the advantages of 'shared situation awareness' and battlefield digitization in advanced war-fighting experiments (AWE) to be conducted in March 1997 at the Army's National Training Center in California. Computing Devices is designated the primary hardware developer for the militarized version of the battlefield awareness computers. The first generation of militarized battlefield awareness computer, designated as the V3 computer, was an integration of off-the-shelf components developed to meet the agressive delivery requirements of the Task Force XXI AWE. The design efficiency and cost effectiveness of the computer hardware were secondary in importance to delivery deadlines imposed by the March 1997 AWE. However, declining defense budgets will impose cost constraints on the Force XXI production hardware that can only be met by rigorous value engineering to further improve design optimization for battlefield awareness without compromising the level of reliability the military has come to expect in modern military hardened vetronics. To answer the Army's needs for a more cost effective computing solution, Computing Devices developed a second generation 'combat ready' battlefield awareness computer, designated the V3+, which is designed specifically to meet the upcoming demands of Force XXI (FBCB2) and beyond. The primary design objective is to achieve a technologically superior design, value engineered to strike an optimal balance between reliability, life cycle cost, and procurement cost. Recognizing that the diverse digitization demands of Force XXI cannot be adequately met by any one computer hardware solution, Computing Devices is planning to develop a notebook sized military computer designed for space limited vehicle-mounted applications, as well as a high-performance portable workstation equipped with a 19', full color, ultra-high resolution and high brightness active matrix liquid crystal display (AMLCD) targeting the command posts and tactical operations centers (TOC) applications. Together with the wearable computers Computing Devices developed at the Minneapolis facility for dismounted soldiers, Computing Devices will have a complete suite of interoperable battlefield awareness computers spanning the entire spectrum of battle digitization operating environments. Although this paper's primary focus is on a second generation 'combat ready' battlefield awareness computer or the V3+, this paper also briefly discusses the extension of the V3+ architecture to address the needs of the embedded and command post applications.3080

American-built hardware for ASPT undergoes pre-delivery preparations

NASA Image and Video Library

1974-09-11

S74-28295 (September 1974) --- American-built hardware for the joint U.S.-USSR Apollo-Soyuz Test Project mission undergoes pre-delivery preparations in the giant clean room at Rockwell International Corporation?s Space Division at Downey, California. The U.S. portion of the ASTP docking system is in the right foreground. In the right background is the cylindrical-shaped docking module, which is designed to link the Apollo and Soyuz spacecraft when they dock in Earth orbit next summer. In the left background is the Apollo Command Module which they will carry the three American astronauts into Earth orbit. Photo credit: NASA

Time maintenance system for the BMDO MSX spacecraft

NASA Technical Reports Server (NTRS)

Hermes, Martin J.

1994-01-01

The Johns Hopkins University Applied Physics Laboratory (APL) is responsible for designing and implementing a clock maintenance system for the Ballistic Missile Defense Organizations (BMDO) Midcourse Space Experiment (MSX) spacecraft. The MSX spacecraft has an on-board clock that will be used to control execution of time-dependent commands and to time tag all science and housekeeping data received from the spacecraft. MSX mission objectives have dictated that this spacecraft time, UTC(MSX), maintain a required accuracy with respect to UTC(USNO) of +/- 10 ms with a +/- 1 ms desired accuracy. APL's atomic time standards and the downlinked spacecraft time were used to develop a time maintenance system that will estimate the current MSX clock time offset during an APL pass and make estimates of the clock's drift and aging using the offset estimates from many passes. Using this information, the clock's accuracy will be maintained by uplinking periodic clock correction commands. The resulting time maintenance system is a combination of offset measurement, command/telemetry, and mission planning hardware and computing assets. All assets provide necessary inputs for deciding when corrections to the MSX spacecraft clock must be made to maintain its required accuracy without inhibiting other mission objectives. The MSX time maintenance system is described as a whole and the clock offset measurement subsystem, a unique combination of precision time maintenance and measurement hardware controlled by a Macintosh computer, is detailed. Simulations show that the system estimates the MSX clock offset to less than+/- 33 microseconds.

CoNNeCT Baseband Processor Module Boot Code SoftWare (BCSW)

NASA Technical Reports Server (NTRS)

Yamamoto, Clifford K.; Orozco, David S.; Byrne, D. J.; Allen, Steven J.; Sahasrabudhe, Adit; Lang, Minh

2012-01-01

This software provides essential startup and initialization routines for the CoNNeCT baseband processor module (BPM) hardware upon power-up. A command and data handling (C&DH) interface is provided via 1553 and diagnostic serial interfaces to invoke operational, reconfiguration, and test commands within the code. The BCSW has features unique to the hardware it is responsible for managing. In this case, the CoNNeCT BPM is configured with an updated CPU (Atmel AT697 SPARC processor) and a unique set of memory and I/O peripherals that require customized software to operate. These features include configuration of new AT697 registers, interfacing to a new HouseKeeper with a flash controller interface, a new dual Xilinx configuration/scrub interface, and an updated 1553 remote terminal (RT) core. The BCSW is intended to provide a "safe" mode for the BPM when initially powered on or when an unexpected trap occurs, causing the processor to reset. The BCSW allows the 1553 bus controller in the spacecraft or payload controller to operate the BPM over 1553 to upload code; upload Xilinx bit files; perform rudimentary tests; read, write, and copy the non-volatile flash memory; and configure the Xilinx interface. Commands also exist over 1553 to cause the CPU to jump or call a specified address to begin execution of user-supplied code. This may be in the form of a real-time operating system, test routine, or specific application code to run on the BPM.

The MGS Avionics System Architecture: Exploring the Limits of Inheritance

NASA Technical Reports Server (NTRS)

Bunker, R.

1994-01-01

Mars Global Surveyor (MGS) avionics system architecture comprises much of the electronics on board the spacecraft: electrical power, attitude and articulation control, command and data handling, telecommunications, and flight software. Schedule and cost constraints dictated a mix of new and inherited designs, especially hardware upgrades based on findings of the Mars Observer failure review boards.

Spacelab payload accommodation handbook. Appendix A: Avionics interface definition

NASA Technical Reports Server (NTRS)

1978-01-01

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

Joint Fire Support

DTIC Science & Technology

2010-06-30

intelligence application package for theater battle management core system ( TBMCS ) functionality at wing and squadron levels. The automated four... TBMCS , Joint Surveillance and Target Attack Radar System (Ground Control Station), and Global Command and Control System, as well as with Allied FA...The TBMCS is a force level integrated air C2 system. TBMCS provides hardware, software, and communications interfaces to support the preparation

Physiological Investigation of Localized Temperature Effects on Vigilance Performance

DTIC Science & Technology

2014-03-27

Department of Systems Engineering Graduate School of Engineering and Management Air Force Institute of Technology Air University Air Education and...Training Command In Partial Fulfillment of the Requirements for the Degree of Master of Science in Systems Engineering Justine D. Jeroski, BS...electrodes (right). ...................................................... 14 Figure A 3. BIOPAC © hardware system showing placement of ECG

USV Path Planning Using Potential Field Model

DTIC Science & Technology

2017-09-01

control system and hardware used. Figure 24. Control System Block Diagram The course commands are passed via Wi - Fi to the USV where the low...plane about the center. The estimated moment of inertia is 2 2 2 2 2( ) 36(1.35 0.98 ) 8.35 12 12 m b wI kg m+ += = = • . (41) b. Added

End-to-End Data System Architecture for the Space Station Biological Research Project

NASA Technical Reports Server (NTRS)

Mian, Arshad; Scimemi, Sam; Adeni, Kaiser; Picinich, Lou; Ramos, Rubin (Technical Monitor)

1998-01-01

The Space Station Biological Research Project (SSBRP) Is developing hardware referred to as the "facility" for providing life sciences research capability on the International Space Station. This hardware includes several biological specimen habitats, habitat holding racks, a centrifuge and a glovebox. An SSBRP end to end data system architecture has been developed to allow command and control of the facility from the ground, either with crew assistance or autonomously. The data system will be capable of handling commands, sensor data, and video from multiple cameras. The data will traverse through several onboard and ground networks and processing entities including the SSBRP and Space Station onboard and ground data systems. A large number of onboard and ground (,entities of the data system are being developed by the Space Station Program, other NASA centers and the International Partners. The SSBRP part of the system which includes the habitats, holding racks, and the ground operations center, User Operations Facility (UOF) will be developed by a multitude of geographically distributed development organizations. The SSBRP has the responsibility to define the end to end data and communications systems to make the interfaces manageable and verifiable with multiple contractors with widely varying development constraints and schedules. This paper provides an overview of the SSBRP end-to-end data system. Specifically, it describes the hardware, software and functional interactions of individual systems, and interface requirements among various entities of the end-to-end system.

Introduction to the computational structural mechanics testbed

NASA Technical Reports Server (NTRS)

Lotts, C. G.; Greene, W. H.; Mccleary, S. L.; Knight, N. F., Jr.; Paulson, S. S.; Gillian, R. E.

1987-01-01

The Computational Structural Mechanics (CSM) testbed software system based on the SPAR finite element code and the NICE system is described. This software is denoted NICE/SPAR. NICE was developed at Lockheed Palo Alto Research Laboratory and contains data management utilities, a command language interpreter, and a command language definition for integrating engineering computational modules. SPAR is a system of programs used for finite element structural analysis developed for NASA by Lockheed and Engineering Information Systems, Inc. It includes many complementary structural analysis, thermal analysis, utility functions which communicate through a common database. The work on NICE/SPAR was motivated by requirements for a highly modular and flexible structural analysis system to use as a tool in carrying out research in computational methods and exploring computer hardware. Analysis examples are presented which demonstrate the benefits gained from a combination of the NICE command language with a SPAR computational modules.

Current trends in hardware and software for brain-computer interfaces (BCIs)

NASA Astrophysics Data System (ADS)

Brunner, P.; Bianchi, L.; Guger, C.; Cincotti, F.; Schalk, G.

2011-04-01

A brain-computer interface (BCI) provides a non-muscular communication channel to people with and without disabilities. BCI devices consist of hardware and software. BCI hardware records signals from the brain, either invasively or non-invasively, using a series of device components. BCI software then translates these signals into device output commands and provides feedback. One may categorize different types of BCI applications into the following four categories: basic research, clinical/translational research, consumer products, and emerging applications. These four categories use BCI hardware and software, but have different sets of requirements. For example, while basic research needs to explore a wide range of system configurations, and thus requires a wide range of hardware and software capabilities, applications in the other three categories may be designed for relatively narrow purposes and thus may only need a very limited subset of capabilities. This paper summarizes technical aspects for each of these four categories of BCI applications. The results indicate that BCI technology is in transition from isolated demonstrations to systematic research and commercial development. This process requires several multidisciplinary efforts, including the development of better integrated and more robust BCI hardware and software, the definition of standardized interfaces, and the development of certification, dissemination and reimbursement procedures.

Our Schools--Our Hope: Reflections on Catholic Identity from the 2011 Catholic Higher Education Collaborative Conference

ERIC Educational Resources Information Center

O'Connell, David M.; Harrington, Donald J.; Monsegur, Barbara L.; Vogtner, Karen; Burnford, Thomas W.; Krebbs, Mary Jane

2012-01-01

These proceedings include selected presentations on Catholic identity by six participants of the 2011 Catholic Higher Education Collaborative (CHEC) Conference on Catholic Identity at The Catholic University of America (CUA). The conference, jointly sponsored by CUA and St. John's University, is the fourth in a series of five national conferences…

Report of the 2016 Uniform Regional Scab Nursery for spring wheat parents

USDA-ARS?s Scientific Manuscript database

The Uniform Regional Scab Nursery for Spring Wheat Parents (URSN) was grown for the 21st year in 2016. Five locations (Brookings, SD, St. Paul and Crookston, MN, Prosper, ND, and Morden, Canada) reported results. A total of 33 entries was included in the 2016 URSN, in addition to the resistant chec...

The Household Detective Primer: Protecting Your Children from Toxins in the Home. CHEC's Guide to Environmental Childproofing.

ERIC Educational Resources Information Center

Schubert, Sandra; Zelinsky, Benjamin

Designed for parents, this primer presents information on threats to children's health that can be found in every American home, including disinfectants, art supplies, pesticides, and toxins in food and drinking water. The primer also provides practical information on safe and environmentally friendly household cleaners and disinfectants, outlines…

Passepartout Sherpa - A low-cost, reusable transportation system into the stratosphere for small experiments

NASA Astrophysics Data System (ADS)

Taraba, M.; Fauland, H.; Turetschek, T.; Stumptner, W.; Kudielka, V.; Scheer, D.; Sattler, B.; Fritz, A.; Stingl, B.; Fuchs, H.; Gubo, B.; Hettrich, S.; Hirtl, A.; Unger, E.; Soucek, A.; Frischauf, N.; Grömer, G.

2014-12-01

The Passepartout sounding balloon transportation system for low-mass (< 1200 g) experiments or hardware for validation to an altitude of 35 km is described. We present the general flight configuration, set-up of the flight control system, environmental and position sensors, power system, buoyancy considerations as well as the ground control infrastructure including recovery operations. In the telemetry and command module the integrated airborne computer is able to control the experiment, transmit telemetry and environmental data and allows for a duplex communication to a control centre for tele-commanding. The experiment module is mounted below the telemetry and command module and can either work as a standalone system or be controlled by the airborne computer. This spacing between experiment- and control unit allows for a high flexibility in the experiment design. After a parachute landing, the on-board satellite based recovery subsystems allow for a rapid tracking and recovery of the telemetry and command module and the experiment. We discuss flight data and lessons learned from two representative flights with research payloads.

Adaptive signal processing at NOSC

NASA Astrophysics Data System (ADS)

Albert, T. R.

1992-03-01

Adaptive signal processing work at the Naval Ocean Systems Center (NOSC) dates back to the late 1960s. It began as an IR/IED project by John McCool, who made use of an adaptive algorithm that had been developed by Professor Bernard Widrow of Stanford University. In 1972, a team lead by McCool built the first hardware implementation of the algorithm that could process in real-time at acoustic bandwidths. Early tests with the two units that were built were extremely successful, and attracted much attention. Sponsors from different commands provided funding to develop hardware for submarine, surface ship, airborne, and other systems. In addition, an effort was initiated to analyze performance and behavior of the algorithm. Most of the hardware development and analysis efforts were active through the 1970s, and a few into the 1980s. One of the original programs continues to this date.

Hardware fault insertion and instrumentation system: Mechanization and validation

NASA Technical Reports Server (NTRS)

Benson, J. W.

1987-01-01

Automated test capability for extensive low-level hardware fault insertion testing is developed. The test capability is used to calibrate fault detection coverage and associated latency times as relevant to projecting overall system reliability. Described are modifications made to the NASA Ames Reconfigurable Flight Control System (RDFCS) Facility to fully automate the total test loop involving the Draper Laboratories' Fault Injector Unit. The automated capability provided included the application of sequences of simulated low-level hardware faults, the precise measurement of fault latency times, the identification of fault symptoms, and bulk storage of test case results. A PDP-11/60 served as a test coordinator, and a PDP-11/04 as an instrumentation device. The fault injector was controlled by applications test software in the PDP-11/60, rather than by manual commands from a terminal keyboard. The time base was especially developed for this application to use a variety of signal sources in the system simulator.

Power Efficient Hardware Architecture of SHA-1 Algorithm for Trusted Mobile Computing

NASA Astrophysics Data System (ADS)

Kim, Mooseop; Ryou, Jaecheol

The Trusted Mobile Platform (TMP) is developed and promoted by the Trusted Computing Group (TCG), which is an industry standard body to enhance the security of the mobile computing environment. The built-in SHA-1 engine in TMP is one of the most important circuit blocks and contributes the performance of the whole platform because it is used as key primitives supporting platform integrity and command authentication. Mobile platforms have very stringent limitations with respect to available power, physical circuit area, and cost. Therefore special architecture and design methods for low power SHA-1 circuit are required. In this paper, we present a novel and efficient hardware architecture of low power SHA-1 design for TMP. Our low power SHA-1 hardware can compute 512-bit data block using less than 7,000 gates and has a power consumption about 1.1 mA on a 0.25μm CMOS process.

Langley Storage facility which houses remains of Apollo 204 craft

NASA Technical Reports Server (NTRS)

1990-01-01

A warehouse holding Apollo 204 hardware and investigative data is seen at Langley Research Center in Virginia. The command module, damaged in the 1967 Apollo fire, its heat shield, booster protective cover and 81 cartons of data and other related materials occupy 3,300 cubic feet. Astronauts Virgil I. Grissom, Roger B. Chaffee and Edward H. White II perished in the Apollo 204 spacecraft fire on Jan. 27, 1967 on Launch Complex 34 at Cape Canaveral. The hardware has been stored at Langley since 1967. PLEASE NOTE UPDATE: In early May of 1990, NASA announced plans to move the hardware and related data to permanent storage with the Challenger debris in an abandoned missile silo at Cape Canaveral Air Force Station (CCAFS), Florida. However, at month's end, NASA announced it had decided to keep the capsule at Langley for an indefinite period of time.

Langley Storage facility which houses remains of Apollo 204 craft

NASA Technical Reports Server (NTRS)

1990-01-01

Part of 81 cartons of Apollo 204 hardware and investigation data are seen in storage at Langley Research Center in Virginia. The command module, damaged in the 1967 Apollo fire, its heat shield, booster protective cover and the cartons occupy 3,300 cubic feet of Langley's storage space. Astronauts Virgil I. Grissom, Roger B. Chaffee and Edward H. White II perished in the Apollo 204 spacecraft fire on Jan. 27, 1967 on Launch Complex 34, Cape Canaveral. The hardware has been stored at Langley since 1967. PLEASE NOTE UPDATE: In early May of 1990, NASA announced plans to move the hardware and related data to permanent storage with the Challenger debris in an abandoned missile silo at Cape Canaveral Air Force Station (CCAFS), Florida. However, at month's end, NASA announced it had decided to keep the capsule at Langley for an indefinite period of time.

Ground Operations Aerospace Language (GOAL). Volume 3: Data bank

NASA Technical Reports Server (NTRS)

1973-01-01

The GOAL (Ground Operations Aerospace Language) test programming language was developed for use in ground checkout operations in a space vehicle launch environment. To insure compatibility with a maximum number of applications, a systematic and error-free method of referencing command/response (analog and digital) hardware measurements is a principle feature of the language. Central to the concept of requiring the test language to be independent of launch complex equipment and terminology is that of addressing measurements via symbolic names that have meaning directly in the hardware units being tested. To form the link from test program through test system interfaces to the units being tested the concept of a data bank has been introduced. The data bank is actually a large cross-reference table that provides pertinent hardware data such as interface unit addresses, data bus routings, or any other system values required to locate and access measurements.

A spacecraft computer repairable via command.

NASA Technical Reports Server (NTRS)

Fimmel, R. O.; Baker, T. E.

1971-01-01

The MULTIPAC is a central data system developed for deep-space probes with the distinctive feature that it may be repaired during flight via command and telemetry links by reprogramming around the failed unit. The computer organization uses pools of identical modules which the program organizes into one or more computers called processors. The interaction of these modules is dynamically controlled by the program rather than hardware. In the event of a failure, new programs are entered which reorganize the central data system with a somewhat reduced total processing capability aboard the spacecraft. Emphasis is placed on the evolution of the system architecture and the final overall system design rather than the specific logic design.

Realization of Intelligent Measurement and Control System for Limb Rehabilitation Based on PLC and Touch Screen

NASA Astrophysics Data System (ADS)

Liu, Xiangquan

According to the treatment needs of patients with limb movement disorder, on the basis of the limb rehabilitative training prototype, function of measure and control system are analyzed, design of system hardware and software is completed. The touch screen which is adopt as host computer and man-machine interaction window is responsible for sending commands and training information display; The PLC which is adopt as slave computer is responsible for receiving control command from touch screen, collecting the sensor data, regulating torque and speed of motor by analog output according to the different training mode, realizing ultimately active and passive training for limb rehabilitation therapy.

Controlling Laboratory Processes From A Personal Computer

NASA Technical Reports Server (NTRS)

Will, H.; Mackin, M. A.

1991-01-01

Computer program provides natural-language process control from IBM PC or compatible computer. Sets up process-control system that either runs without operator or run by workers who have limited programming skills. Includes three smaller programs. Two of them, written in FORTRAN 77, record data and control research processes. Third program, written in Pascal, generates FORTRAN subroutines used by other two programs to identify user commands with device-driving routines written by user. Also includes set of input data allowing user to define user commands to be executed by computer. Requires personal computer operating under MS-DOS with suitable hardware interfaces to all controlled devices. Also requires FORTRAN 77 compiler and device drivers written by user.

Modeling to Improve the Risk Reduction Process for Command File Errors

NASA Technical Reports Server (NTRS)

Meshkat, Leila; Bryant, Larry; Waggoner, Bruce

2013-01-01

The Jet Propulsion Laboratory has learned that even innocuous errors in the spacecraft command process can have significantly detrimental effects on a space mission. Consequently, such Command File Errors (CFE), regardless of their effect on the spacecraft, are treated as significant events for which a root cause is identified and corrected. A CFE during space mission operations is often the symptom of imbalance or inadequacy within the system that encompasses the hardware and software used for command generation as well as the human experts and processes involved in this endeavor. As we move into an era of increased collaboration with other NASA centers and commercial partners, these systems become more and more complex. Consequently, the ability to thoroughly model and analyze CFEs formally in order to reduce the risk they pose is increasingly important. In this paper, we summarize the results of applying modeling techniques previously developed to the DAWN flight project. The original models were built with the input of subject matter experts from several flight projects. We have now customized these models to address specific questions for the DAWN flight project and formulating use cases to address their unique mission needs. The goal of this effort is to enhance the project's ability to meet commanding reliability requirements for operations and to assist them in managing their Command File Errors.

Swanson in U.S. Laboratory

NASA Image and Video Library

2014-09-02

ISS040-E-123259 (2 Sept. 2014) --- NASA astronaut Steve Swanson, Expedition 40 commander, prepares to set up the Portable Pulmonary Function System hardware for Sprint VO2max sessions in the Destiny laboratory of the International Space Station. The Sprint experiment measures the effectiveness of high-intensity, low-volume exercise training in minimizing the loss of muscle mass and bone density that occurs during spaceflight.

Swanson in U.S. Laboratory

NASA Image and Video Library

2014-09-02

ISS040-E-123262 (2 Sept. 2014) --- NASA astronaut Steve Swanson, Expedition 40 commander, sets up the Portable Pulmonary Function System hardware for Sprint VO2max sessions in the Destiny laboratory of the International Space Station. The Sprint experiment measures the effectiveness of high-intensity, low-volume exercise training in minimizing the loss of muscle mass and bone density that occurs during spaceflight.

New Tools for a New Terrain Air Force Support to Special Operations in the Cyber Environment

DTIC Science & Technology

2016-08-01

54 3 PREFACE As a career targeteer for the US...capabilities of a toolkit of cyber options, from hardware on the front lines to “digital reachback” relationships with USCYBERCOM, is to leave...of career fields, including, but not limited to, cyberspace operations, intelligence, aircrew operations, command and control systems operations, and

STS-105 Crew Training in VR Lab

NASA Image and Video Library

2001-03-15

JSC2001-00751 (15 March 2001) --- Astronaut Scott J. Horowitz, STS-105 mission commander, uses the virtual reality lab at the Johnson Space Center (JSC) to train for his duties aboard the Space Shuttle Discovery. This type of computer interface paired with virtual reality training hardware and software helps to prepare the entire team for dealing with International Space Station (ISS) elements.

PromISS 4 hardware set up in the MSG during Expedition 12

NASA Image and Video Library

2006-01-18

ISS012-E-16162 (18 Jan. 2006) --- Astronaut William S. (Bill) McArthur, Expedition 12 commander and NASA space station science officer, configures the Microgravity Science Glovebox (MSG) facility to prepare for the installation and activation of the Protein Crystal Growth Monitoring by Digital Holographic Microscope (PromISS) experiment in the Destiny laboratory on the International Space Station.

Kelly works on the MSG

NASA Image and Video Library

2010-12-27

ISS026-E-022582 (27 Dec. 2010) --- NASA astronaut Scott Kelly, Expedition 26 commander, works with Capillary Channel Flow (CCF) experiment hardware in the Microgravity Science Glovebox (MSG) in the Destiny laboratory of the International Space Station. CCF is a versatile experiment for studying a critical variety of inertial-capillary dominated flows key to spacecraft systems that cannot be studied on the ground.

PromISS 4 hardware set up in the MSG during Expedition 12

NASA Image and Video Library

2006-01-19

ISS012-E-16237 (19 Jan. 2006) --- Astronaut William S. (Bill) McArthur, Expedition 12 commander and NASA space station science officer, configures the Microgravity Science Glovebox (MSG) facility to prepare for the installation and activation of the Protein Crystal Growth Monitoring by Digital Holographic Microscope (PromISS) experiment in the Destiny laboratory on the International Space Station.

PromISS 4 hardware set up in the MSG during Expedition 12

NASA Image and Video Library

2006-01-19

ISS012-E-16245 (19 Jan. 2006) --- Astronaut William S. (Bill) McArthur, Expedition 12 commander and NASA space station science officer, configures the Microgravity Science Glovebox (MSG) facility to prepare for the installation and activation of the Protein Crystal Growth Monitoring by Digital Holographic Microscope (PromISS) experiment in the Destiny laboratory on the International Space Station.

Kelly works on the MSG

NASA Image and Video Library

2010-12-27

ISS026-E-022581 (27 Dec. 2010) --- NASA astronaut Scott Kelly, Expedition 26 commander, works with Capillary Channel Flow (CCF) experiment hardware in the Microgravity Science Glovebox (MSG) in the Destiny laboratory of the International Space Station. CCF is a versatile experiment for studying a critical variety of inertial-capillary dominated flows key to spacecraft systems that cannot be studied on the ground.

SSRL Emergency Response Shore Tool

NASA Technical Reports Server (NTRS)

Mah, Robert W.; Papasin, Richard; McIntosh, Dawn M.; Denham, Douglas; Jorgensen, Charles; Betts, Bradley J.; Del Mundo, Rommel

2006-01-01

The SSRL Emergency Response Shore Tool (wherein SSRL signifies Smart Systems Research Laboratory ) is a computer program within a system of communication and mobile-computing software and hardware being developed to increase the situational awareness of first responders at building collapses. This program is intended for use mainly in planning and constructing shores to stabilize partially collapsed structures. The program consists of client and server components, runs in the Windows operating system on commercial off-the-shelf portable computers, and can utilize such additional hardware as digital cameras and Global Positioning System devices. A first responder can enter directly, into a portable computer running this program, the dimensions of a required shore. The shore dimensions, plus an optional digital photograph of the shore site, can then be uploaded via a wireless network to a server. Once on the server, the shore report is time-stamped and made available on similarly equipped portable computers carried by other first responders, including shore wood cutters and an incident commander. The staff in a command center can use the shore reports and photographs to monitor progress and to consult with structural engineers to assess whether a building is in imminent danger of further collapse.

Microbial load monitor

NASA Technical Reports Server (NTRS)

Caplin, R. S.; Royer, E. R.

1978-01-01

Attempts are made to provide a total design of a Microbial Load Monitor (MLM) system flight engineering model. Activities include assembly and testing of Sample Receiving and Card Loading Devices (SRCLDs), operator related software, and testing of biological samples in the MLM. Progress was made in assembling SRCLDs with minimal leaks and which operate reliably in the Sample Loading System. Seven operator commands are used to control various aspects of the MLM such as calibrating and reading the incubating reading head, setting the clock and reading time, and status of Card. Testing of the instrument, both in hardware and biologically, was performed. Hardware testing concentrated on SRCLDs. Biological testing covered 66 clinical and seeded samples. Tentative thresholds were set and media performance listed.

Outsourcing Turns IT Leaders into the New Air Traffic Controllers

ERIC Educational Resources Information Center

Raths, David

2010-01-01

Many chief information officers (CIOs) have come to accept and even embrace the role of outsourcers in their portfolio of IT services. In 2009, 47 percent of the 352 CIOs surveyed by the Center for Higher Education Chief Information Officer Studies (CHECS) said they had selectively outsourced some part of the IT function, up from 43 percent the…

"Deja vu All over Again": Commentary on the Catholic Higher Education Collaborative Conference on Leadership at Loyola University Chicago

ERIC Educational Resources Information Center

Schuttloffel, Merylann J.

2010-01-01

In fall 2007, nine Catholic colleges and universities began a collaborative process to explore ways Catholic institutions of higher education (CIHE) could increase effective support of pre-K-12 Catholic schools. This new organization, Catholic Higher Education Collaborative (CHEC), committed to hosting a series of six conferences focused on…

Effective Alcohol, Tobacco and Other Drug Intervention and Prevention Using Online Game-Based, E-Learning: An Evidence-Informed Program That Works

ERIC Educational Resources Information Center

Schweizer, Heidi; Hayslett, Carrianne; Bansal, Naveen; Ronco, Sharron; Schafer, Richard

2014-01-01

Background: The host of costly individual and societal consequences of alcohol, tobacco, and other drugs (ATOD) use underscores the importance of ATOD prevention education. "It's Up 2U" is an evidence-informed, game-based, e-learning ATOD prevention program developed by Children's Health Education Center (CHEC) targeting middle school…

Sample Analysis at Mars Instrument Simulator

NASA Technical Reports Server (NTRS)

Benna, Mehdi; Nolan, Tom

2013-01-01

The Sample Analysis at Mars Instrument Simulator (SAMSIM) is a numerical model dedicated to plan and validate operations of the Sample Analysis at Mars (SAM) instrument on the surface of Mars. The SAM instrument suite, currently operating on the Mars Science Laboratory (MSL), is an analytical laboratory designed to investigate the chemical and isotopic composition of the atmosphere and volatiles extracted from solid samples. SAMSIM was developed using Matlab and Simulink libraries of MathWorks Inc. to provide MSL mission planners with accurate predictions of the instrument electrical, thermal, mechanical, and fluid responses to scripted commands. This tool is a first example of a multi-purpose, full-scale numerical modeling of a flight instrument with the purpose of supplementing or even eliminating entirely the need for a hardware engineer model during instrument development and operation. SAMSIM simulates the complex interactions that occur between the instrument Command and Data Handling unit (C&DH) and all subsystems during the execution of experiment sequences. A typical SAM experiment takes many hours to complete and involves hundreds of components. During the simulation, the electrical, mechanical, thermal, and gas dynamics states of each hardware component are accurately modeled and propagated within the simulation environment at faster than real time. This allows the simulation, in just a few minutes, of experiment sequences that takes many hours to execute on the real instrument. The SAMSIM model is divided into five distinct but interacting modules: software, mechanical, thermal, gas flow, and electrical modules. The software module simulates the instrument C&DH by executing a customized version of the instrument flight software in a Matlab environment. The inputs and outputs to this synthetic C&DH are mapped to virtual sensors and command lines that mimic in their structure and connectivity the layout of the instrument harnesses. This module executes, and thus validates, complex command scripts prior to their up-linking to the SAM instrument. As an output, this module generates synthetic data and message logs at a rate that is similar to the actual instrument.

Intelligent Systems and Advanced User Interfaces for Design, Operation, and Maintenance of Command Management Systems

NASA Technical Reports Server (NTRS)

Mitchell, Christine M.

1998-01-01

Historically Command Management Systems (CMS) have been large, expensive, spacecraft-specific software systems that were costly to build, operate, and maintain. Current and emerging hardware, software, and user interface technologies may offer an opportunity to facilitate the initial formulation and design of a spacecraft-specific CMS as well as a to develop a more generic or a set of core components for CMS systems. Current MOC (mission operations center) hardware and software include Unix workstations, the C/C++ and Java programming languages, and X and Java window interfaces representations. This configuration provides the power and flexibility to support sophisticated systems and intelligent user interfaces that exploit state-of-the-art technologies in human-machine systems engineering, decision making, artificial intelligence, and software engineering. One of the goals of this research is to explore the extent to which technologies developed in the research laboratory can be productively applied in a complex system such as spacecraft command management. Initial examination of some of the issues in CMS design and operation suggests that application of technologies such as intelligent planning, case-based reasoning, design and analysis tools from a human-machine systems engineering point of view (e.g., operator and designer models) and human-computer interaction tools, (e.g., graphics, visualization, and animation), may provide significant savings in the design, operation, and maintenance of a spacecraft-specific CMS as well as continuity for CMS design and development across spacecraft with varying needs. The savings in this case is in software reuse at all stages of the software engineering process.

Modular open RF architecture: extending VICTORY to RF systems

NASA Astrophysics Data System (ADS)

Melber, Adam; Dirner, Jason; Johnson, Michael

2015-05-01

Radio frequency products spanning multiple functions have become increasingly critical to the warfighter. Military use of the electromagnetic spectrum now includes communications, electronic warfare (EW), intelligence, and mission command systems. Due to the urgent needs of counterinsurgency operations, various quick reaction capabilities (QRCs) have been fielded to enhance warfighter capability. Although these QRCs were highly successfully in their respective missions, they were designed independently resulting in significant challenges when integrated on a common platform. This paper discusses how the Modular Open RF Architecture (MORA) addresses these challenges by defining an open architecture for multifunction missions that decomposes monolithic radio systems into high-level components with welldefined functions and interfaces. The functional decomposition maximizes hardware sharing while minimizing added complexity and cost due to modularization. MORA achieves significant size, weight and power (SWaP) savings by allowing hardware such as power amplifiers and antennas to be shared across systems. By separating signal conditioning from the processing that implements the actual radio application, MORA exposes previously inaccessible architecture points, providing system integrators with the flexibility to insert third-party capabilities to address technical challenges and emerging requirements. MORA leverages the Vehicular Integration for Command, Control, Communication, Computers, Intelligence, Surveillance, and Reconnaissance (C4ISR)/EW Interoperability (VICTORY) framework. This paper concludes by discussing how MORA, VICTORY and other standards such as OpenVPX are being leveraged by the U.S. Army Research, Development, and Engineering Command (RDECOM) Communications Electronics Research, Development, and Engineering Center (CERDEC) to define a converged architecture enabling rapid technology insertion, interoperability and reduced SWaP.

The ISS Fluids Integrated Rack (FIR): a Summary of Capabilities

NASA Astrophysics Data System (ADS)

Gati, F.; Hill, M. E.

2002-01-01

The Fluids Integrated Rack (FIR) is a modular, multi-user scientific research facility that will fly in the U.S. laboratory module, Destiny, of the International Space Station (ISS). The FIR will be one of the two racks that will make up the Fluids and Combustion Facility (FCF) - the other being the Combustion Integrated Rack (CIR). The ISS will provide the FCF with the necessary resources, such as power and cooling. While the ISS crew will be available for experiment operations, their time will be limited. The FCF is, therefore, being designed for autonomous operations and remote control operations. Control of the FCF will be primarily through the Telescience Support Center (TSC) at the Glenn Research Center. The FCF is being designed to accommodate a wide range of combustion and fluids physics experiments within the ISS resources and constraints. The primary mission of the FIR, however, is to accommodate experiments from four major fluids physics disciplines: Complex Fluids; Multiphase Flow and Heat Transfer; Interfacial Phenomena; and Dynamics and Stability. The design of the FIR is flexible enough to accommodate experiments from other science disciplines such as Biotechnology. The FIR flexibility is a result of the large volume dedicated for experimental hardware, easily re-configurable diagnostics that allow for unique experiment configurations, and it's customizable software. The FIR will utilize six major subsystems to accommodate this broad scope of fluids physics experiments. The major subsystems are: structural, environmental, electrical, gaseous, command and data management, and imagers and illumination. Within the rack, the FIR's structural subsystem provides an optics bench type mechanical interface for the precise mounting of experimental hardware; including optical components. The back of the bench is populated with FIR avionics packages and light sources. The interior of the rack is isolated from the cabin through two rack doors that are hinged near the top and bottom of the rack. Transmission of micro-gravity disturbances to and from the rack is minimized through the Active Rack Isolation System (ARIS). The environmental subsystem will utilize air and water to remove heat generated by facility and experimental hardware. The air will be circulated throughout the rack and will be cooled by an air-water heat exchanger. Water will be used directly to cool some of the FIR components and will also be available to cool experiment hardware as required. The electrical subsystem includes the Electrical Power Control Unit (EPCU), which provides 28 VDC and 120 VDC power to the facility and the experiment hardware. The EPCU will also provide power management and control functions, as well as fault protection capabilities. The FIR will provide access to the ISS gaseous nitrogen and vacuum systems. These systems are available to support experiment operations such as the purging of experimental cells, creating flows within experimental cells and providing dry conditions where needed. The FIR Command and Data Management subsystem (CDMS) provides command and data handling for both facility and experiment hardware. The Input Output Processor (IOP) provides the overall command and data management functions for the rack including downlinking or writing data to removable drives. The IOP will also monitor the health and status of the rack subsystems. The Image Processing and Storage Units (IPSU) will perform diagnostic control and image data acquisition functions. An IPSU will be able to control a digital camera, receive image data from that camera and process/ compress image data as necessary. The Fluids Science and Avionics Package (FSAP) will provide the primary control over an experiment. The FSAP contains various computer boards/cards that will perform data and control functions. To support the imaging needs, cameras and illumination sources will be available to the investigator. Both color analog and black and white digital cameras with lenses are expected. These cameras will be capable of high resolution and, separately, frame rates up to 32,000 frames per second. Lenses for these cameras will provide both microscopic and macroscopic views. The FIR will provide two illumination sources, a 532 nm Nd:YAG laser and a white light source, both with adjustable power output. The FIR systems are being designed to maximize the amount of science that can be done on-orbit. Experiments will be designed and efficiently operated. Each individual experiment must determine the best configuration of utilizing facility capabilities and resources with augmentation of specific experiment hardware. Efficient operations will be accomplished via a combination of on-orbit physical component change-outs or processing by the crew, and software updates via ground commanding or by the crew. Careful coordination by ground and on-orbit personnel regarding the on-orbit storage and downlinking of image data will also be very important.

Tracker controls development and control architecture for the Hobby-Eberly Telescope Wide Field Upgrade

NASA Astrophysics Data System (ADS)

Mock, Jason R.; Beno, Joe; Rafferty, Tom H.; Cornell, Mark E.

2010-07-01

To enable the Hobby-Eberly Telescope Wide Field Upgrade, the University of Texas Center for Electromechanics and McDonald Observatory are developing a precision tracker system - a 15,000 kg robot to position a 3,100 kg payload within 10 microns of a desired dynamic track. Performance requirements to meet science needs and safety requirements that emerged from detailed Failure Modes and Effects Analysis resulted in a system of 14 precision controlled actuators and 100 additional analog and digital devices (primarily sensors and safety limit switches). This level of system complexity and emphasis on fail-safe operation is typical of large modern telescopes and numerous industrial applications. Due to this complexity, demanding accuracy requirements, and stringent safety requirements, a highly versatile and easily configurable centralized control system that easily links with modeling and simulation tools during the hardware and software design process was deemed essential. The Matlab/Simulink simulation environment, coupled with dSPACE controller hardware, was selected for controls development and realization. The dSPACE real-time operating system collects sensor information; motor commands are transmitted over a PROFIBUS network to servo amplifiers and drive motor status is received over the same network. Custom designed position feedback loops, supplemented by feed forward force commands for enhanced performance, and algorithms to accommodate self-locking gearboxes (for safety), reside in dSPACE. To interface the dSPACE controller directly to absolute Heidenhain sensors with EnDat 2.2 protocol, a custom communication board was developed. This paper covers details of software and hardware, design choices and analysis, and supporting simulations (primarily Simulink).

STS-120 crew along with Expedition crew members Dan Tani and Sandra Magnus

NASA Image and Video Library

2007-08-09

JSC2007-E-41539 (9 Aug. 2007) --- Astronaut Pamela A. Melroy, STS-120 commander, uses the virtual reality lab at Johnson Space Center to train for her duties aboard the space shuttle and space station. This type of computer interface, paired with virtual reality training hardware and software, helps to prepare the entire team for dealing with space station elements.

STS-111 Training in VR lab with Expedition IV and V Crewmembers

NASA Image and Video Library

2001-10-18

JSC2001-E-39090 (18 October 2001) --- Cosmonaut Valeri G. Korzun, Expedition Five mission commander representing Rosaviakosmos, uses the virtual reality lab at the Johnson Space Center (JSC) to train for his duties on the International Space Station (ISS). This type of computer interface paired with virtual reality training hardware and software helps the entire team for dealing with ISS elements.

STS-120 crew along with Expedition crew members Dan Tani and Sandra Magnus

NASA Image and Video Library

2007-08-09

JSC2007-E-41531 (9 Aug. 2007) --- Astronaut Pamela A. Melroy, STS-120 commander, uses the virtual reality lab at Johnson Space Center to train for her duties aboard the space shuttle and space station. This type of computer interface, paired with virtual reality training hardware and software, helps to prepare the entire team for dealing with space station elements.

STS-43 crewmembers perform various tasks on OV-104's aft flight deck

NASA Image and Video Library

1991-08-11

STS043-37-012 (2-11 Aug 1991) --- Three STS-43 astronauts are busy at work onboard the earth-orbiting space shuttle Atlantis. Astronaut Shannon W. Lucid is pictured performing one of several tests on Computer hardware with space station applications in mind. Sharing the aft flight deck with Lucid are Michael A. Baker (left), pilot and John E. Blaha, mission commander.

An Analysis of Unplanned Requirements and Their Impact on the Naval Electronic Systems Command

DTIC Science & Technology

1976-06-01

Evaluation Repair Turnaround Time Ship Alteration Management Information System Shipbuilding and Conversion, Navy Standard Hardware Program Ships Parts...pending assigment of a NSN. Such equipments would have little opportunity to accumulate any demand history. Secondly, the relatively low percentage of...mentioned above. Unfortunately, sufficient historical information was not available to fully accomplish this goal. In the case of assets acquired from

FD115 (Flight Day 115) SPRINT leg muscle self scan

NASA Image and Video Library

2011-10-03

ISS029-E-025280 (3 Oct. 2011) --- NASA astronaut Mike Fossum, Expedition 29 commander, performs a SPRINT leg muscle self scan in the Columbus laboratory of the International Space Station. Fossum powered on the Ultrasound 2 (USND-2) unit and Video Power Converter (VPC) hardware, and connected the VPC to Human Research Facility 1 (HRF-1) in order to perform this activity.

FD115 (Flight Day 115) SPRINT leg muscle self scan

NASA Image and Video Library

2011-10-03

ISS029-E-025270 (3 Oct. 2011) --- NASA astronaut Mike Fossum, Expedition 29 commander, performs a SPRINT leg muscle self scan in the Columbus laboratory of the International Space Station. Fossum powered on the Ultrasound 2 (USND-2) unit and Video Power Converter (VPC) hardware, and connected the VPC to Human Research Facility 1 (HRF-1) in order to perform this activity.

Independent Orbiter Assessment (IOA): Analysis of the displays and controls subsystem

NASA Technical Reports Server (NTRS)

Trahan, W. H.; Prust, E. E.

1987-01-01

The results of the Independent Orbiter Assessment (IOA) of the Failure Modes and Effects Analysis (FMEA) and Critical Items List (CIL) are presented. The IOA approach features a top-down analysis of the hardware to determine failure modes, criticality, and potential critical items. To preserve independence, this analysis was accomplished without reliance upon the results contained within the NASA FMEA/CIL documentation. This report documents the independent analysis results corresponding to the Orbiter Displays and Controls (D and C) subsystem hardware. The function of the D and C hardware is to provide the crew with the monitor, command, and control capabilities required for management of all normal and contingency mission and flight operations. The D and C hardware for which failure modes analysis was performed consists of the following: Acceleration Indicator (G-METER); Head Up Display (HUD); Display Driver Unit (DDU); Alpha/Mach Indicator (AMI); Horizontal Situation Indicator (HSI); Attitude Director Indicator (ADI); Propellant Quantity Indicator (PQI); Surface Position Indicator (SPI); Altitude/Vertical Velocity Indicator (AVVI); Caution and Warning Assembly (CWA); Annunciator Control Assembly (ACA); Event Timer (ET); Mission Timer (MT); Interior Lighting; and Exterior Lighting. Each hardware item was evaluated and analyzed for possible failure modes and effects. Criticality was assigned based upon the severity of the effect for each failure mode.

Independent Orbiter Assessment (IOA): Analysis of the manned maneuvering unit

NASA Technical Reports Server (NTRS)

Bailey, P. S.

1986-01-01

Results of the Independent Orbiter Assessment (IOA) of the Failure Modes and Effects Analysis (FMEA) and Critical Items List (CIL) are presented. The IOA approach features a top-down analysis of the hardware to determine failure modes, criticality, and potential critical items (PCIs). To preserve indepedence, this analysis was accomplished without reliance upon the results contained within the NASA FMEA/CIL documentation. This report documents the independent analysis results corresponding to the Manned Maneuvering Unit (MMU) hardware. The MMU is a propulsive backpack, operated through separate hand controllers that input the pilot's translational and rotational maneuvering commands to the control electronics and then to the thrusters. The IOA analysis process utilized available MMU hardware drawings and schematics for defining hardware subsystems, assemblies, components, and hardware items. Final levels of detail were evaluated and analyzed for possible failure modes and effects. Criticality was assigned based upon the worst case severity of the effect for each identified failure mode. The IOA analysis of the MMU found that the majority of the PCIs identified are resultant from the loss of either the propulsion or control functions, or are resultant from inability to perform an immediate or future mission. The five most severe criticalities identified are all resultant from failures imposed on the MMU hand controllers which have no redundancy within the MMU.

The AST3 controlling and operating software suite for automatic sky survey

NASA Astrophysics Data System (ADS)

Hu, Yi; Shang, Zhaohui; Ma, Bin; Hu, Keliang

2016-07-01

We have developed a specialized software package, called ast3suite, to achieve the remote control and automatic sky survey for AST3 (Antarctic Survey Telescope) from scratch. It includes several daemon servers and many basic commands. Each program does only one single task, and they work together to make AST3 a robotic telescope. A survey script calls basic commands to carry out automatic sky survey. Ast3suite was carefully tested in Mohe, China in 2013 and has been used at Dome, Antarctica in 2015 and 2016 with the real hardware for practical sky survey. Both test results and practical using showed that ast3suite had worked very well without any manual auxiliary as we expected.

Evaluation of Electromechanical Systems Dynamically Emulating a Candidate Hydrokinetic Turbine

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

Cavagnaro, Robert J.; Neely, Jason C.; Fay, Franois-Xavier

The use of controllable motor-generator sets to emulate the dynamics of a hydrokinetic turbine is evaluated as an alternative to field testing a prototype. The emulator control dynamic equations are presented, methods for scaling turbine parameters are examined, and experimental results are presented from three electromechanical emulation machines (EEMs) programmed to emulate the same vertical-axis fixed-pitch turbine. Although hardware platforms and control implementations varied, results show that each EEM is successful in emulating the turbine model, thus demonstrating the general feasibility of the approach. However, performance of motor control under torque command, current command or speed command differed. In onemore » of the EEMs evaluated, the power take off controller tracks the maximum power-point of the turbine in response to turbulence. Utilizing realistic inflow conditions and control laws, the emulator dynamic speed response is shown to agree well at low frequencies with numerical simulation but to deviate at high frequencies.« less

Evaluation of Electromechanical Systems Dynamically Emulating a Candidate Hydrokinetic Turbine

DOE PAGES

Cavagnaro, Robert J.; Neely, Jason C.; Fay, Franois-Xavier; ...

2016-11-06

The use of controllable motor-generator sets to emulate the dynamics of a hydrokinetic turbine is evaluated as an alternative to field testing a prototype. The emulator control dynamic equations are presented, methods for scaling turbine parameters are examined, and experimental results are presented from three electromechanical emulation machines (EEMs) programmed to emulate the same vertical-axis fixed-pitch turbine. Although hardware platforms and control implementations varied, results show that each EEM is successful in emulating the turbine model, thus demonstrating the general feasibility of the approach. However, performance of motor control under torque command, current command or speed command differed. In onemore » of the EEMs evaluated, the power take off controller tracks the maximum power-point of the turbine in response to turbulence. Utilizing realistic inflow conditions and control laws, the emulator dynamic speed response is shown to agree well at low frequencies with numerical simulation but to deviate at high frequencies.« less

The K9 On-Board Rover Architecture

NASA Technical Reports Server (NTRS)

Bresina, John L.; Bualat, Maria; Fair, Michael; Washington, Richard; Wright, Anne

2006-01-01

This paper describes the software architecture of NASA Ames Research Center s K9 rover. The goal of the onboard software architecture team was to develop a modular, flexible framework that would allow both high- and low-level control of the K9 hardware. Examples of low-level control are the simple drive or pan/tilt commands which are handled by the resource managers, and examples of high-level control are the command sequences which are handled by the conditional executive. In between these two control levels are complex behavioral commands which are handled by the pilot, such as drive to goal with obstacle avoidance or visually servo to a target. This paper presents the design of the architecture as of Fall 2000. We describe the state of the architecture implementation as well as its current evolution. An early version of the architecture was used for K9 operations during a dual-rover field experiment conducted by NASA Ames Research Center (ARC) and the Jet Propulsion Laboratory (JPL) from May 14 to May 16, 2000.

KSC-97PC948

NASA Image and Video Library

1997-06-28

STS-94 Commander James D. Halsell, Jr., speaks to the media at the Shuttle Landing Facility after the crew arrived at Kennedy Space Center in preparation for the reflight of the Microgravity Science Laboratory-1 mission. Launch is scheduled for July 1, 1997, at 2:37 p.m. EDT. From left to right, the crew members are Payload Specialists Gregory T. Linteris and Roger K. Crouch; Mission Specialists Michael L. Gernhardt and Donald A. Thomas; Payload Commander Janice E. Voss; Pilot Susan Leigh Still and Commander James D. Halsell, Jr. One of the T-38 jets aboard which the crew arrived can be seen in the background. The laboratory was scheduled to fly again with the full complement of STS-83 experiments after that mission was cut short due to a faulty fuel cell. During the scheduled 16-day STS-94 mission, the experiments will be used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducts combustion, protein crystal growth and materials processing experiments

Concurrent simulation of a parallel jaw end effector

NASA Technical Reports Server (NTRS)

Bynum, Bill

1985-01-01

A system of programs developed to aid in the design and development of the command/response protocol between a parallel jaw end effector and the strategic planner program controlling it are presented. The system executes concurrently with the LISP controlling program to generate a graphical image of the end effector that moves in approximately real time in response to commands sent from the controlling program. Concurrent execution of the simulation program is useful for revealing flaws in the communication command structure arising from the asynchronous nature of the message traffic between the end effector and the strategic planner. Software simulation helps to minimize the number of hardware changes necessary to the microprocessor driving the end effector because of changes in the communication protocol. The simulation of other actuator devices can be easily incorporated into the system of programs by using the underlying support that was developed for the concurrent execution of the simulation process and the communication between it and the controlling program.

AMS,Chang-Diaz works with computers in the middeck

NASA Image and Video Library

2016-08-24

STS091-378-028 (2-12 June 1998) --- Astronaut Franklin R. Chang-Diaz, payload commander, inputs data on a laptop computer associated with the Alpha Magnetic Spectrometer (AMS) hardware located in the aft cargo bay. Reference JSC photo number STS091-367-033, which shows the hardware as seen from Russia's Mir space station, which was docked with Discovery at the time. AMS is the first large magnet experiment ever placed in Earth orbit. The scientific goal of this high-energy physics experiment is to increase our understanding of the composition and origin of the universe. It is designed to search for and measure charged particles, including antimatter, outside Earth's atmosphere. The charge of such particles can be identified by their trajectories in a magnetic field.

A structurally adaptive space crane concept for assembling space systems on orbit

NASA Technical Reports Server (NTRS)

Dorsey, John T.; Sutter, Thomas R.; Wu, K. C.

1992-01-01

A space crane concept is presented which is based on erectable truss hardware to achieve high stiffness and low mass booms and articulating-truss joints which can be assembled on orbit. The hardware is characterized by linear load-deflection response and is structurally predictable. The crane can be reconfigured into different geometries to meet future assembly requirements. Articulating-truss joint concepts with significantly different geometries are analyzed and found to have similar static and dynamic performance, which indicates that criteria other than structural and kinematic performance can be used to select a joint. Passive damping and an open-loop preshaped command input technique greatly enhance the structural damping in the space crane and may preclude the need for an active vibrations suppression system.

Structurally adaptive space crane concept for assembling space systems on orbit

NASA Technical Reports Server (NTRS)

Dorsey, John T.; Sutter, Thomas R.; Wu, K. Chauncey

1992-01-01

Many future human space exploration missions will probably require large vehicles that must be assembled on orbit. Thus, a device that can move, position, and assemble large and massive spacecraft components on orbit becomes essential for these missions. A concept is described for such a device: a space crane concept that uses erectable truss hardware to achieve high-stiffness and low-mass booms and uses articulating truss joints that can be assembled on orbit. The hardware has been tested and shown to have linear load-deflection response and to be structurally predictable. The hardware also permits the crane to be reconfigured into different geometries to satisfy future assembly requirements. A number of articulating and rotary joint concepts have been sized and analyzed, and the results are discussed. Two strategies were proposed to suppress motion-induced vibration: placing viscous dampers in selected truss struts and preshaping motion commands. Preliminary analyses indicate that these techniques have the potential to greatly enhance structural damping.

The best of both worlds : integrating textual and visual command interfaces for Mars Rover Operations

NASA Technical Reports Server (NTRS)

Maxwell, Scott A.; Cooper, Brian; Hartman, Frank; Wright, John; Yen, Jeng; Leger, Chris

2005-01-01

A Mars rover is a complex system, and driving one is a complex endeavor. Rover driver must be intimately familiar with the hardware and software of the mobility system and of the robotic arm. They must rapidly assess threats in the terrain, then creatively combine their knowledge o f the vehicle and its environment to achieve each day's science and engineering objective.

New Hardware for Tethered Balloons,

DTIC Science & Technology

1980-01-01

package contained a differential- pressure switch , and a command receiver. Long wires extended up to the gas valves to actuate them, and a long tube was...similar in appear- ance to the former valve, but does contain batteries, an aneroid- operated switch, and a differential- pressure switch . Design is such...that either the aneroid-operated switch or the differential- pressure switch can be easily removed for checking Or setting in the laboratory. Likewise the

LO-CO-GRAF (Low Cost Graphics): Generating Maps to Support Command and Control/Crisis Management Using Small Computers.

DTIC Science & Technology

1988-03-01

Kernel System (GKS). This combination of hardware and software allows real-time generation of maps using DMA digitized data.[Ref. 4: p. 44, 46] Though...releases are in MST*.BOO. MSV55X.BOO Sanyo MBC-550 with IBM compatible video board MSVAP3.BOO NEC APC3 MSVAPC.BOO NEC APC MSVAPR.BOO ACT Apricot MSVDM2

Expedition 18 Station Development Test Objectives (STDO) Session 1

NASA Image and Video Library

2009-02-19

ISS018-E-033816 (19 Feb. 2009) --- Astronaut Michael Fincke, Expedition 18 commander, removes, cleans and replaces electronic test components on a single test card using Component Repair Equipment (CRE-1) hardware in a portable glovebox facility in the Harmony node of the International Space Station. Fincke unsoldered 1 1/2 components from an integrated circuit board and re-soldered new components including an integrated circuit chip.

Expedition 18 Station Development Test Objectives (STDO) Session 1

NASA Image and Video Library

2009-02-19

ISS018-E-033818 (19 Feb. 2009) --- Astronaut Michael Fincke, Expedition 18 commander, removes, cleans and replaces electronic test components on a single test card using Component Repair Equipment (CRE-1) hardware in a portable glovebox facility in the Harmony node of the International Space Station. Fincke unsoldered 1 1/2 components from an integrated circuit board and re-soldered new components including an integrated circuit chip.

A simple approach to a vision-guided unmanned vehicle

NASA Astrophysics Data System (ADS)

Archibald, Christopher; Millar, Evan; Anderson, Jon D.; Archibald, James K.; Lee, Dah-Jye

2005-10-01

This paper describes the design and implementation of a vision-guided autonomous vehicle that represented BYU in the 2005 Intelligent Ground Vehicle Competition (IGVC), in which autonomous vehicles navigate a course marked with white lines while avoiding obstacles consisting of orange construction barrels, white buckets and potholes. Our project began in the context of a senior capstone course in which multi-disciplinary teams of five students were responsible for the design, construction, and programming of their own robots. Each team received a computer motherboard, a camera, and a small budget for the purchase of additional hardware, including a chassis and motors. The resource constraints resulted in a simple vision-based design that processes the sequence of images from the single camera to determine motor controls. Color segmentation separates white and orange from each image, and then the segmented image is examined using a 10x10 grid system, effectively creating a low resolution picture for each of the two colors. Depending on its position, each filled grid square influences the selection of an appropriate turn magnitude. Motor commands determined from the white and orange images are then combined to yield the final motion command for video frame. We describe the complete algorithm and the robot hardware and we present results that show the overall effectiveness of our control approach.

Expert system for UNIX system reliability and availability enhancement

NASA Astrophysics Data System (ADS)

Xu, Catherine Q.

1993-02-01

Highly reliable and available systems are critical to the airline industry. However, most off-the-shelf computer operating systems and hardware do not have built-in fault tolerant mechanisms, the UNIX workstation is one example. In this research effort, we have developed a rule-based Expert System (ES) to monitor, command, and control a UNIX workstation system with hot-standby redundancy. The ES on each workstation acts as an on-line system administrator to diagnose, report, correct, and prevent certain types of hardware and software failures. If a primary station is approaching failure, the ES coordinates the switch-over to a hot-standby secondary workstation. The goal is to discover and solve certain fatal problems early enough to prevent complete system failure from occurring and therefore to enhance system reliability and availability. Test results show that the ES can diagnose all targeted faulty scenarios and take desired actions in a consistent manner regardless of the sequence of the faults. The ES can perform designated system administration tasks about ten times faster than an experienced human operator. Compared with a single workstation system, our hot-standby redundancy system downtime is predicted to be reduced by more than 50 percent by using the ES to command and control the system.

Expert System for UNIX System Reliability and Availability Enhancement

NASA Technical Reports Server (NTRS)

Xu, Catherine Q.

1993-01-01

Highly reliable and available systems are critical to the airline industry. However, most off-the-shelf computer operating systems and hardware do not have built-in fault tolerant mechanisms, the UNIX workstation is one example. In this research effort, we have developed a rule-based Expert System (ES) to monitor, command, and control a UNIX workstation system with hot-standby redundancy. The ES on each workstation acts as an on-line system administrator to diagnose, report, correct, and prevent certain types of hardware and software failures. If a primary station is approaching failure, the ES coordinates the switch-over to a hot-standby secondary workstation. The goal is to discover and solve certain fatal problems early enough to prevent complete system failure from occurring and therefore to enhance system reliability and availability. Test results show that the ES can diagnose all targeted faulty scenarios and take desired actions in a consistent manner regardless of the sequence of the faults. The ES can perform designated system administration tasks about ten times faster than an experienced human operator. Compared with a single workstation system, our hot-standby redundancy system downtime is predicted to be reduced by more than 50 percent by using the ES to command and control the system.

Medical Operations Support for ISS Operations - The Role of the BME Operations Team Leads

NASA Technical Reports Server (NTRS)

Janney, Rob; Sabatier, Veronica

2010-01-01

This slide presentation reviews the role of the biomedical flight controllers (BMEs), and BME Operations Team Leads (OTLs) in providing medical support for personnel on the International Space Station. This presentation will concentrate on role of the BME OTLs, who provide the integration function across the integration function across all Crew Health Care System (CHeCS) disciplines for operational products and medical procedures.

Development of Hardware-in-the-Loop Simulation Based on Gazebo and Pixhawk for Unmanned Aerial Vehicles

NASA Astrophysics Data System (ADS)

Nguyen, Khoa Dang; Ha, Cheolkeun

2018-04-01

Hardware-in-the-loop simulation (HILS) is well known as an effective approach in the design of unmanned aerial vehicles (UAV) systems, enabling engineers to test the control algorithm on a hardware board with a UAV model on the software. Performance of HILS is determined by performances of the control algorithm, the developed model, and the signal transfer between the hardware and software. The result of HILS is degraded if any signal could not be transferred to the correct destination. Therefore, this paper aims to develop a middleware software to secure communications in HILS system for testing the operation of a quad-rotor UAV. In our HILS, the Gazebo software is used to generate a nonlinear six-degrees-of-freedom (6DOF) model, sensor model, and 3D visualization for the quad-rotor UAV. Meanwhile, the flight control algorithm is designed and implemented on the Pixhawk hardware. New middleware software, referred to as the control application software (CAS), is proposed to ensure the connection and data transfer between Gazebo and Pixhawk using the multithread structure in Qt Creator. The CAS provides a graphical user interface (GUI), allowing the user to monitor the status of packet transfer, and perform the flight control commands and the real-time tuning parameters for the quad-rotor UAV. Numerical implementations have been performed to prove the effectiveness of the middleware software CAS suggested in this paper.

Hardware-in-the-loop projector system for light detection and ranging sensor testing

NASA Astrophysics Data System (ADS)

Kim, Hajin J.; Naumann, Charles B.; Cornell, Michael C.

2012-08-01

Efforts in developing a synthetic environment for testing light detection and ranging (LADAR) sensors in a hardware-in-the-loop simulation are continuing at the Aviation and Missile Research, Engineering, and Development Center of the U.S. Army Research, Engineering and Development Command (RDECOM). Current activities have concentrated on evaluating the optical projection techniques for the LADAR synthetic environment. Schemes for generating the optical signals representing the individual pixels of the projection are of particular interest. Several approaches have been investigated and tested with emphasis on operating wavelength, intensity dynamic range and uniformity, and flexibility in pixel waveform generation. This paper will discuss some of the results from these current efforts at RDECOM's System Simulation and Development Directorate's Electro Optical Technology Development Laboratory.

Current efforts on developing an HWIL synthetic environment for LADAR sensor testing at AMRDEC

NASA Astrophysics Data System (ADS)

Kim, Hajin J.; Cornell, Michael C.; Naumann, Charles B.

2005-05-01

Efforts in developing a synthetic environment for testing LADAR sensors in a hardware-in-the-loop simulation are continuing at the Aviation and Missile Research, Engineering, and Development Center (AMRDEC) of the U.S. Army Research, Engineering and Development Command (RDECOM). Current activities have concentrated on developing the optical projection hardware portion of the synthetic environment. These activities range from system level design down to component level testing. Of particular interest have been schemes for generating the optical signals representing the individual pixels of the projection. Several approaches have been investigated and tested with emphasis on operating wavelength, intensity dynamic range and uniformity, and flexibility in pixel waveform generation. This paper will discuss some of the results from these current efforts at RDECOM's Advanced Simulation Center (ASC).

KSC-08pd1962

NASA Image and Video Library

2008-07-11

CAPE CANAVERAL, Fla. – In the Orbiter Processing Facility at NASA's Kennedy Space Center, STS-125 crew members are lowered into space shuttle Atlantis' payload bay for a close look at the hardware. Equipment familiarization is part of the crew equipment interface test, which provides hands-on experience with hardware and equipment for the mission. Crew members are Commander Scott Altman, Pilot Gregory C. Johnson, and Mission Specialists Michael Good, Megan McArthur, John Grunsfeld, Mike Massimino and Andrew Feustel. Atlantis is targeted to launch Oct. 8 on the STS-125 mission to service the Hubble Space Telescope. The mission crew will perform history-making, on-orbit “surgery” on two important science instruments aboard the telescope. After capturing the telescope, two teams of spacewalking astronauts will perform the repairs during five planned spacewalks. Photo credit: NASA/Kim Shiflett

KSC-08pd1960

NASA Image and Video Library

2008-07-11

CAPE CANAVERAL, Fla. – In the Orbiter Processing Facility at NASA's Kennedy Space Center, STS-125 crew members are lowered into space shuttle Atlantis' payload bay for a close look at the hardware. Equipment familiarization is part of the crew equipment interface test, which provides hands-on experience with hardware and equipment for the mission. Crew members are Commander Scott Altman, Pilot Gregory C. Johnson, and Mission Specialists Michael Good, Megan McArthur, John Grunsfeld, Mike Massimino and Andrew Feustel. Atlantis is targeted to launch Oct. 8 on the STS-125 mission to service the Hubble Space Telescope. The mission crew will perform history-making, on-orbit “surgery” on two important science instruments aboard the telescope. After capturing the telescope, two teams of spacewalking astronauts will perform the repairs during five planned spacewalks. Photo credit: NASA/Kim Shiflett

Evaluation of a Tool for Producing and Presenting Interactive Videodisc Job Aids

DTIC Science & Technology

1994-03-01

and MacroMind Director, which lacks some authoring capablities (Macromedia Inc, approximate cost of Sinclude systems in Macintosh format such as...HyperCair (Claris Corp., approximate cost of $199) or SuperCmd (Aldus Corp., approximate cost of $299) and systems in Windows format such as Guide 3.1...scripting language to be used with a wide variety of hardware components. The ELVIS hypermedia system uses manufaturers ’ external commands to control

STS-134 crew and Expedition 24/25 crew member Shannon Walker

NASA Image and Video Library

2010-03-25

JSC2010-E-043667 (25 March 2010) --- NASA astronaut Mark Kelly, STS-134 commander, uses the virtual reality lab in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center to train for some of his duties aboard the space shuttle and space station. This type of computer interface, paired with virtual reality training hardware and software, helps to prepare crew members for dealing with space station elements.

STS-120 crew along with Expedition crew members Dan Tani and Sandra Magnus

NASA Image and Video Library

2007-08-09

JSC2007-E-41540 (9 Aug. 2007) --- Astronauts Pamela A. Melroy, STS-120 commander, and European Space Agency's (ESA) Paolo Nespoli, mission specialist, use the virtual reality lab at Johnson Space Center to train for their duties aboard the space shuttle and space station. This type of computer interface, paired with virtual reality training hardware and software, helps to prepare the entire team for dealing with space station elements.

Interservice/Industry Training, Simulation and Education Conference Partnerships for Learning in the New Millennium Abstracts

DTIC Science & Technology

2000-01-01

for flight test data, and both generic and specialized tools of data filtering , data calibration, modeling , system identification, and simulation...GRAMMATICAL MODEL AND PARSER FOR AIR TRAFFIC CONTROLLER’S COMMANDS 11 A SPEECH-CONTROLLED INTERACTIVE VIRTUAL ENVIRONMENT FOR SHIP FAMILIARIZATION 12... MODELING AND SIMULATION IN THE 21ST CENTURY 23 NEW COTS HARDWARE AND SOFTWARE REDUCE THE COST AND EFFORT IN REPLACING AGING FLIGHT SIMULATORS SUBSYSTEMS

Impact of New DoD Directives on Marine Corps Acquisition Policy at Milestone IV

DTIC Science & Technology

1991-03-01

Logistics Services Center (DLSC) files are compatible on the Effective Transfer Data Base. The Hardware Systems Command ( HSC ) develops a uniform stock...financial evaluation. Based on established review dates, the HSC publishes the location and time of the stock transfer review meeting. Forty-five days...letter to NAVSUP. The HSC also maintains adequate documentation to justify material that they retain and ensures that items designated for retention at the

Information Security Considerations for Applications Using Apache Accumulo

DTIC Science & Technology

2014-09-01

Distributed File System INSCOM United States Army Intelligence and Security Command JPA Java Persistence API JSON JavaScript Object Notation MAC Mandatory... MySQL [13]. BigTable can process 20 petabytes per day [14]. High degree of scalability on commodity hardware. NoSQL databases do not rely on highly...manipulation in relational databases. NoSQL databases each have a unique programming interface that uses a lower level procedural language (e.g., Java

Automatic Thermal Infrared Panoramic Imaging Sensor

DTIC Science & Technology

2006-11-01

hibernation, in which power supply to the server computer , the wireless network hardware, the GPS receiver, and the electronic compass / tilt sensor...prototype. At the operator’s command on the client laptop, the receiver wakeup device on the server side will switch on the ATX power supply at the...server, to resume the power supply to all the APTIS components. The embedded computer will resume all of the functions it was performing when put

KENNEDY SPACE CENTER, FLA. - Greeted by cheers from wellwishers at KSC and eager for their ventur into space on the Microgrvity Science Laboratory-1 (MSL-1) mission, the STS-83 astronauts depart the Operations and Checkout Building on their way to Launch Pad 39A. Leading the seven-member crew is Mission Commander James D. Halsell Jr. Behind Halsell and to his right is Pilot Susan L. Still. Behind Still is Payload Commander Janice Voss, with Mission Specialist Donald A. Thomas to her left. Behind Thomas, in order, are Mission Specialist Michael L. Gernhardt and Payload Specialists Roger K. Crouch and Gregory T. Linteris. During the scheduled 16-day STS-83 mission, the MSL-1 will be used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducts combustion, protein crystal growth and materials processing experiments. Also onboard is the Hitchhiker Cryogenic Flexible Diode (CRYOFD) experiment payload, which is attched to the right side of Columbia's payload bay.

NASA Image and Video Library

1997-04-04

KENNEDY SPACE CENTER, FLA. - Greeted by cheers from wellwishers at KSC and eager for their ventur into space on the Microgrvity Science Laboratory-1 (MSL-1) mission, the STS-83 astronauts depart the Operations and Checkout Building on their way to Launch Pad 39A. Leading the seven-member crew is Mission Commander James D. Halsell Jr. Behind Halsell and to his right is Pilot Susan L. Still. Behind Still is Payload Commander Janice Voss, with Mission Specialist Donald A. Thomas to her left. Behind Thomas, in order, are Mission Specialist Michael L. Gernhardt and Payload Specialists Roger K. Crouch and Gregory T. Linteris. During the scheduled 16-day STS-83 mission, the MSL-1 will be used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducts combustion, protein crystal growth and materials processing experiments. Also onboard is the Hitchhiker Cryogenic Flexible Diode (CRYOFD) experiment payload, which is attched to the right side of Columbia's payload bay.

Addressing the Hard Factors for Command File Errors by Probabilistic Reasoning

NASA Technical Reports Server (NTRS)

Meshkat, Leila; Bryant, Larry

2014-01-01

Command File Errors (CFE) are managed using standard risk management approaches at the Jet Propulsion Laboratory. Over the last few years, more emphasis has been made on the collection, organization, and analysis of these errors for the purpose of reducing the CFE rates. More recently, probabilistic modeling techniques have been used for more in depth analysis of the perceived error rates of the DAWN mission and for managing the soft factors in the upcoming phases of the mission. We broadly classify the factors that can lead to CFE's as soft factors, which relate to the cognition of the operators and hard factors which relate to the Mission System which is composed of the hardware, software and procedures used for the generation, verification & validation and execution of commands. The focus of this paper is to use probabilistic models that represent multiple missions at JPL to determine the root cause and sensitivities of the various components of the mission system and develop recommendations and techniques for addressing them. The customization of these multi-mission models to a sample interplanetary spacecraft is done for this purpose.

Technological evaluation of gesture and speech interfaces for enabling dismounted soldier-robot dialogue

NASA Astrophysics Data System (ADS)

Kattoju, Ravi Kiran; Barber, Daniel J.; Abich, Julian; Harris, Jonathan

2016-05-01

With increasing necessity for intuitive Soldier-robot communication in military operations and advancements in interactive technologies, autonomous robots have transitioned from assistance tools to functional and operational teammates able to service an array of military operations. Despite improvements in gesture and speech recognition technologies, their effectiveness in supporting Soldier-robot communication is still uncertain. The purpose of the present study was to evaluate the performance of gesture and speech interface technologies to facilitate Soldier-robot communication during a spatial-navigation task with an autonomous robot. Gesture and speech semantically based spatial-navigation commands leveraged existing lexicons for visual and verbal communication from the U.S Army field manual for visual signaling and a previously established Squad Level Vocabulary (SLV). Speech commands were recorded by a Lapel microphone and Microsoft Kinect, and classified by commercial off-the-shelf automatic speech recognition (ASR) software. Visual signals were captured and classified using a custom wireless gesture glove and software. Participants in the experiment commanded a robot to complete a simulated ISR mission in a scaled down urban scenario by delivering a sequence of gesture and speech commands, both individually and simultaneously, to the robot. Performance and reliability of gesture and speech hardware interfaces and recognition tools were analyzed and reported. Analysis of experimental results demonstrated the employed gesture technology has significant potential for enabling bidirectional Soldier-robot team dialogue based on the high classification accuracy and minimal training required to perform gesture commands.

Integrated Electronic Warfare System Advanced Development Model (ADM); Appendix 26 - Signal Sorter (SS) Supervisor Design Specification & Flow Diagrams.

DTIC Science & Technology

1977-10-01

These modules make up a multi-task priority real - time operating system in which each of the functions of the Supervisor is performed by one or more tasks. The Initialization module performs the initialization of the Supervisor software and hardware including the Input Buffer, the FIFO, and the Track Correlator This module is used both at initial program load time and upon receipt of a SC Initialization Command.

Indiva: a middleware for managing distributed media environment

NASA Astrophysics Data System (ADS)

Ooi, Wei-Tsang; Pletcher, Peter; Rowe, Lawrence A.

2003-12-01

This paper presents a unified set of abstractions and operations for hardware devices, software processes, and media data in a distributed audio and video environment. These abstractions, which are provided through a middleware layer called Indiva, use a file system metaphor to access resources and high-level commands to simplify the development of Internet webcast and distributed collaboration control applications. The design and implementation of Indiva are described and examples are presented to illustrate the usefulness of the abstractions.

iss053e156180

NASA Image and Video Library

2017-11-09

iss053e156180 (Nov. 9, 2017) --- Expedition 53 Commander Randy Bresnik (foreground) and Flight Engineer Paolo Nespoli are at the controls of the robotics workstation in the Destiny laboratory module training for the approach, rendezvous and grapple of the Orbital ATK Cygnus resupply ship. Both astronauts were in the cupola operating the Canadarm2 robotic arm to grapple Cygnus when it arrived Nov. 14, 2017, delivering nearly 7,400 pounds of crew supplies, science experiments, computer gear, vehicle equipment and spacewalk hardware.

iss053e156160

NASA Image and Video Library

2017-11-09

iss053e156160 (Nov. 9, 2017) --- Expedition 53 Commander Randy Bresnik is at the controls of the robotics workstation in the Destiny laboratory module training for the approach, rendezvous and grapple of the Orbital ATK Cygnus resupply ship. He and Flight Engineer Paolo Nespoli were in the cupola operating the Canadarm2 robotic arm to grapple Cygnus when it arrived Nov. 14, 2017, delivering nearly 7,400 pounds of crew supplies, science experiments, computer gear, vehicle equipment and spacewalk hardware.

STS-109 Crew Training in VR Lab, Building 9

NASA Image and Video Library

2001-08-08

JSC2001-E-24452 (8 August 2001) --- Astronauts John M. Grunsfeld (left), STS-109 payload commander, and Nancy J. Currie, mission specialist, use the virtual reality lab at the Johnson Space Center (JSC) to train for some of their duties aboard the Space Shuttle Columbia. This type of computer interface paired with virtual reality training hardware and software helps to prepare the entire team to perform its duties during the fourth Hubble Space Telescope (HST) servicing mission.

STS-134 crew and Expedition 24/25 crew member Shannon Walker

NASA Image and Video Library

2010-03-25

JSC2010-E-043666 (25 March 2010) --- NASA astronauts Mark Kelly (background), STS-134 commander; and Andrew Feustel, mission specialist, use the virtual reality lab in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center to train for some of their duties aboard the space shuttle and space station. This type of computer interface, paired with virtual reality training hardware and software, helps to prepare crew members for dealing with space station elements.

STS-134 crew and Expedition 24/25 crew member Shannon Walker

NASA Image and Video Library

2010-03-25

JSC2010-E-043668 (25 March 2010) --- NASA astronauts Mark Kelly (background), STS-134 commander; and Andrew Feustel, mission specialist, use the virtual reality lab in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center to train for some of their duties aboard the space shuttle and space station. This type of computer interface, paired with virtual reality training hardware and software, helps to prepare crew members for dealing with space station elements.

STS-111 Training in VR lab with Expedition IV and V Crewmembers

NASA Image and Video Library

2001-10-18

JSC2001-E-39082 (18 October 2001) --- Cosmonaut Valeri G. Korzun (left), Expedition Five mission commander, and astronaut Carl E. Walz, Expedition Four flight engineer, use the virtual reality lab at the Johnson Space Center (JSC) to train for their duties on the International Space Station (ISS). This type of computer interface paired with virtual reality training hardware and software helps the entire team for dealing with ISS elements. Korzun represents Rosaviakosmos.

Application of the Modular Command and Control Structure (MCES) to Marine Corps SINCGARS Allocation

DTIC Science & Technology

1991-07-01

The first goal is to delineate the difference between the system being analyzed and its environment . To bound the C3 system, the analyst should...hardware and software entities and structures, is related to the forces it controls and the environmental stimuli to which it responds, including the enemy...M CES represents the environmental facto:s that require explicit assumptions in the problem. This ring may be seen as including the major scenario

Studies to design and develop improved remote manipulator systems

NASA Technical Reports Server (NTRS)

Hill, J. W.; Sword, A. J.

1973-01-01

Remote manipulator control considered is based on several levels of automatic supervision which derives manipulator commands from an analysis of sensor states and task requirements. Principle sensors are manipulator joint position, tactile, and currents. The tactile sensor states can be displayed visually in perspective or replicated in the operator's control handle of perceived by the automatic supervisor. Studies are reported on control organization, operator performance and system performance measures. Unusual hardware and software details are described.

Project Longshot: A mission to Alpha Centauri

NASA Technical Reports Server (NTRS)

West, Curtis; Chamberlain, Sally; Pagan, Neftali; Stevens, Robert

1989-01-01

Project Longshot, an exercise in the Advanced Design Program for Space, had as its destination Alpha Centauri, the closest star system to our own solar system. Alpha Centauri, a trinary star system, is 4.34 light years from earth. Although Project Longshot is impossible based on existing technologies, areas that require further investigation in order to make this feat possible are identified. Three areas where advances in technology are needed are propulsion, data processing for autonomous command and control functions, and reliability. Propulsion, possibly by antimatter annihilation; navigation and navigation aids; reliable hardware and instruments; artificial intelligence to eliminate the need for command telemetry; laser communication; and a reliable, compact, and lightweight power system that converts energy efficiently and reliably present major challenges. Project Longshot promises exciting advances in science and technology and new information concerning the universe.

President and Mrs. Clinton watch launch of Space Shuttle Discovery

NASA Technical Reports Server (NTRS)

1998-01-01

Watching a successful launch of Space Shuttle Discovery from the roof of the Launch Control Center are (left to right) Astronaut Eileen Collins (in flight suit) with unidentified companions, NASA Administrator Daniel Goldin, Astronaut Robert Cabana, First Lady Hillary Rodham Clinton, and U.S. President Bill Clinton. This was the first launch of a Space Shuttle to be viewed by President Clinton, or any President to date. They attended the launch to witness the return to space of American legend John H. Glenn Jr., payload specialist on mission STS-95. Collins will command the crew of STS-93, the first woman to hold that position. Cabana will command the crew of STS-88, the first Space Shuttle mission to carry hardware to space for the assembly of the International Space Station, targeted for liftoff on Dec. 3.

Off-line programming motion and process commands for robotic welding of Space Shuttle main engines

NASA Technical Reports Server (NTRS)

Ruokangas, C. C.; Guthmiller, W. A.; Pierson, B. L.; Sliwinski, K. E.; Lee, J. M. F.

1987-01-01

The off-line-programming software and hardware being developed for robotic welding of the Space Shuttle main engine are described and illustrated with diagrams, drawings, graphs, and photographs. The menu-driven workstation-based interactive programming system is designed to permit generation of both motion and process commands for the robotic workcell by weld engineers (with only limited knowledge of programming or CAD systems) on the production floor. Consideration is given to the user interface, geometric-sources interfaces, overall menu structure, weld-parameter data base, and displays of run time and archived data. Ongoing efforts to address limitations related to automatic-downhand-configuration coordinated motion, a lack of source codes for the motion-control software, CAD data incompatibility, interfacing with the robotic workcell, and definition of the welding data base are discussed.

VIRTUAL FRAME BUFFER INTERFACE

NASA Technical Reports Server (NTRS)

Wolfe, T. L.

1994-01-01

Large image processing systems use multiple frame buffers with differing architectures and vendor supplied user interfaces. This variety of architectures and interfaces creates software development, maintenance, and portability problems for application programs. The Virtual Frame Buffer Interface program makes all frame buffers appear as a generic frame buffer with a specified set of characteristics, allowing programmers to write code which will run unmodified on all supported hardware. The Virtual Frame Buffer Interface converts generic commands to actual device commands. The virtual frame buffer consists of a definition of capabilities and FORTRAN subroutines that are called by application programs. The virtual frame buffer routines may be treated as subroutines, logical functions, or integer functions by the application program. Routines are included that allocate and manage hardware resources such as frame buffers, monitors, video switches, trackballs, tablets and joysticks; access image memory planes; and perform alphanumeric font or text generation. The subroutines for the various "real" frame buffers are in separate VAX/VMS shared libraries allowing modification, correction or enhancement of the virtual interface without affecting application programs. The Virtual Frame Buffer Interface program was developed in FORTRAN 77 for a DEC VAX 11/780 or a DEC VAX 11/750 under VMS 4.X. It supports ADAGE IK3000, DEANZA IP8500, Low Resolution RAMTEK 9460, and High Resolution RAMTEK 9460 Frame Buffers. It has a central memory requirement of approximately 150K. This program was developed in 1985.

Three Corner Sat Communications System

NASA Technical Reports Server (NTRS)

Anderson, Bobby; Horan, Stephen

2000-01-01

Three Corner Satellite is a constellation of three nanosatellites designed and built by students. New Mexico State University has taken on the design of the communications system for this constellation. The system includes the forward link, return link, and the crosslink. Due to size, mass, power, and financial constraints, we must design a small, light, power efficient, and inexpensive communications system. This thesis presents the design of a radio system to accomplish the data transmission requirements in light of the system constraints. In addition to the hardware design, the operational commands needed by the satellite's on-board computer to control and communicate with the communications hardware will be presented. In order for the hardware to communicate with the ground stations, we will examine the link budgets derived from the radiated power of the transmitters, link distance, data modulation, and data rate for each link. The antenna design for the constellation is analyzed using software and testing the physical antennas on a model satellite. After the analysis and testing, a combination of different systems will meet and exceed the requirements and constraints of the Three Corner Satellite constellation.

Flight code validation simulator

NASA Astrophysics Data System (ADS)

Sims, Brent A.

1996-05-01

An End-To-End Simulation capability for software development and validation of missile flight software on the actual embedded computer has been developed utilizing a 486 PC, i860 DSP coprocessor, embedded flight computer and custom dual port memory interface hardware. This system allows real-time interrupt driven embedded flight software development and checkout. The flight software runs in a Sandia Digital Airborne Computer and reads and writes actual hardware sensor locations in which Inertial Measurement Unit data resides. The simulator provides six degree of freedom real-time dynamic simulation, accurate real-time discrete sensor data and acts on commands and discretes from the flight computer. This system was utilized in the development and validation of the successful premier flight of the Digital Miniature Attitude Reference System in January of 1995 at the White Sands Missile Range on a two stage attitude controlled sounding rocket.

Field Programmable Gate Array Failure Rate Estimation Guidelines for Launch Vehicle Fault Tree Models

NASA Technical Reports Server (NTRS)

Al Hassan, Mohammad; Novack, Steven D.; Hatfield, Glen S.; Britton, Paul

2017-01-01

Today's launch vehicles complex electronic and avionic systems heavily utilize the Field Programmable Gate Array (FPGA) integrated circuit (IC). FPGAs are prevalent ICs in communication protocols such as MIL-STD-1553B, and in control signal commands such as in solenoid/servo valves actuations. This paper will demonstrate guidelines to estimate FPGA failure rates for a launch vehicle, the guidelines will account for hardware, firmware, and radiation induced failures. The hardware contribution of the approach accounts for physical failures of the IC, FPGA memory and clock. The firmware portion will provide guidelines on the high level FPGA programming language and ways to account for software/code reliability growth. The radiation portion will provide guidelines on environment susceptibility as well as guidelines on tailoring other launch vehicle programs historical data to a specific launch vehicle.

Macromolecular Crystallization in Microfluidics for the International Space Station

NASA Technical Reports Server (NTRS)

Monaco, Lisa A.; Spearing, Scott

2003-01-01

At NASA's Marshall Space Flight Center, the Iterative Biological Crystallization (IBC) project has begun development on scientific hardware for macromolecular crystallization on the International Space Station (ISS). Currently ISS crystallization research is limited to solution recipes that were prepared on the ground prior to launch. The proposed hardware will conduct solution mixing and dispensing on board the ISS, be fully automated, and have imaging functions via remote commanding from the ground. Utilizing microfluidic technology, IBC will allow for on orbit iterations. The microfluidics LabChip(R) devices that have been developed, along with Caliper Technologies, will greatly benefit researchers by allowing for precise fluid handling of nano/pico liter sized volumes. IBC will maximize the amount of science return by utilizing the microfluidic approach and be a valuable tool to structural biologists investigating medically relevant projects.

Scalable large format 3D displays

NASA Astrophysics Data System (ADS)

Chang, Nelson L.; Damera-Venkata, Niranjan

2010-02-01

We present a general framework for the modeling and optimization of scalable large format 3-D displays using multiple projectors. Based on this framework, we derive algorithms that can robustly optimize the visual quality of an arbitrary combination of projectors (e.g. tiled, superimposed, combinations of the two) without manual adjustment. The framework creates for the first time a new unified paradigm that is agnostic to a particular configuration of projectors yet robustly optimizes for the brightness, contrast, and resolution of that configuration. In addition, we demonstrate that our algorithms support high resolution stereoscopic video at real-time interactive frame rates achieved on commodity graphics hardware. Through complementary polarization, the framework creates high quality multi-projector 3-D displays at low hardware and operational cost for a variety of applications including digital cinema, visualization, and command-and-control walls.

KSC-08pd1961

NASA Image and Video Library

2008-07-11

CAPE CANAVERAL, Fla. – In the Orbiter Processing Facility at NASA's Kennedy Space Center, STS-125 crew members are lowered into space shuttle Atlantis' payload bay for a close look at the hardware. Equipment familiarization is part of the crew equipment interface test, which provides hands-on experience with hardware and equipment for the mission. Crew members are Commander Scott Altman, Pilot Gregory C. Johnson, and Mission Specialists Michael Good, Megan McArthur, John Grunsfeld, Mike Massimino (reaching toward the airlock) and Andrew Feustel. Atlantis is targeted to launch Oct. 8 on the STS-125 mission to service the Hubble Space Telescope. The mission crew will perform history-making, on-orbit “surgery” on two important science instruments aboard the telescope. After capturing the telescope, two teams of spacewalking astronauts will perform the repairs during five planned spacewalks. Photo credit: NASA/Kim Shiflett

Software Assurance Measurement -- State of the Practice

DTIC Science & Technology

2013-11-01

quality and productivity. 30+ languages, C/C++, Java , .NET, Oracle, PeopleSoft, SAP, Siebel, Spring, Struts, Hibernate , and all major databases. ChecKing...NET 39 ActionScript 39 Ada 40 C/C++ 40 Java 41 JavaScript 42 Objective-C 42 Opa 42 Packages 42 Perl 42 PHP 42 Python 42 Formal Methods...Suite—A tool for Ada, C, C++, C#, and Java code that comprises various analyses such as architecture checking, interface analyses, and clone detection

System for Estimating Horizontal Velocity During Descent

NASA Technical Reports Server (NTRS)

Johnson, Andrew; Cheng, Yang; Wilson, Reg; Goguen, Jay; Martin, Alejandro San; Leger, Chris; Matthies, Larry

2007-01-01

The descent image motion estimation system (DIMES) is a system of hardware and software, designed for original use in estimating the horizontal velocity of a spacecraft descending toward a landing on Mars. The estimated horizontal velocity is used in generating rocket-firing commands to reduce the horizontal velocity as part of an overall control scheme to minimize the landing impact. DIMES can also be used for estimating the horizontal velocity of a remotely controlled or autonomous aircraft for purposes of navigation and control.

PASSAGES experiment

NASA Image and Video Library

2010-10-19

ISS025-E-008371 (20 Oct. 2010) --- NASA astronaut Doug Wheelock, Expedition 25 commander, uses Neurospat hardware to perform a science session with the European Space Agency PASSAGES experiment in the Columbus laboratory of the International Space Station. PASSAGES is designed to test how astronauts interpret visual information in weightlessness. It aims at studying the effects of microgravity on the use of the ‘Eye-Height’ strategy for estimating allowed actions in an environment, and whether this could possibly decrease after a long exposure to weightlessness.

ESA PASSAGES experiment

NASA Image and Video Library

2011-10-06

ISS029-E-021641 (6 Oct. 2011) --- NASA astronaut Mike Fossum, Expedition 29 commander, uses Neurospat hardware to perform a science session with the European Space Agency PASSAGES experiment in the Columbus laboratory of the International Space Station. PASSAGES is designed to test how astronauts interpret visual information in weightlessness. It aims at studying the effects of microgravity on the use of the 'Eye-Height' strategy for estimating allowed actions in an environment, and whether this could possibly decrease after a long exposure to weightlessness.

Proceedings Papers of the AFSC (Air Force Systems Command) Avionics Standardization Conference (2nd) Held at Dayton, Ohio on 30 November-2 December 1982. Volume 2

DTIC Science & Technology

1982-11-01

groups. The Air Force is concerned with such issues such as resource allocation to foster and prcomotc standards, transitioning from current to future...perform automatic resource allocation , generate MATE Intermediate code, and provide formatted output listings. d. MATE Test Executive (MTE). The MTE...AFFECTED BY THESE STANDARDS TO KNOW JUST WHAT IS AVAILABLE TO SUPPORT THEM: THE HARDWARE; THE COMPLIANCE TESTING ; THE TOOLS NECESSARY TO FACILITATE DESIGN

Balancing Materiel Readiness Risks and Concurrency in Weapon System Acquisition: A Handbook for Program Managers

DTIC Science & Technology

1984-07-15

ftViCCii UWNC COMMAND MIX CM AFT DCP OUTUNC moo ffEOUCST FOR PROGRAM DECISION DRAFT DCP AFSC REVIEW RECOWMEM CATIONS OHI*OC Arse wioc...CS.P3 F16. El*. P» MCA Exhibit 4-6b. EMBEDDED COMPUTER HARDWARE vs. SOFTWARE Exhibit 4-6c. DoD EMBEDDED COMPUTER MARKET 31.J1...the mix of stores carried by that vehicle 6. Anticipated combat tactics employed by the carrying or launching vehicle and its maneuvering

Using virtual reality and game technology to assist command and control

NASA Astrophysics Data System (ADS)

Riead, Lorien H.; Straub, James; Mangino, Joseph

2017-04-01

Recent improvements in virtual reality hardware have brought this technology to the point where easily-obtained commercial equipment can conceivably provide an affordable and relatively unexplored alternative to the traditional monitor and keyboard view of the tactical space. In addition, commercially available game engines provide several advantages for tactical applications. Using these technologies, we have created a concept of a low-cost display that allows for real-time immersive planning and strategy, with suggestions for further exploration.

Design Guidance for Command, Control, Communications, and Intelligence (C3I) Facility Cooling Systems

DTIC Science & Technology

1989-05-01

Typical ranges are from 50 to 70 OF. If a chiller is dedicated to serving water-cooled electronic equipment, the chilled water temperature setpoint can...can be satisfied with 50 OF chilled water. The COP of the dedicated chiller is improved by raising the chilled water setpoint , and the total life-cycle...USACERL TECHNICAL REPORT E-89/10 May 1989 Studies in Optimizing HVAC Hardware for C31 Facilities US Army Corps of Engineers Construction Engineering

A Logical Design of a Session Services Control Layer of a Distributed Network Architecture for SPLICE (Stock Point Logistics Integrated Communication Environment).

DTIC Science & Technology

1984-06-01

Eacn stock point is autonomous witn respect to how it implements data processing support, as long as it accommodates the Navy Supply Systems Command...has its own data elements, files, programs , transactions, users, reports, and some have additional hardware. To augment them all and not force redesign... programs are written to request session establishments among them using only logical addressing names (mailboxes) whicn are independent from physical

STS-132 crew during their MSS/SIMP EVA3 OPS 4 training

NASA Image and Video Library

2010-01-28

JSC2010-E-014956 (28 Jan. 2010) --- NASA astronauts Ken Ham (left foreground), STS-132 commander; Michael Good, mission specialist; and Tony Antonelli (right), pilot, use the virtual reality lab in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center to train for some of their duties aboard the space shuttle and space station. This type of computer interface, paired with virtual reality training hardware and software, helps to prepare crew members for dealing with space station elements.

STS-111 Training in VR lab with Expedition IV and V Crewmembers

NASA Image and Video Library

2001-10-18

JSC2001-E-39085 (18 October 2001) --- Cosmonaut Valeri G. Korzun (left), Expedition Five mission commander, astronaut Peggy A. Whitson, Expedition Five flight engineer, and astronaut Carl E. Walz, Expedition Four flight engineer, use the virtual reality lab at the Johnson Space Center (JSC) to train for their duties on the International Space Station (ISS). This type of computer interface paired with virtual reality training hardware and software helps the entire team for dealing with ISS elements. Korzun represents Rosaviakosmos.

Progress re-supply ship

NASA Image and Video Library

2010-01-14

ISS01-324-002 (18 November 2000) --- A Progress supply ship linked up to the orbiting International Space Station (ISS) at 3:48 GMT, November 18, bringing Expedition 1 commander William M. Shepherd, pilot Yuri P. Gidzenko and flight engineer Sergei K. Krikalev two tons of food, clothing, hardware and holiday gifts from their families. The photograph was taken with a 35mm camera and the film was later handed over to the STS-97 crew members for return to Earth and subsequent processing.

The Aerospace Energy Systems Laboratory: A BITBUS networking application

NASA Technical Reports Server (NTRS)

Glover, Richard D.; Oneill-Rood, Nora

1989-01-01

The NASA Ames-Dryden Flight Research Facility developed a computerized aircraft battery servicing facility called the Aerospace Energy Systems Laboratory (AESL). This system employs distributed processing with communications provided by a 2.4-megabit BITBUS local area network. Customized handlers provide real time status, remote command, and file transfer protocols between a central system running the iRMX-II operating system and ten slave stations running the iRMX-I operating system. The hardware configuration and software components required to implement this BITBUS application are required.

Ground facility for information reception, processing, dissemination and scientific instruments management setup in the CORONAS-PHOTON space project

NASA Astrophysics Data System (ADS)

Buslov, A. S.; Kotov, Yu. D.; Yurov, V. N.; Bessonov, M. V.; Kalmykov, P. A.; Oreshnikov, E. M.; Alimov, A. M.; Tumanov, A. V.; Zhuchkova, E. A.

2011-06-01

This paper deals with the organizational structure of ground-based receiving, processing, and dissemination of scientific information created by the Astrophysics Institute of the Scientific Research Nuclear University, Moscow Engineering Physics Institute. Hardware structure and software features are described. The principles are given for forming sets of control commands for scientific equipment (SE) devices, and statistics data are presented on the operation of facility during flight tests of the spacecraft (SC) in the course of one year.

Veg-01 Plant Harvest

NASA Image and Video Library

2014-06-10

ISS040-E-009125 (10 June 2014) --- In the International Space Station?s Harmony node, NASA astronaut Steve Swanson, Expedition 40 commander, harvests a crop of red romaine lettuce plants that were grown from seed inside the station?s Veggie facility, a low-cost plant growth chamber that uses a flat-panel light bank for plant growth and crew observation. For the Veg-01 experiment, researchers are testing and validating the Veggie hardware, and the plants will be returned to Earth to determine food safety.

Veg-01 Plant Harvest

NASA Image and Video Library

2014-06-10

ISS040-E-009124 (10 June 2014) --- In the International Space Station?s Harmony node, NASA astronaut Steve Swanson, Expedition 40 commander, harvests a crop of red romaine lettuce plants that were grown from seed inside the station?s Veggie facility, a low-cost plant growth chamber that uses a flat-panel light bank for plant growth and crew observation. For the Veg-01 experiment, researchers are testing and validating the Veggie hardware, and the plants will be returned to Earth to determine food safety.

Veg-01 Plant Harvest

NASA Image and Video Library

2014-06-10

ISS040-E-009116 (10 June 2014) --- In the International Space Station?s Harmony node, NASA astronaut Steve Swanson, Expedition 40 commander, harvests a crop of red romaine lettuce plants that were grown from seed inside the station?s Veggie facility, a low-cost plant growth chamber that uses a flat-panel light bank for plant growth and crew observation. For the Veg-01 experiment, researchers are testing and validating the Veggie hardware, and the plants will be returned to Earth to determine food safety.

Marshburn in Kibo

NASA Image and Video Library

2013-04-15

ISS035-E-020060 (15 April 2013) --- NASA astronaut Tom Marshburn works on the Inter Module Ventilation (IMV) Flow Measurement in Kibo Japanese Experiment Module (JEM)aboard the Earth-orbiting International Space Station. Expedition 35 Commander Chris Hadfield, an astronaut with the Canadian Space Agency, and Marshburn set up the velocicalc hardware and measured the IMV flow coming from the JEM Pressurized Module (JPM) IMV overhead aft inlet, starboard aft inlet, and starboard forward outlet. The measurements are part of routine preventative maintenance to ensure quality airflow in the modules.

Lineger and Tsibliev during EVA outside Mir Space Station

NASA Image and Video Library

1997-04-29

NM23-48-009 (29 April 1997) --- United States astronaut Jerry M. Linenger, cosmonaut guest researcher, works outside the Russian Mir Space Station during a joint United States-Russian space walk on April 29, 1997. He was joined by Mir-23 commander Vasili V. Tsibliyev (out of frame) for the five-hour Extravehicular Activity (EVA) designed to deploy scientific instruments and retrieve other science hardware. At the top of the frame is a Russian Progress re-supply capsule docked to the Mir’s Kvant-1 module.

LABORATORY PROCESS CONTROLLER USING NATURAL LANGUAGE COMMANDS FROM A PERSONAL COMPUTER

NASA Technical Reports Server (NTRS)

Will, H.

1994-01-01

The complex environment of the typical research laboratory requires flexible process control. This program provides natural language process control from an IBM PC or compatible machine. Sometimes process control schedules require changes frequently, even several times per day. These changes may include adding, deleting, and rearranging steps in a process. This program sets up a process control system that can either run without an operator, or be run by workers with limited programming skills. The software system includes three programs. Two of the programs, written in FORTRAN77, record data and control research processes. The third program, written in Pascal, generates the FORTRAN subroutines used by the other two programs to identify the user commands with the user-written device drivers. The software system also includes an input data set which allows the user to define the user commands which are to be executed by the computer. To set the system up the operator writes device driver routines for all of the controlled devices. Once set up, this system requires only an input file containing natural language command lines which tell the system what to do and when to do it. The operator can make up custom commands for operating and taking data from external research equipment at any time of the day or night without the operator in attendance. This process control system requires a personal computer operating under MS-DOS with suitable hardware interfaces to all controlled devices. The program requires a FORTRAN77 compiler and user-written device drivers. This program was developed in 1989 and has a memory requirement of about 62 Kbytes.

Apollo experience report: Guidance and control systems. Mission control programmer for unmanned missions AS-202, Apollo 4, and Apollo 6

NASA Technical Reports Server (NTRS)

Holloway, G. F.

1975-01-01

An unmanned test flight program required to evaluate the command module heat shield and the structural integrity of the command and service module/Saturn launch vehicle is described. The mission control programer was developed to provide the unmanned interface between the guidance and navigation computer and the other spacecraft systems for mission event sequencing and real-time ground control during missions AS-202, Apollo 4, and Apollo 6. The development of this unmanned programer is traced from the initial concept through the flight test phase. Detailed discussions of hardware development problems are given with the resulting solutions. The mission control programer functioned correctly without any flight anomalies for all missions. The Apollo 4 mission control programer was reused for the Apollo 6 flight, thus being one of the first subsystems to be reflown on an Apollo space flight.

STS-94 Columbia Landing at KSC

NASA Technical Reports Server (NTRS)

1997-01-01

The Space Shuttle orbiter Columbia glides in for a touchdown on Runway 33 at KSCs Shuttle Landing Facility at approximately 6:46 a.m. EDT with Mission Commander James D. Halsell Jr. and Pilot Susan L. Still at the controls to complete the STS-94 mission. Also on board are Mission Specialist Donald A. Thomas, Mission Specialist Michael L. Gernhardt, Payload Commander Janice Voss, and Payload Specialists Roger K.Crouch and Gregory T. Linteris. During the Microgravity Science Laboratory-1 (MSL-1) mission, the Spacelab module was used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducted combustion, protein crystal growth and materials processing experiments. This mission was a reflight of the STS-83 mission that lifted off from KSC in April of this year. That space flight was cut short due to indications of a faulty fuel cell.

Characterization of Orbital Debris Via Hyper-Velocity Ground-Based Tests

NASA Technical Reports Server (NTRS)

Cowardin, Heather

2015-01-01

To replicate a hyper-velocity fragmentation event using modern-day spacecraft materials and construction techniques to better improve the existing DoD and NASA breakup models. DebriSat is intended to be representative of modern LEO satellites.Major design decisions were reviewed and approved by Aerospace subject matter experts from different disciplines. DebriSat includes 7 major subsystems. Attitude determination and control system (ADCS), command and data handling (C&DH), electrical power system (EPS), payload, propulsion, telemetry tracking and command (TT&C), and thermal management. To reduce cost, most components are emulated based on existing design of flight hardware and fabricated with the same materials. A key laboratory-based test, Satellite Orbital debris Characterization Impact Test (SOCIT), supporting the development of the DoD and NASA satellite breakup models was conducted at AEDC in 1992 .Breakup models based on SOCIT have supported many applications and matched on-orbit events reasonably well over the years.

Space Situational Awareness in the Joint Space Operations Center

NASA Astrophysics Data System (ADS)

Wasson, M.

2011-09-01

Flight safety of orbiting resident space objects is critical to our national interest and defense. United States Strategic Command has assigned the responsibility for Space Situational Awareness (SSA) to its Joint Functional Component Command - Space (JFCC SPACE) at Vandenberg Air Force Base. This paper will describe current SSA imperatives, new developments in SSA tools and developments in Defensive Operations. Current SSA processes are being examined to capture, and possibly improve, tasking of SSN sensors and "new" space-based sensors, "common" conjunction assessment methodology, and SSA sharing due to the growth seen over the last two years. The stand-up of a Defensive Ops Branch will highlight the need for advanced analysis and collaboration across space, weather, intelligence, and cyber specialties. New developments in SSA tools will be a description of computing hardware/software upgrades planned as well as the use of User-Defined Operating Pictures and visualization applications.

STS-94 Columbia Landing at KSC (before main gear touchdown)

NASA Technical Reports Server (NTRS)

1997-01-01

The Space Shuttle orbiter Columbia glides in for a touchdown on Runway 33 at KSCs Shuttle Landing Facility at approximately 6:46 a.m. EDT with Mission Commander James D. Halsell Jr. and Pilot Susan L. Still at the controls to complete the STS-94 mission. Also on board are Mission Specialist Donald A. Thomas, Mission Specialist Michael L. Gernhardt, Payload Commander Janice Voss, and Payload Specialists Roger K.Crouch and Gregory T. Linteris. During the Microgravity Science Laboratory-1 (MSL-1) mission, the Spacelab module was used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducted combustion, protein crystal growth and materials processing experiments. This mission was a reflight of the STS-83 mission that lifted off from KSC in April of this year. That space flight was cut short due to indications of a faulty fuel cell.

Remote Software Application and Display Development

NASA Technical Reports Server (NTRS)

Sanders, Brandon T.

2014-01-01

The era of the shuttle program has come to an end, but only to give rise to newer and more exciting projects. Now is the time of the Orion spacecraft, a work of art designed to exceed all previous endeavors of man. NASA is exiting the time of exploration and is entering a new period, a period of pioneering. With this new mission, many of NASAs organizations must undergo a great deal of change and development to support the Orion missions. The Spaceport Command and Control System (SCCS) is the new system that will provide NASA the ability to launch rockets into orbit and thus control Orion and other spacecraft as the goal of populating Mars becomes ever increasingly tangible. Since the previous control system, Launch Processing System (LPS), was primarily designed to launch the shuttles, SCCS was needed as Kennedy Space Center (KSC) reorganized to a multiuser spaceport for commercial flights, providing a more versatile control over rockets. Within SCCS, is the Launch Control System (LCS), which is the remote software behind the command and monitoring of flight and ground system hardware. This internship at KSC has involved two main components in LCS, including Remote Software Application and Display development. The display environment provides a graphical user interface for an operator to view and see if any cautions are raised, while the remote applications are the backbone that communicate with hardware, and then relay the data back to the displays. These elements go hand in hand as they provide monitoring and control over hardware and software alike from the safety of the Launch Control Center. The remote software applications are written in Application Control Language (ACL), which must undergo unit testing to ensure data integrity. This paper describes both the implementation and writing of unit tests in ACL code for remote software applications, as well as the building of remote displays to be used in the Launch Control Center (LCC).

Skylab mission report, third visit

NASA Technical Reports Server (NTRS)

1974-01-01

An evaluation is presented of the operational and engineering aspects of the third Skylab visit, including information on the performance of the command and service module and the experiment hardware, the crew's evaluation of the visit, and other visit-related areas of interest such as biomedical observations. The specific areas discussed are contained in the following: (1) solar physics and astrophysics investigations; (2) Comet Kohoutek experiments; (3) medical experiments; (4) earth observations, including data for the multispectral photographic facility, the earth terrain camera, and the microwave radiometer/scattermometer and altimeter; (5) engineering and technology experiments; (6) food and medical operational equipment; (7) hardware and experiment anomalies; and (8) mission support, mission objectives, flight planning, and launch phase summary. Conclusions discussed as a result of the third visit to Skylab involve the advancement of the sciences, practical applications, the durability of man and systems in space, and spaceflight effectiveness and economy.

Cone-beam micro-CT system based on LabVIEW software.

PubMed

Ionita, Ciprian N; Hoffmann, Keneth R; Bednarek, Daniel R; Chityala, Ravishankar; Rudin, Stephen

2008-09-01

Construction of a cone-beam computed tomography (CBCT) system for laboratory research usually requires integration of different software and hardware components. As a result, building and operating such a complex system require the expertise of researchers with significantly different backgrounds. Additionally, writing flexible code to control the hardware components of a CBCT system combined with designing a friendly graphical user interface (GUI) can be cumbersome and time consuming. An intuitive and flexible program structure, as well as the program GUI for CBCT acquisition, is presented in this note. The program was developed in National Instrument's Laboratory Virtual Instrumentation Engineering Workbench (LabVIEW) graphical language and is designed to control a custom-built CBCT system but has been also used in a standard angiographic suite. The hardware components are commercially available to researchers and are in general provided with software drivers which are LabVIEW compatible. The program structure was designed as a sequential chain. Each step in the chain takes care of one or two hardware commands at a time; the execution of the sequence can be modified according to the CBCT system design. We have scanned and reconstructed over 200 specimens using this interface and present three examples which cover different areas of interest encountered in laboratory research. The resulting 3D data are rendered using a commercial workstation. The program described in this paper is available for use or improvement by other researchers.

Multi-Mission System Architecture Platform: Design and Verification of the Remote Engineering Unit

NASA Technical Reports Server (NTRS)

Sartori, John

2005-01-01

The Multi-Mission System Architecture Platform (MSAP) represents an effort to bolster efficiency in the spacecraft design process. By incorporating essential spacecraft functionality into a modular, expandable system, the MSAP provides a foundation on which future spacecraft missions can be developed. Once completed, the MSAP will provide support for missions with varying objectives, while maintaining a level of standardization that will minimize redesign of general system components. One subsystem of the MSAP, the Remote Engineering Unit (REU), functions by gathering engineering telemetry from strategic points on the spacecraft and providing these measurements to the spacecraft's Command and Data Handling (C&DH) subsystem. Before the MSAP Project reaches completion, all hardware, including the REU, must be verified. However, the speed and complexity of the REU circuitry rules out the possibility of physical prototyping. Instead, the MSAP hardware is designed and verified using the Verilog Hardware Definition Language (HDL). An increasingly popular means of digital design, HDL programming provides a level of abstraction, which allows the designer to focus on functionality while logic synthesis tools take care of gate-level design and optimization. As verification of the REU proceeds, errors are quickly remedied, preventing costly changes during hardware validation. After undergoing the careful, iterative processes of verification and validation, the REU and MSAP will prove their readiness for use in a multitude of spacecraft missions.

Development and Flight Testing of an Autonomous Landing Gear Health-Monitoring System

NASA Technical Reports Server (NTRS)

Woodard, Stanley E.; Coffey, Neil C.; Gonzalez, Guillermo A.; Taylor, B. Douglas; Brett, Rube R.; Woodman, Keith L.; Weathered, Brenton W.; Rollins, Courtney H.

2003-01-01

Development and testing of an adaptable vehicle health-monitoring architecture is presented. The architecture is being developed for a fleet of vehicles. It has three operational levels: one or more remote data acquisition units located throughout the vehicle; a command and control unit located within the vehicle; and, a terminal collection unit to collect analysis results from all vehicles. Each level is capable of performing autonomous analysis with a trained expert system. Communication between all levels is done with wireless radio frequency interfaces. The remote data acquisition unit has an eight channel programmable digital interface that allows the user discretion for choosing type of sensors; number of sensors, sensor sampling rate and sampling duration for each sensor. The architecture provides framework for a tributary analysis. All measurements at the lowest operational level are reduced to provide analysis results necessary to gauge changes from established baselines. These are then collected at the next level to identify any global trends or common features from the prior level. This process is repeated until the results are reduced at the highest operational level. In the framework, only analysis results are forwarded to the next level to reduce telemetry congestion. The system's remote data acquisition hardware and non-analysis software have been flight tested on the NASA Langley B757's main landing gear. The flight tests were performed to validate the following: the wireless radio frequency communication capabilities of the system, the hardware design, command and control; software operation; and, data acquisition, storage and retrieval.

Virtual and flexible digital signal processing system based on software PnP and component works

NASA Astrophysics Data System (ADS)

He, Tao; Wu, Qinghua; Zhong, Fei; Li, Wei

2005-05-01

An idea about software PnP (Plug & Play) is put forward according to the hardware PnP. And base on this idea, a virtual flexible digital signal processing system (FVDSPS) is carried out. FVDSPS is composed of a main control center, many sub-function modules and other hardware I/O modules. Main control center sends out commands to sub-function modules, and manages running orders, parameters and results of sub-functions. The software kernel of FVDSPS is DSP (Digital Signal Processing) module, which communicates with the main control center through some protocols, accept commands or send requirements. The data sharing and exchanging between the main control center and the DSP modules are carried out and managed by the files system of the Windows Operation System through the effective communication. FVDSPS real orients objects, orients engineers and orients engineering problems. With FVDSPS, users can freely plug and play, and fast reconfigure a signal process system according to engineering problems without programming. What you see is what you get. Thus, an engineer can orient engineering problems directly, pay more attention to engineering problems, and promote the flexibility, reliability and veracity of testing system. Because FVDSPS orients TCP/IP protocol, through Internet, testing engineers, technology experts can be connected freely without space. Engineering problems can be resolved fast and effectively. FVDSPS can be used in many fields such as instruments and meter, fault diagnosis, device maintenance and quality control.

Desert Rats 2010 Operations Tests: Insights from the Geology Crew Members

NASA Technical Reports Server (NTRS)

Bleacher, J. E.; Hurtado, J. M., Jr.; Young, K. E.; Rice, J.; Garry, W. B.; Eppler, D.

2011-01-01

Desert Research and Technology Studies (Desert RATS) is a multi-year series of tests of NASA hardware and operations deployed in the high desert of Arizona. Conducted annually since 1997, these activities exercise planetary surface hardware and operations in relatively harsh conditions where long-distance, multi-day roving is achievable. Such activities not only test vehicle subsystems, they also stress communications and operations systems and enable testing of science operations approaches that advance human and robotic surface exploration capabilities. Desert RATS 2010 tested two crewed rovers designed as first-generation prototypes of small pressurized vehicles, consistent with exploration architecture designs. Each rover provided the internal volume necessary for crewmembers to live and work for periods up to 14 days, as well as allowing for extravehicular activities (EVAs) through the use of rear-mounted suit ports. The 2010 test was designed to simulate geologic science traverses over a 14-day period through a volcanic field that is analogous to volcanic terrains observed throughout the Solar System. The test was conducted between 31 August and 13 September 2010. Two crewmembers lived in and operated each rover for a week with a "shift change" on day 7, resulting in a total of eight test subjects for the two-week period. Each crew consisted of an engineer/commander and an experienced field geologist. Three of the engineer/commanders were experienced astronauts with at least one Space Shuttle flight. The field geologists were drawn from the scientific community, based on funded and published field expertise.

A modular suite of hardware enabling spaceflight cell culture research

NASA Technical Reports Server (NTRS)

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

2004-01-01

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

Applications of Modeling and Simulation for Flight Hardware Processing at Kennedy Space Center

NASA Technical Reports Server (NTRS)

Marshall, Jennifer L.

2010-01-01

The Boeing Design Visualization Group (DVG) is responsible for the creation of highly-detailed representations of both on-site facilities and flight hardware using computer-aided design (CAD) software, with a focus on the ground support equipment (GSE) used to process and prepare the hardware for space. Throughout my ten weeks at this center, I have had the opportunity to work on several projects: the modification of the Multi-Payload Processing Facility (MPPF) High Bay, weekly mapping of the Space Station Processing Facility (SSPF) floor layout, kinematics applications for the Orion Command Module (CM) hatches, and the design modification of the Ares I Upper Stage hatch for maintenance purposes. The main goal of each of these projects was to generate an authentic simulation or representation using DELMIA V5 software. This allowed for evaluation of facility layouts, support equipment placement, and greater process understanding once it was used to demonstrate future processes to customers and other partners. As such, I have had the opportunity to contribute to a skilled team working on diverse projects with a central goal of providing essential planning resources for future center operations.

NASA Operational Simulator for Small Satellites: Tools for Software Based Validation and Verification of Small Satellites

NASA Technical Reports Server (NTRS)

Grubb, Matt

2016-01-01

The NASA Operational Simulator for Small Satellites (NOS3) is a suite of tools to aid in areas such as software development, integration test (IT), mission operations training, verification and validation (VV), and software systems check-out. NOS3 provides a software development environment, a multi-target build system, an operator interface-ground station, dynamics and environment simulations, and software-based hardware models. NOS3 enables the development of flight software (FSW) early in the project life cycle, when access to hardware is typically not available. For small satellites there are extensive lead times on many of the commercial-off-the-shelf (COTS) components as well as limited funding for engineering test units (ETU). Considering the difficulty of providing a hardware test-bed to each developer tester, hardware models are modeled based upon characteristic data or manufacturers data sheets for each individual component. The fidelity of each hardware models is such that FSW executes unaware that physical hardware is not present. This allows binaries to be compiled for both the simulation environment, and the flight computer, without changing the FSW source code. For hardware models that provide data dependent on the environment, such as a GPS receiver or magnetometer, an open-source tool from NASA GSFC (42 Spacecraft Simulation) is used to provide the necessary data. The underlying infrastructure used to transfer messages between FSW and the hardware models can also be used to monitor, intercept, and inject messages, which has proven to be beneficial for VV of larger missions such as James Webb Space Telescope (JWST). As hardware is procured, drivers can be added to the environment to enable hardware-in-the-loop (HWIL) testing. When strict time synchronization is not vital, any number of combinations of hardware components and software-based models can be tested. The open-source operator interface used in NOS3 is COSMOS from Ball Aerospace. For testing, plug-ins are implemented in COSMOS to control the NOS3 simulations, while the command and telemetry tools available in COSMOS are used to communicate with FSW. NOS3 is actively being used for FSW development and component testing of the Simulation-to-Flight 1 (STF-1) CubeSat. As NOS3 matures, hardware models have been added for common CubeSat components such as Novatel GPS receivers, ClydeSpace electrical power systems and batteries, ISISpace antenna systems, etc. In the future, NASA IVV plans to distribute NOS3 to other CubeSat developers and release the suite to the open-source community.

A Dedicated Microprocessor Controller for a Bound Document Scanner.

DTIC Science & Technology

1984-06-01

focused onto the CCD which converts the image into 2048 pixels. After the pixel data are processed by the scanner hardware, they are sent to the display...data in real time after the data on each of the 2048 pixel elements .-.- .---.; . has been transferred out of the device. Display-control commands and...05 06 07 Fig. 4.9 2716 EPROM Block D~iagram and Pin Assignment HE-E 64 BYTES RA ’ FFF 4095 INTERNAL I FCO 4032 EXECUTABLE FBP 4031 RA Soo0 2048 _ _7FF

Portrait of the Mir 23 crew in the Base Block

NASA Image and Video Library

1997-02-26

NM23-48-003 (29 April 1997) --- Cosmonaut Vasili V. Tsibliyev, Mir-23 commander, operates at the end of the Russian Mir Space Station’s STRELA boom during a space walk on April 29, 1997. He was joined by United States astronaut Jerry M. Linenger, cosmonaut guest researcher, in an effort to deploy scientific instruments and retrieve other science hardware. At the lower left of the picture is the Kvant-1 module. Hovering above it is the Sofora tower, which was once used for an experiment in attitude control of the Mir.

KSC-03pd1103

NASA Image and Video Library

2003-04-10

KENNEDY SPACE CENTER, FLA. -- Kennedy Space Center workers chat with Forest Service workers at the Hemphill site in East Texas before heading out to the field for grid searches. KSC workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

KSC-03pd1109

NASA Image and Video Library

2003-04-10

KENNEDY SPACE CENTER, FLA. -- A memorial erected by the Hemphill, Texas, community commemorates a location where remains of a fallen Columbia astronaut were found. Kennedy Space Center workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

Lineger and Tsibliev during EVA outside Mir Space Station

NASA Image and Video Library

1997-04-29

NM23-48-009 (29 April 1997) --- United States astronaut Jerry M. Linenger, cosmonaut guest researcher, works outside the Russian Mir Space Station during a joint United States-Russian space walk on April 29, 1997. He was joined by Mir-23 commander Vasili V. Tsibliyev (out of frame) for the five-hour Extravehicular Activity (EVA) designed to deploy scientific instruments and retrieve other science hardware. At the top of the frame is a Russian Progress re-supply capsule docked to the Mir’s Kvant-1 module.

KSC-2009-6141

NASA Image and Video Library

2009-11-06

CAPE CANAVERAL, Fla. – In Orbiter Processing Facility-3 at NASA's Kennedy Space Center in Florida, STS-130 Commander George Zamka dressed in clean-room attire, known as a "bunny suit," gets the feel of the cockpit of space shuttle Endeavour. The crew is at Kennedy for a crew equipment interface test, or CEIT, which provides hands-on training and observation of shuttle and flight hardware. The STS-130 flight will carry the Tranquility pressurized module with a built-in cupola to the International Space Station aboard Endeavour. Launch is targeted for Feb. 4, 2010. Photo credit: NASA/Kim Shiflett

KSC-06pd2358

NASA Image and Video Library

2006-10-14

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, STS-116 Commander Mark Polansky checks the cockpit window of Discovery as part of a Crew Equipment Interface Test (CEIT). A CEIT allows astronauts to become familiar with equipment and hardware they will use on the mission. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Kim Shiflett

KSC-06pd2357

NASA Image and Video Library

2006-10-14

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, STS-116 Commander Mark Polansky checks the cockpit window as part of a Crew Equipment Interface Test (CEIT). A CEIT allows astronauts to become familiar with equipment and hardware they will use on the mission. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Kim Shiflett

Digital Baseband Architecture For Transponder

NASA Technical Reports Server (NTRS)

Nguyen, Tien M.; Yeh, Hen-Geul

1995-01-01

Proposed advanced transponder for long-distance radio communication system with turnaround ranging contains carrier-signal-tracking loop including baseband digital "front end." For reduced cost, transponder includes analog intermediate-frequency (IF) section and analog automatic gain control (AGC) loop at first of two IF mixers. However, second IF mixer redesigned to ease digitization of baseband functions. To conserve power and provide for simpler and smaller transponder hardware, baseband digital signal-processing circuits designed to implement undersampling scheme. Furthermore, sampling scheme and sampling frequency chosen so redesign involves minimum modification of command-detector unit (CDU).

A tensor approach to modeling of nonhomogeneous nonlinear systems

NASA Technical Reports Server (NTRS)

Yurkovich, S.; Sain, M.

1980-01-01

Model following control methodology plays a key role in numerous application areas. Cases in point include flight control systems and gas turbine engine control systems. Typical uses of such a design strategy involve the determination of nonlinear models which generate requested control and response trajectories for various commands. Linear multivariable techniques provide trim about these motions; and protection logic is added to secure the hardware from excursions beyond the specification range. This paper reports upon experience in developing a general class of such nonlinear models based upon the idea of the algebraic tensor product.

Flight Avionics Hardware Roadmap

NASA Technical Reports Server (NTRS)

Hodson, Robert; McCabe, Mary; Paulick, Paul; Ruffner, Tim; Some, Rafi; Chen, Yuan; Vitalpur, Sharada; Hughes, Mark; Ling, Kuok; Redifer, Matt;

Using Multi-Core Systems for Rover Autonomy

NASA Technical Reports Server (NTRS)

Clement, Brad; Estlin, Tara; Bornstein, Benjamin; Springer, Paul; Anderson, Robert C.

2010-01-01

Task Objectives are: (1) Develop and demonstrate key capabilities for rover long-range science operations using multi-core computing, (a) Adapt three rover technologies to execute on SOA multi-core processor (b) Illustrate performance improvements achieved (c) Demonstrate adapted capabilities with rover hardware, (2) Targeting three high-level autonomy technologies (a) Two for onboard data analysis (b) One for onboard command sequencing/planning, (3) Technologies identified as enabling for future missions, (4)Benefits will be measured along several metrics: (a) Execution time / Power requirements (b) Number of data products processed per unit time (c) Solution quality

KSC-03PD-1103

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. -- Kennedy Space Center workers chat with Forest Service workers at the Hemphill site in East Texas before heading out to the field for grid searches. KSC workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

Development of a Power Electronics Unit for the Space Station Plasma Contactor

NASA Technical Reports Server (NTRS)

Hamley, John A.; Hill, Gerald M.; Patterson, Michael J.; Saggio, Joseph, Jr.; Terdan, Fred; Mansell, Justin D.

1994-01-01

A hollow cathode plasma contactor has been baselined as a charge control device for the Space Station (SS) to prevent deleterious interactions of coated structural components with the ambient plasma. NASA LeRC Work Package 4 initiated the development of a plasma contactor system comprised of a Power Electronics Unit (PEU), an Expellant Management Unit (EMU), a command and data interface, and a Plasma Contactor Unit (PCU). A breadboard PEU was designed and fabricated. The breadboard PEU contains a cathode heater and discharge power supply, which were required to operate the PCU, a control and auxiliary power converter, an EMU interface, a command and telemetry interface, and a controller. The cathode heater and discharge supplies utilized a push-pull topology with a switching frequency of 20 kHz and pulse-width-modulated (PWM) control. A pulse ignition circuit derived from that used in arcjet power processors was incorporated in the discharge supply for discharge ignition. An 8088 based microcontroller was utilized in the breadboard model to provide a flexible platform for controller development with a simple command/data interface incorporating a direct connection to SS Mulitplexer/Demultiplexer (MDM) analog and digital I/O cards. Incorporating this in the flight model would eliminate the hardware and software overhead associated with a 1553 serial interface. The PEU autonomously operated the plasma contactor based on command inputs and was successfully integrated with a prototype plasma contactor unit demonstrating reliable ignition of the discharge and steady-state operation.

BMDS/SSA Integrated Sensing Demonstration (BISD)

NASA Astrophysics Data System (ADS)

Turner, T.; Springford, K.; Grimaldi, L.

2011-09-01

This demonstration is intended to provide a near-term prototype, leave-behind capability for integrating Ballistic Missile Defense System (BMDS) ground sensors for use in the Space Situational Awareness (SSA) mission. Closed-loop tasking and cueing capability will be implemented, and a demonstration of net-centric space data dissemination using the BMDS sensors will be undertaken using various SSA mission threads. The demonstration is designed to highlight the implications of modifying software and/or hardware at the BMDS command and control node so that cost, risk, and schedule for an operational implementation can be fully understood. Additionally, this demonstration is intended to assess the impacts to both mission areas as a multi-mission, non-traditional sensor capability is integrated into the SSA mission. A successful demonstration will have many leave-behind capabilities and first-of-its-kind achievements to include: a) an extensible SSA operational prototype configuration for BMDS X-Band radars such as AN/TPY-2 and Sea-Based X-Band (SBX) b) a prototype SSA tasking and cueing capability between the Joint Functional Component Command for Space (JFCC Space) Joint Space Operations Center (JSpOC) and the Command, Control, Battle Management, and Communications (C2BMC) Experimental Laboratory (X-Lab), extensible to the Combatant Commands (COCOMS), and out to BMDS sensors c) a capability for a twoway, net-centric, interface for JSpOC space operations, to include translation from net-centric communications to legacy systems and d) processing of BMDS X-Band Radar tracks in the Space Defense Operations Center (SPADOC).

Design and development of control unit and software for the ADFOSC instrument of the 3.6 m Devasthal optical telescope

NASA Astrophysics Data System (ADS)

Kumar, T. S.

2016-08-01

In this paper, we describe the details of control unit and GUI software for positioning two filter wheels, a slit wheel and a grism wheel in the ADFOSC instrument. This is a first generation instrument being built for the 3.6 m Devasthal optical telescope. The control hardware consists of five electronic boards based on low cost 8-bit PIC microcontrollers and are distributed over I2C bus. The four wheels are controlled by four identical boards which are configured in I2C slave mode while the fifth board acts as an I2C master for sending commands to and receiving status from the slave boards. The master also communicates with the interfacing PC over TCP/IP protocol using simple ASCII commands. For moving the wheels stepper motors along with suitable amplifiers have been employed. Homing after powering ON is achieved using hall effect sensors. By implementing distributed control units having identical design modularity is achieved enabling easier maintenance and upgradation. A GUI based software for commanding the instrument is developed in Microsoft Visual C++. For operating the system during observations the user selects normal mode while the engineering mode is available for offering additional flexibility and low level control during maintenance and testing. A detailed time-stamped log of commands, status and errors are continuously generated. Both the control unit and the software have been successfully tested and integrated with the ADFOSC instrument.

Payload Bay Canister being transported to Pad 39A for a fit chec

NASA Image and Video Library

2007-01-22

This payload canister is being transported to Launch Pad 39A for a "fit check." At a later date, the canister will be used to transport to the pad the S3/S4 solar arrays that are the payload for mission STS-117. The mission will launch on Space Shuttle Atlantis for the 21st flight to the International Space Station, and the crew of six will continue the construction of station with the installation of the arrays. The launch of Atlantis is targeted for March 16.

Experimental Validation: Subscale Aircraft Ground Facilities and Integrated Test Capability

NASA Technical Reports Server (NTRS)

Bailey, Roger M.; Hostetler, Robert W., Jr.; Barnes, Kevin N.; Belcastro, Celeste M.; Belcastro, Christine M.

2005-01-01

Experimental testing is an important aspect of validating complex integrated safety critical aircraft technologies. The Airborne Subscale Transport Aircraft Research (AirSTAR) Testbed is being developed at NASA Langley to validate technologies under conditions that cannot be flight validated with full-scale vehicles. The AirSTAR capability comprises a series of flying sub-scale models, associated ground-support equipment, and a base research station at NASA Langley. The subscale model capability utilizes a generic 5.5% scaled transport class vehicle known as the Generic Transport Model (GTM). The AirSTAR Ground Facilities encompass the hardware and software infrastructure necessary to provide comprehensive support services for the GTM testbed. The ground facilities support remote piloting of the GTM aircraft, and include all subsystems required for data/video telemetry, experimental flight control algorithm implementation and evaluation, GTM simulation, data recording/archiving, and audio communications. The ground facilities include a self-contained, motorized vehicle serving as a mobile research command/operations center, capable of deployment to remote sites when conducting GTM flight experiments. The ground facilities also include a laboratory based at NASA LaRC providing near identical capabilities as the mobile command/operations center, as well as the capability to receive data/video/audio from, and send data/audio to the mobile command/operations center during GTM flight experiments.

Honeywell optical investigations on FLASH program

NASA Astrophysics Data System (ADS)

O'Rourke, Ken; Peterson, Eric; Yount, Larry

1995-05-01

The increasing performance and reduction of life cycle cost requirements placed on commercial and military transport aircraft are resulting in more complex, highly integrated aircraft control and management systems. The use of fiber optic data transmission media can make significant contributions in achieving these performance and cost goals. The Honeywell portion of Task 2A on the Fly-by-Light Advanced System Hardware (FLASH) program is evaluating a Primary Flight Control System (PFCS) using pilot and copilot inputs from Active Hand Controllers (AHC) which are optically linked to the primary flight Control Computers (PFCC). Customer involvement is an important element of the Task 2A activity. Establishing customer requirements and perspectives on productization of systems developed under FLASH are key to future product success. The Honeywell elements of the PFCS demonstrator provide a command path that is optically interfaced from crew inputs to commands of distributed, smart actuation subsystems commands. Optical communication architectures are implemented using several protocols including the new AS-1773A 20 Mbps data bus standard. The interconnecting fiber optic cable plant is provided by our Task 1A teammate McDonnell Douglas Aerospace (West). Fiber optic cable plant fabrication uses processed, tools and materials reflecting necessary advances in manufacturing required to make fly-by-light avionics systems marketable.

Software systems for operation, control, and monitoring of the EBEX instrument

NASA Astrophysics Data System (ADS)

Milligan, Michael; Ade, Peter; Aubin, François; Baccigalupi, Carlo; Bao, Chaoyun; Borrill, Julian; Cantalupo, Christopher; Chapman, Daniel; Didier, Joy; Dobbs, Matt; Grainger, Will; Hanany, Shaul; Hillbrand, Seth; Hubmayr, Johannes; Hyland, Peter; Jaffe, Andrew; Johnson, Bradley; Kisner, Theodore; Klein, Jeff; Korotkov, Andrei; Leach, Sam; Lee, Adrian; Levinson, Lorne; Limon, Michele; MacDermid, Kevin; Matsumura, Tomotake; Miller, Amber; Pascale, Enzo; Polsgrove, Daniel; Ponthieu, Nicolas; Raach, Kate; Reichborn-Kjennerud, Britt; Sagiv, Ilan; Tran, Huan; Tucker, Gregory S.; Vinokurov, Yury; Yadav, Amit; Zaldarriaga, Matias; Zilic, Kyle

2010-07-01

We present the hardware and software systems implementing autonomous operation, distributed real-time monitoring, and control for the EBEX instrument. EBEX is a NASA-funded balloon-borne microwave polarimeter designed for a 14 day Antarctic flight that circumnavigates the pole. To meet its science goals the EBEX instrument autonomously executes several tasks in parallel: it collects attitude data and maintains pointing control in order to adhere to an observing schedule; tunes and operates up to 1920 TES bolometers and 120 SQUID amplifiers controlled by as many as 30 embedded computers; coordinates and dispatches jobs across an onboard computer network to manage this detector readout system; logs over 3 GiB/hour of science and housekeeping data to an onboard disk storage array; responds to a variety of commands and exogenous events; and downlinks multiple heterogeneous data streams representing a selected subset of the total logged data. Most of the systems implementing these functions have been tested during a recent engineering flight of the payload, and have proven to meet the target requirements. The EBEX ground segment couples uplink and downlink hardware to a client-server software stack, enabling real-time monitoring and command responsibility to be distributed across the public internet or other standard computer networks. Using the emerging dirfile standard as a uniform intermediate data format, a variety of front end programs provide access to different components and views of the downlinked data products. This distributed architecture was demonstrated operating across multiple widely dispersed sites prior to and during the EBEX engineering flight.

DebriSat: The New Hypervelocity Impact Test for Satellite Breakup Fragment Characterization

NASA Technical Reports Server (NTRS)

Cowardin, Heather

2015-01-01

To replicate a hyper-velocity fragmentation event using modern-day spacecraft materials and construction techniques to better improve the existing DoD and NASA breakup models: DebriSat is intended to be representative of modern LEO satellites. Major design decisions were reviewed and approved by Aerospace subject matter experts from different disciplines. DebriSat includes 7 major subsystems. Attitude determination and control system (ADCS), command and data handling (C&DH), electrical power system (EPS), payload, propulsion, telemetry tracking and command (TT&C), and thermal management. To reduce cost, most components are emulated based on existing design of flight hardware and fabricated with the same materials. center dotA key laboratory-based test, Satellite Orbital debris Characterization Impact Test (SOCIT), supporting the development of the DoD and NASA satellite breakup models was conducted at AEDC in 1992. Breakup models based on SOCIT have supported many applications and matched on-orbit events reasonably well over the years.

Embedded systems for supporting computer accessibility.

PubMed

Mulfari, Davide; Celesti, Antonio; Fazio, Maria; Villari, Massimo; Puliafito, Antonio

2015-01-01

Nowadays, customized AT software solutions allow their users to interact with various kinds of computer systems. Such tools are generally available on personal devices (e.g., smartphones, laptops and so on) commonly used by a person with a disability. In this paper, we investigate a way of using the aforementioned AT equipments in order to access many different devices without assistive preferences. The solution takes advantage of open source hardware and its core component consists of an affordable Linux embedded system: it grabs data coming from the assistive software, which runs on the user's personal device, then, after processing, it generates native keyboard and mouse HID commands for the target computing device controlled by the end user. This process supports any operating system available on the target machine and it requires no specialized software installation; therefore the user with a disability can rely on a single assistive tool to control a wide range of computing platforms, including conventional computers and many kinds of mobile devices, which receive input commands through the USB HID protocol.

Sliding mode disturbance observer-based control of a twin rotor MIMO system.

PubMed

Rashad, Ramy; El-Badawy, Ayman; Aboudonia, Ahmed

2017-07-01

This work proposes a robust tracking controller for a helicopter laboratory setup known as the twin rotor MIMO system (TRMS) using an integral sliding mode controller. To eliminate the discontinuity in the control signal, the controller is augmented by a sliding mode disturbance observer. The actuator dynamics is handled using a backstepping approach which is applicable due to the continuous chattering-free nature of the command signals generated using the disturbance observer based controller. To avoid the complexity of analytically differentiating the command signals, a first order sliding mode differentiator is used. Stability analysis of the closed loop system and the ultimate boundedness of the tracking error is proved using Lyapunov stability arguments. The proposed controller is validated by several simulation studies and is compared to other schemes in the literature. Experimental results using a hardware-in-the-loop system validate the robustness and effectiveness of the proposed controller. Copyright © 2017 ISA. Published by Elsevier Ltd. All rights reserved.

Software architecture for intelligent image processing using Prolog

NASA Astrophysics Data System (ADS)

Jones, Andrew C.; Batchelor, Bruce G.

1994-10-01

We describe a prototype system for interactive image processing using Prolog, implemented by the first author on an Apple Macintosh computer. This system is inspired by Prolog+, but differs from it in two particularly important respects. The first is that whereas Prolog+ assumes the availability of dedicated image processing hardware, with which the Prolog system communicates, our present system implements image processing functions in software using the C programming language. The second difference is that although our present system supports Prolog+ commands, these are implemented in terms of lower-level Prolog predicates which provide a more flexible approach to image manipulation. We discuss the impact of the Apple Macintosh operating system upon the implementation of the image-processing functions, and the interface between these functions and the Prolog system. We also explain how the Prolog+ commands have been implemented. The system described in this paper is a fairly early prototype, and we outline how we intend to develop the system, a task which is expedited by the extensible architecture we have implemented.

An integrated dexterous robotic testbed for space applications

NASA Technical Reports Server (NTRS)

Li, Larry C.; Nguyen, Hai; Sauer, Edward

1992-01-01

An integrated dexterous robotic system was developed as a testbed to evaluate various robotics technologies for advanced space applications. The system configuration consisted of a Utah/MIT Dexterous Hand, a PUMA 562 arm, a stereo vision system, and a multiprocessing computer control system. In addition to these major subsystems, a proximity sensing system was integrated with the Utah/MIT Hand to provide capability for non-contact sensing of a nearby object. A high-speed fiber-optic link was used to transmit digitized proximity sensor signals back to the multiprocessing control system. The hardware system was designed to satisfy the requirements for both teleoperated and autonomous operations. The software system was designed to exploit parallel processing capability, pursue functional modularity, incorporate artificial intelligence for robot control, allow high-level symbolic robot commands, maximize reusable code, minimize compilation requirements, and provide an interactive application development and debugging environment for the end users. An overview is presented of the system hardware and software configurations, and implementation is discussed of subsystem functions.

A gimbal platform stabilization for topographic applications

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

Michele, Mangiameli, E-mail: michele.mangiameli@dica.unict.it; Giuseppe, Mussumeci

2015-03-10

The aim of this work is the stabilization of a Gimbal platform for optical sensors acquisitions in topographic applications using mobile vehicles. The stabilization of the line of sight (LOS) consists in tracking the command velocity in presence of nonlinear noise due to the external environment. The hardware architecture is characterized by an Ardupilot platform that allows the control of both the mobile device and the Gimbal. Here we developed a new approach to stabilize the Gimbal platform, which is based on neural network. For the control system, we considered a plant that represents the transfer function of the servomore » system control model for an inertial stabilized Gimbal platform. The transductor used in the feed-back line control is characterized by the Rate Gyro transfer function installed onboard of Ardupilot. For the simulation and investigation of the system performance, we used the Simulink tool of Matlab. Results show that the hardware/software approach is efficient, reliable and cheap for direct photogrammetry, as well as for general purpose applications using mobile vehicles.« less

The X-38 Spacecraft Fault-Tolerant Avionics System

NASA Technical Reports Server (NTRS)

Kouba,Coy; Buscher, Deborah; Busa, Joseph

2003-01-01

In 1995 NASA began an experimental program to develop a reusable crew return vehicle (CRV) for the International Space Station. The purpose of the CRV was threefold: (i) to bring home an injured or ill crewmember; (ii) to bring home the entire crew if the Shuttle fleet was grounded; and (iii) to evacuate the crew in the case of an imminent Station threat (i.e., fire, decompression, etc). Built at the Johnson Space Center, were two approach and landing prototypes and one spacecraft demonstrator (called V201). A series of increasingly complex ground subsystem tests were completed, and eight successful high-altitude drop tests were achieved to prove the design concept. In this program, an unprecedented amount of commercial-off-the-shelf technology was utilized in this first crewed spacecraft NASA has built since the Shuttle program. Unfortunately, in 2002 the program was canceled due to changing Agency priorities. The vehicle was 80% complete and the program was shut down in such a manner as to preserve design, development, test and engineering data. This paper describes the X-38 V201 fault-tolerant avionics system. Based on Draper Laboratory's Byzantine-resilient fault-tolerant parallel processing system and their "network element" hardware, each flight computer exchanges information on a strict timescale to process input data, compare results, and issue voted vehicle output commands. Major accomplishments achieved in this development include: (i) a space qualified two-fault tolerant design using mostly COTS (hardware and operating system); (ii) a single event upset tolerant network element board, (iii) on-the-fly recovery of a failed processor; (iv) use of synched cache; (v) realignment of memory to bring back a failed channel; (vi) flight code automatically generated from the master measurement list; and (vii) built in-house by a team of civil servants and support contractors. This paper will present an overview of the avionics system and the hardware implementation, as well as the system software and vehicle command & telemetry functions. Potential improvements and lessons learned on this program are also discussed.

Physiology of chimpanzees in orbit. Part 2: Interface document

NASA Technical Reports Server (NTRS)

Firstenberg, A.

1972-01-01

Interface requirements are presented for the design and development of an earth orbiting experiment to be known as POCO, Physiology of Chimpanzees in Orbit. The POCO experiment may be designed to operate within an orbiting space station (provided artificial gravity measures are not employed), a Saturn 4-B workshop, an Apollo command module or service module, a Saturn-1B spacecraft LM adapter, or aboard one of the presently conceived appendages connected by an umbilical to a space station. This document sets forth the experiment definition and requirements and describes the hardware under development to accomplish these objectives.

Space Shuttle orbiter Columbia touches down at Edwards Air Force Base

NASA Image and Video Library

1981-04-14

S81-30744 (14 April 1981) --- The rear wheels of the space shuttle orbiter Columbia are about to touch down on Rogers Lake (a dry bed) at Edwards Air Force Base in southern California to successfully complete a stay in space of more than two days. Astronauts John W. Young, STS-1 commander, and Robert L. Crippen, pilot, are aboard the vehicle. The mission marked the first NASA flight to end with a wheeled landing and represents the beginning of a new age of spaceflight that will employ the same hardware repeatedly. Photo credit: NASA

Mission management, planning, and cost: PULSE Attitude And Control Systems (AACS)

NASA Technical Reports Server (NTRS)

1990-01-01

The Pluto unmanned long-range scientific explorer (PULSE) is a probe that will do a flyby of Pluto. It is a low weight, relatively low costing vehicle which utilizes mostly off-the-shelf hardware, but not materials or techniques that will be available after 1999. A design, fabrication, and cost analysis is presented. PULSE will be launched within the first decade of the twenty-first century. The topics include: (1) scientific instrumentation; (2) mission management, planning, and costing; (3) power and propulsion systems; (4) structural subsystem; (5) command, control, and communication; and (6) attitude and articulation control.

Short Message Service (SMS) Command and Control (C2) Awareness in Android-based Smartphones Using Kernel-Level Auditing

DTIC Science & Technology

2012-06-14

Display 480 x 800 pixels (3.7 inches) CPU Qualcomm QSD8250 1GHz Memory (internal) 512MB RAM / 512 MB ROM Kernel version 2.6.35.7-ge0fb012 Figure 3.5: HTC...development and writing). The 34 MSM kernel provided by the AOSP and compatible with the HTC Nexus One’s motherboard and Qualcomm chipset, is used for this...building the kernel is having the prebuilt toolchains and the right kernel for the hardware. Many HTC products use Qualcomm processors which uses the

Will the future of knowledge work automation transform personalized medicine?

PubMed

Naik, Gauri; Bhide, Sanika S

2014-09-01

Today, we live in a world of 'information overload' which demands high level of knowledge-based work. However, advances in computer hardware and software have opened possibilities to automate 'routine cognitive tasks' for knowledge processing. Engineering intelligent software systems that can process large data sets using unstructured commands and subtle judgments and have the ability to learn 'on the fly' are a significant step towards automation of knowledge work. The applications of this technology for high throughput genomic analysis, database updating, reporting clinically significant variants, and diagnostic imaging purposes are explored using case studies.

KSC-03pd1105

NASA Image and Video Library

2003-04-10

KENNEDY SPACE CENTER, FLA. -- David Mclaughlin, Prototype Lab technician at Kennedy Space Center, (center) poses with his Native American search team, the Laguna Firefighters from New Mexico, at the Hemphill site. Kennedy Space Center workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

KSC-03pd1113

NASA Image and Video Library

2003-04-09

KENNEDY SPACE CENTER, FLA. -- Kennedy Space Center and Forest Service workers pose in front of a helicopter landed at the Nacogdoches field site. The helicopter is one of those being used to survey for parts of Columbia. KSC workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

Operations Nomenclature [Annexes

NASA Technical Reports Server (NTRS)

Shannon, Yvette Y.

2011-01-01

The purpose of Operations Nomenclature (OpNom) is to document methods for denoting all hardware and software and associated data referenced by operations products produced by the International Space Station (ISS) operations community. This includes Operations Data File (ODF) procedures, ground and onboard displays, mission rules, commands, messages and advisories, planning products, etc. This document applies to all agencies and individuals participating in or contributing to ISS mission operations. Mission operations include ground checkout, training, and simulations, as well as real-time activities. The document also applies to all operations documentation (paper or electronic media) and other products that refer to ISS-related equipment or activities.

A diagnostic prototype of the potable water subsystem of the Space Station Freedom ECLSS

NASA Technical Reports Server (NTRS)

Lukefahr, Brenda D.; Rochowiak, Daniel M.; Benson, Brian L.; Rogers, John S.; Mckee, James W.

1989-01-01

In analyzing the baseline Environmental Control and Life Support System (ECLSS) command and control architecture, various processes are found which would be enhanced by the use of knowledge based system methods of implementation. The most suitable process for prototyping using rule based methods are documented, while domain knowledge resources and other practical considerations are examined. Requirements for a prototype rule based software system are documented. These requirements reflect Space Station Freedom ECLSS software and hardware development efforts, and knowledge based system requirements. A quick prototype knowledge based system environment is researched and developed.

Federal Emergency Management Information System (FEMIS) system administration guide. Version 1.2

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

Burford, M.J.; Burnett, R.A.; Curtis, L.M.

The Federal Emergency Management Information System (FEMIS) is an emergency management planning and analysis tool that is being developed under the direction of the US Army Chemical biological Defense Command. The FEMIS System Administration Guide defines FEMIS hardware and software requirements and gives instructions for installing the FEMIS system package. System administrators, database administrators, and general users can use this guide to install, configure, and maintain the FEMIS client software package. This document provides a description of the FEMIS environment; distribution media; data, communications, and electronic mail servers; user workstations; and system management.

Programming Language Software For Graphics Applications

NASA Technical Reports Server (NTRS)

Beckman, Brian C.

1993-01-01

New approach reduces repetitive development of features common to different applications. High-level programming language and interactive environment with access to graphical hardware and software created by adding graphical commands and other constructs to standardized, general-purpose programming language, "Scheme". Designed for use in developing other software incorporating interactive computer-graphics capabilities into application programs. Provides alternative to programming entire applications in C or FORTRAN, specifically ameliorating design and implementation of complex control and data structures typifying applications with interactive graphics. Enables experimental programming and rapid development of prototype software, and yields high-level programs serving as executable versions of software-design documentation.

Firing Room Remote Application Software Development

NASA Technical Reports Server (NTRS)

Liu, Kan

2014-01-01

The Engineering and Technology Directorate (NE) at National Aeronautics and Space Administration (NASA) Kennedy Space Center (KSC) is designing a new command and control system for the checkout and launch of Space Launch System (SLS) and future rockets. The purposes of the semester long internship as a remote application software developer include the design, development, integration, and verification of the software and hardware in the firing rooms, in particular with the Mobile Launcher (ML) Launch Accessories subsystem. In addition, a Conversion Fusion project was created to show specific approved checkout and launch engineering data for public-friendly display purposes.

Firing Room Remote Application Software Development

NASA Technical Reports Server (NTRS)

Liu, Kan

2015-01-01

The Engineering and Technology Directorate (NE) at National Aeronautics and Space Administration (NASA) Kennedy Space Center (KSC) is designing a new command and control system for the checkout and launch of Space Launch System (SLS) and future rockets. The purposes of the semester long internship as a remote application software developer include the design, development, integration, and verification of the software and hardware in the firing rooms, in particular with the Mobile Launcher (ML) Launch Accessories (LACC) subsystem. In addition, a software test verification procedure document was created to verify and checkout LACC software for Launch Equipment Test Facility (LETF) testing.

Sensor Authentication: Embedded Processor Code

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

Svoboda, John

2012-09-25

Described is the c code running on the embedded Microchip 32bit PIC32MX575F256H located on the INL developed noise analysis circuit board. The code performs the following functions: Controls the noise analysis circuit board preamplifier voltage gains of 1, 10, 100, 000 Initializes the analog to digital conversion hardware, input channel selection, Fast Fourier Transform (FFT) function, USB communications interface, and internal memory allocations Initiates high resolution 4096 point 200 kHz data acquisition Computes complex 2048 point FFT and FFT magnitude. Services Host command set Transfers raw data to Host Transfers FFT result to host Communication error checking

Eight microprocessor-based instrument data systems in the Galileo Orbiter spacecraft

NASA Technical Reports Server (NTRS)

Barry, R. C.

1980-01-01

Instrument data systems consist of a microprocessor, 3K bytes of Read Only Memory and 3K bytes of Random Access Memory. It interfaces with the spacecraft data bus through an isolated user interface with a direct memory access bus adaptor, and/or parallel data from instrument devices such as registers, buffers, analog to digital converters, multiplexers, and solid state sensors. These data systems support the spacecraft hardware and software communication protocol, decode and process instrument commands, generate continuous instrument operating modes, control the instrument mechanisms, acquire, process, format, and output instrument science data.

Command Flight Path Display. Phase I and II.

DTIC Science & Technology

1983-09-01

transmissions over the standard 56K baud interface. The PS-300 was a commercial unit and required some modifications to ensure its reliability in an...1 H7750-AA Battery Backup NADC 5 Oct E2 9 1 LA-12D Decwriter SAI/RtS 4 11ov 82 10 1 BC03M-25 Null Modem Cable SAI/RM0S 4 Nov 82 35 2 ~%*~’ .5°’ 11 1...of about 1200 baud. (The interface hardware is capable of 56K baud transmission, but the standard PS-300 firmware is only able to process input

KSC-07pd3555

NASA Image and Video Library

2007-11-30

KENNEDY SPACE CENTER, FLA. -- In the Orbiter Processing Facility, STS-123 crew members inspect the thermal protection system tiles on the underside of space shuttle Endeavour. From left are Mission Specialists Takao Doi, Michael Foreman and Richard Linnehan, Pilot Gregory Johnson (turned away), Commander Dominic Gorie and Mission Specialist Robert Behnken. They are at NASA's Kennedy Space Center for a crew equipment interface test, a process of familiarization with payloads, hardware and the space shuttle. The STS-123 mission is targeted for launch on space shuttle Endeavour on Feb. 14. It will be the 25th assembly flight of the station. Photo credit: NASA/Kim Shiflett

KSC-07pd3553

NASA Image and Video Library

2007-11-30

KENNEDY SPACE CENTER, FLA. -- In the Orbiter Processing Facility, STS-123 crew members inspect the wheel well on the underside of space shuttle Endeavour. From left front are astronaut Garrett Reisman, Mission Specialists Takao Doi, Michael Foreman and Richard Linnehan, Commander Dominic Gorie, Pilot Gregory Johnson and Mission Specialist Robert Behnken. They are at NASA's Kennedy Space Center for a crew equipment interface test, a process of familiarization with payloads, hardware and the space shuttle. The STS-123 mission is targeted for launch on space shuttle Endeavour on Feb. 14. It will be the 25th assembly flight of the station. Photo credit: NASA/Kim Shiflett

Richard B. Russell Dam and Lake, Savannah River, Georgia and South Carolina Final Foundation Report, Concrete Dam, Embankments and Powerhouse. Volume 2. Appendices

DTIC Science & Technology

1989-10-03

Georgia. TESTED 8y CHEcKED BY REPORTED BY, C PHONE 0 WIRE *GVJ DE SAMPLED BY OATE : SAO FORM IS$ Page of 20 24 OCT So Previous editions of this fore are...block for bto; line system. Cos- - $514.00 PO)8 - Second Stage Dike VE - Mod D Change in design for portion of 2nd stage cofferdike near tie-in with...ATION (Coordinteat~ Station)N14; _______________________________________12. MANUFACTURER’S DESIGNATION OF DRILL. 3. DRILLING AGENCY d~l gjr GvA.IIw1

Advancements in hardware-in-the-loop simulations at the U.S. Army Aviation and Missile Command

NASA Astrophysics Data System (ADS)

Buford, James A.; Jolly, Alexander C.; Mobley, Scott B.; Sholes, William J.

2000-07-01

A greater awareness of and increased interest in the use of modeling and simulation (M&S) has been demonstrated at many levels within the Department of Defense (DoD) and all the Armed Services agencies in recent years. M&S application is regarded as a viable means of lowering the life cycle costs of missile defense and tactical missile weapon system acquisition beginning with studies of new concepts of war-fighting through user training and post-deployment support. The Aviation and Missile Research, Engineering, and Development Center (AMRDEC) of the U.S. Army Aviation and Missile Command (AMCOM) has an extensive history of applying all types of M&S to weapons system development and has been a particularly strong advocate of hardware-in-the-loop (HWIL) simulation and test for many years. Over the past 40 years AMRDEC has developed and maintained the Advanced Simulation Center (ASC) which provides world-class, high fidelity, specific and dedicated HWIL simulation and test capabilities for the Army's missile defense and tactical missile program offices in both the infrared and radio frequency sensor domains. The ASC facility uses M&S to conduct daily HWIL missile simulations and tests to support flight tests, missile/system development, independent verification and validation of weapon system embedded software and simulations, and missile/system performance against current and future threat environments. This paper describes the ASC role, recaps the past year, describes the HWIL components and advancements, and outlines the path-ahead for the ASC in terms of both missile and complete system HWIL simulations and test with a focus on the imaging infrared systems.

Development and Flight Testing of an Adaptive Vehicle Health-Monitoring Architecture

NASA Technical Reports Server (NTRS)

Woodard, Stanley E.; Coffey, Neil C.; Gonzalez, Guillermo A.; Taylor, B. Douglas; Brett, Rube R.; Woodman, Keith L.; Weathered, Brenton W.; Rollins, Courtney H.

2002-01-01

On going development and testing of an adaptable vehicle health-monitoring architecture is presented. The architecture is being developed for a fleet of vehicles. It has three operational levels: one or more remote data acquisition units located throughout the vehicle; a command and control unit located within the vehicle, and, a terminal collection unit to collect analysis results from all vehicles. Each level is capable of performing autonomous analysis with a trained expert system. The expert system is parameterized, which makes it adaptable to be trained to both a user's subject reasoning and existing quantitative analytic tools. Communication between all levels is done with wireless radio frequency interfaces. The remote data acquisition unit has an eight channel programmable digital interface that allows the user discretion for choosing type of sensors; number of sensors, sensor sampling rate and sampling duration for each sensor. The architecture provides framework for a tributary analysis. All measurements at the lowest operational level are reduced to provide analysis results necessary to gauge changes from established baselines. These are then collected at the next level to identify any global trends or common features from the prior level. This process is repeated until the results are reduced at the highest operational level. In the framework, only analysis results are forwarded to the next level to reduce telemetry congestion. The system's remote data acquisition hardware and non-analysis software have been flight tested on the NASA Langley B757's main landing gear. The flight tests were performed to validate the following: the wireless radio frequency communication capabilities of the system, the hardware design, command and control; software operation and, data acquisition, storage and retrieval.

Imaging Sensor Flight and Test Equipment Software

NASA Technical Reports Server (NTRS)

Freestone, Kathleen; Simeone, Louis; Robertson, Byran; Frankford, Maytha; Trice, David; Wallace, Kevin; Wilkerson, DeLisa

2007-01-01

The Lightning Imaging Sensor (LIS) is one of the components onboard the Tropical Rainfall Measuring Mission (TRMM) satellite, and was designed to detect and locate lightning over the tropics. The LIS flight code was developed to run on a single onboard digital signal processor, and has operated the LIS instrument since 1997 when the TRMM satellite was launched. The software provides controller functions to the LIS Real-Time Event Processor (RTEP) and onboard heaters, collects the lightning event data from the RTEP, compresses and formats the data for downlink to the satellite, collects housekeeping data and formats the data for downlink to the satellite, provides command processing and interface to the spacecraft communications and data bus, and provides watchdog functions for error detection. The Special Test Equipment (STE) software was designed to operate specific test equipment used to support the LIS hardware through development, calibration, qualification, and integration with the TRMM spacecraft. The STE software provides the capability to control instrument activation, commanding (including both data formatting and user interfacing), data collection, decompression, and display and image simulation. The LIS STE code was developed for the DOS operating system in the C programming language. Because of the many unique data formats implemented by the flight instrument, the STE software was required to comprehend the same formats, and translate them for the test operator. The hardware interfaces to the LIS instrument using both commercial and custom computer boards, requiring that the STE code integrate this variety into a working system. In addition, the requirement to provide RTEP test capability dictated the need to provide simulations of background image data with short-duration lightning transients superimposed. This led to the development of unique code used to control the location, intensity, and variation above background for simulated lightning strikes at user-selected locations.

The contaminant analysis automation robot implementation for the automated laboratory

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

Younkin, J.R.; Igou, R.E.; Urenda, T.D.

1995-12-31

The Contaminant Analysis Automation (CAA) project defines the automated laboratory as a series of standard laboratory modules (SLM) serviced by a robotic standard support module (SSM). These SLMs are designed to allow plug-and-play integration into automated systems that perform standard analysis methods (SAM). While the SLMs are autonomous in the execution of their particular chemical processing task, the SAM concept relies on a high-level task sequence controller (TSC) to coordinate the robotic delivery of materials requisite for SLM operations, initiate an SLM operation with the chemical method dependent operating parameters, and coordinate the robotic removal of materials from the SLMmore » when its commands and events has been established to allow ready them for transport operations as well as performing the Supervisor and Subsystems (GENISAS) software governs events from the SLMs and robot. The Intelligent System Operating Environment (ISOE) enables the inter-process communications used by GENISAS. CAA selected the Hewlett-Packard Optimized Robot for Chemical Analysis (ORCA) and its associated Windows based Methods Development Software (MDS) as the robot SSM. The MDS software is used to teach the robot each SLM position and required material port motions. To allow the TSC to command these SLM motions, a hardware and software implementation was required that allowed message passing between different operating systems. This implementation involved the use of a Virtual Memory Extended (VME) rack with a Force CPU-30 computer running VxWorks; a real-time multitasking operating system, and a Radiuses PC compatible VME computer running MDS. A GENISAS server on The Force computer accepts a transport command from the TSC, a GENISAS supervisor, over Ethernet and notifies software on the RadiSys PC of the pending command through VMEbus shared memory. The command is then delivered to the MDS robot control software using a Windows Dynamic Data Exchange conversation.« less

Advanced Communications Technology Satellite high burst rate link evaluation terminal experiment control and monitor software maintenance manual, version 1.0

NASA Technical Reports Server (NTRS)

Reinhart, Richard C.

1992-01-01

The Experiment Control and Monitor (EC&M) software was developed at NASA Lewis Research Center to support the Advanced Communications Technology Satellite (ACTS) High Burst Rate Link Evaluation Terminal (HBR-LET). The HBR-LET is an experimenter's terminal to communicate with the ACTS for various investigations by government agencies, universities, and industry. The EC&M software is one segment of the Control and Performance Monitoring (C&PM) software system of the HBR-LET. The EC&M software allows users to initialize, control, and monitor the instrumentation within the HBR-LET using a predefined sequence of commands. Besides instrument control, the C&PM software system is also responsible for computer communication between the HBR-LET and the ACTS NASA Ground Station and for uplink power control of the HBR-LET to demonstrate power augmentation during rain fade events. The EC&M Software User's Guide, Version 1.0 (NASA-CR-189160) outlines the commands required to install and operate the EC&M software. Input and output file descriptions, operator commands, and error recovery procedures are discussed in the document. The EC&M Software Maintenance Manual, Version 1.0 (NASA-CR-189161) is a programmer's guide that describes current implementation of the EC&M software from a technical perspective. An overview of the EC&M software, computer algorithms, format representation, and computer hardware configuration are included in the manual.

Increased incidence of cancer and cancer-related mortality among persons with chronic hepatitis C infection, 2006-2010.

PubMed

Allison, Robert D; Tong, Xin; Moorman, Anne C; Ly, Kathleen N; Rupp, Loralee; Xu, Fujie; Gordon, Stuart C; Holmberg, Scott D

2015-10-01

Persons chronically infected with the hepatitis C virus (HCV) may be at higher risk for developing and dying from non-liver cancers than the general population. 12,126 chronic HCV-infected persons in the Chronic Hepatitis Cohort Study (CHeCS) contributed 39,984 person-years of follow-up from 2006 to 2010 and were compared to 133,795,010 records from 13 Surveillance, Epidemiology and End Results Program (SEER) cancer registries, and approximately 12 million U.S. death certificates from Multiple Cause of Death (MCOD) data. Measurements included standardized rate ratios (SRR) and relative risk (RR). The incidence of the following cancers was significantly higher among patients with chronic HCV infection: liver (SRR, 48.6 [95% CI, 44.4-52.7]), pancreas (2.5 [1.7-3.2]), rectum (2.1 [1.3-2.8]), kidney (1.7 [1.1-2.2]), non-Hodgkin lymphoma (NHL) (1.6 [1.2-2.1]), and lung (1.6 [1.3-1.9]). Age-adjusted mortality was significantly higher among patients with: liver (RR, 29.6 [95% CI, 29.1-30.1]), oral (5.2 [5.1-5.4]), rectum (2.6 [2.5-2.7]), NHL (2.3 [2.2-2.31]), and pancreatic (1.63 [1.6-1.7]) cancers. The mean ages of cancer diagnosis and cancer-related death were significantly younger among CHeCS HCV cohort patients compared to the general population for many cancers. Incidence and mortality of many types of non-liver cancers were higher, and age at diagnosis and death younger, in patients with chronic HCV infection compared to the general population. Published by Elsevier B.V.

A Cloud-based, Open-Source, Command-and-Control Software Paradigm for Space Situational Awareness (SSA)

NASA Astrophysics Data System (ADS)

Melton, R.; Thomas, J.

With the rapid growth in the number of space actors, there has been a marked increase in the complexity and diversity of software systems utilized to support SSA target tracking, indication, warning, and collision avoidance. Historically, most SSA software has been constructed with "closed" proprietary code, which limits interoperability, inhibits the code transparency that some SSA customers need to develop domain expertise, and prevents the rapid injection of innovative concepts into these systems. Open-source aerospace software, a rapidly emerging, alternative trend in code development, is based on open collaboration, which has the potential to bring greater transparency, interoperability, flexibility, and reduced development costs. Open-source software is easily adaptable, geared to rapidly changing mission needs, and can generally be delivered at lower costs to meet mission requirements. This paper outlines Ball's COSMOS C2 system, a fully open-source, web-enabled, command-and-control software architecture which provides several unique capabilities to move the current legacy SSA software paradigm to an open source model that effectively enables pre- and post-launch asset command and control. Among the unique characteristics of COSMOS is the ease with which it can integrate with diverse hardware. This characteristic enables COSMOS to serve as the command-and-control platform for the full life-cycle development of SSA assets, from board test, to box test, to system integration and test, to on-orbit operations. The use of a modern scripting language, Ruby, also permits automated procedures to provide highly complex decision making for the tasking of SSA assets based on both telemetry data and data received from outside sources. Detailed logging enables quick anomaly detection and resolution. Integrated real-time and offline data graphing renders the visualization of the both ground and on-orbit assets simple and straightforward.

Closed-loop thrust and pressure profile throttling of a nitrous oxide/hydroxyl-terminated polybutadiene hybrid rocket motor

NASA Astrophysics Data System (ADS)

Peterson, Zachary W.

Hybrid motors that employ non-toxic, non-explosive components with a liquid oxidizer and a solid hydrocarbon fuel grain have inherently safe operating characteristics. The inherent safety of hybrid rocket motors offers the potential to greatly reduce overall operating costs. Another key advantage of hybrid rocket motors is the potential for in-flight shutdown, restart, and throttle by controlling the pressure drop between the oxidizer tank and the injector. This research designed, developed, and ground tested a closed-loop throttle controller for a hybrid rocket motor using nitrous oxide and hydroxyl-terminated polybutadiene as propellants. The research simultaneously developed closed-loop throttle algorithms and lab scale motor hardware to evaluate the fidelity of the throttle simulations and algorithms. Initial open-loop motor tests were performed to better classify system parameters and to validate motor performance values. Deep-throttle open-loop tests evaluated limits of stable thrust that can be achieved on the test hardware. Open-loop tests demonstrated the ability to throttle the motor to less than 10% of maximum thrust with little reduction in effective specific impulse and acoustical stability. Following the open-loop development, closed-loop, hardware-in-the-loop tests were performed. The closed-loop controller successfully tracked prescribed step and ramp command profiles with a high degree of fidelity. Steady-state accuracy was greatly improved over uncontrolled thrust.

Use of a hardware token for Grid authentication by the MICE data distribution framework

NASA Astrophysics Data System (ADS)

Nebrensky, JJ; Martyniak, J.

2017-10-01

The international Muon Ionization Cooling Experiment (MICE) is designed to demonstrate the principle of muon ionisation cooling for the first time. Data distribution and archiving, batch reprocessing, and simulation are all carried out using the EGI Grid infrastructure, in particular the facilities provided by GridPP in the UK. To prevent interference - especially accidental data deletion - these activities are separated by different VOMS roles. Data acquisition, in particular, can involve 24/7 operation for a number of weeks and so for moving the data out of the MICE Local Control Room at the experiment a valid, VOMS-enabled, Grid proxy must be made available continuously over that time. The MICE "Data Mover" agent is now using a robot certificate stored on a hardware token (Feitian ePass2003) from which a cron job generates a “plain” proxy to which the VOMS authorisation extensions are added in a separate transaction. A valid short-lifetime proxy is thus continuously available to the Data Mover process. The Feitian ePass2003 was chosen because it was both significantly cheaper and easier to actually purchase than the token commonly referred to in the community at that time; however there was no software support for the hardware. This paper describes the software packages, process and commands used to deploy the token into production.

The instrument control software package for the Habitable-Zone Planet Finder spectrometer

NASA Astrophysics Data System (ADS)

Bender, Chad F.; Robertson, Paul; Stefansson, Gudmundur Kari; Monson, Andrew; Anderson, Tyler; Halverson, Samuel; Hearty, Frederick; Levi, Eric; Mahadevan, Suvrath; Nelson, Matthew; Ramsey, Larry; Roy, Arpita; Schwab, Christian; Shetrone, Matthew; Terrien, Ryan

2016-08-01

We describe the Instrument Control Software (ICS) package that we have built for The Habitable-Zone Planet Finder (HPF) spectrometer. The ICS controls and monitors instrument subsystems, facilitates communication with the Hobby-Eberly Telescope facility, and provides user interfaces for observers and telescope operators. The backend is built around the asynchronous network software stack provided by the Python Twisted engine, and is linked to a suite of custom hardware communication protocols. This backend is accessed through Python-based command-line and PyQt graphical frontends. In this paper we describe several of the customized subsystem communication protocols that provide access to and help maintain the hardware systems that comprise HPF, and show how asynchronous communication benefits the numerous hardware components. We also discuss our Detector Control Subsystem, built as a set of custom Python wrappers around a C-library that provides native Linux access to the SIDECAR ASIC and Hawaii-2RG detector system used by HPF. HPF will be one of the first astronomical instruments on sky to utilize this native Linux capability through the SIDECAR Acquisition Module (SAM) electronics. The ICS we have created is very flexible, and we are adapting it for NEID, NASA's Extreme Precision Doppler Spectrometer for the WIYN telescope; we will describe this adaptation, and describe the potential for use in other astronomical instruments.

A decade of telerobotics in rehabilitation: Demonstrated utility blocked by the high cost of manipulation and the complexity of the user interface

NASA Technical Reports Server (NTRS)

Leifer, Larry; Michalowski, Stefan; Vanderloos, Machiel

1991-01-01

The Stanford/VA Interactive Robotics Laboratory set out in 1978 to test the hypothesis that industrial robotics technology could be applied to serve the manipulation needs of severely impaired individuals. Five generations of hardware, three generations of system software, and over 125 experimental subjects later, we believe that genuine utility is achievable. The experience includes development of over 65 task applications using voiced command, joystick control, natural language command and 3D object designation technology. A brief foray into virtual environments, using flight simulator technology, was instructive. If reality and virtuality come for comparable prices, you cannot beat reality. A detailed review of assistive robot anatomy and the performance specifications needed to achieve cost/beneficial utility will be used to support discussion of the future of rehabilitation telerobotics. Poised on the threshold of commercial viability, but constrained by the high cost of technically adequate manipulators, this worthy application domain flounders temporarily. In the long run, it will be the user interface that governs utility.

Processing Ocean Images to Detect Large Drift Nets

NASA Technical Reports Server (NTRS)

Veenstra, Tim

2009-01-01

A computer program processes the digitized outputs of a set of downward-looking video cameras aboard an aircraft flying over the ocean. The purpose served by this software is to facilitate the detection of large drift nets that have been lost, abandoned, or jettisoned. The development of this software and of the associated imaging hardware is part of a larger effort to develop means of detecting and removing large drift nets before they cause further environmental damage to the ocean and to shores on which they sometimes impinge. The software is capable of near-realtime processing of as many as three video feeds at a rate of 30 frames per second. After a user sets the parameters of an adjustable algorithm, the software analyzes each video stream, detects any anomaly, issues a command to point a high-resolution camera toward the location of the anomaly, and, once the camera has been so aimed, issues a command to trigger the camera shutter. The resulting high-resolution image is digitized, and the resulting data are automatically uploaded to the operator s computer for analysis.

STS-94 Columbia Landing at KSC (drag chute deploy)

NASA Technical Reports Server (NTRS)

1997-01-01

The Space Shuttle orbiter Columbia touches down on Runway 33 at KSCs Shuttle Landing Facility at 6:46:34 a.m. EDT with Mission Commander James D. Halsell Jr. and Pilot Susan L. Still at the controls to complete the STS-94 mission. Also on board are Mission Specialist Donald A. Thomas, Mission Specialist Michael L. Gernhardt, Payload Commander Janice Voss, and Payload Specialists Roger K. Crouch and Gregory T. Linteris. During the Microgravity Science Laboratory-1 (MSL-1) mission, the Spacelab module was used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducted combustion, protein crystal growth and materials processing experiments. This mission was a reflight of the STS-83 mission that lifted off from KSC in April of this year. That space flight was cut short due to indications of a faulty fuel cell. This was Columbias 11th landing at KSC and the 38th landing at the space center in the history of the Shuttle program.

Design and Implementation of a Brain Computer Interface System for Controlling a Robotic Claw

NASA Astrophysics Data System (ADS)

Angelakis, D.; Zoumis, S.; Asvestas, P.

2017-11-01

The aim of this paper is to present the design and implementation of a brain-computer interface (BCI) system that can control a robotic claw. The system is based on the Emotiv Epoc headset, which provides the capability of simultaneous recording of 14 EEG channels, as well as wireless connectivity by means of the Bluetooth protocol. The system is initially trained to decode what user thinks to properly formatted data. The headset communicates with a personal computer, which runs a dedicated software application, implemented under the Processing integrated development environment. The application acquires the data from the headset and invokes suitable commands to an Arduino Uno board. The board decodes the received commands and produces corresponding signals to a servo motor that controls the position of the robotic claw. The system was tested successfully on a healthy, male subject, aged 28 years. The results are promising, taking into account that no specialized hardware was used. However, tests on a larger number of users is necessary in order to draw solid conclusions regarding the performance of the proposed system.

STS-73 Landing - Front view prior to Main Gear Touchdown

NASA Technical Reports Server (NTRS)

1995-01-01

The orbiter Columbia returns to Earth, laden with microgravity research samples accumulated over a nearly 16-day spaceflight. Columbia touched down on the first landing opportunity at KSC's Shuttle Landing Facility, Runway 33, at 6:45 a.m. EST. Mission STS-73 marked the second flight of the U.S. Microgravity Laboratory (USML-2). The seven crew members assigned to STS-73 split into two teams to conduct around-the-clock microgravity research in a Spacelab module located in the orbiter payload bay as well as in the orbiter middeck. The mission commander is Kenneth D. Bowersox; Kent V. Rominger is the pilot. Kathryn C. Thornton is the payload commander, and the two mission specialists are Catherine G. Coleman and Michael E. Lopez- Alegria. To obtain the best results from the many experiments conducted during the mission, two payload specialists, Albert Sacco Jr. and Fred W. Leslie, also were assigned to the crew. The STS-73 mission will become the second longest in Shuttle program history, and Columbia -- loaded with research samples and USML-2 hardware -- weighs the most of any orbiter upon return.

A case of the birth and death of a high reliability healthcare organisation.

PubMed

Roberts, K H; Madsen, P; Desai, V; Van Stralen, D

2005-06-01

High reliability organisations (HROs) are those in which errors rarely occur. To accomplish this they conduct relatively error free operations over long periods of time and make consistently good decisions resulting in high quality and reliability. Some organisational processes that characterise HROs are process auditing, implementing appropriate reward systems, avoiding quality degradation, appropriately perceiving that risk exists and developing strategies to deal with it, and command and control. Command and control processes include migrating decision making, redundancy in people or hardware, developing situational awareness, formal rules and procedures, and training. These processes must be tailored to the specific organisation implementing them. These processes were applied to a paediatric intensive care unit (PICU) where care was derived from problem solving methodology rather than protocol. After a leadership change, the unit returned to the hierarchical medical model of care. Important outcome variables such as infant mortality, patient return to the PICU after discharge, days on the PICU, air transports, degraded. Implications for clinical practice include providing caregivers with sufficient flexibility to meet changing situations, encouraging teamwork, and avoiding shaming, naming, and blaming.

A flexible computerized system for environmental data acquisition and transmission

NASA Astrophysics Data System (ADS)

Zappalà, G.

2009-04-01

In recent years increasing importance has been addressed to the knowledge of the marine environment, either to help detecting and understanding global climate change phenomena, or to protect and preserve those coastal areas, where multiple interests converge (linked to the tourism, recreational or productive activities…) and which suffer greater impact from anthropogenic activities; this has in turn stimulated the start of research programs devoted to the monitoring and surveillance of these particular zones, coupling the needs for knowledge, sustainable development and exploitation of natural resources. There is an increasing need to have data available in real time or near real time in order to intervene in emergency situations. Cabled or wireless data transmission can be used. The first allows the transmission of a higher amount of data only in coastal sites, while the second gives a bigger flexibility in terms of application to different environments; more, using mobile phone services (either terrestrial or satellite), it is possible to allocate the data centre in the most convenient place, without any need of proximity to the sea. Traditional oceanographic techniques, based on ship surveys, hardly fit the needs of operational oceanography, because of their high cost and fragmentary nature, both in spatial and temporal domains. To obtain a good synopticity, it is necessary to complement traditional ship observations with measurements from fixed stations (buoys moored in sites chosen to be representative of wider areas, or to constitute a sentinel against the arrival of pollutants), satellite observations, use of ships of opportunity and of newly developed instruments, like the gliders, or towed sliding devices, like the SAVE. Modern instruments rely on an electronic heart; an integrated hardware-software system developed in Messina is here presented, used in various versions to control data acquisition and transmission on buoys or on ship-based instrumentation. The data acquisition and transmission system is based on IEEE P996.1 standard boards, implementing a PC-like architecture; basically, it consists in a Pentium family CPU (the fist prototypes used a 40 MHz 386 CPU), a variable number of RS-232 ports to connect measuring instruments and communication devices, an analog to digital converter (8 inputs 12 or 16 bit), power outputs with connected circuit status feedback to drive actuators and switch on and off the measuring systems, satellite and/or cellular phone modem, GPS; the mass storage is supplied by Disk on Chip (DOC) devices. According to the needs, it can be fully or only partly implemented. The software environment is Datalight ROMDOS v. 6, an MS-DOS compatible Operating System. The software has been written in Microsoft Professional Compiled BASIC v. 7.1. and Microsoft Macro Assembler v. 5.0. It enables to fully control the system instruments both in local and remote mode using a special set of macro commands (that can be combined into sequences using a simple text editor) that include also conditional execution of branches; this feature can be very useful in case of partial operativity of the system due, for instance, to low battery level or failure of some instrument. Available commands include: • System management commands • Instrument management commands • Conditional branch commands • Data transmission commands Collected data are locally stored and can be transmitted as e-mails, so increasing their safety against loosing and making the global data path fault tolerant using the peculiarities of the e-mail system. The first version was used in a network of coastal monitoring buoys funded by the Italian SAM program; a second one to equip an automatic multiple launcher for expendable probes to be used in ships of opportunity, designed and built in the framework of an EU funded program, "MFSTEP". Every hour, a "sequence manager" starts a macro-command sequence, that can be different for each time and is remotely reprogrammable; new releases of the software and of the sequences are uploadable to the station without suspending its normal activity. The macro-commands enable to manage the data acquisition and transmission, the mission programming, the station hardware and the measuring instruments. In the "launcher" version the program also controls real time and position acquisition, comparison against set points-times, launch, data acquisition and transmission, ancillary functions. The whole system can be connected to another computer (local laptop or remote desktop) using a terminal software; however, to fully and easily use its capabilities, a remote control program has been written in Microsoft Visual Basic, running in Windows environment. This program enables to transfer files to and from the measuring system, set up all its functionalities, and, if needed, take control of all the system operations. Thanks to the PC-like hardware architecture, it is easy to upgrade the system to more powerful processors without the need to modify the software, which, in turn, can be easily programmed using standard development packages.

Avionics System Architecture Tool

NASA Technical Reports Server (NTRS)

Chau, Savio; Hall, Ronald; Traylor, marcus; Whitfield, Adrian

2005-01-01

Avionics System Architecture Tool (ASAT) is a computer program intended for use during the avionics-system-architecture- design phase of the process of designing a spacecraft for a specific mission. ASAT enables simulation of the dynamics of the command-and-data-handling functions of the spacecraft avionics in the scenarios in which the spacecraft is expected to operate. ASAT is built upon I-Logix Statemate MAGNUM, providing a complement of dynamic system modeling tools, including a graphical user interface (GUI), modeling checking capabilities, and a simulation engine. ASAT augments this with a library of predefined avionics components and additional software to support building and analyzing avionics hardware architectures using these components.

KSC-03PD-1101

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. -- Lisa DeVries uses a sensor to test a piece of Columbia at the Barksdale Hangar for toxic fumes. DeVries, on assignment at Barksdale, La., works with United Space Alliance Safety at Kennedy Space Center. KSC workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., Hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

KSC-03pd1107

NASA Image and Video Library

2003-04-10

KENNEDY SPACE CENTER, FLA. -- Members of a U.S. Forest Service search team walk a grid during a Columbia Recovery search near the Hemphill site. The group is accompanied by a space program worker able to identify potential hazards of Shuttle parts. Kennedy Space Center workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

KSC-03pd1106

NASA Image and Video Library

2003-04-10

KENNEDY SPACE CENTER, FLA. -- Members of a U.S. Forest Service search team walk a grid during a Columbia Recovery search near the Hemphill site. The group is accompanied by a space program worker able to identify potential hazards of Shuttle parts. Kennedy Space Center workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

KSC-03pd1115

NASA Image and Video Library

2003-04-09

KENNEDY SPACE CENTER, FLA. -- Members of a U.S. Forest Service search team walk a grid during a Columbia Recovery search near the Nacogdoches site. The group is accompanied by a space program worker able to identify potential hazards of Shuttle parts. Kennedy Space Center workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

A Real-Time Telemetry Simulator of the IUS Spacecraft

NASA Technical Reports Server (NTRS)

Drews, Michael E.; Forman, Douglas A.; Baker, Damon M.; Khazoyan, Louis B.; Viazzo, Danilo

1998-01-01

A real-time telemetry simulator of the IUS spacecraft has recently entered operation to train Flight Control Teams for the launch of the AXAF telescope from the Shuttle. The simulator has proven to be a successful higher fidelity implementation of its predecessor, while affirming the rapid development methodology used in its design. Although composed of COTS hardware and software, the system simulates the full breadth of the mission: Launch, Pre-Deployment-Checkout, Burn Sequence, and AXAF/IUS separation. Realism is increased through patching the system into the operations facility to simulate IUS telemetry, Shuttle telemetry, and the Tracking Station link (commands and status message).

KSC-03pd1114

NASA Image and Video Library

2003-04-09

KENNEDY SPACE CENTER, FLA. -- Space Gateway Support Security Officer Jeff Ellison signs in a worker at the Nacogdoches site. In the background, NASA site lead Ronnie Lawson (left) speaks with his United Space Alliance counterpart George Odom. Kennedy Space Center workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

KSC-03pd1117

NASA Image and Video Library

2003-04-09

KENNEDY SPACE CENTER, FLA. -- John Lopez of Bristol, Texas, a crew boss for a camp crew at the Nacogdoches site, looks over tents used by U.S. Forest Service workers in the field searching for parts of Columbia. Kennedy Space Center workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

KSC-03pd1102

NASA Image and Video Library

2003-04-10

KENNEDY SPACE CENTER, FLA. -- (From left) Dean Schaaf, Barksdale site manager and NASA KSC Shuttle Process Integration Ground Operations manager, and Elliot Clement, an United Space Alliance engineer at Kennedy Space Center, inspect bagged pieces of Columbia at the Barksdale Hangar site. KSC workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

KSC-03pd1101

NASA Image and Video Library

2003-04-10

KENNEDY SPACE CENTER, FLA. -- Lisa DeVries uses a sensor to test a piece of Columbia at the Barksdale Hangar for toxic fumes. DeVries, on assignment at Barksdale, La., works with United Space Alliance Safety at Kennedy Space Center. KSC workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., Hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

HHDTC - Cmdr Halsell photographs hardware

NASA Image and Video Library

2016-08-12

STS083-313-012 (4-8 April 1997) --- Astronaut James D. Halsell, Jr., mission commander, uses a Hi-8mm camcorder to videotape the Hand Held Diffusion Test Cells (HHDTC), in the Spacelab Module aboard the Earth-orbiting Space Shuttle Columbia. Each test cell has three chambers containing a protein solution, a buffer solution and a precipitant solution chamber. Using the liquid-liquid diffusion method, the different fluids are brought into contact but not mixed. Over a period of time, the fluids will diffuse into each other through the random motion of molecules. The gradual increase in concentration of the precipitant within the protein solution causes the proteins to crystallize.

KSC-97PC946

NASA Image and Video Library

1997-06-28

STS-94 Commander James D. Halsell, Jr., arrives at the Shuttle Landing Facility aboard a T-38 jet in preparation for the reflight of the Microgravity Science Laboratory-1 mission. Launch is scheduled for July 1, 1997, at 2:37 p.m. EDT. The laboratory was scheduled to fly again with the full complement of STS-83 experiments after that mission was cut short due to a faulty fuel cell. During the scheduled 16-day STS-94 mission, the experiments will be used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducts combustion, protein crystal growth and materials processing experiments

KSC-07pd3552

NASA Image and Video Library

2007-11-30

KENNEDY SPACE CENTER, FLA. -- In the Orbiter Processing Facility, STS-123 crew members inspect the wheel well on the underside of space shuttle Endeavour. Seen kneeling in front are Mission Specialists Richard Linnehan, Robert Behnken and Pilot Gregory Johnson. Behind them are Mission Specialists Takao Doi and Michael Foreman and Commander Dominic Gorie. They are at NASA's Kennedy Space Center for a crew equipment interface test, a process of familiarization with payloads, hardware and the space shuttle. The STS-123 mission is targeted for launch on space shuttle Endeavour on Feb. 14. It will be the 25th assembly flight of the station. Photo credit: NASA/Kim Shiflett

Development of Ada language control software for the NASA power management and distribution test bed

NASA Technical Reports Server (NTRS)

Wright, Ted; Mackin, Michael; Gantose, Dave

1989-01-01

The Ada language software developed to control the NASA Lewis Research Center's Power Management and Distribution testbed is described. The testbed is a reduced-scale prototype of the electric power system to be used on space station Freedom. It is designed to develop and test hardware and software for a 20-kHz power distribution system. The distributed, multiprocessor, testbed control system has an easy-to-use operator interface with an understandable English-text format. A simple interface for algorithm writers that uses the same commands as the operator interface is provided, encouraging interactive exploration of the system.

ESSAA: Embedded system safety analysis assistant

NASA Technical Reports Server (NTRS)

Wallace, Peter; Holzer, Joseph; Guarro, Sergio; Hyatt, Larry

1987-01-01

The Embedded System Safety Analysis Assistant (ESSAA) is a knowledge-based tool that can assist in identifying disaster scenarios. Imbedded software issues hazardous control commands to the surrounding hardware. ESSAA is intended to work from outputs to inputs, as a complement to simulation and verification methods. Rather than treating the software in isolation, it examines the context in which the software is to be deployed. Given a specified disasterous outcome, ESSAA works from a qualitative, abstract model of the complete system to infer sets of environmental conditions and/or failures that could cause a disasterous outcome. The scenarios can then be examined in depth for plausibility using existing techniques.

KSC-08pd1953

NASA Image and Video Library

2008-07-11

CAPE CANAVERAL, Fla. – In the Orbiter Processing Facility at NASA's Kennedy Space Center, STS-125 Commander Scott Altman examines the cockpit window on space shuttle Atlantis. The inspection is part of the crew equipment interface test, which provides hands-on experience with hardware and equipment for the mission. Atlantis is targeted to launch Oct. 8 on the STS-125 mission to service the Hubble Space Telescope. The mission crew will perform history-making, on-orbit “surgery” on two important science instruments aboard the telescope. After capturing the telescope, two teams of spacewalking astronauts will perform the repairs during five planned spacewalks. Photo credit: NASA/Kim Shiflett

KSC-08pd1954

NASA Image and Video Library

2008-07-11

CAPE CANAVERAL, Fla. – In the Orbiter Processing Facility at NASA's Kennedy Space Center, STS-125 Commander Scott Altman examines the cockpit window on space shuttle Atlantis, checking for sharp edges. The inspection is part of the crew equipment interface test, which provides hands-on experience with hardware and equipment for the mission. Atlantis is targeted to launch Oct. 8 on the STS-125 mission to service the Hubble Space Telescope. The mission crew will perform history-making, on-orbit “surgery” on two important science instruments aboard the telescope. After capturing the telescope, two teams of spacewalking astronauts will perform the repairs during five planned spacewalks. Photo credit: NASA/Kim Shiflett

Observations and impressions from lunar orbit

NASA Technical Reports Server (NTRS)

Mattingly, T. K.; El-Baz, F.; Laidley, R. A.

1972-01-01

On Apollo 16, the command module pilot made observations of particular surface features and processes to complement photographic and other remotely sensed data. Emphasis was placed on geological problems that required the extreme dynamic range and color sensitivities of the human eye; repetitive observations of varying sun angles and viewing directions; and, in some cases, on-the-scene interpretations. Visual observations and impressions recorded during the mission verified the effectiveness of the hardware and techniques used. The orbiting observer functioned both as a sensor, in otherwise inaccessible areas such as earthshine and shadows, and as a designator of potentially significant data that were acquired on the photographic record.

Hardware multiplier processor

DOEpatents

Pierce, Paul E.

1986-01-01

A hardware processor is disclosed which in the described embodiment is a memory mapped multiplier processor that can operate in parallel with a 16 bit microcomputer. The multiplier processor decodes the address bus to receive specific instructions so that in one access it can write and automatically perform single or double precision multiplication involving a number written to it with or without addition or subtraction with a previously stored number. It can also, on a single read command automatically round and scale a previously stored number. The multiplier processor includes two concatenated 16 bit multiplier registers, two 16 bit concatenated 16 bit multipliers, and four 16 bit product registers connected to an internal 16 bit data bus. A high level address decoder determines when the multiplier processor is being addressed and first and second low level address decoders generate control signals. In addition, certain low order address lines are used to carry uncoded control signals. First and second control circuits coupled to the decoders generate further control signals and generate a plurality of clocking pulse trains in response to the decoded and address control signals.

The walking robot project

NASA Technical Reports Server (NTRS)

Williams, P.; Sagraniching, E.; Bennett, M.; Singh, R.

1991-01-01

A walking robot was designed, analyzed, and tested as an intelligent, mobile, and a terrain adaptive system. The robot's design was an application of existing technologies. The design of the six legs modified and combines well understood mechanisms and was optimized for performance, flexibility, and simplicity. The body design incorporated two tripods for walking stability and ease of turning. The electrical hardware design used modularity and distributed processing to drive the motors. The software design used feedback to coordinate the system and simple keystrokes to give commands. The walking machine can be easily adapted to hostile environments such as high radiation zones and alien terrain. The primary goal of the leg design was to create a leg capable of supporting a robot's body and electrical hardware while walking or performing desired tasks, namely those required for planetary exploration. The leg designers intent was to study the maximum amount of flexibility and maneuverability achievable by the simplest and lightest leg design. The main constraints for the leg design were leg kinematics, ease of assembly, degrees of freedom, number of motors, overall size, and weight.

Astronaut Prepares for Mission With Virtual Reality Hardware

NASA Technical Reports Server (NTRS)

2001-01-01

Astronaut John M. Grunsfeld, STS-109 payload commander, uses virtual reality hardware at Johnson Space Center to rehearse some of his duties prior to the STS-109 mission. The most familiar form of virtual reality technology is some form of headpiece, which fits over your eyes and displays a three dimensional computerized image of another place. Turn your head left and right, and you see what would be to your sides; turn around, and you see what might be sneaking up on you. An important part of the technology is some type of data glove that you use to propel yourself through the virtual world. This technology allows NASA astronauts to practice International Space Station work missions in advance. Currently, the medical community is using the new technologies in four major ways: To see parts of the body more accurately, for study, to make better diagnosis of disease and to plan surgery in more detail; to obtain a more accurate picture of a procedure during surgery; to perform more types of surgery with the most noninvasive, accurate methods possible; and to model interactions among molecules at a molecular level.

Programmable personality interface for the dynamic infrared scene generator (IRSG2)

NASA Astrophysics Data System (ADS)

Buford, James A., Jr.; Mobley, Scott B.; Mayhall, Anthony J.; Braselton, William J.

1998-07-01

As scene generator platforms begin to rely specifically on commercial off-the-shelf (COTS) hardware and software components, the need for high speed programmable personality interfaces (PPIs) are required for interfacing to Infrared (IR) flight computer/processors and complex IR projectors in the hardware-in-the-loop (HWIL) simulation facilities. Recent technological advances and innovative applications of established technologies are beginning to allow development of cost effective PPIs to interface to COTS scene generators. At the U.S. Army Aviation and Missile Command (AMCOM) Missile Research, Development, and Engineering Center (MRDEC) researchers have developed such a PPI to reside between the AMCOM MRDEC IR Scene Generator (IRSG) and either a missile flight computer or the dynamic Laser Diode Array Projector (LDAP). AMCOM MRDEC has developed several PPIs for the first and second generation IRSGs (IRSG1 and IRSG2), which are based on Silicon Graphics Incorporated (SGI) Onyx and Onyx2 computers with Reality Engine 2 (RE2) and Infinite Reality (IR/IR2) graphics engines. This paper provides an overview of PPIs designed, integrated, tested, and verified at AMCOM MRDEC, specifically the IRSG2's PPI.

The CMS tracker control system

NASA Astrophysics Data System (ADS)

Dierlamm, A.; Dirkes, G. H.; Fahrer, M.; Frey, M.; Hartmann, F.; Masetti, L.; Militaru, O.; Shah, S. Y.; Stringer, R.; Tsirou, A.

2008-07-01

The Tracker Control System (TCS) is a distributed control software to operate about 2000 power supplies for the silicon modules of the CMS Tracker and monitor its environmental sensors. TCS must thus be able to handle about 104 power supply parameters, about 103 environmental probes from the Programmable Logic Controllers of the Tracker Safety System (TSS), about 105 parameters read via DAQ from the DCUs in all front end hybrids and from CCUs in all control groups. TCS is built on top of an industrial SCADA program (PVSS) extended with a framework developed at CERN (JCOP) and used by all LHC experiments. The logical partitioning of the detector is reflected in the hierarchical structure of the TCS, where commands move down to the individual hardware devices, while states are reported up to the root which is interfaced to the broader CMS control system. The system computes and continuously monitors the mean and maximum values of critical parameters and updates the percentage of currently operating hardware. Automatic procedures switch off selected parts of the detector using detailed granularity and avoiding widespread TSS intervention.

Optics derotator servo control system for SONG Telescope

NASA Astrophysics Data System (ADS)

Xu, Jin; Ren, Changzhi; Ye, Yu

2012-09-01

The Stellar Oscillations Network Group (SONG) is an initiative which aims at designing and building a groundbased network of 1m telescopes dedicated to the study of phenomena occurring in the time domain. Chinese standard node of SONG is an Alt-Az Telescope of F/37 with 1m diameter. Optics derotator control system of SONG telescope adopts the development model of "Industrial Computer + UMAC Motion Controller + Servo Motor".1 Industrial computer is the core processing part of the motion control, motion control card(UMAC) is in charge of the details on the motion control, Servo amplifier accepts the control commands from UMAC, and drives the servo motor. The position feedback information comes from the encoder, to form a closed loop control system. This paper describes in detail hardware design and software design for the optics derotator servo control system. In terms of hardware design, the principle, structure, and control algorithm of servo system based on optics derotator are analyzed and explored. In terms of software design, the paper proposes the architecture of the system software based on Object-Oriented Programming.

Hardware multiplier processor

DOEpatents

Pierce, P.E.

A hardware processor is disclosed which in the described embodiment is a memory mapped multiplier processor that can operate in parallel with a 16 bit microcomputer. The multiplier processor decodes the address bus to receive specific instructions so that in one access it can write and automatically perform single or double precision multiplication involving a number written to it with or without addition or subtraction with a previously stored number. It can also, on a single read command automatically round and scale a previously stored number. The multiplier processor includes two concatenated 16 bit multiplier registers, two 16 bit concatenated 16 bit multipliers, and four 16 bit product registers connected to an internal 16 bit data bus. A high level address decoder determines when the multiplier processor is being addressed and first and second low level address decoders generate control signals. In addition, certain low order address lines are used to carry uncoded control signals. First and second control circuits coupled to the decoders generate further control signals and generate a plurality of clocking pulse trains in response to the decoded and address control signals.

Urban Operations in the Year 2020 (Operations en zone urbaine en l’an 2020)

DTIC Science & Technology

2003-04-01

d’un ennemi, l’accent étant alors mis sur la phase correspondante du concept. C’est ainsi que , pour mettre l’ennemi en échec, on a généralement...recommande que l’OTAN développe des capacités à utiliser dans des zones urbaines en se concentrant sur les besoins essentiels mis en évidence dans la... on peut citer les véhicules sans pilote et les armes non létales, qui permettent de réduire les pertes, ainsi que les dispositifs de largage de

GRODY - GAMMA RAY OBSERVATORY DYNAMICS SIMULATOR IN ADA

NASA Technical Reports Server (NTRS)

Stark, M.

1994-01-01

Analysts use a dynamics simulator to test the attitude control system algorithms used by a satellite. The simulator must simulate the hardware, dynamics, and environment of the particular spacecraft and provide user services which enable the analyst to conduct experiments. Researchers at Goddard's Flight Dynamics Division developed GRODY alongside GROSS (GSC-13147), a FORTRAN simulator which performs the same functions, in a case study to assess the feasibility and effectiveness of the Ada programming language for flight dynamics software development. They used popular object-oriented design techniques to link the simulator's design with its function. GRODY is designed for analysts familiar with spacecraft attitude analysis. The program supports maneuver planning as well as analytical testing and evaluation of the attitude determination and control system used on board the Gamma Ray Observatory (GRO) satellite. GRODY simulates the GRO on-board computer and Control Processor Electronics. The analyst/user sets up and controls the simulation. GRODY allows the analyst to check and update parameter values and ground commands, obtain simulation status displays, interrupt the simulation, analyze previous runs, and obtain printed output of simulation runs. The video terminal screen display allows visibility of command sequences, full-screen display and modification of parameters using input fields, and verification of all input data. Data input available for modification includes alignment and performance parameters for all attitude hardware, simulation control parameters which determine simulation scheduling and simulator output, initial conditions, and on-board computer commands. GRODY generates eight types of output: simulation results data set, analysis report, parameter report, simulation report, status display, plots, diagnostic output (which helps the user trace any problems that have occurred during a simulation), and a permanent log of all runs and errors. The analyst can send results output in graphical or tabular form to a terminal, disk, or hardcopy device, and can choose to have any or all items plotted against time or against each other. Goddard researchers developed GRODY on a VAX 8600 running VMS version 4.0. For near real time performance, GRODY requires a VAX at least as powerful as a model 8600 running VMS 4.0 or a later version. To use GRODY, the VAX needs an Ada Compilation System (ACS), Code Management System (CMS), and 1200K memory. GRODY is written in Ada and FORTRAN.

Secure Authentication for Remote Patient Monitoring with Wireless Medical Sensor Networks †

PubMed Central

Hayajneh, Thaier; Mohd, Bassam J; Imran, Muhammad; Almashaqbeh, Ghada; Vasilakos, Athanasios V.

2016-01-01

There is broad consensus that remote health monitoring will benefit all stakeholders in the healthcare system and that it has the potential to save billions of dollars. Among the major concerns that are preventing the patients from widely adopting this technology are data privacy and security. Wireless Medical Sensor Networks (MSNs) are the building blocks for remote health monitoring systems. This paper helps to identify the most challenging security issues in the existing authentication protocols for remote patient monitoring and presents a lightweight public-key-based authentication protocol for MSNs. In MSNs, the nodes are classified into sensors that report measurements about the human body and actuators that receive commands from the medical staff and perform actions. Authenticating these commands is a critical security issue, as any alteration may lead to serious consequences. The proposed protocol is based on the Rabin authentication algorithm, which is modified in this paper to improve its signature signing process, making it suitable for delay-sensitive MSN applications. To prove the efficiency of the Rabin algorithm, we implemented the algorithm with different hardware settings using Tmote Sky motes and also programmed the algorithm on an FPGA to evaluate its design and performance. Furthermore, the proposed protocol is implemented and tested using the MIRACL (Multiprecision Integer and Rational Arithmetic C/C++) library. The results show that secure, direct, instant and authenticated commands can be delivered from the medical staff to the MSN nodes. PMID:27023540

Secure Authentication for Remote Patient Monitoring with Wireless Medical Sensor Networks.

PubMed

Hayajneh, Thaier; Mohd, Bassam J; Imran, Muhammad; Almashaqbeh, Ghada; Vasilakos, Athanasios V

2016-03-24

There is broad consensus that remote health monitoring will benefit all stakeholders in the healthcare system and that it has the potential to save billions of dollars. Among the major concerns that are preventing the patients from widely adopting this technology are data privacy and security. Wireless Medical Sensor Networks (MSNs) are the building blocks for remote health monitoring systems. This paper helps to identify the most challenging security issues in the existing authentication protocols for remote patient monitoring and presents a lightweight public-key-based authentication protocol for MSNs. In MSNs, the nodes are classified into sensors that report measurements about the human body and actuators that receive commands from the medical staff and perform actions. Authenticating these commands is a critical security issue, as any alteration may lead to serious consequences. The proposed protocol is based on the Rabin authentication algorithm, which is modified in this paper to improve its signature signing process, making it suitable for delay-sensitive MSN applications. To prove the efficiency of the Rabin algorithm, we implemented the algorithm with different hardware settings using Tmote Sky motes and also programmed the algorithm on an FPGA to evaluate its design and performance. Furthermore, the proposed protocol is implemented and tested using the MIRACL (Multiprecision Integer and Rational Arithmetic C/C++) library. The results show that secure, direct, instant and authenticated commands can be delivered from the medical staff to the MSN nodes.

Development of a platform-independent receiver control system for SISIFOS

NASA Astrophysics Data System (ADS)

Lemke, Roland; Olberg, Michael

1998-05-01

Up to now receiver control software was a time consuming development usually written by receiver engineers who had mainly the hardware in mind. We are presenting a low-cost and very flexible system which uses a minimal interface to the real hardware, and which makes it easy to adapt to new receivers. Our system uses Tcl/Tk as a graphical user interface (GUI), SpecTcl as a GUI builder, Pgplot as plotting software, a simple query language (SQL) database for information storage and retrieval, Ethernet socket to socket communication and SCPI as a command control language. The complete system is in principal platform independent but for cost saving reasons we are using it actually on a PC486 running Linux 2.0.30, which is a copylefted Unix. The only hardware dependent part are the digital input/output boards, analog to digital and digital to analog convertors. In the case of the Linux PC we are using a device driver development kit to integrate the boards fully into the kernel of the operating system, which indeed makes them look like an ordinary device. The advantage of this system is firstly the low price and secondly the clear separation between the different software components which are available for many operating systems. If it is not possible, due to CPU performance limitations, to run all the software in a single machine,the SQL-database or the graphical user interface could be installed on separate computers.

Space vehicle with customizable payload and docking station

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

Judd, Stephen; Dallmann, Nicholas; McCabe, Kevin

A "black box" space vehicle solution may allow a payload developer to define the mission space and provide mission hardware within a predetermined volume and with predetermined connectivity. Components such as the power module, radios and boards, attitude determination and control system (ADCS), command and data handling (C&DH), etc. may all be provided as part of a "stock" (i.e., core) space vehicle. The payload provided by the payload developer may be plugged into the space vehicle payload section, tested, and launched without custom development of core space vehicle components by the payload developer. A docking station may facilitate convenient developmentmore » and testing of the space vehicle while reducing handling thereof.« less

KSC-03pd1116

NASA Image and Video Library

2003-04-09

KENNEDY SPACE CENTER, FLA. -- Temporary camp worker Michael Trujillo of North New Mexico displays chaps in the supply tent at the Nacogdoches site. The chaps are used by U.S. Forest Service, Environmental Protection Agency and space program workers searching through dense forests in East Texas. Kennedy Space Center workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

The Inertial Upper Stage - Flight experience and capabilities

NASA Astrophysics Data System (ADS)

Kuhns, Randall H.; Maricich, Peter L.; Bangsund, Edward L.; Friske, Stephen A.; Hallman, Wayne P.; Goldstein, Allen E.

1993-10-01

The Inertial Upper Stage (IUS) is a two-stage rocket designed to place a variety of payloads in high earth orbit or on interplanetary trajectories, which has been boosted to date, together with its payloads, from the earth's surface to low altitude park orbits by the USAF Titan launcher and the NASA Space Shuttle. This paper discusses the IUS redundancy and presents data on the value of the IST's redundant design and the past uses of the vehicle's redundant capability to achieve mission success. The value of IUS's redundancy has been confirmed on several flights. The paper presents block diagrams of the IUS redundancy architecture and of the redundancy hardware switching and commands.

Spacecraft fault tolerance: The Magellan experience

NASA Technical Reports Server (NTRS)

Kasuda, Rick; Packard, Donna Sexton

1993-01-01

Interplanetary and earth orbiting missions are now imposing unique fault tolerant requirements upon spacecraft design. Mission success is the prime motivator for building spacecraft with fault tolerant systems. The Magellan spacecraft had many such requirements imposed upon its design. Magellan met these requirements by building redundancy into all the major subsystem components and designing the onboard hardware and software with the capability to detect a fault, isolate it to a component, and issue commands to achieve a back-up configuration. This discussion is limited to fault protection, which is the autonomous capability to respond to a fault. The Magellan fault protection design is discussed, as well as the developmental and flight experiences and a summary of the lessons learned.

New design conception and development of the synchronizer/data buffer system in CDA station for China's GMS

NASA Astrophysics Data System (ADS)

Tong, Kai; Fan, Shiming; Gong, Derong; Lu, Zuming; Liu, Jian

The synchronizer/data buffer (SDB) in the command and data acquisition station for China's future Geostationary Meteorological Satellite is described. Several computers and special microprocessors are used in tandem with minimized hardware to fulfill all of the functions. The high-accuracy digital phase locked loop is operated by computer and by controlling the count value of the 20-MHz clock to acquire and track such signals as sun pulse, scan synchronization detection pulse, and earth pulse. Sun pulse and VISSR data are recorded precisely and economically by digitizing the time relation. The VISSR scan timing and equiangular control timing, and equal time sampling on satellite are also discussed.

Design and implementation of a robot control system with traded and shared control capability

NASA Technical Reports Server (NTRS)

Hayati, S.; Venkataraman, S. T.

1989-01-01

Preliminary results are reported from efforts to design and develop a robotic system that will accept and execute commands from either a six-axis teleoperator device or an autonomous planner, or combine the two. Such a system should have both traded as well as shared control capability. A sharing strategy is presented whereby the overall system, while retaining positive features of teleoperated and autonomous operation, loses its individual negative features. A two-tiered shared control architecture is considered here, consisting of a task level and a servo level. Also presented is a computer architecture for the implementation of this system, including a description of the hardware and software.

STS-81 launch view

NASA Image and Video Library

1998-06-15

STS081-S-006 (12 Jan. 1997) --- The Space Shuttle Atlantis lifts off from Pad 39B at 4:27:23 a.m. (EST) Jan. 12, 1997 on its way for a docking mission with Russia's Mir Space Station. Onboard are six astronauts and a SPACEHAB Double Module (DM), along with a large supply of food, water, hardware and other materials for Mir. Astronaut Jerry M. Linenger, now onboard Atlantis, will trade places with John E. Blaha, cosmonaut guest researcher, onboard Mir since mid September 1996. Along with Linenger, other crewmembers now aboard Atlantis are astronauts Michael A. Baker, commander; Brent W. Jett, Jr., pilot; and mission specialists John M. Grunsfeld, Marsha S. Ivins and Peter J. K. (Jeff) Wisoff.

Robot geometry calibration

NASA Technical Reports Server (NTRS)

Hayati, Samad; Tso, Kam; Roston, Gerald

1988-01-01

Autonomous robot task execution requires that the end effector of the robot be positioned accurately relative to a reference world-coordinate frame. The authors present a complete formulation to identify the actual robot geometric parameters. The method applies to any serial link manipulator with arbitrary order and combination of revolute and prismatic joints. A method is also presented to solve the inverse kinematic of the actual robot model which usually is not a so-called simple robot. Experimental results performed by utilizing a PUMA 560 with simple measurement hardware are presented. As a result of this calibration a precision move command is designed and integrated into a robot language, RCCL, and used in the NASA Telerobot Testbed.

Dynamics and control simulation of the Spacelab Experiment Pointing Mount

NASA Technical Reports Server (NTRS)

Marsh, E. L.; Ward, R. S.

1977-01-01

Computer simulations were developed to evaluate the performance of four Experiment Pointing Mounts (EPM) being considered for Spacelab experiments in the 1980-1990 time frame. The system modeled compromises a multibody system consisting of the shuttle, a mechanical isolation device, the EPM, celestial and inertial sensors, bearings, gimbal torque motors and associated nonlinearities, the experiment payload, and control and estimator algorithms. Each mount was subjected to a common disturbance (shuttle vernier thruster firing and man push off) and command (stellar pointing or solar raster scan) input. The fundamental limitation common to all mounts was found to be sensor noise. System dynamics and hardware nonlinearities have secondary effects on pointing performance for sufficiently high bandwidth.

President and Mrs. Clinton watch launch of Space Shuttle Discovery

NASA Technical Reports Server (NTRS)

1998-01-01

Watching a successful launch of Space Shuttle Discovery from the roof of the Launch Control Center are (left to right) U.S. President Bill Clinton, First Lady Hillary Rodham Clinton, Astronaut Robert Cabana and NASA Administrator Daniel Goldin. This was the first launch of a Space Shuttle to be viewed by President Clinton, or any President to date. They attended the launch to witness the return to space of American legend John H. Glenn Jr., payload specialist on mission STS-95. Cabana will command the crew of STS-88, the first Space Shuttle mission to carry hardware to space for the assembly of the International Space Station, targeted for liftoff on Dec. 3.

MIT's role in project Apollo. Volume 2: Optical, radar, and candidate subsystems

NASA Technical Reports Server (NTRS)

1972-01-01

The development of optical, radar, and candidate subsystems for Project Apollo is discussed. The design and development of the optical subsystems for both the Apollo command and lunar spacecraft are described. Design approaches, problems, and solutions are presented. The evolution of radar interfaces with the GN&C system is discussed; these interfaces involved both hardware and software in a relatively complex interrelationship. The design and development of three candidate subsystems are also described. The systems were considered for use in Apollo, but were not incorporated into the final GN&C system. The three subsystems discussed are the star tracker-horizon photometer, the map and data viewer and the lunar module optical rendezvous system.

Soldier-Warfighter Operationally Responsive Deployer for Space

NASA Technical Reports Server (NTRS)

Davis, Benny; Huebner, Larry; Kuhns, Richard

2015-01-01

The Soldier-Warfighter Operationally Responsive Deployer for Space (SWORDS) project was a joint project between the U.S. Army Space & Missile Defense Command (SMDC) and NASA. The effort, lead by SMDC, was intended to develop a three-stage liquid bipropellant (liquid oxygen/liquid methane), pressure-fed launch vehicle capable of inserting a payload of at least 25 kg to a 750-km circular orbit. The vehicle design was driven by low cost instead of high performance. SWORDS leveraged commercial industry standards to utilize standard hardware and technologies over customized unique aerospace designs. SWORDS identified broadly based global industries that have achieved adequate levels of quality control and reliability in their products and then designed around their expertise and business motivations.

STS-101: Crew Activity Report/Flight Day 10 Highlights

NASA Technical Reports Server (NTRS)

2000-01-01

This video presents a report from the Space Shuttle Atlantis Crew. The crew consists of James D. Halsell, Jr., Mission Commander; Scott Horowitz, Pilot; and Mission Specialists Mary Ellen Weber, Jeffrey N. Williams, James S. Voss, Susan J. Helms, and Yuri Vladimirovich Usachev. The crew made preparations for the Space Shuttle Atlantis return to Earth. Weber gave a general overview of refurbishments done to the International Space Station such as maintenance of the electrical system, one to three thousands of pounds of new hardware supplied to I.S.S. and a supply of personal hygiene products. Also live animation of the Spacehab Module is given where supplies bound for the Space Station are stored.

Common aperture multispectral sensor flight test program

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

Bird, R.S.; Kaufman, C.S.

1996-11-01

This paper will provide an overview of the Common Aperture Multispectral Sensor (CAMS) Hardware Demonstrator. CAMS is a linescanning sensor that simultaneously collected digital imagery over the Far-IR (8 to 12 {mu}m) and visible spectral (0.55 to 1.1 PM) spectral bands, correlated at the pixel level. CAMS was initially sponsored by the U.S. Naval Air System Commands F/A-18 program office (PMA-265). The current CAMS field tests are under the direction of Northrop-Grumman for the Defense Nuclear Agency (DNA) in support of the Follow-On Open Skies Sensor Evaluation Program (FOSEP) and are scheduled to be conducted in April 1996. 8 figs.,more » 4 tabs.« less

Web-based interactive drone control using hand gesture

NASA Astrophysics Data System (ADS)

Zhao, Zhenfei; Luo, Hao; Song, Guang-Hua; Chen, Zhou; Lu, Zhe-Ming; Wu, Xiaofeng

2018-01-01

This paper develops a drone control prototype based on web technology with the aid of hand gesture. The uplink control command and downlink data (e.g., video) are transmitted by WiFi communication, and all the information exchange is realized on web. The control command is translated from various predetermined hand gestures. Specifically, the hardware of this friendly interactive control system is composed by a quadrotor drone, a computer vision-based hand gesture sensor, and a cost-effective computer. The software is simplified as a web-based user interface program. Aided by natural hand gestures, this system significantly reduces the complexity of traditional human-computer interaction, making remote drone operation more intuitive. Meanwhile, a web-based automatic control mode is provided in addition to the hand gesture control mode. For both operation modes, no extra application program is needed to be installed on the computer. Experimental results demonstrate the effectiveness and efficiency of the proposed system, including control accuracy, operation latency, etc. This system can be used in many applications such as controlling a drone in global positioning system denied environment or by handlers without professional drone control knowledge since it is easy to get started.

The ChIP-Seq tools and web server: a resource for analyzing ChIP-seq and other types of genomic data.

PubMed

Ambrosini, Giovanna; Dreos, René; Kumar, Sunil; Bucher, Philipp

2016-11-18

ChIP-seq and related high-throughput chromatin profilig assays generate ever increasing volumes of highly valuable biological data. To make sense out of it, biologists need versatile, efficient and user-friendly tools for access, visualization and itegrative analysis of such data. Here we present the ChIP-Seq command line tools and web server, implementing basic algorithms for ChIP-seq data analysis starting with a read alignment file. The tools are optimized for memory-efficiency and speed thus allowing for processing of large data volumes on inexpensive hardware. The web interface provides access to a large database of public data. The ChIP-Seq tools have a modular and interoperable design in that the output from one application can serve as input to another one. Complex and innovative tasks can thus be achieved by running several tools in a cascade. The various ChIP-Seq command line tools and web services either complement or compare favorably to related bioinformatics resources in terms of computational efficiency, ease of access to public data and interoperability with other web-based tools. The ChIP-Seq server is accessible at http://ccg.vital-it.ch/chipseq/ .

KSC-97pc602

NASA Image and Video Library

1997-04-08

KENNEDY SPACE CENTER, FLA. -- The Space Shuttle Columbia touches down on Runway 33 at KSC's Shuttle Landing Facility at 2:33:11 p.m. EDT, April 8, to conclude the Microgravity Science Laboratory-1 (MSL-1) mission. At main gear touchdown, the STS-83 mission duration was 3 days, 23 hours, 12 minutes. The planned 16-day mission was cut short by a faulty fuel cell. This is only the third time in Shuttle program history that an orbiter was brought home early due to mechanical problems. This was also the 36th KSC landing since the program began in 1981. Mission Commander James D. Halsell, Jr. flew Columbia to a perfect landing with help from Pilot Susan L. Still. Other crew members are Payload Commander Janice E. Voss; Mission Specialists Michael L. Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. In spite of the abbreviated flight, the crew was able to perform MSL-1 experiments. The Spacelab-module-based experiments were used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station and to conduct combustion, protein crystal growth and materials processing investigations

KSC-97PC959

NASA Image and Video Library

1997-07-01

KENNEDY SPACE CENTER, Fla. -- The Space Shuttle Columbia soars from Launch Pad 39A at 2:02 p.m. EDT July 1 to begin the 16-day STS-94 Microgravity Science Laboratory-1 (MSL-1) mission. The launch window was opened 47 minutes earlier than the originally scheduled time of 2:37 p.m. to improve the opportunity to lift off before Florida summer rain showers reached the space center. The crew members are Mission Commander James D. Halsell Jr.; Pilot Susan L. Still; Payload Commander Janice Voss; Mission Specialists Michael L.Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. During the space flight, the MSL-1 will be used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducts combustion, protein crystal growth and materials processing experiments. Also onboard is the Hitchhiker Cryogenic Flexible Diode (CRYOFD) experiment payload, which is attached to the right side of Columbia’s payload bay. These payloads had previously flown on the STS-83 mission in April, which was cut short after nearly four days because of indications of a faulty fuel cell. STS-94 is a reflight of that mission

KSC-97pc608

NASA Image and Video Library

1997-04-08

KENNEDY SPACE CENTER, FLA. -- The Space Shuttle Columbia touches down on Runway 33 at KSC's Shuttle Landing Facility at 2:33:11 p.m. EDT, April 8, to conclude the Microgravity Science Laboratory-1 (MSL-1) mission. At main gear touchdown, the STS-83 mission duration was 3 days, 23 hours, 12 minutes. The planned 16-day mission was cut short by a faulty fuel cell. This is only the third time in Shuttle program history that an orbiter was brought home early due to mechanical problems. This was also the 36th KSC landing since the program began in 1981. Mission Commander James D. Halsell, Jr. flew Columbia to a perfect landing with help from Pilot Susan L. Still. Other crew members are Payload Commander Janice E. Voss; Mission Specialists Michael L. Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. In spite of the abbreviated flight, the crew was able to perform MSL-1 experiments. The Spacelab-module-based experiments were used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station and to conduct combustion, protein crystal growth and materials processing investigations

KSC-97PC965

NASA Image and Video Library

1997-07-01

KENNEDY SPACE CENTER, Fla. -- The Space Shuttle Columbia soars from Launch Pad 39A at 2:02 p.m. EDT July 1 to begin the 16-day STS-94 Microgravity Science Laboratory-1 (MSL-1) mission. The launch window was opened 47 minutes earlier than the originally scheduled time of 2:37 p.m. to improve the opportunity to lift off before Florida summer rain showers reached the space center. The crew members are Mission Commander James D. Halsell Jr.; Pilot Susan L. Still; Payload Commander Janice Voss; Mission Specialists Michael L.Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. During the space flight, the MSL-1 will be used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducts combustion, protein crystal growth and materials processing experiments. Also onboard is the Hitchhiker Cryogenic Flexible Diode (CRYOFD) experiment payload, which is attached to the right side of Columbia’s payload bay. These payloads had previously flown on the STS-83 mission in April, which was cut short after nearly four days because of indications of a faulty fuel cell. STS-94 is a reflight of that mission

KSC-97PC1052

NASA Image and Video Library

1997-07-17

KENNEDY SPACE CENTER, FLA. -- With its drag chute deployed, the Space Shuttle Orbiter Columbia touches down on Runway 33 at KSC’s Shuttle Landing Facility at 6:46:34 a.m. EDT with Mission Commander James D. Halsell Jr. and Pilot Susan L. Still at the controls to complete the STS-94 mission. Also on board are Mission Specialist Donald A. Thomas, Mission Specialist Michael L. Gernhardt , Payload Commander Janice Voss, and Payload Specialists Roger K. Crouch and Gregory T. Linteris. Mission elapsed time for STS-94 was 15 days,16 hours, 44 seconds. During the Microgravity Science Laboratory-1 (MSL-1) mission, the Spacelab module was used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducted combustion, protein crystal growth and materials processing experiments. This mission was a reflight of the STS-83 mission that lifted off from KSC in April of this year. That space flight was cut short due to indications of a faulty fuel cell. This was Columbia’s 11th landing at KSC and the 38th landing at the space center in the history of the Shuttle program

KSC-97pc599

NASA Image and Video Library

1997-04-08

KENNEDY SPACE CENTER, FLA. -- With drag chute deployed, the Space Shuttle Columbia hurtles down Runway 33 at KSCþs Shuttle Landing Facility to conclude the Microgravity Science Laboratory-1 (MSL-1) mission. With main gear touchdown at 2:33:11 p.m. EDT, April 8, the STS-83 mission duration was 3 days, 23 hours, 12 minutes. The planned 16-day mission was cut short by a faulty fuel cell. This is only the third time in Shuttle program history that an orbiter was brought home early due to a mechanical problem. This was also the 36th KSC landing since the program began in 1981. Mission Commander James D. Halsell, Jr. flew Columbia to a perfect landing with help from Pilot Susan L. Still. Other crew members are Payload Commander Janice E. Voss; Mission Specialists Michael L.Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. In spite of the abbreviated flight, the crew was able to perform MSL-1 experiments. The Spacelab-module-based experiments were used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station and to conduct combustion, protein crystal growth and materials processing investigations

KSC-97PC960

NASA Image and Video Library

1997-07-01

KENNEDY SPACE CENTER, Fla. -- The Space Shuttle Columbia soars from Launch Pad 39A at 2:02 p.m. EDT July 1 to begin the 16-day STS-94 Microgravity Science Laboratory-1 (MSL-1) mission. The launch window was opened 47 minutes earlier than the originally scheduled time of 2:37 p.m. to improve the opportunity to lift off before Florida summer rain showers reached the space center. The crew members are Mission Commander James D. Halsell Jr.; Pilot Susan L. Still; Payload Commander Janice Voss; Mission Specialists Michael L.Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. During the space flight, the MSL-1 will be used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducts combustion, protein crystal growth and materials processing experiments. Also onboard is the Hitchhiker Cryogenic Flexible Diode (CRYOFD) experiment payload, which is attached to the right side of Columbia’s payload bay. These payloads had previously flown on the STS-83 mission in April, which was cut short after nearly four days because of indications of a faulty fuel cell. STS-94 is a reflight of that mission

KSC-97PC1049

NASA Image and Video Library

1997-07-17

KENNEDY SPACE CENTER, FLA. -- With its drag chute deployed, the Space Shuttle Orbiter Columbia touches down on Runway 33 at KSC’s Shuttle Landing Facility at 6:46:34 a.m. EDT with Mission Commander James D. Halsell Jr. and Pilot Susan L. Still at the controls to complete the STS-94 mission. Also on board are Mission Specialist Donald A. Thomas, Mission Specialist Michael L. Gernhardt , Payload Commander Janice Voss, and Payload Specialists Roger K. Crouch and Gregory T. Linteris. Mission elapsed time for STS-94 was 15 days,16 hours, 44 seconds. During the Microgravity Science Laboratory-1 (MSL-1) mission, the Spacelab module was used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducted combustion, protein crystal growth and materials processing experiments. This mission was a reflight of the STS-83 mission that lifted off from KSC in April of this year. That space flight was cut short due to indications of a faulty fuel cell. This was Columbia’s 11th landing at KSC and the 38th landing at the space center in the history of the Shuttle program

KSC-97pc600

NASA Image and Video Library

1997-04-08

KENNEDY SPACE CENTER, FLA. -- The Space Shuttle Columbia touches down on Runway 33 at KSC's Shuttle Landing Facility at 2:33:11 p.m. EDT, April 8, to conclude the Microgravity Science Laboratory-1 (MSL-1) mission. At main gear touchdown, the STS-83 mission duration was 3 days, 23 hours, 12 minutes. The planned 16-day mission was cut short by a faulty fuel cell. This is only the third time in Shuttle program history that an orbiter was brought home early due to mechanical problems. This was also the 36th KSC landing since the program began in 1981. Mission Commander James D. Halsell, Jr. flew Columbia to a perfect landing with help from Pilot Susan L. Still. Other crew members are Payload Commander Janice E. Voss; Mission Specialists Michael L. Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. In spite of the abbreviated flight, the crew was able to perform MSL-1 experiments. The Spacelab-module-based experiments were used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station and to conduct combustion, protein crystal growth and materials processing investigations

KSC-97PC1045

NASA Image and Video Library

1997-07-17

KENNEDY SPACE CENTER, FLA. -- With its drag chute deployed, the Space Shuttle Orbiter Columbia touches down on Runway 33 at KSC’s Shuttle Landing Facility at 6:46:34 a.m. EDT with Mission Commander James D. Halsell Jr. and Pilot Susan L. Still at the controls to complete the STS-94 mission. Also on board are Mission Specialist Donald A. Thomas, Mission Specialist Michael L. Gernhardt , Payload Commander Janice Voss, and Payload Specialists Roger K. Crouch and Gregory T. Linteris. Mission elapsed time for STS-94 was 15 days,16 hours, 44 seconds. During the Microgravity Science Laboratory-1 (MSL-1) mission, the Spacelab module was used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducted combustion, protein crystal growth and materials processing experiments. This mission was a reflight of the STS-83 mission that lifted off from KSC in April of this year. That space flight was cut short due to indications of a faulty fuel cell. This was Columbia’s 11th landing at KSC and the 38th landing at the space center in the history of the Shuttle program

KSC-s9400005

NASA Image and Video Library

1997-07-01

The Space Shuttle Columbia soars from Launch Pad 39A at 2:02 p.m. EDT July 1 to begin the 16-day STS-94 Microgravity Science Laboratory-1 (MSL-1) mission. The launch window was opened 47 minutes earlier than the originally scheduled time of 2:37 p.m. to improve the opportunity to lift off before Florida summer rain showers reached the space center. The crew members are Mission Commander James D. Halsell Jr.; Pilot Susan L. Still; Payload Commander Janice Voss; Mission Specialists Michael L.Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. During the space flight, the MSL-1 will be used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducts combustion, protein crystal growth and materials processing experiments. Also onboard is the Hitchhiker Cryogenic Flexible Diode (CRYOFD) experiment payload, which is attached to the right side of Columbia’s payload bay. These payloads had previously flown on the STS-83 mission in April, which was cut short after nearly four days because of indications of a faulty fuel cell. STS-94 is a reflight of that mission

KSC-97PC962

NASA Image and Video Library

1997-07-01

KENNEDY SPACE CENTER, Fla. -- The Space Shuttle Columbia soars from Launch Pad 39A at 2:02 p.m. EDT July 1 to begin the 16-day STS-94 Microgravity Science Laboratory-1 (MSL-1) mission. The launch window was opened 47 minutes earlier than the originally scheduled time of 2:37 p.m. to improve the opportunity to lift off before Florida summer rain showers reached the space center. The crew members are Mission Commander James D. Halsell Jr.; Pilot Susan L. Still; Payload Commander Janice Voss; Mission Specialists Michael L.Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. During the space flight, the MSL-1 will be used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducts combustion, protein crystal growth and materials processing experiments. Also onboard is the Hitchhiker Cryogenic Flexible Diode (CRYOFD) experiment payload, which is attached to the right side of Columbia’s payload bay. These payloads had previously flown on the STS-83 mission in April, which was cut short after nearly four days because of indications of a faulty fuel cell. STS-94 is a reflight of that mission

KSC-97PC966

NASA Image and Video Library

1997-07-01

KENNEDY SPACE CENTER, Fla. -- The Space Shuttle Columbia soars from Launch Pad 39A at 2:02 p.m. EDT July 1 to begin the 16-day STS-94 Microgravity Science Laboratory-1 (MSL-1) mission. The launch window was opened 47 minutes earlier than the originally scheduled time of 2:37 p.m. to improve the opportunity to lift off before Florida summer rain showers reached the space center. The crew members are Mission Commander James D. Halsell Jr.; Pilot Susan L. Still; Payload Commander Janice Voss; Mission Specialists Michael L.Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. During the space flight, the MSL-1 will be used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducts combustion, protein crystal growth and materials processing experiments. Also onboard is the Hitchhiker Cryogenic Flexible Diode (CRYOFD) experiment payload, which is attached to the right side of Columbia’s payload bay. These payloads had previously flown on the STS-83 mission in April, which was cut short after nearly four days because of indications of a faulty fuel cell. STS-94 is a reflight of that mission

KSC-97PC1051

NASA Image and Video Library

1997-07-17

KENNEDY SPACE CENTER, FLA. -- With its drag chute deployed, the Space Shuttle Orbiter Columbia touches down on Runway 33 at KSC’s Shuttle Landing Facility at 6:46:34 a.m. EDT with Mission Commander James D. Halsell Jr. and Pilot Susan L. Still at the controls to complete the STS-94 mission. Also on board are Mission Specialist Donald A. Thomas, Mission Specialist Michael L. Gernhardt , Payload Commander Janice Voss, and Payload Specialists Roger K. Crouch and Gregory T. Linteris. Mission elapsed time for STS-94 was 15 days,16 hours, 44 seconds. During the Microgravity Science Laboratory-1 (MSL-1) mission, the Spacelab module was used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducted combustion, protein crystal growth and materials processing experiments. This mission was a reflight of the STS-83 mission that lifted off from KSC in April of this year. That space flight was cut short due to indications of a faulty fuel cell. This was Columbia’s 11th landing at KSC and the 38th landing at the space center in the history of the Shuttle program

KSC-97PC961

NASA Image and Video Library

1997-07-01

KENNEDY SPACE CENTER, Fla. -- The Space Shuttle Columbia soars from Launch Pad 39A at 2:02 p.m. EDT July 1 to begin the 16-day STS-94 Microgravity Science Laboratory-1 (MSL-1) mission. The launch window was opened 47 minutes earlier than the originally scheduled time of 2:37 p.m. to improve the opportunity to lift off before Florida summer rain showers reached the space center. The crew members are Mission Commander James D. Halsell Jr.; Pilot Susan L. Still; Payload Commander Janice Voss; Mission Specialists Michael L.Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. During the space flight, the MSL-1 will be used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducts combustion, protein crystal growth and materials processing experiments. Also onboard is the Hitchhiker Cryogenic Flexible Diode (CRYOFD) experiment payload, which is attached to the right side of Columbia’s payload bay. These payloads had previously flown on the STS-83 mission in April, which was cut short after nearly four days because of indications of a faulty fuel cell. STS-94 is a reflight of that mission

KSC-97PC964

NASA Image and Video Library

1997-07-01

KENNEDY SPACE CENTER, Fla. -- The Space Shuttle Columbia soars from Launch Pad 39A at 2:02 p.m. EDT July 1 to begin the 16-day STS-94 Microgravity Science Laboratory-1 (MSL-1) mission. The launch window was opened 47 minutes earlier than the originally scheduled time of 2:37 p.m. to improve the opportunity to lift off before Florida summer rain showers reached the space center. The crew members are Mission Commander James D. Halsell Jr.; Pilot Susan L. Still; Payload Commander Janice Voss; Mission Specialists Michael L.Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. During the space flight, the MSL-1 will be used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducts combustion, protein crystal growth and materials processing experiments. Also onboard is the Hitchhiker Cryogenic Flexible Diode (CRYOFD) experiment payload, which is attached to the right side of Columbia’s payload bay. These payloads had previously flown on the STS-83 mission in April, which was cut short after nearly four days because of indications of a faulty fuel cell. STS-94 is a reflight of that mission

KSC-97PC963

NASA Image and Video Library

1997-07-01

KENNEDY SPACE CENTER, Fla. -- The Space Shuttle Columbia soars from Launch Pad 39A at 2:02 p.m. EDT July 1 to begin the 16-day STS-94 Microgravity Science Laboratory-1 (MSL-1) mission. The launch window was opened 47 minutes earlier than the originally scheduled time of 2:37 p.m. to improve the opportunity to lift off before Florida summer rain showers reached the space center. The crew members are Mission Commander James D. Halsell Jr.; Pilot Susan L. Still; Payload Commander Janice Voss; Mission Specialists Michael L.Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. During the space flight, the MSL-1 will be used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducts combustion, protein crystal growth and materials processing experiments. Also onboard is the Hitchhiker Cryogenic Flexible Diode (CRYOFD) experiment payload, which is attached to the right side of Columbia’s payload bay. These payloads had previously flown on the STS-83 mission in April, which was cut short after nearly four days because of indications of a faulty fuel cell. STS-94 is a reflight of that mission

KSC-97pc601

NASA Image and Video Library

1997-04-08

KENNEDY SPACE CENTER, FLA. -- The Space Shuttle Columbia touches down on Runway 33 at KSC's Shuttle Landing Facility at 2:33:11 p.m. EDT, April 8, to conclude the Microgravity Science Laboratory-1 (MSL-1) mission. At main gear touchdown, the STS-83 mission duration was 3 days, 23 hours, 12 minutes. The planned 16-day mission was cut short by a faulty fuel cell. This is only the third time in Shuttle program history that an orbiter was brought home early due to mechanical problems. This was also the 36th KSC landing since the program began in 1981. Mission Commander James D. Halsell, Jr. flew Columbia to a perfect landing with help from Pilot Susan L. Still. Other crew members are Payload Commander Janice E. Voss; Mission Specialists Michael L. Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. In spite of the abbreviated flight, the crew was able to perform MSL-1 experiments. The Spacelab-module-based experiments were used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station and to conduct combustion, protein crystal growth and materials processing investigations

KSC-97pc603

NASA Image and Video Library

1997-04-08

KENNEDY SPACE CENTER, FLA. -- The Space Shuttle Columbia prepares to touch down on Runway 33 at KSC's Shuttle Landing Facility at approximately 2:33 p.m. EDT, April 8, to conclude the Microgravity Science Laboratory-1 (MSL-1) mission. At main gear touchdown, the STS-83 mission duration will be just under four days. The planned 16-day mission was cut short by a faulty fuel cell. This is only the third time in Shuttle program history that an orbiter was brought home early due to mechanical problems. This was also the 36th KSC landing since the program began in 1981. Mission Commander James D. Halsell, Jr. flew Columbia to a perfect landing with help from Pilot Susan L. Still. Other crew members are Payload Commander Janice E. Voss; Mission Specialists Michael L.Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. In spite of the abbreviated flight, the crew was able to perform MSL-1 experiments. The Spacelab-module-based experiments were used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station and to conduct combustion, protein crystal growth and materials processing investigations

KSC-97pc604

NASA Image and Video Library

1997-04-08

KENNEDY SPACE CENTER, FLA. -- With drag chute deployed, the Space Shuttle Columbia hurtles down Runway 33 at KSC's Shuttle Landing Facility to conclude the Microgravity Science Laboratory-1 (MSL-1) mission. With main gear touchdown at 2:33:11 p.m. EDT, April 8, the STS-83 mission duration was 3 days, 23 hours, 12 minutes. The planned 16-day mission was cut short by a faulty fuel cell. This is only the third time in Shuttle program history that an orbiter was brought home early due to a mechanical problem. This was also the 36th KSC landing since the program began in 1981. Mission Commander James D. Halsell, Jr. flew Columbia to a perfect landing with help from Pilot Susan L. Still. Other crew members are Payload Commander Janice E. Voss; Mission Specialists Michael L.Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. In spite of the abbreviated flight, the crew was able to perform MSL-1 experiments. The Spacelab-module-based experiments were used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station and to conduct combustion, protein crystal growth and materials processing investigations

KSC-97PC958

NASA Image and Video Library

1997-07-01

The STS-94 crew walks out of the Operations and Checkout Building and heads for the Astrovan that will transport them to Launch Pad 39A as KSC employees show their support. Waving to the crowd and leading the way are Mission Commander James D. Halsell, Jr. and Pilot Susan L. Still. Behind Still is Mission Specialist Donald A.Thomas, followed by Mission Specialist Michael L. Gernhardt , Payload Commander Janice Voss, and Payload Specialists Roger K.Crouch and Gregory T. Linteris. During the scheduled 16-day Microgravity Science Laboratory-1 (MSL-1) mission, the Spacelab module will be used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducts combustion, protein crystal growth and materials processing experiments. Also onboard is the Hitchhiker Cryogenic Flexible Diode (CRYOFD) experiment payload, which is attached to the right side of Columbia’s payload bay.The Space Shuttle Columbia is scheduled to lift off when the launch window opens at 1:50 p.m. EDT, July 1. The launch window was opened 47 minutes early to improve the opportunity to lift off before Florida summer rain showers reached the space center

Decoding static and dynamic arm and hand gestures from the JPL BioSleeve

NASA Astrophysics Data System (ADS)

Wolf, M. T.; Assad, C.; Stoica, A.; You, Kisung; Jethani, H.; Vernacchia, M. T.; Fromm, J.; Iwashita, Y.

This paper presents methods for inferring arm and hand gestures from forearm surface electromyography (EMG) sensors and an inertial measurement unit (IMU). These sensors, together with their electronics, are packaged in an easily donned device, termed the BioSleeve, worn on the forearm. The gestures decoded from BioSleeve signals can provide natural user interface commands to computers and robots, without encumbering the users hands and without problems that hinder camera-based systems. Potential aerospace applications for this technology include gesture-based crew-autonomy interfaces, high degree of freedom robot teleoperation, and astronauts' control of power-assisted gloves during extra-vehicular activity (EVA). We have developed techniques to interpret both static (stationary) and dynamic (time-varying) gestures from the BioSleeve signals, enabling a diverse and adaptable command library. For static gestures, we achieved over 96% accuracy on 17 gestures and nearly 100% accuracy on 11 gestures, based solely on EMG signals. Nine dynamic gestures were decoded with an accuracy of 99%. This combination of wearableEMGand IMU hardware and accurate algorithms for decoding both static and dynamic gestures thus shows promise for natural user interface applications.

Orbiter Camera Payload System

NASA Technical Reports Server (NTRS)

1980-01-01

Components for an orbiting camera payload system (OCPS) include the large format camera (LFC), a gas supply assembly, and ground test, handling, and calibration hardware. The LFC, a high resolution large format photogrammetric camera for use in the cargo bay of the space transport system, is also adaptable to use on an RB-57 aircraft or on a free flyer satellite. Carrying 4000 feet of film, the LFC is usable over the visible to near IR, at V/h rates of from 11 to 41 milliradians per second, overlap of 10, 60, 70 or 80 percent and exposure times of from 4 to 32 milliseconds. With a 12 inch focal length it produces a 9 by 18 inch format (long dimension in line of flight) with full format low contrast resolution of 88 lines per millimeter (AWAR), full format distortion of less than 14 microns and a complement of 45 Reseau marks and 12 fiducial marks. Weight of the OCPS as supplied, fully loaded is 944 pounds and power dissipation is 273 watts average when in operation, 95 watts in standby. The LFC contains an internal exposure sensor, or will respond to external command. It is able to photograph starfields for inflight calibration upon command.

A Method for the Control of Multigrasp Myoelectric Prosthetic Hands

PubMed Central

Dalley, Skyler Ashton; Varol, Huseyin Atakan; Goldfarb, Michael

2012-01-01

This paper presents the design and preliminary experimental validation of a multigrasp myoelectric controller. The described method enables direct and proportional control of multigrasp prosthetic hand motion among nine characteristic postures using two surface electromyography electrodes. To assess the efficacy of the control method, five nonamputee subjects utilized the multigrasp myoelectric controller to command the motion of a virtual prosthesis between random sequences of target hand postures in a series of experimental trials. For comparison, the same subjects also utilized a data glove, worn on their native hand, to command the motion of the virtual prosthesis for similar sequences of target postures during each trial. The time required to transition from posture to posture and the percentage of correctly completed transitions were evaluated to characterize the ability to control the virtual prosthesis using each method. The average overall transition times across all subjects were found to be 1.49 and 0.81 s for the multigrasp myoelectric controller and the native hand, respectively. The average transition completion rates for both were found to be the same (99.2%). Supplemental videos demonstrate the virtual prosthesis experiments, as well as a preliminary hardware implementation. PMID:22180515

Space Shuttle Columbia touches down on Runway 33

NASA Technical Reports Server (NTRS)

1997-01-01

KENNEDY SPACE CENTER, FLA. -- The Space Shuttle Columbia touches down on Runway 33 at KSC''';s Shuttle Landing Facility at 2:33:11 p.m. EDT, April 8, to conclude the Microgravity Science Laboratory-1 (MSL-1) mission. At main gear touchdown, the STS-83 mission duration was 3 days, 23 hours, 12 minutes. The planned 16-day mission was cut short by a faulty fuel cell. This is only the third time in Shuttle program history that an orbiter was brought home early due to mechanical problems. This was also the 36th KSC landing since the program began in 1981. Mission Commander James D. Halsell, Jr. flew Columbia to a perfect landing with help from Pilot Susan L. Still. Other crew members are Payload Commander Janice E. Voss; Mission Specialists Michael L. Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. In spite of the abbreviated flight, the crew was able to perform MSL-1 experiments. The Spacelab-module-based experiments were used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station and to conduct combustion, protein crystal growth and materials processing investigations.

Space Shuttle Columbia prepares to touch down on Runway 33

NASA Technical Reports Server (NTRS)

1997-01-01

KENNEDY SPACE CENTER, FLA. -- The Space Shuttle Columbia prepares to touch down on Runway 33 at KSC''';s Shuttle Landing Facility at approximately 2:33 p.m. EDT, April 8, to conclude the Microgravity Science Laboratory-1 (MSL-1) mission. At main gear touchdown, the STS-83 mission duration will be just under four days. The planned 16-day mission was cut short by a faulty fuel cell. This is only the third time in Shuttle program history that an orbiter was brought home early due to mechanical problems. This was also the 36th KSC landing since the program began in 1981. Mission Commander James D. Halsell, Jr. flew Columbia to a perfect landing with help from Pilot Susan L. Still. Other crew members are Payload Commander Janice E. Voss; Mission Specialists Michael L.Gernhardt and Donald A. Thomas; and Payload Specialists Roger K. Crouch and Gregory T. Linteris. In spite of the abbreviated flight, the crew was able to perform MSL-1 experiments. The Spacelab-module-based experiments were used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station and to conduct combustion, protein crystal growth and materials processing investigations.

STS-94 Columbia Landing at KSC (main gear touchdown)

NASA Technical Reports Server (NTRS)

1997-01-01

With its drag chute deployed, the Space Shuttle Orbiter Columbia touches down on Runway 33 at KSCs Shuttle Landing Facility at 6:46:34 a.m. EDT with Mission Commander James D. Halsell Jr. and Pilot Susan L. Still at the controls to complete the STS-94 mission. Also on board are Mission Specialist Donald A. Thomas, Mission Specialist Michael L. Gernhardt , Payload Commander Janice Voss, and Payload Specialists Roger K. Crouch and Gregory T. Linteris. Mission elapsed time for STS-94 was 15 days,16 hours, 44 seconds. During the Microgravity Science Laboratory-1 (MSL-1) mission, the Spacelab module was used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducted combustion, protein crystal growth and materials processing experiments. This mission was a reflight of the STS-83 mission that lifted off from KSC in April of this year. That space flight was cut short due to indications of a faulty fuel cell. This was Columbias 11th landing at KSC and the 38th landing at the space center in the history of the Shuttle program.

Evaluation of inertial devices for the control of large, flexible, space-based telerobotic arms

NASA Technical Reports Server (NTRS)

Montgomery, Raymond C.; Kenny, Sean P.; Ghosh, Dave; Shenhar, Joram

1993-01-01

Inertial devices, including sensors and actuators, offer the potential of improving the tracking of telerobotic commands for space-based robots by smoothing payload motions and suppressing vibrations. In this paper, inertial actuators (specifically, torque-wheels and reaction-masses) are studied for that potential application. Batch simulation studies are presented which show that torque-wheels can reduce the overshoot in abrupt stop commands by 82 percent for a two-link arm. For man-in-the-loop evaluation, a real-time simulator has been developed which samples a hand-controller, solves the nonlinear equations of motion, and graphically displays the resulting motion on a computer workstation. Currently, two manipulator models, a two-link, rigid arm and a single-link, flexible arm, have been studied. Results are presented which show that, for a single-link arm, a reaction-mass/torque-wheel combination at the payload end can yield a settling time of 3 s for disturbances in the first flexible mode as opposed to 10 s using only a hub motor. A hardware apparatus, which consists of a single-link, highly flexible arm with a hub motor and a torque-wheel, has been assembled to evaluate the concept and is described herein.

Web-based interactive drone control using hand gesture.

PubMed

Zhao, Zhenfei; Luo, Hao; Song, Guang-Hua; Chen, Zhou; Lu, Zhe-Ming; Wu, Xiaofeng

2018-01-01

This paper develops a drone control prototype based on web technology with the aid of hand gesture. The uplink control command and downlink data (e.g., video) are transmitted by WiFi communication, and all the information exchange is realized on web. The control command is translated from various predetermined hand gestures. Specifically, the hardware of this friendly interactive control system is composed by a quadrotor drone, a computer vision-based hand gesture sensor, and a cost-effective computer. The software is simplified as a web-based user interface program. Aided by natural hand gestures, this system significantly reduces the complexity of traditional human-computer interaction, making remote drone operation more intuitive. Meanwhile, a web-based automatic control mode is provided in addition to the hand gesture control mode. For both operation modes, no extra application program is needed to be installed on the computer. Experimental results demonstrate the effectiveness and efficiency of the proposed system, including control accuracy, operation latency, etc. This system can be used in many applications such as controlling a drone in global positioning system denied environment or by handlers without professional drone control knowledge since it is easy to get started.

Evaluation of inertial devices for the control of large, flexible, space-based telerobotic arms

NASA Astrophysics Data System (ADS)

Montgomery, Raymond C.; Kenny, Sean P.; Ghosh, Dave; Shenhar, Joram

1993-02-01

Inertial devices, including sensors and actuators, offer the potential of improving the tracking of telerobotic commands for space-based robots by smoothing payload motions and suppressing vibrations. In this paper, inertial actuators (specifically, torque-wheels and reaction-masses) are studied for that potential application. Batch simulation studies are presented which show that torque-wheels can reduce the overshoot in abrupt stop commands by 82 percent for a two-link arm. For man-in-the-loop evaluation, a real-time simulator has been developed which samples a hand-controller, solves the nonlinear equations of motion, and graphically displays the resulting motion on a computer workstation. Currently, two manipulator models, a two-link, rigid arm and a single-link, flexible arm, have been studied. Results are presented which show that, for a single-link arm, a reaction-mass/torque-wheel combination at the payload end can yield a settling time of 3 s for disturbances in the first flexible mode as opposed to 10 s using only a hub motor. A hardware apparatus, which consists of a single-link, highly flexible arm with a hub motor and a torque-wheel, has been assembled to evaluate the concept and is described herein.

STS-94 Columbia Landing at KSC (side view with sunrise)

NASA Technical Reports Server (NTRS)

1997-01-01

With its drag chute deployed, the Space Shuttle Orbiter Columbia touches down on Runway 33 at KSCs Shuttle Landing Facility at 6:46:34 a.m. EDT with Mission Commander James D. Halsell Jr. and Pilot Susan L. Still at the controls to complete the STS-94 mission. Also on board are Mission Specialist Donald A. Thomas, Mission Specialist Michael L. Gernhardt , Payload Commander Janice Voss, and Payload Specialists Roger K. Crouch and Gregory T. Linteris. Mission elapsed time for STS-94 was 15 days,16 hours, 44 seconds. During the Microgravity Science Laboratory-1 (MSL-1) mission, the Spacelab module was used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducted combustion, protein crystal growth and materials processing experiments. This mission was a reflight of the STS-83 mission that lifted off from KSC in April of this year. That space flight was cut short due to indications of a faulty fuel cell. This was Columbias 11th landing at KSC and the 38th landing at the space center in the history of the Shuttle program.

R4SA for Controlling Robots

NASA Technical Reports Server (NTRS)

Aghazarian, Hrand

2009-01-01

The R4SA GUI mentioned in the immediately preceding article is a userfriendly interface for controlling one or more robot(s). This GUI makes it possible to perform meaningful real-time field experiments and research in robotics at an unmatched level of fidelity, within minutes of setup. It provides such powerful graphing modes as that of a digitizing oscilloscope that displays up to 250 variables at rates between 1 and 200 Hz. This GUI can be configured as multiple intuitive interfaces for acquisition of data, command, and control to enable rapid testing of subsystems or an entire robot system while simultaneously performing analysis of data. The R4SA software establishes an intuitive component-based design environment that can be easily reconfigured for any robotic platform by creating or editing setup configuration files. The R4SA GUI enables event-driven and conditional sequencing similar to those of Mars Exploration Rover (MER) operations. It has been certified as part of the MER ground support equipment and, therefore, is allowed to be utilized in conjunction with MER flight hardware. The R4SA GUI could also be adapted to use in embedded computing systems, other than that of the MER, for commanding and real-time analysis of data.

Combined comfort model of thermal comfort and air quality on buses in Hong Kong.

PubMed

Shek, Ka Wing; Chan, Wai Tin

2008-01-25

Air-conditioning settings are important factors in controlling the comfort of passengers on buses. The local bus operators control in-bus air quality and thermal environment by conforming to the prescribed levels stated in published standards. As a result, the settings are merely adjusted to fulfill the standards, rather than to satisfy the passengers' thermal comfort and air quality. Such "standard-oriented" practices are not appropriate; the passengers' preferences and satisfaction should be emphasized instead. Thus a "comfort-oriented" philosophy should be implemented to achieve a comfortable in-bus commuting environment. In this study, the achievement of a comfortable in-bus environment was examined with emphasis on thermal comfort and air quality. Both the measurement of physical parameters and subjective questionnaire surveys were conducted to collect practical in-bus thermal and air parameters data, as well as subjective satisfaction and sensation votes from the passengers. By analyzing the correlation between the objective and subjective data, a combined comfort models were developed. The models helped in evaluating the percentage of dissatisfaction under various combinations of passengers' sensation votes towards thermal comfort and air quality. An effective approach integrated the combined comfort model, hardware and software systems and the bus air-conditioning system could effectively control the transient in-bus environment. By processing and analyzing the data from the continuous monitoring system with the combined comfort model, air-conditioning setting adjustment commands could be determined and delivered to the hardware. This system adjusted air-conditioning settings depending on real-time commands along the bus journey. Therefore, a comfortable in-bus air quality and thermal environment could be achieved and efficiently maintained along the bus journey despite dynamic outdoor influences. Moreover, this model can help optimize air-conditioning control by striking a beneficial balance between energy conservation and passengers' satisfaction level.

Fundamental Space Biology-1: HHR and Incubator for ISS Space Life Sciences

NASA Astrophysics Data System (ADS)

Kirven-Brooks, M.; Fahlen, T.; Sato, K.; Reiss-Bubenheim, D.

The Space Station Biological Research Project (SSBRP) is developing an Incubator and a Habitat Holding Rack (HHR) to support life science experiments aboard the International Space Station (ISS). The HHR provides for cooling and power needs, and supports data transfer (including telemetry, commanding, video processing, Ethernet), video compression, and data and command storage). The Incubator is a habitat that provides for controlled temperature between +4 C and +45 C and air circulation. It has a set of connector ports for power, analog and digital sensors, and video pass-through to support experiment-unique hardware within the Incubator specimen chamber. The Incubator exchanges air with the ISS cabin. The Fundamental Space Biology-1 (FSB-1) Project will be delivering, the HHR and two Incubators to ISS. The two inaugural experiments to be conducted on ISS using this hardware will investigate the biological effects of the space environment on two model organisms, Saccharomyces cerevisiae (S. cerevisiae; yeast) and Caenorhabditis elegans (C. elegans; nematode). The {M}odel {Y}east {C}ultures {o}n {S}tation (MYCOS) experiment will support examination of the effect of microgravity and cosmic radiation on yeast biology. In the second series of experiments during the same increment, the effects of microgravity and space environment radiation on C. elegans will be examined. The {F}undamental Space Biology {I}ncubator {E}xperiment {R}esearch using {C}. {e}legans (FIERCE) study is designed to support a long duration, multi-generational study of nematodes. FIERCE on-orbit science operations will include video monitoring, sub-culturing and periodic fixation and freezing of samples. For both experiments, investigators will be solicited via an International Space Life Sciences Research Announcement. In the near future, the Centrifuge Accommodation Module will be delivered to ISS, which will house the SSBRP 2.5 m Centrifuge Rotor. The Incubator can be placed onto the Centrifuge Rotor, which is capable of supporting variable gravity experiments from microgravity through 2g.

A fault-tolerant intelligent robotic control system

NASA Technical Reports Server (NTRS)

Marzwell, Neville I.; Tso, Kam Sing

1993-01-01

This paper describes the concept, design, and features of a fault-tolerant intelligent robotic control system being developed for space and commercial applications that require high dependability. The comprehensive strategy integrates system level hardware/software fault tolerance with task level handling of uncertainties and unexpected events for robotic control. The underlying architecture for system level fault tolerance is the distributed recovery block which protects against application software, system software, hardware, and network failures. Task level fault tolerance provisions are implemented in a knowledge-based system which utilizes advanced automation techniques such as rule-based and model-based reasoning to monitor, diagnose, and recover from unexpected events. The two level design provides tolerance of two or more faults occurring serially at any level of command, control, sensing, or actuation. The potential benefits of such a fault tolerant robotic control system include: (1) a minimized potential for damage to humans, the work site, and the robot itself; (2) continuous operation with a minimum of uncommanded motion in the presence of failures; and (3) more reliable autonomous operation providing increased efficiency in the execution of robotic tasks and decreased demand on human operators for controlling and monitoring the robotic servicing routines.

Time Synchronization/Stamping Method with Visible Light Communication and Energy Harvesting Methods for Wireless Sensor Network Inside Ariane 5 Vehicle Equipment Bay

NASA Astrophysics Data System (ADS)

Kesuma, Hendra; Niederkleine, Kris; Schmale, Sebastian; Ahobala, Tejas; Paul, Steffen; Sebald, Johannes

2016-08-01

In this work we design and implement efficient time synchronization/stamping method for Wireless Sensor Network inside the Vehicle Equipment Bay (VEB) of the ARIANE 5. The sensor nodes in the network do not require real time clock (RTC) hardware to store and stamp each measurement data performed by the sensors. There will be only the measurement sequence information, previous time (clock) information, measurement data and its related data protocol information sent back to the Access Point (AP). This lead to less data transmission, less energy and less time required by the sensor nodes to operate and also leads to longer battery life time. The Visible Light Communication (VLC) is used, to provide energy, to synchronize time and to deliver the commands to the sensor nodes in the network. By employing star network topology, a part of solar cell as receiver, the conventional receiver (RF/Infrared) is neglected to reduce amount of hardware and energy consumption. The infrared transmitter on the sensor node is deployed to minimize the electromagnetic interference in the launcher and does not require a complicated circuit in comparison to a RF transmitter.

STS-88 crew use simulators and virtual reality in preflight training

NASA Image and Video Library

1998-04-08

S98-05078 (8 Apr. 1998) --- With crew mates looking on, astronaut Nancy J. Currie, mission specialist, uses hardware in the virtual reality lab at the Johnson Space Center (JSC) to train for her duties aboard the Space Shuttle Endeavour. She is flanked by astronaut Robert Cabana (left), commander; and Frederick W. Sturckow (right), pilot. This type computer interface paired with virtual reality training hardware for the assigned space-walking astronauts -- Jerry L. Ross and James H. Newman -- helps to prepare the entire team for dealing with International Space Station (ISS) elements. One of those elements will be the Functional Cargo Block (FGB), which will have been launched a couple of weeks prior to STS-88. Once the FGB is captured using the Remote Manipulator System (RMS) of the Endeavour, Currie will maneuver the robot arm to dock the FGB to the conical mating adapter at the top of Node 1, to be carried in the Endeavour's cargo bay. In ensuing days, three Extravehicular Activity?s (EVA) by Ross and Newman will be performed to make power, data and utility connections between the two modules. Looking on is Scott A. Bleisath (behind Currie), with the EVA Systems Group at JSC.

STS-88 crew use simulators and virtual reality in preflight training

NASA Image and Video Library

1998-04-08

S98-05077 (8 Apr. 1998) --- With crew mates looking on, astronaut Nancy J. Currie, mission specialist, uses hardware in the virtual reality lab at the Johnson Space Center (JSC) to train for her duties aboard the Space Shuttle Endeavour. She is flanked by astronaut Robert Cabana (left), commander; and Frederick W. Sturckow (right), pilot. This type computer interface paired with virtual reality training hardware for the assigned space-walking astronauts -- Jerry L. Ross and James H. Newman -- helps to prepare the entire team for dealing with International Space Station (ISS) elements. One of those elements will be the Functional Cargo Block (FGB), which will have been launched a couple of weeks prior to STS-88. Once the FGB is captured using the Remote Manipulator System (RMS) of the Endeavour, Currie will maneuver the robot arm to dock the FGB to the conical mating adapter at the top of Node 1, to be carried in the Endeavour's cargo bay. In ensuing days, three Extravehicular Activity?s (EVA) by Ross and Newman will be performed to make power, data and utility connections between the two modules. Looking on is Scott A. Bleisath (behind Currie), with the EVA Systems Group at JSC.

Thirty Meter Telescope narrow-field infrared adaptive optics system real-time controller prototyping results

NASA Astrophysics Data System (ADS)

Smith, Malcolm; Kerley, Dan; Chapin, Edward L.; Dunn, Jennifer; Herriot, Glen; Véran, Jean-Pierre; Boyer, Corinne; Ellerbroek, Brent; Gilles, Luc; Wang, Lianqi

2016-07-01

Prototyping and benchmarking was performed for the Real-Time Controller (RTC) of the Narrow Field InfraRed Adaptive Optics System (NFIRAOS). To perform wavefront correction, NFIRAOS utilizes two deformable mirrors (DM) and one tip/tilt stage (TTS). The RTC receives wavefront information from six Laser Guide Star (LGS) Shack- Hartmann WaveFront Sensors (WFS), one high-order Natural Guide Star Pyramid WaveFront Sensor (PWFS) and multiple low-order instrument detectors. The RTC uses this information to determine the commands to send to the wavefront correctors. NFIRAOS is the first light AO system for the Thirty Meter Telescope (TMT). The prototyping was performed using dual-socket high performance Linux servers with the real-time (PREEMPT_RT) patch and demonstrated the viability of a commercial off-the-shelf (COTS) hardware approach to large scale AO reconstruction. In particular, a large custom matrix vector multiplication (MVM) was benchmarked which met the required latency requirements. In addition all major inter-machine communication was verified to be adequate using 10Gb and 40Gb Ethernet. The results of this prototyping has enabled a CPU-based NFIRAOS RTC design to proceed with confidence and that COTS hardware can be used to meet the demanding performance requirements.

Essential SpaceWire Hardware Capabilities for a Robust Network

NASA Technical Reports Server (NTRS)

Birmingham, Michael; Krimchansky, Alexander; Anderson, William; Lombardi, Matthew

2016-01-01

The Geostationary Operational Environmental Satellite R-Series Program (GOES-R) mission is a joint program between National Oceanic & Atmospheric Administration (NOAA) and National Aeronautics & Space Administration (NASA) Goddard Space Flight Center (GSFC). GOES-R project selected SpaceWire as the best solution to satisfy the desire for simple and flexible instrument to spacecraft command and telemetry communications. GOES-R development and integration is complete and the observatory is scheduled for launch October 2016. The spacecraft design was required to support redundant SpaceWire links for each instrument side, as well as to route the fewest number of connections through a Slip Ring Assembly necessary to support Solar pointing instruments. The final design utilized two different router designs. The SpaceWire standard alone does not ensure the most practical or reliable network. On GOES-R a few key hardware capabilities were identified that merit serious consideration for future designs. Primarily these capabilities address persistent port stalls and the prevention of receive buffer overflows. Workarounds were necessary to overcome shortcomings that could be avoided in future designs if they utilize the capabilities, discussed in this paper, above and beyond the requirements of the SpaceWire standard.

Virtual commissioning of automated micro-optical assembly

NASA Astrophysics Data System (ADS)

Schlette, Christian; Losch, Daniel; Haag, Sebastian; Zontar, Daniel; Roßmann, Jürgen; Brecher, Christian

2015-02-01

In this contribution, we present a novel approach to enable virtual commissioning for process developers in micro-optical assembly. Our approach aims at supporting micro-optics experts to effectively develop assisted or fully automated assembly solutions without detailed prior experience in programming while at the same time enabling them to easily implement their own libraries of expert schemes and algorithms for handling optical components. Virtual commissioning is enabled by a 3D simulation and visualization system in which the functionalities and properties of automated systems are modeled, simulated and controlled based on multi-agent systems. For process development, our approach supports event-, state- and time-based visual programming techniques for the agents and allows for their kinematic motion simulation in combination with looped-in simulation results for the optical components. First results have been achieved for simply switching the agents to command the real hardware setup after successful process implementation and validation in the virtual environment. We evaluated and adapted our system to meet the requirements set by industrial partners-- laser manufacturers as well as hardware suppliers of assembly platforms. The concept is applied to the automated assembly of optical components for optically pumped semiconductor lasers and positioning of optical components for beam-shaping

Cost-Effectiveness of Collaborative Care for the Treatment of Depressive Disorders in Primary Care: A Systematic Review

PubMed Central

Grochtdreis, Thomas; Brettschneider, Christian; Wegener, Annemarie; Watzke, Birgit; Riedel-Heller, Steffi; Härter, Martin; König, Hans-Helmut

2015-01-01

Background For the treatment of depressive disorders, the framework of collaborative care has been recommended, which showed improved outcomes in the primary care sector. Yet, an earlier literature review did not find sufficient evidence to draw robust conclusions on the cost-effectiveness of collaborative care. Purpose To systematically review studies on the cost-effectiveness of collaborative care, compared with usual care for the treatment of patients with depressive disorders in primary care. Methods A systematic literature search in major databases was conducted. Risk of bias was assessed using the Cochrane Collaboration’s tool. Methodological quality of the articles was assessed using the Consensus on Health Economic Criteria (CHEC) list. To ensure comparability across studies, cost data were inflated to the year 2012 using country-specific gross domestic product inflation rates, and were adjusted to international dollars using purchasing power parities (PPP). Results In total, 19 cost-effectiveness analyses were reviewed. The included studies had sample sizes between n = 65 to n = 1,801, and time horizons between six to 24 months. Between 42% and 89% of the CHEC quality criteria were fulfilled, and in only one study no risk of bias was identified. A societal perspective was used by five studies. Incremental costs per depression-free day ranged from dominance to US$PPP 64.89, and incremental costs per QALY from dominance to US$PPP 874,562. Conclusion Despite our review improved the comparability of study results, cost-effectiveness of collaborative care compared with usual care for the treatment of patients with depressive disorders in primary care is ambiguous depending on willingness to pay. A still considerable uncertainty, due to inconsistent methodological quality and results among included studies, suggests further cost-effectiveness analyses using QALYs as effect measures and a time horizon of at least 1 year. PMID:25993034

Direction of flagellar rotation in bacterial cell envelopes.

PubMed Central

Ravid, S; Eisenbach, M

1984-01-01

Cell envelopes with functional flagella, isolated from wild-type strains of Escherichia coli and Salmonella typhimurium by formation of spheroplasts with penicillin and subsequent osmotic lysis, demonstrate counterclockwise (CCW)-biased rotation when energized with an electron donor for respiration, DL-lactate. Since the direction of flagellar rotation in bacteria is central to the expression of chemotaxis, we studied the cause of this bias. Our main observations were: (i) spheroplasts acquired a clockwise (CW) bias if instead of being lysed they were further incubated with penicillin; (ii) repellents temporarily caused CW rotation of tethered bacteria and spheroplasts but not of their derived cell envelopes; (iii) deenergizing CW-rotating cheV bacteria by KCN or arsenate treatment caused CCW bias; (iv) cell envelopes isolated from CW-rotating cheC and cheV mutants retained the CW bias, unlike envelopes isolated from cheB and cheZ mutants, which upon cytoplasmic release lost this bias and acquired CCW bias; and (v) an inwardly directed, artificially induced proton current rotated tethered envelopes in CCW direction, but an outwardly directed current was unable to rotate the envelopes. It is concluded that (i) a cytoplasmic constituent is required for the expression of CW rotation (or repression of CCW rotation) in strains which are not defective in the switch; (ii) in the absence of this cytoplasmic constituent, the motor is not reversible in such strains, and it probably is mechanically constricted so as to permit CCW sense of rotation only; (iii) the requirement of CW rotation for ATP is not at the level of the motor or the switch but at one of the preceding functional steps of the chemotaxis machinery; (iv) the cheC and cheV gene products are associated with the cytoplasmic membrane; and (v) direct interaction between the switch-motor system and the repellent sensors is improbable. Images PMID:6370958

Systematic review of economic evaluations of vaccination programs in mainland China: Are they sufficient to inform decision making?

PubMed

Pan, Xiong-Fei; Griffiths, Ulla K; Pennington, Mark; Yu, Hongjie; Jit, Mark

2015-11-17

The purpose of the study was to systematically review economic evaluations of vaccine programs conducted in mainland China. We searched for economic evaluations of vaccination in China published prior to August 3, 2015 in eight English-language and three Chinese-language databases. Each article was appraised against the 19-item Consensus on Health Economic Criteria list (CHEC-list). We found 23 papers evaluating vaccines against hepatitis B (8 articles), Streptococcus pneumoniae (5 articles), human papillomavirus (3 articles), Japanese encephalitis (2 articles), rotavirus (2 articles), hepatitis A (1 article), Enterovirus 71 (1 article) and influenza (1 article). Studies conformed to a mean of 12 (range: 6-18) items in the CHEC-list criteria. Five of six Chinese-language articles conformed to fewer than half of the 19 criteria items. The main criteria that studies failed to conform to included: inappropriate measurement (20 articles) and valuation (18 articles) of treatment and/or vaccination costs, no discussion about distributional implications (18 articles), missing major health outcomes (14 articles), no discussion about generalizability to other contexts (14 articles), and inadequate sensitivity analysis (13 articles). In addition, ten studies did not include major cost components of vaccination programs, and nine did not report outcomes in terms of life years even in cases where QALYs or DALYs were calculated. Only 13 studies adopted a societal perspective for analysis. All studies concluded that the appraised vaccination programs were cost-effective except for one evaluation of universal 7-valent pneumococcal conjugate vaccine (PCV-7) in children. However, three of the five studies on PCV-7 showed poor overall quality, and the number of studies on vaccines other than hepatitis B vaccine and PCV-7 was limited. In conclusion, major methodological flaws and reporting problems exist in current economic evaluations of vaccination programs in China. Local guidelines for good practice and reporting, institutional mechanisms and education may help to improve the overall quality of these evaluations. Copyright © 2015 Elsevier Ltd. All rights reserved.

Prostate cancer surveillance by occupation and industry: the Canadian Census Health and Environment Cohort (CanCHEC).

PubMed

Sritharan, Jeavana; MacLeod, Jill; Harris, Shelley; Cole, Donald C; Harris, Anne; Tjepkema, Michael; Peters, Paul A; Demers, Paul A

2018-04-01

As there are no well-established modifiable risk factors for prostate cancer, further evidence is needed on possible factors such as occupation. Our study uses one of the largest Canadian worker cohorts to examine occupation, industry, and prostate cancer and to assess patterns of prostate cancer rates. The Canadian Census Health and Environment Cohort (CanCHEC) was established by linking the 1991 Canadian Census Cohort to the Canadian Cancer Database (1969-2010), Canadian Mortality Database (1991-2011), and Tax Summary Files (1981-2011). A total of 37,695 prostate cancer cases were identified in men aged 25-74 based on age at diagnosis. Cox proportional hazards models were used to estimate hazards ratios and 95% confidence intervals. In men aged 25-74 years, elevated risks were observed in the following occupations: senior management (HR = 1.12, 95% CI: 1.04-1.20); office and administration (HR = 1.19, 95% CI: 1.11-1.27); finance services (HR = 1.09, 95% CI: 1.04-1.14); education (HR = 1.05, 95% CI: 1.00-1.11); agriculture and farm management (HR = 1.12, 95% CI: 1.06-1.17); farm work (HR = 1.11, 95% CI: 1.01-1.21); construction managers (HR = 1.07, 95% CI: 1.01-1.14); firefighting (HR = 1.17, 95% CI: 1.01-1.36); and police work (HR = 1.22, 95% CI: 1.09-1.36). Decreased risks were observed across other construction and transportation occupations. Results by industry were consistent with occupation results. Associations were identified for white-collar, agriculture, protective services, construction, and transportation occupations. These findings emphasize the need for further study of job-related exposures and the potential influence of nonoccupational factors such as screening practices. © 2018 The Authors. Cancer Medicine published by John Wiley & Sons Ltd.

EVA training for Exp. 27 crew member Ron Garan, Exp. 28 Mike Fossum and STS-135 Doug Hurley, Rex Walheim and Sandra Magnus

NASA Image and Video Library

2011-01-18

JSC2011-E-003204 (18 Jan. 2011) --- NASA astronauts Rex Walheim, STS-135 mission specialist; and Mike Fossum (foreground), Expedition 28 flight engineer and Expedition 29 commander; use the virtual reality lab in the Space Vehicle Mock-up Facility at NASA's Johnson Space Center to train for some of their duties aboard the space shuttle and space station. This type of computer interface, paired with virtual reality training hardware and software, helps to prepare crew members for dealing with space station elements. STS-135 is planned to be the final mission of the space shuttle program. Photo credit: NASA or National Aeronautics and Space Administration

Cygnus Orbital ATK OA-6 Final Hatch Closure

NASA Image and Video Library

2016-03-06

Inside the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida, the hatch is closed for the upcoming flight of a Cygnus cargo vessel. The spacecraft is scheduled for the upcoming Orbital ATK Commercial Resupply Services-6 mission to deliver hardware and supplies to the International Space Station. When members of the ISS Expedition 47 crew open the hatch, they will be greeted with a sign noting the spacecraft was named SS Rick Husband in honor of the commander of the STS-107 mission. On that flight, the crew of the space shuttle Columbia was lost during re-entry on Feb. 1, 2003. The Cygnus is scheduled to lift off atop a United Launch Alliance Atlas V rocket on March 22.

KSC-03pd1108

NASA Image and Video Library

2003-04-10

KENNEDY SPACE CENTER, FLA. -- Members of a Columbia Recovery search team take a break while walking a grid during a search near the Hemphill site. At center is NASA engineer Clay Thomlinson. The U.S. Forest Service group is accompanied by a space program worker able to identify potential hazards of Shuttle parts. Kennedy Space Center workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

KSC-03pd1104

NASA Image and Video Library

2003-04-10

KENNEDY SPACE CENTER, FLA. -- At left, David Mclaughlin, Prototype Lab technician at Kennedy Space Center, listens to a coworker at the Hemphill site in East Texas before going to the field with his search team. Mclaughlin holds a walking stick used to beat down briars and knock away snakes in the East Texas woods. Kennedy Space Center workers are participating in the Columbia Recovery efforts at the Lufkin (Texas) Command Center, four field sites in East Texas, and the Barksdale, La., hangar site. KSC is working with representatives from other NASA Centers and with those from a number of federal, state and local agencies in the recovery effort. KSC provides vehicle technical expertise in the field to identify, collect and return Shuttle hardware to KSC.

STS-109 MS Linnehan and Grunsfeld in payload bay during first EVA

NASA Image and Video Library

2002-03-04

STS109-E-5253 (4 March 2002) --- Astronaut Richard M. Linnehan, mission specialist, is about to wrap up the first phase of a seven-hour space walk in the cargo bay of the Space Shuttle Columbia. Linnehan's feet are anchored to a restraint on the end of the Remote Manipulator System (RMS) robotic arm. The piece of hardware putting on a bright glow in left foreground is the furled old solar array that astronauts Linnehan and John M. Grunsfeld, payload commander, earlier removed from Hubble Space Telescope. The old array is now latched in Columbia's cargo bay for return to Earth. The two went on to install the replacement starboard array. The image was recorded with a digital still camera.

HyspIRI Intelligent Payload Module(IPM) and Benchmarking Algorithms for Upload

NASA Technical Reports Server (NTRS)

Mandl, Daniel

2010-01-01

Features: Hardware: a) Xilinx Virtex-5 (GSFC Space Cube 2); b) 2 x 400MHz PPC; c) 100MHz Bus; d) 2 x 512MB SDRAM; e) Dual Gigabit Ethernet. Support Linux kernel 2.6.31 (gcc version 4.2.2). Support software running in stand alone mode for better performance. Can stream raw data up to 800 Mbps. Ready for operations. Software Application Examples: Band-stripping Algiotrhmsl:cloud, sulfur, flood, thermal, SWIL, NDVI, NDWI, SIWI, oil spills, algae blooms, etc. Corrections: geometric, radiometric, atmospheric. Core Flight System/dynamic software bus. CCSDS File Delivery Protocol. Delay Tolerant Network. CASPER /onboard planning. Fault monitoring/recovery software. S/C command and telemetry software. Data compression. Sensor Web for Autonomous Mission Operations.

Opportunities for Launch Site Integrated System Health Engineering and Management

NASA Technical Reports Server (NTRS)

Waterman, Robert D.; Langwost, Patricia E.; Waterman, Susan J.

2005-01-01

The launch site processing flow involves operations such as functional verification, preflight servicing and launch. These operations often include hazards that must be controlled to protect human life and critical space hardware assets. Existing command and control capabilities are limited to simple limit checking durig automated monitoring. Contingency actions are highly dependent on human recognition, decision making, and execution. Many opportunities for Integrated System Health Engineering and Management (ISHEM) exist throughout the processing flow. This paper will present the current human-centered approach to health management as performed today for the shuttle and space station programs. In addition, it will address some of the more critical ISHEM needs, and provide recommendations for future implementation of ISHEM at the launch site.

STS-81 launch view

NASA Image and Video Library

1998-06-15

STS081-S-007 (12 Jan. 1997) --- Framed by a silhouette of Florida foliage, the Space Shuttle Atlantis lifts off from Pad 39B at 4:27:23 a.m. (EST) Jan. 12, 1997 on its way for a docking mission with Russia's Mir Space Station. Onboard are six astronauts and a SPACEHAB Double Module (DM), along with a large supply of food, water, hardware and other materials for Mir. Astronaut Jerry M. Linenger, now onboard Atlantis, will trade places with John E. Blaha, cosmonaut guest researcher, onboard Mir since mid September 1996. Along with Linenger, other crewmembers now aboard Atlantis are astronauts Michael A. Baker, commander; Brent W. Jett, Jr., pilot; and mission specialists John M. Grunsfeld, Marsha S. Ivins and Peter J. K. (Jeff) Wisoff.

ITA, a portable program for the interactive analysis of data from tracer experiments

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

Wootton, R.; Ashley, K.

ITA is a portable program for analyzing data from tracer experiments, most of the mathematical and graphical work being carried out by subroutines from the NAG and DASL libraries. The program can be used in batch or interactive mode, commands being typed in an English-like language, in free format. Data can be entered from a terminal keyboard or read from a file, and can be validated by printing or plotting them. Erroneous values can be corrected by appropriate editing. Analysis can involve elementary statistics, multiple-isotope crossover corrections, convolution or deconvolution, polyexponential curve-fitting, spline interpolation and/or compartmental analysis. On those installationsmore » with the appropriate hardware, high-resolution graphs can be drawn.« less

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

NASA Technical Reports Server (NTRS)

Bowyer, C. S.

1977-01-01

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

Thermally-Constrained Fuel-Optimal ISS Maneuvers

NASA Technical Reports Server (NTRS)

Bhatt, Sagar; Svecz, Andrew; Alaniz, Abran; Jang, Jiann-Woei; Nguyen, Louis; Spanos, Pol

2015-01-01

Optimal Propellant Maneuvers (OPMs) are now being used to rotate the International Space Station (ISS) and have saved hundreds of kilograms of propellant over the last two years. The savings are achieved by commanding the ISS to follow a pre-planned attitude trajectory optimized to take advantage of environmental torques. The trajectory is obtained by solving an optimal control problem. Prior to use on orbit, OPM trajectories are screened to ensure a static sun vector (SSV) does not occur during the maneuver. The SSV is an indicator that the ISS hardware temperatures may exceed thermal limits, causing damage to the components. In this paper, thermally-constrained fuel-optimal trajectories are presented that avoid an SSV and can be used throughout the year while still reducing propellant consumption significantly.

Avionics Simulation, Development and Software Engineering

NASA Technical Reports Server (NTRS)

Francis, Ronald C.; Settle, Gray; Tobbe, Patrick A.; Kissel, Ralph; Glaese, John; Blanche, Jim; Wallace, L. D.

2001-01-01

This monthly report summarizes the work performed under contract NAS8-00114 for Marshall Space Flight Center in the following tasks: 1) Purchase Order No. H-32831D, Task Order 001A, GPB Program Software Oversight; 2) Purchase Order No. H-32832D, Task Order 002, ISS EXPRESS Racks Software Support; 3) Purchase Order No. H-32833D, Task Order 003, SSRMS Math Model Integration; 4) Purchase Order No. H-32834D, Task Order 004, GPB Program Hardware Oversight; 5) Purchase Order No. H-32835D, Task Order 005, Electrodynamic Tether Operations and Control Analysis; 6) Purchase Order No. H-32837D, Task Order 007, SRB Command Receiver/Decoder; and 7) Purchase Order No. H-32838D, Task Order 008, AVGS/DART SW and Simulation Support

Shuttle payload S-band communications study

NASA Technical Reports Server (NTRS)

Springett, J. C.

1979-01-01

The work to identify, evaluate, and make recommendations concerning the functions and interfaces of those orbiter avionic subsystems which are dedicated to, or play some part in, handling communication signals (telemetry and command) to/from payloads (spacecraft) that will be carried into orbit by the shuttle is reported. Some principal directions of the research are: (1) analysis of the ability of the various avionic equipment to interface with and appropriately process payload signals; (2) development of criteria which will foster equipment compatibility with diverse types of payloads and signals; (3) study of operational procedures, especially those affecting signal acquisition; (4) trade-off analysis for end-to-end data link performance optimization; (5) identification of possible hardware design weakness which might degrade signal processing performance.

A High-Availability, Distributed Hardware Control System Using Java

NASA Technical Reports Server (NTRS)

Niessner, Albert F.

2011-01-01

Two independent coronagraph experiments that require 24/7 availability with different optical layouts and different motion control requirements are commanded and controlled with the same Java software system executing on many geographically scattered computer systems interconnected via TCP/IP. High availability of a distributed system requires that the computers have a robust communication messaging system making the mix of TCP/IP (a robust transport), and XML (a robust message) a natural choice. XML also adds the configuration flexibility. Java then adds object-oriented paradigms, exception handling, heavily tested libraries, and many third party tools for implementation robustness. The result is a software system that provides users 24/7 access to two diverse experiments with XML files defining the differences

HETDEX tracker control system design and implementation

NASA Astrophysics Data System (ADS)

Beno, Joseph H.; Hayes, Richard; Leck, Ron; Penney, Charles; Soukup, Ian

2012-09-01

To enable the Hobby-Eberly Telescope Dark Energy Experiment, The University of Texas at Austin Center for Electromechanics and McDonald Observatory developed a precision tracker and control system - an 18,000 kg robot to position a 3,100 kg payload within 10 microns of a desired dynamic track. Performance requirements to meet science needs and safety requirements that emerged from detailed Failure Modes and Effects Analysis resulted in a system of 13 precision controlled actuators and 100 additional analog and digital devices (primarily sensors and safety limit switches). Due to this complexity, demanding accuracy requirements, and stringent safety requirements, two independent control systems were developed. First, a versatile and easily configurable centralized control system that links with modeling and simulation tools during the hardware and software design process was deemed essential for normal operation including motion control. A second, parallel, control system, the Hardware Fault Controller (HFC) provides independent monitoring and fault control through a dedicated microcontroller to force a safe, controlled shutdown of the entire system in the event a fault is detected. Motion controls were developed in a Matlab-Simulink simulation environment, and coupled with dSPACE controller hardware. The dSPACE real-time operating system collects sensor information; motor commands are transmitted over a PROFIBUS network to servo amplifiers and drive motor status is received over the same network. To interface the dSPACE controller directly to absolute Heidenhain sensors with EnDat 2.2 protocol, a custom communication board was developed. This paper covers details of operational control software, the HFC, algorithms, tuning, debugging, testing, and lessons learned.

Encryption for Remote Control via Internet or Intranet

NASA Technical Reports Server (NTRS)

Lineberger, Lewis

2005-01-01

A data-communication protocol has been devised to enable secure, reliable remote control of processes and equipment via a collision-based network, while using minimal bandwidth and computation. The network could be the Internet or an intranet. Control is made secure by use of both a password and a dynamic key, which is sent transparently to a remote user by the controlled computer (that is, the computer, located at the site of the equipment or process to be controlled, that exerts direct control over the process). The protocol functions in the presence of network latency, overcomes errors caused by missed dynamic keys, and defeats attempts by unauthorized remote users to gain control. The protocol is not suitable for real-time control, but is well suited for applications in which control latencies up to about 0.5 second are acceptable. The encryption scheme involves the use of both a dynamic and a private key, without any additional overhead that would degrade performance. The dynamic key is embedded in the equipment- or process-monitor data packets sent out by the controlled computer: in other words, the dynamic key is a subset of the data in each such data packet. The controlled computer maintains a history of the last 3 to 5 data packets for use in decrypting incoming control commands. In addition, the controlled computer records a private key (password) that is given to the remote computer. The encrypted incoming command is permuted by both the dynamic and private key. A person who records the command data in a given packet for hostile purposes cannot use that packet after the public key expires (typically within 3 seconds). Even a person in possession of an unauthorized copy of the command/remote-display software cannot use that software in the absence of the password. The use of a dynamic key embedded in the outgoing data makes the central-processing unit overhead very small. The use of a National Instruments DataSocket(TradeMark) (or equivalent) protocol or the User Datagram Protocol makes it possible to obtain reasonably short response times: Typical response times in event-driven control, using packets sized .300 bytes, are <0.2 second for commands issued from locations anywhere on Earth. The protocol requires that control commands represent absolute values of controlled parameters (e.g., a specified temperature), as distinguished from changes in values of controlled parameters (e.g., a specified increment of temperature). Each command is issued three or more times to ensure delivery in crowded networks. The use of absolute-value commands prevents additional (redundant) commands from causing trouble. Because a remote controlling computer receives "talkback" in the form of data packets from the controlled computer, typically within a time interval < or =1 s, the controlling computer can re-issue a command if network failure has occurred. The controlled computer, the process or equipment that it controls, and any human operator(s) at the site of the controlled equipment or process should be equipped with safety measures to prevent damage to equipment or injury to humans. These features could be a combination of software, external hardware, and intervention by the human operator(s). The protocol is not fail-safe, but by adopting these safety measures as part of the protocol, one makes the protocol a robust means of controlling remote processes and equipment by use of typical office computers via intranets and/or the Internet.

Transitioning to Intel-based Linux Servers in the Payload Operations Integration Center

NASA Technical Reports Server (NTRS)

Guillebeau, P. L.

2004-01-01

The MSFC Payload Operations Integration Center (POIC) is the focal point for International Space Station (ISS) payload operations. The POIC contains the facilities, hardware, software and communication interface necessary to support payload operations. ISS ground system support for processing and display of real-time spacecraft and telemetry and command data has been operational for several years. The hardware components were reaching end of life and vendor costs were increasing while ISS budgets were becoming severely constrained. Therefore it has been necessary to migrate the Unix portions of our ground systems to commodity priced Intel-based Linux servers. hardware architecture including networks, data storage, and highly available resources. This paper will concentrate on the Linux migration implementation for the software portion of our ground system. The migration began with 3.5 million lines of code running on Unix platforms with separate servers for telemetry, command, Payload information management systems, web, system control, remote server interface and databases. The Intel-based system is scheduled to be available for initial operational use by August 2004 The overall migration to Intel-based Linux servers in the control center involves changes to the This paper will address the Linux migration study approach including the proof of concept, criticality of customer buy-in and importance of beginning with POSlX compliant code. It will focus on the development approach explaining the software lifecycle. Other aspects of development will be covered including phased implementation, interim milestones and metrics measurements and reporting mechanisms. This paper will also address the testing approach covering all levels of testing including development, development integration, IV&V, user beta testing and acceptance testing. Test results including performance numbers compared with Unix servers will be included. need for a smooth transition while maintaining real-time support. An important aspect of the paper will involve challenges and lessons learned. product compatibility, implications of phasing decisions and tracking of dependencies, particularly non- software dependencies. The paper will also discuss scheduling challenges providing real-time flight support during the migration and the requirement to incorporate in the migration changes being made simultaneously for flight support. This paper will also address the deployment approach including user involvement in testing and the , This includes COTS product compatibility, implications of phasing decisions and tracking of dependencies, particularly non- software dependencies. The paper will also discuss scheduling challenges providing real-time flight support during the migration and the requirement to incorporate in the migration changes being made simultaneously for flight support.

Les infestations par les poux de tête : une mise à jour clinique.

PubMed

Cummings, Carl; Finlay, Jane C; MacDonald, Noni E

2018-02-01

Les infestations par les poux de tête ( Pediculus humanus capitis ) ne constituent ni un risque sanitaire primaire ni un vecteur de maladie, mais représentent plutôt un problème de société au coût impor- tant. Pour diagnostiquer une infestation, il faut déceler un pou vivant. Même si les pyréthines et la perméthrine demeurent les traitements de première intention au Canada, la solution de myristate d'isopropyle et de ST-cyclométhicone et la diméticone peuvent être envisagées en deuxième intention après un échec thérapeutique démontré.

Hardware in the Loop Testing of an Iodine-Fed Hall Thruster

NASA Technical Reports Server (NTRS)

Polzin, Kurt A.; Peeples, Steven R.; Cecil, Jim; Lewis, Brandon L.; Molina Fraticelli, Jose C.; Clark, James P.

2015-01-01

CUBESATS are relatively new spacecraft platforms that are typically deployed from a launch vehicle as a secondary payload,1 providing low-cost access to space for a wide range of end-users. These satellites are comprised of building blocks having dimensions of 10x10x10 cm cu and a mass of 1.33 kg (a 1-U size). While providing low-cost access to space, a major operational limitation is the lack of a propulsion system that can fit within a CubeSat and is capable of executing high delta v maneuvers. This makes it difficult to use CubeSats on missions requiring certain types of maneuvers (i.e. formation flying, spacecraft rendezvous). Recently, work has been performed investigating the use of iodine as a propellant for Hall-effect thrusters (HETs) 2 that could subsequently be used to provide a high specific impulse path to CubeSat propulsion. Iodine stores as a dense solid at very low pressures, making it acceptable as a propellant on a secondary payload. It has exceptionally high ?Isp (density times specific impulse), making it an enabling technology for small satellite near-term applications and providing the potential for systems-level advantages over mid-term high power electric propulsion options. Iodine flow can also be thermally regulated, subliming at relatively low temperature ( less than100 C) to yield I2 vapor at or below 50 torr. At low power, the measured performance of an iodine-fed HET is very similar to that of a state-of-the-art xenon-fed thruster. Just as importantly, the current-voltage discharge characteristics of low power iodine-fed and xenon-fed thrusters are remarkably similar, potentially reducing development and qualifications costs by making it possible to use an already-qualified xenon-HET PPU in an iodine-fed system. Finally, a cold surface can be installed in a vacuum test chamber on which expended iodine propellant can deposit. In addition, the temperature doesn't have to be extremely cold to maintain a low vapor pressure in the vacuum chamber (it is under 10(exp -6) torr at -75 C), making it possible to 'cryopump' the propellant with lower-cost recirculating refrigerant-based systems as opposed to using liquid nitrogen or low temperature gaseous helium cryopanels. In the present paper, we describe testing performed using an iodine-fed 200 W Hall thruster mounted to a thrust stand and operated in conjunction with MSFCs Small Projects Rapid Integration and Test Environment (SPRITE) Portable Hardware In the Loop (PHIL) hardware. This work is performed in support of the iodine satellite (iSAT) project, which aims to fly a 200-W iodine-fed thruster on a 12-U CubeSat. The SPRITE PHIL hardware allows a given vehicle to do a checkout of its avionics algorithm by allowing it to monitor and feed data to simulated sensors and effectors in a digital environment. These data are then used to determine the attitude of the vehicle and a separate computer is used to interpret the data set and visualize it using a 3D graphical interface. The PHIL hardware allows the testing of the vehicles bus by providing 'real' hardware interfaces (in the case of this test a real RS422 bus) and specific components can be modeled to show their interactions with the avionics algorithm (e.g. a thruster model). For the iSAT project the PHIL is used to visualize the operating cycle of the thruster and the subsequent effect this thrusting has on the attitude of the satellite over a given period of time. The test is controlled using software running on an Andrews Space Cortex 160 flight computer. This computer is the current baseline for a full iSAT mission. While the test could be conducted with a lab computer and software, the team chose to exercise the propulsion system with a representative CubeSat-class computer. For purposes of this test, the "flight" software monitored the propulsion and PPU systems, controlled operation of the thruster, and provided thruster state data to the PHIL simulation. Commands to operate the thruster were initiated from an operator's workstation outside the vacuum chamber and passed through the Cortex 160 to exercise portions of the flight avionics. Two custom-designed pieces of electronics hardware have been designed to operate the propellant feed system. One piece of hardware is an auxiliary board that controls a latch valve, proportional flow control valves (PFCVs) and valve heaters as well as measuring pressures, temperatures and PFCV feedback voltage. An onboard FPGA provides a serial link for issuing commands and manages all lower level input-output functions. The other piece of hardware is a power distribution board, which accepts a standard bus voltage input and converts this voltage into all the different current-voltage types required to operate the auxiliary board. These electronics boards are located in the vacuum chamber near the thruster, exposing this hardware to both the vacuum and plasma environments they would encounter during a mission, with these components communicating to the flight computer through an RS-422 interface. The auxiliary board FPGA provides a 28V MOSFET switch circuit with a 20ms pulse to open or close the iodine propellant feed system latch valve. The FPGA provides a pulse width modulation (PWM) signal to a DC/DC boost converter to produce the 12-120V needed for control of the proportional flow control valve. There are eight MOSFET-switched heating circuits in the system. Heaters are 28V and located in the latch valve, PFCV, propellant tank and propellant feed lines. Both the latch valve and PFCV have thermistors built into them for temperature monitoring. There are also seven resistance temperature device (RTD) circuits on the auxiliary board that can be used to measure the propellant tank and feedline temperatures. The signals are conditioned and sent to an analog to digital converter (ADC), which is directly commanded and controlled by the FPGA.

Autonomous Satellite Command and Control through the World Wide Web: Phase 3

NASA Technical Reports Server (NTRS)

Cantwell, Brian; Twiggs, Robert

1998-01-01

NASA's New Millenium Program (NMP) has identified a variety of revolutionary technologies that will support orders of magnitude improvements in the capabilities of spacecraft missions. This program's Autonomy team has focused on science and engineering automation technologies. In doing so, it has established a clear development roadmap specifying the experiments and demonstrations required to mature these technologies. The primary developmental thrusts of this roadmap are in the areas of remote agents, PI/operator interface, planning/scheduling fault management, and smart execution architectures. Phases 1 and 2 of the ASSET Project (previously known as the WebSat project) have focused on establishing World Wide Web-based commanding and telemetry services as an advanced means of interfacing a spacecraft system with the PI and operators. Current automated capabilities include Web-based command submission, limited contact scheduling, command list generation and transfer to the ground station, spacecraft support for demonstrations experiments, data transfer from the ground station back to the ASSET system, data archiving, and Web-based telemetry distribution. Phase 2 was finished in December 1996. During January-December 1997 work was commenced on Phase 3 of the ASSET Project. Phase 3 is the subject of this report. This phase permitted SSDL and its project partners to expand the ASSET system in a variety of ways. These added capabilities included the advancement of ground station capabilities, the adaptation of spacecraft on-board software, and the expansion of capabilities of the ASSET management algorithms. Specific goals of Phase 3 were: (1) Extend Web-based goal-level commanding for both the payload PI and the spacecraft engineer; (2) Support prioritized handling of multiple PIs as well as associated payload experimenters; (3) Expand the number and types of experiments supported by the ASSET system and its associated spacecraft; (4) Implement more advanced resource management, modeling and fault management capabilities that integrate the space and ground segments of the space system hardware; (5) Implement a beacon monitoring test; (6) Implement an experimental blackboard controller for space system management; (7) Further define typical ground station developments required for Internet-based remote control and for full system automation of the PI-to-spacecraft link. Each of those goals is examined in the next section. Significant sections of this report were also published as a conference paper.

Integration & Validation of LCU with Different Sub-systems for Diacrode based amplifier

NASA Astrophysics Data System (ADS)

Rajnish, Kumar; Verma, Sriprakash; Soni, Dipal; Patel, Hriday; Suthar, Gajendra; Dalicha, Hrushikesh; Dhola, Hitesh; Patel, Amit; Upadhayay, Dishang; Jha, Akhil; Patel, Manoj; Trivedi, Rajesh; Machchhar, Harsha; Singh, Raghuraj; Mukherjee, Aparajita

2017-04-01

ITER-India is responsible to deliver nine (8+1 spare) ICH & CD Power Sources to ITER. Each power source is capable to deliver 2.5 MW at 35 to 65 MHz frequency range with a load condition up to VSWR 2:1. For remote operation of different subsystems, Local Control Unit (LCU) is developed. LCU is developed using PXI hardware and Schneider PLC with Lab VIEW-RT developmental environment. All the protection function of the amplifier is running on PXI 7841 R module that ensures hard wired protection logic. There are three level of protection function- first by power supply itself that detects overcurrent/overvoltage and trips itself and generate trip signal for further action. There are some direct hardwired signal interfaces between power supplies to protect the amplifier. Second level of protection is generated through integrated controller of amplifier i.e. Command Control Embedded (CCE) against arc and Anode over current. Third level of Protection is through LCU where different fault signals are received and processed to generate off command for different sub-systems. Before connecting different subsystem with High power RF amplifiers (Driver & Final stage), each subsystem is individually tested through LCU. All protection functions are tested before hooking up the subsystems with main amplifier and initiating RF operation.

Managing the Implementation of Mission Operations Automation

NASA Technical Reports Server (NTRS)

Sodano, R.; Crouse, P.; Odendahl, S.; Fatig, M.; McMahon, K.; Lakin, J.

2006-01-01

Reducing the cost of mission operations has necessitated a high level of automation both on spacecraft and ground systems. While automation on spacecraft is implemented during the design phase, ground system automation tends to be implemented during the prime mission operations phase. Experience has shown that this tendency for late automation development can be hindered by several factors: additional hardware and software resources may need to be procured; software must be developed and tested on a non-interference basis with primary operations with limited manpower; and established procedures may not be suited for automation requiring substantial rework. In this paper we will review the experience of successfully automating mission operations for seven on-orbit missions: the Compton Gamma Ray Observatory (CGRO), the Rossi X-Ray Timing Explorer (RXTE), the Advanced Composition Explorer (ACE), the Far Ultraviolet Spectroscopic Explorer (FUSE), Interplanetary Physics Laboratory (WIND), Polar Plasma Laboratory (POLAR), and the Imager for Magnetopause-to-Aurora Global Exploration (IMAGE). We will provide lessons learned in areas such as: spacecraft recorder management, procedure development, lights out commanding from the ground system vs. stored command loads, spacecraft contingency response time, and ground station interfaces. Implementing automation strategies during the mission concept and spacecraft integration and test phase as the most efficient method will be discussed.

Programmable Ultra-Lightweight System Adaptable Radio

NASA Technical Reports Server (NTRS)

Werkheiser, Arthur

2015-01-01

The programmable ultra-lightweight system adaptable radio (PULSAR) is a NASA Marshall Space Flight Center transceiver designed for the CubeSat market, but has the potential for other markets. The PULSAR project aims to reduce size, weight, and power while increasing telemetry data rate. The current version of the PULSAR has a mass of 2.2 kg and a footprint of 10.8 cm2. The height depends on the specific configuration. The PULSAR S-Band Communications Subsystem is an S- and X-band transponder system comprised of a receiver/detector (receiver) element, a transmitter element(s), and related power distribution, command, control, and telemetry element for operation and information interfaces. It is capable of receiving commands, encoding and transmitting telemetry, as well as providing tracking data in a manner compatible with Earthbased ground stations, near Earth network, and deep space network station resources. The software-defined radio's (SDR's) data format characteristics can be defined and reconfigured during spaceflight or prior to launch. The PULSAR team continues to evolve the SDR to improve the performance and form factor to meet the requirements that the CubeSat market space requires. One of the unique features is that the actual radio design can change (somewhat), but not require any hardware modifications due to the use of field programmable gate arrays.

Monitoring Temperature and Fan Speed Using Ganglia and Winbond Chips

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

McCaffrey, Cattie; /SLAC

2006-09-27

Effective monitoring is essential to keep a large group of machines, like the ones at Stanford Linear Accelerator Center (SLAC), up and running. SLAC currently uses Ganglia Monitoring System to observe about 2000 machines, analyzing metrics like CPU usage and I/O rate. However, metrics essential to machine hardware health, such as temperature and fan speed, are not being monitored. Many machines have a Winbond w83782d chip which monitors three temperatures, two of which come from dual CPUs, and returns the information when the sensor command is invoked. Ganglia also provides a feature, gmetric, that allows the users to monitor theirmore » own metrics and incorporate them into the monitoring system. The programming language Perl is chosen to implement a script that invokes the sensors command, extracts the temperature and fan speed information, and calls gmetric with the appropriate arguments. Two machines were used to test the script; the two CPUs on each machine run at about 65 Celsius, which is well within the operating temperature range (The maximum safe temperature range is 77-82 Celsius for the Pentium III processors being used). Installing the script on all machines with a Winbond w83782d chip allows the SLAC Scientific Computing and Computing Services group (SCCS) to better evaluate current cooling methods.« less

Development and Control of the Naval Postgraduate School Planar Autonomous Docking Simulator (NPADS)

NASA Astrophysics Data System (ADS)

Porter, Robert D.

2002-09-01

The objective of this thesis was to design, construct and develop the initial autonomous control algorithm for the NPS Planar Autonomous Docking Simulator (NPADS) The effort included hardware design, fabrication, installation and integration; mass property determination; and the development and testing of control laws utilizing MATLAB and Simulink for modeling and LabView for NPADS control, The NPADS vehicle uses air pads and a granite table to simulate a 2-D, drag-free, zero-g space environment, It is a completely self-contained vehicle equipped with eight cold-gas, bang-bang type thrusters and a reaction wheel for motion control, A 'star sensor' CCD camera locates the vehicle on the table while a color CCD docking camera and two robotic arms will locate and dock with a target vehicle, The on-board computer system leverages PXI technology and a single source, simplifying systems integration, The vehicle is powered by two lead-acid batteries for completely autonomous operation, A graphical user interface and wireless Ethernet enable the user to command and monitor the vehicle from a remote command and data acquisition computer. Two control algorithms were developed and allow the user to either control the thrusters and reaction wheel manually or simply specify a desired location and rotation angle,

Applying Model-Based Reasoning to the FDIR of the Command and Data Handling Subsystem of the International Space Station

NASA Technical Reports Server (NTRS)

Robinson, Peter; Shirley, Mark; Fletcher, Daryl; Alena, Rick; Duncavage, Dan; Lee, Charles

2003-01-01

All of the International Space Station (ISS) systems which require computer control depend upon the hardware and software of the Command and Data Handling System (C&DH) system, currently a network of over 30 386-class computers called Multiplexor/Dimultiplexors (MDMs)[18]. The Caution and Warning System (C&W)[7], a set of software tasks that runs on the MDMs, is responsible for detecting, classifying, and reporting errors in all ISS subsystems including the C&DH. Fault Detection, Isolation and Recovery (FDIR) of these errors is typically handled with a combination of automatic and human effort. We are developing an Advanced Diagnostic System (ADS) to augment the C&W system with decision support tools to aid in root cause analysis as well as resolve differing human and machine C&DH state estimates. These tools which draw from sources in model-based reasoning[ 16,291, will improve the speed and accuracy of flight controllers by reducing the uncertainty in C&DH state estimation, allowing for a more complete assessment of risk. We have run tests with ISS telemetry and focus on those C&W events which relate to the C&DH system itself. This paper describes our initial results and subsequent plans.

System administrator`s guide to CDPS. Version 1.0

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

Didier, B.T.; Portwood, M.H.

The System Administrator`s Guide to CDPS is intended for those responsible for setting up and maintaining the hardware and software of a Common Mapping Standard (CMS) Date Production System (CDPS) installation. This guide assists the system administrator in performing typical administrative functions. It is not intended to replace the Ultrix Documentation Set that should be available for a DCPS installation. The Ultrix Documentation Set will be required to provide details on referenced Ultrix commands as well as procedures for performing Ultrix maintenance functions. There are six major sections in this guide. Section 1 introduces the system administrator to CDPS andmore » describes the assumptions that are made by this guide. Section 2 describes the CDPS platform configuration. Section 3 describes the platform preparation that is required to install the CDPS software. Section 4 describes the CPS software and its installation procedures. Section 5 describes the CDS software and its installation procedures. Section 6 describes various operation and maintenance procedures. Four appendices are also provided. Appendix A contains a list of used acronyms. Appendix B provides a terse description of common Ultrix commands that are used in administrative functions. Appendix C provides sample CPS and CDS configuration files. Appendix D provides a required list and a recommended list of Ultrix software subsets for installation on a CDPS platform.« less

Review of mobile health technology for military mental health.

PubMed

Shore, Jay H; Aldag, Matt; McVeigh, Francis L; Hoover, Ronald L; Ciulla, Robert; Fisher, Ashley

2014-08-01

Mental health problems pose challenges for military veterans, returning service members, and military family members including spouses and children. Challenges to meeting mental health needs include improving access to care and improving quality of care. Mobile Health, or "mHealth," can help meet these needs in the garrison and civilian environments. mHealth brings unique capabilities to health care provision through the use of mobile device technologies. This report identifies high-priority mHealth technology development considerations in two categories. First, priority considerations specific to mental health care provision include safety, privacy, evidence-based practice, efficacy studies, and temperament. Second, priority considerations broadly applicable to mHealth include security, outcomes, ease of use, carrier compliance, hardware, provider perspectives, data volume, population, regulation, command policy, and reimbursement. Strategic planning for the advancement of these priority considerations should be coordinated with stated Department of Defense capability needs to maximize likelihood of adoption. This report also summarizes three leading, military programs focused on mHealth projects in mental health, The Telemedicine and Advanced Technology Research Center, The Military Operational Medicine Research Program, United States Army Medical Research and Materiel Command, and The National Center for Telehealth and Technology. Reprint & Copyright © 2014 Association of Military Surgeons of the U.S.

IT Security Support for the Spaceport Command Control System Development

NASA Technical Reports Server (NTRS)

Varise, Brian

2014-01-01

My job title is IT Security support for the Spaceport Command & Control System Development. As a cyber-security analyst it is my job to ensure NASA's information stays safe from cyber threats, such as, viruses, malware and denial-of-service attacks by establishing and enforcing system access controls. Security is very important in the world of technology and it is used everywhere from personal computers to giant networks ran by Government agencies worldwide. Without constant monitoring analysis, businesses, public organizations and government agencies are vulnerable to potential harmful infiltration of their computer information system. It is my responsibility to ensure authorized access by examining improper access, reporting violations, revoke access, monitor information request by new programming and recommend improvements. My department oversees the Launch Control System and networks. An audit will be conducted for the LCS based on compliance with the Federal Information Security Management Act (FISMA) and The National Institute of Standards and Technology (NIST). I recently finished analyzing the SANS top 20 critical controls to give cost effective recommendations on various software and hardware products for compliance. Upon my completion of this internship, I will have successfully completed my duties as well as gain knowledge that will be helpful to my career in the future as a Cyber Security Analyst.

Control algorithm implementation for a redundant degree of freedom manipulator

NASA Technical Reports Server (NTRS)

Cohan, Steve

1991-01-01

This project's purpose is to develop and implement control algorithms for a kinematically redundant robotic manipulator. The manipulator is being developed concurrently by Odetics Inc., under internal research and development funding. This SBIR contract supports algorithm conception, development, and simulation, as well as software implementation and integration with the manipulator hardware. The Odetics Dexterous Manipulator is a lightweight, high strength, modular manipulator being developed for space and commercial applications. It has seven fully active degrees of freedom, is electrically powered, and is fully operational in 1 G. The manipulator consists of five self-contained modules. These modules join via simple quick-disconnect couplings and self-mating connectors which allow rapid assembly/disassembly for reconfiguration, transport, or servicing. Each joint incorporates a unique drive train design which provides zero backlash operation, is insensitive to wear, and is single fault tolerant to motor or servo amplifier failure. The sensing system is also designed to be single fault tolerant. Although the initial prototype is not space qualified, the design is well-suited to meeting space qualification requirements. The control algorithm design approach is to develop a hierarchical system with well defined access and interfaces at each level. The high level endpoint/configuration control algorithm transforms manipulator endpoint position/orientation commands to joint angle commands, providing task space motion. At the same time, the kinematic redundancy is resolved by controlling the configuration (pose) of the manipulator, using several different optimizing criteria. The center level of the hierarchy servos the joints to their commanded trajectories using both linear feedback and model-based nonlinear control techniques. The lowest control level uses sensed joint torque to close torque servo loops, with the goal of improving the manipulator dynamic behavior. The control algorithms are subjected to a dynamic simulation before implementation.

Advanced communications technology satellite high burst rate link evaluation terminal communication protocol software user's guide, version 1.0

NASA Technical Reports Server (NTRS)

Reinhart, Richard C.

1993-01-01

The Communication Protocol Software was developed at the NASA Lewis Research Center to support the Advanced Communications Technology Satellite High Burst Rate Link Evaluation Terminal (ACTS HBR-LET). The HBR-LET is an experimenters terminal to communicate with the ACTS for various experiments by government, university, and industry agencies. The Communication Protocol Software is one segment of the Control and Performance Monitor (C&PM) Software system of the HBR-LET. The Communication Protocol Software allows users to control and configure the Intermediate Frequency Switch Matrix (IFSM) on board the ACTS to yield a desired path through the spacecraft payload. Besides IFSM control, the C&PM Software System is also responsible for instrument control during HBR-LET experiments, uplink power control of the HBR-LET to demonstrate power augmentation during signal fade events, and data display. The Communication Protocol Software User's Guide, Version 1.0 (NASA CR-189162) outlines the commands and procedures to install and operate the Communication Protocol Software. Configuration files used to control the IFSM, operator commands, and error recovery procedures are discussed. The Communication Protocol Software Maintenance Manual, Version 1.0 (NASA CR-189163, to be published) is a programmer's guide to the Communication Protocol Software. This manual details the current implementation of the software from a technical perspective. Included is an overview of the Communication Protocol Software, computer algorithms, format representations, and computer hardware configuration. The Communication Protocol Software Test Plan (NASA CR-189164, to be published) provides a step-by-step procedure to verify the operation of the software. Included in the Test Plan is command transmission, telemetry reception, error detection, and error recovery procedures.

Challenges of the Cassini Test Bed Simulating the Saturnian Environment

NASA Technical Reports Server (NTRS)

Hernandez, Juan C.; Badaruddin, Kareem S.

2007-01-01

The Cassini-Huygens mission is a joint NASA and European Space Agency (ESA) mission to collect scientific data of the Saturnian system and is managed by the Jet Propulsion Laboratory (JPL). After having arrived in Saturn orbit and releasing the ESA's Huygens probe for a highly successful descent and landing mission on Saturn's moon Titan, the Cassini orbiter continues on its tour of Saturn, its satellites, and the Saturnian environment. JPL's Cassini Integrated Test laboratory (ITL) is a dedicated high fidelity test bed that verifies and validates command sequences and flight software before upload to the Cassini spacecraft. The ITL provides artificial stimuli that allow a highly accurate hardware-in-the-loop test bed model that tests the operation of the Cassini spacecraft on the ground. This enables accurate prediction and recreation of mission events and flight software and hardware behavior. As we discovered more about the Saturnian environment, a combination of creative test methods and simulation changes were necessary to simulate the harmful effect that the optical and physical environment has on the pointing performance of Cassini. This paper presents the challenges experienced and overcome in that endeavor to simulate and test the post Saturn Orbit Insertion (SOI) and Probe Relay tour phase of the Cassini mission.

Computer architecture for efficient algorithmic executions in real-time systems: New technology for avionics systems and advanced space vehicles

NASA Technical Reports Server (NTRS)

Carroll, Chester C.; Youngblood, John N.; Saha, Aindam

1987-01-01

Improvements and advances in the development of computer architecture now provide innovative technology for the recasting of traditional sequential solutions into high-performance, low-cost, parallel system to increase system performance. Research conducted in development of specialized computer architecture for the algorithmic execution of an avionics system, guidance and control problem in real time is described. A comprehensive treatment of both the hardware and software structures of a customized computer which performs real-time computation of guidance commands with updated estimates of target motion and time-to-go is presented. An optimal, real-time allocation algorithm was developed which maps the algorithmic tasks onto the processing elements. This allocation is based on the critical path analysis. The final stage is the design and development of the hardware structures suitable for the efficient execution of the allocated task graph. The processing element is designed for rapid execution of the allocated tasks. Fault tolerance is a key feature of the overall architecture. Parallel numerical integration techniques, tasks definitions, and allocation algorithms are discussed. The parallel implementation is analytically verified and the experimental results are presented. The design of the data-driven computer architecture, customized for the execution of the particular algorithm, is discussed.

Update on the DIII-D ECH system: experiments, gyrotrons, advanced diagnostics, and controls

NASA Astrophysics Data System (ADS)

Lohr, John; Brambila, Rigoberto; Cengher, Mirela; Gorelov, Yuri; Grosnickle, William; Moeller, Charles; Ponce, Dan; Torrezan, Antonio; Ives, Lawrence; Reed, Michael; Blank, Monica; Felch, Kevin; Parisuaña, Claudia; LeViness, Alexandra

2017-08-01

The ECH system on DIII-D is continuing to be upgraded, while simultaneously being operated nearly daily for plasma experiments. The latest major hardware addition is a new 117.5 GHz gyrotron, which generated 1.7 MW for short pulses during factory testing. A new gyrotron control system based on Field Programmable Gate Array (FPGA) technology with very high speed system data acquisition has significantly increased the flexibility and reliability of individual gyrotron operation. We have improved the performance of the fast mirror scanning, both by increasing the scan speeds and by adding new algorithms for controlling the aiming using commands generated by the Plasma Control System (PCS). The system is used for transport studies, ELM control, current profile control, non-inductive current generation, suppression of MHD modes, startup assist, plasma density control, and other applications. A program of protective measures, which has been in place for more than two years, has eliminated damage to hardware and diagnostics caused by overdense operation. Other activities not directly related to fusion research have used the ECH system to test components, study methods for improving production of semiconductor junctions and materials, and test the feasibility of using ground based microwave systems to power satellites into orbit.

Integrated Application of Active Controls (IAAC) technology to an advanced subsonic transport project: Test act system validation

NASA Technical Reports Server (NTRS)

1985-01-01

The primary objective of the Test Active Control Technology (ACT) System laboratory tests was to verify and validate the system concept, hardware, and software. The initial lab tests were open loop hardware tests of the Test ACT System as designed and built. During the course of the testing, minor problems were uncovered and corrected. Major software tests were run. The initial software testing was also open loop. These tests examined pitch control laws, wing load alleviation, signal selection/fault detection (SSFD), and output management. The Test ACT System was modified to interface with the direct drive valve (DDV) modules. The initial testing identified problem areas with DDV nonlinearities, valve friction induced limit cycling, DDV control loop instability, and channel command mismatch. The other DDV issue investigated was the ability to detect and isolate failures. Some simple schemes for failure detection were tested but were not completely satisfactory. The Test ACT System architecture continues to appear promising for ACT/FBW applications in systems that must be immune to worst case generic digital faults, and be able to tolerate two sequential nongeneric faults with no reduction in performance. The challenge in such an implementation would be to keep the analog element sufficiently simple to achieve the necessary reliability.

System-Level Testing of the Advanced Stirling Radioisotope Generator Engineering Hardware

NASA Technical Reports Server (NTRS)

Chan, Jack; Wiser, Jack; Brown, Greg; Florin, Dominic; Oriti, Salvatore M.

2014-01-01

To support future NASA deep space missions, a radioisotope power system utilizing Stirling power conversion technology was under development. This development effort was performed under the joint sponsorship of the Department of Energy and NASA, until its termination at the end of 2013 due to budget constraints. The higher conversion efficiency of the Stirling cycle compared with that of the Radioisotope Thermoelectric Generators (RTGs) used in previous missions (Viking, Pioneer, Voyager, Galileo, Ulysses, Cassini, Pluto New Horizons and Mars Science Laboratory) offers the advantage of a four-fold reduction in Pu-238 fuel, thereby extending its limited domestic supply. As part of closeout activities, system-level testing of flight-like Advanced Stirling Convertors (ASCs) with a flight-like ASC Controller Unit (ACU) was performed in February 2014. This hardware is the most representative of the flight design tested to date. The test fully demonstrates the following ACU and system functionality: system startup; ASC control and operation at nominal and worst-case operating conditions; power rectification; DC output power management throughout nominal and out-of-range host voltage levels; ACU fault management, and system command / telemetry via MIL-STD 1553 bus. This testing shows the viability of such a system for future deep space missions and bolsters confidence in the maturity of the flight design.

Computer architecture for efficient algorithmic executions in real-time systems: new technology for avionics systems and advanced space vehicles

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

Carroll, C.C.; Youngblood, J.N.; Saha, A.

1987-12-01

Improvements and advances in the development of computer architecture now provide innovative technology for the recasting of traditional sequential solutions into high-performance, low-cost, parallel system to increase system performance. Research conducted in development of specialized computer architecture for the algorithmic execution of an avionics system, guidance and control problem in real time is described. A comprehensive treatment of both the hardware and software structures of a customized computer which performs real-time computation of guidance commands with updated estimates of target motion and time-to-go is presented. An optimal, real-time allocation algorithm was developed which maps the algorithmic tasks onto the processingmore » elements. This allocation is based on the critical path analysis. The final stage is the design and development of the hardware structures suitable for the efficient execution of the allocated task graph. The processing element is designed for rapid execution of the allocated tasks. Fault tolerance is a key feature of the overall architecture. Parallel numerical integration techniques, tasks definitions, and allocation algorithms are discussed. The parallel implementation is analytically verified and the experimental results are presented. The design of the data-driven computer architecture, customized for the execution of the particular algorithm, is discussed.« less

Astronauts Prepare for Mission With Virtual Reality Hardware

NASA Technical Reports Server (NTRS)

2001-01-01

Astronauts John M. Grunsfeld (left), STS-109 payload commander, and Nancy J. Currie, mission specialist, use the virtual reality lab at Johnson Space Center to train for upcoming duties aboard the Space Shuttle Columbia. This type of computer interface paired with virtual reality training hardware and software helps to prepare the entire team to perform its duties for the fourth Hubble Space Telescope Servicing mission. The most familiar form of virtual reality technology is some form of headpiece, which fits over your eyes and displays a three dimensional computerized image of another place. Turn your head left and right, and you see what would be to your sides; turn around, and you see what might be sneaking up on you. An important part of the technology is some type of data glove that you use to propel yourself through the virtual world. Currently, the medical community is using the new technologies in four major ways: To see parts of the body more accurately, for study, to make better diagnosis of disease and to plan surgery in more detail; to obtain a more accurate picture of a procedure during surgery; to perform more types of surgery with the most noninvasive, accurate methods possible; and to model interactions among molecules at a molecular level.

Steering and positioning targets for HWIL IR testing at cryogenic conditions

NASA Astrophysics Data System (ADS)

Perkes, D. W.; Jensen, G. L.; Higham, D. L.; Lowry, H. S.; Simpson, W. R.

2006-05-01

In order to increase the fidelity of hardware-in-the-loop ground-truth testing, it is desirable to create a dynamic scene of multiple, independently controlled IR point sources. ATK-Mission Research has developed and supplied the steering mirror systems for the 7V and 10V Space Simulation Test Chambers at the Arnold Engineering Development Center (AEDC), Air Force Materiel Command (AFMC). A portion of the 10V system incorporates multiple target sources beam-combined at the focal point of a 20K cryogenic collimator. Each IR source consists of a precision blackbody with cryogenic aperture and filter wheels mounted on a cryogenic two-axis translation stage. This point source target scene is steered by a high-speed steering mirror to produce further complex motion. The scene changes dynamically in order to simulate an actual operational scene as viewed by the System Under Test (SUT) as it executes various dynamic look-direction changes during its flight to a target. Synchronization and real-time hardware-in-the-loop control is accomplished using reflective memory for each subsystem control and feedback loop. This paper focuses on the steering mirror system and the required tradeoffs of optical performance, precision, repeatability and high-speed motion as well as the complications of encoder feedback calibration and operation at 20K.

SMC Message Browser Projects

NASA Technical Reports Server (NTRS)

Wichmann, Benjamin C.

2013-01-01

I work directly with the System Monitoring and Control (SMC) software engineers who develop, test and release custom and commercial software in support of the Kennedy Space Center Spaceport Command and Control System. (SCCS). SMC uses Commercial Off-The-Shelf (COTS) Enterprise Management Systems (EMS) software which provides a centralized subsystem for configuring, monitoring, and controlling SCCS hardware and software used in the Control Rooms. There are multiple projects being worked on using the COTS EMS software. I am currently working with the HP Operations Manager for UNIX (OMU) software which allows Master Console Operators (MCO) to access, view and interpret messages regarding the status of the SCCS hardware and software. The OMU message browser gets cluttered with messages which can make it difficult for the MCO to manage. My main project involves determining ways to reduce the number of messages being displayed in the OMU message browser. I plan to accomplish this task in two different ways: (1) by correlating multiple messages into one single message being displayed and (2) to create policies that will determine the significance of each message and whether or not it needs to be displayed to the MCO. The core idea is to lessen the number of messages being sent to the OMU message browser so the MCO can more effectively use it.

The Case for Deep Space Telecommunications Relay Stations

NASA Technical Reports Server (NTRS)

Chandler, Charles W.; Miranda, Felix A. (Technical Monitor)

2004-01-01

Each future mission to Jupiter and beyond must carry the traditional suite of telecommunications systems for command and control and for mission data transmission to earth. The telecommunications hardware includes the large antenna and the high-power transmitters that enable the communications link. Yet future spacecraft will be scaled down from the hallmark missions of Galileo and Cassini to Jupiter and Saturn, respectively. This implies that a higher percentage of the spacecraft weight and power must be dedicated to telecommunications system. The following analysis quantifies this impact to future missions and then explores the merits of an alternative approach using deep space relay stations for the link back to earth. It will be demonstrated that a telecommunications relay satellite would reduce S/C telecommunications weight and power sufficiently to add one to two more instruments.

Integrated operations/payloads/fleet analysis. Volume 3: System costs. Appendix A: Program direct costs

NASA Technical Reports Server (NTRS)

1971-01-01

Individualized program direct costs for each satellite program are presented. This breakdown provides the activity level dependent costs for each satellite program. The activity level dependent costs, or, more simply, program direct costs, are comprised of the total payload costs (as these costs are strictly program dependent) and the direct launch vehicle costs. Only those incremental launch vehicle costs associated directly with the satellite program are considered. For expendable launch vehicles the direct costs include the vehicle investment hardware costs and the launch operations costs. For the reusable STS vehicles the direct costs include only the launch operations, recovery operations, command and control, vehicle maintenance, and propellant support. The costs associated with amortization of reusable vehicle investment, RDT&E range support, etc., are not included.

Applications in Data-Intensive Computing

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

Shah, Anuj R.; Adkins, Joshua N.; Baxter, Douglas J.

2010-04-01

This book chapter, to be published in Advances in Computers, Volume 78, in 2010 describes applications of data intensive computing (DIC). This is an invited chapter resulting from a previous publication on DIC. This work summarizes efforts coming out of the PNNL's Data Intensive Computing Initiative. Advances in technology have empowered individuals with the ability to generate digital content with mouse clicks and voice commands. Digital pictures, emails, text messages, home videos, audio, and webpages are common examples of digital content that are generated on a regular basis. Data intensive computing facilitates human understanding of complex problems. Data-intensive applications providemore » timely and meaningful analytical results in response to exponentially growing data complexity and associated analysis requirements through the development of new classes of software, algorithms, and hardware.« less

ISS Expedition 53 U.S. Spacewalk 46

NASA Image and Video Library

2017-10-20

Outside the International Space Station, Expedition 53 Commander Randy Bresnik and Flight Engineer Joe Acaba of NASA conducted a spacewalk Oct. 20 to continue upgrades to and maintenance of station hardware. It was the third spacewalk in two weeks for Expedition 53 crewmembers outside the Quest airlock. During the excursion, Bresnik and Acaba replaced a failed camera light on the new Latching End Effector “hand” on the Canadarm2 robotic arm, installed a new high definition camera on the starboard truss of the complex, replaced a fuse on the Dextre Special Dexterous Manipulator attachment for the arm and removed thermal blankets from two spare electrical routing units for future robotic replacement work, if required. It was the fifth spacewalk in Bresnik’s career and the third for Acaba.

Characterization of quantum well laser diodes for application within the AMRDEC HWIL facilities

NASA Astrophysics Data System (ADS)

Saylor, Daniel A.; Bender, Matt; Cantey, Thomas M.; Beasley, D. B.; Buford, Jim A.

2004-08-01

The U.S. Army's Research, Development, and Engineering Command's (RDECOM) Aviation and Missile Research, Development, and Engineering Center (AMRDEC) provides Hardware-in-the-Loop (HWIL) test support to numerous tactical and theatre missile programs. Critical to the successful execution of these tests is the state-of-the-art technologies employed in the visible and infrared scene projector systems. This paper describes the results of characterizations tests performed on new mid-wave infrared (MWIR) quantum well laser diodes recently provided to AMRDEC by the Naval Research Labs and Sarnoff Industries. These lasers provide a +10X imrovement in MWIR output over the previous technology of lead-salt laser diodes. Performance data on output power, linearity, and solid-angle coverage are presented. A discussion of the laser packages is also provided.

STS-83 Crew Arrival for TCDT

NASA Technical Reports Server (NTRS)

1997-01-01

Members of the STS-83 flight crew pose alongside a T-33 jet trainer aircraft after arriving at the KSC Shuttle Landing Facility for Terminal Countdown Demonstration (TCDT) exercises for that space flight. They are (left to right) Payload Specialist Roger K. Crouch; Pilot Susan L. Still; Mission Commander James D. Halsell, Jr.; Mission Specialist Michael L. Gernhardt; Payload Specialist She is the second woman to fly in this capacity on the Space Shuttle. The Microgravity Science Laboratory-1 (MSL-1) Spacelab module is the primary payload on this 16-day mission. The MSL-1 will used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station, while the seven-member crew conducts combustion, protein crystal growth and materials processing experiments.

Ground Simulation of an Autonomous Satellite Rendezvous and Tracking System Using Dual Robotic Systems

NASA Technical Reports Server (NTRS)

Trube, Matthew J.; Hyslop, Andrew M.; Carignan, Craig R.; Easley, Joseph W.

2012-01-01

A hardware-in-the-loop ground system was developed for simulating a robotic servicer spacecraft tracking a target satellite at short range. A relative navigation sensor package "Argon" is mounted on the end-effector of a Fanuc 430 manipulator, which functions as the base platform of the robotic spacecraft servicer. Machine vision algorithms estimate the pose of the target spacecraft, mounted on a Rotopod R-2000 platform, relay the solution to a simulation of the servicer spacecraft running in "Freespace", which performs guidance, navigation and control functions, integrates dynamics, and issues motion commands to a Fanuc platform controller so that it tracks the simulated servicer spacecraft. Results will be reviewed for several satellite motion scenarios at different ranges. Key words: robotics, satellite, servicing, guidance, navigation, tracking, control, docking.

Software Reliability Issues Concerning Large and Safety Critical Software Systems

NASA Technical Reports Server (NTRS)

Kamel, Khaled; Brown, Barbara

1996-01-01

This research was undertaken to provide NASA with a survey of state-of-the-art techniques using in industrial and academia to provide safe, reliable, and maintainable software to drive large systems. Such systems must match the complexity and strict safety requirements of NASA's shuttle system. In particular, the Launch Processing System (LPS) is being considered for replacement. The LPS is responsible for monitoring and commanding the shuttle during test, repair, and launch phases. NASA built this system in the 1970's using mostly hardware techniques to provide for increased reliability, but it did so often using custom-built equipment, which has not been able to keep up with current technologies. This report surveys the major techniques used in industry and academia to ensure reliability in large and critical computer systems.

Computer aided control of a mechanical arm

NASA Technical Reports Server (NTRS)

Derocher, W. L., Jr.; Zermuehlen, r. O.

1979-01-01

A method for computer-aided remote control of a six-degree-of-freedom manipulator arm involved in the on-orbit servicing of a spacecraft is presented. The control configuration features a supervisory type of control in which each of the segments of a module exchange trajectory is controlled automatically under human supervision, with manual commands to proceed to the next step and in the event of a failure or undesirable outcome. The implementation of the supervisory system is discussed in terms of necessary onboard and ground- or Orbiter-based hardware and software, and a one-g demonstration system built to allow further investigation of system operation is described. Possible applications of the system include the construction of satellite solar power systems, environmental testing and the control of heliostat solar power stations.

NASA Space Technology Draft Roadmap Area 13: Ground and Launch Systems Processing

NASA Technical Reports Server (NTRS)

Clements, Greg

2011-01-01

This slide presentation reviews the technology development roadmap for the area of ground and launch systems processing. The scope of this technology area includes: (1) Assembly, integration, and processing of the launch vehicle, spacecraft, and payload hardware (2) Supply chain management (3) Transportation of hardware to the launch site (4) Transportation to and operations at the launch pad (5) Launch processing infrastructure and its ability to support future operations (6) Range, personnel, and facility safety capabilities (7) Launch and landing weather (8) Environmental impact mitigations for ground and launch operations (9) Launch control center operations and infrastructure (10) Mission integration and planning (11) Mission training for both ground and flight crew personnel (12) Mission control center operations and infrastructure (13) Telemetry and command processing and archiving (14) Recovery operations for flight crews, flight hardware, and returned samples. This technology roadmap also identifies ground, launch and mission technologies that will: (1) Dramatically transform future space operations, with significant improvement in life-cycle costs (2) Improve the quality of life on earth, while exploring in co-existence with the environment (3) Increase reliability and mission availability using low/zero maintenance materials and systems, comprehensive capabilities to ascertain and forecast system health/configuration, data integration, and the use of advanced/expert software systems (4) Enhance methods to assess safety and mission risk posture, which would allow for timely and better decision making. Several key technologies are identified, with a couple of slides devoted to one of these technologies (i.e., corrosion detection and prevention). Development of these technologies can enhance life on earth and have a major impact on how we can access space, eventually making routine commercial space access and improve building and manufacturing, and weather forecasting for example for the effect of these process improvements on our daily lives.

STS-103 Crew Training

NASA Technical Reports Server (NTRS)

1999-01-01

The Hubble Space Telescope (HST) team is preparing for NASA's third scheduled service call to Hubble. This mission, STS-103, will launch from Kennedy Space Center aboard the Space Shuttle Discovery. The seven flight crew members are Commander Curtis L. Brown, Pilot Scott J. Kelly, European Space Agency (ESA) astronaut Jean-Francois Clervoy who will join space walkers Steven L. Smith, C. Michael Foale, John M. Grunsfeld, and ESA astronaut Claude Nicollier. The objectives of the HST Third Servicing Mission (SM3A) are to replace the telescope's six gyroscopes, a Fine-Guidance Sensor, an S-Band Single Access Transmitter, a spare solid-state recorder and a high-voltage/temperature kit for protecting the batteries from overheating. In addition, the crew plans to install an advanced computer that is 20 times faster and has six times the memory of the current Hubble Space Telescope computer. To prepare for these extravehicular activities (EVAs), the SM3A astronauts participated in Crew Familiarization sessions with the actual SM3A flight hardware. During these sessions the crew spent long hours rehearsing their space walks in the Guidance Navigation Simulator and NBL (Neutral Buoyancy Laboratory). Using space gloves, flight Space Support Equipment (SSE), and Crew Aids and Tools (CATs), the astronauts trained with and verified flight orbital replacement unit (ORU) hardware. The crew worked with a number of trainers and simulators, such as the High Fidelity Mechanical Simulator, Guidance Navigation Simulator, System Engineering Simulator, the Aft Shroud Door Trainer, the Forward Shell/Light Shield Simulator, and the Support Systems Module Bay Doors Simulator. They also trained and verified the flight Orbital Replacement Unit Carrier (ORUC) and its ancillary hardware. Discovery's planned 10-day flight is scheduled to end with a night landing at Kennedy.

Adaptive Optimization of Aircraft Engine Performance Using Neural Networks

NASA Technical Reports Server (NTRS)

Simon, Donald L.; Long, Theresa W.

1995-01-01

Preliminary results are presented on the development of an adaptive neural network based control algorithm to enhance aircraft engine performance. This work builds upon a previous National Aeronautics and Space Administration (NASA) effort known as Performance Seeking Control (PSC). PSC is an adaptive control algorithm which contains a model of the aircraft's propulsion system which is updated on-line to match the operation of the aircraft's actual propulsion system. Information from the on-line model is used to adapt the control system during flight to allow optimal operation of the aircraft's propulsion system (inlet, engine, and nozzle) to improve aircraft engine performance without compromising reliability or operability. Performance Seeking Control has been shown to yield reductions in fuel flow, increases in thrust, and reductions in engine fan turbine inlet temperature. The neural network based adaptive control, like PSC, will contain a model of the propulsion system which will be used to calculate optimal control commands on-line. Hopes are that it will be able to provide some additional benefits above and beyond those of PSC. The PSC algorithm is computationally intensive, it is valid only at near steady-state flight conditions, and it has no way to adapt or learn on-line. These issues are being addressed in the development of the optimal neural controller. Specialized neural network processing hardware is being developed to run the software, the algorithm will be valid at steady-state and transient conditions, and will take advantage of the on-line learning capability of neural networks. Future plans include testing the neural network software and hardware prototype against an aircraft engine simulation. In this paper, the proposed neural network software and hardware is described and preliminary neural network training results are presented.

Evaluation of Critical Care Monitor Technology During the US Navy Strong Angel Exercise

NASA Technical Reports Server (NTRS)

Johannesen, John; Rasbury, Jack

2003-01-01

The NASA critical path road map identifies "trauma and acute medical problems" as a clinical capability risk category (http://criticalDath.isc.nasa.gov). Specific risks include major trauma, organ laceration or contusion, hemoperitoneum, pulmonary failure, pneumo- and hemothorax, burn, open bone fracture, blunt head trauma, and penetrating injury. Mitigation of these risks includes the capability for critical care monitoring. Currently, the International Space Station (ISS) Crew Health Care System (CHeCS) does not provide such a capability. The Clinical Space Medicine Strategic Planning Forum (4/8/97), sponsored by NASA Medical Operations, identified the development of trauma care capabilities as one of the top priorities for space medicine. The Clinical Care Capability Development Project (CCCDP) subsequently undertook the task to address this need.

Lightweight Trauma Module - LTM

NASA Technical Reports Server (NTRS)

Hatfield, Thomas

2008-01-01

Current patient movement items (PMI) supporting the military's Critical Care Air Transport Team (CCATT) mission as well as the Crew Health Care System for space (CHeCS) have significant limitations: size, weight, battery duration, and dated clinical technology. The LTM is a small, 20 lb., system integrating diagnostic and therapeutic clinical capabilities along with onboard data management, communication services and automated care algorithms to meet new Aeromedical Evacuation requirements. The Lightweight Trauma Module is an Impact Instrumentation, Inc. project with strong Industry, DoD, NASA, and Academia partnerships aimed at developing the next generation of smart and rugged critical care tools for hazardous environments ranging from the battlefield to space exploration. The LTM is a combination ventilator/critical care monitor/therapeutic system with integrated automatic control systems. Additional capabilities are provided with small external modules.

Development of the command data system and ground software for the SEDSAT-1 microsatellite

NASA Technical Reports Server (NTRS)

Wells, B. Earl

1996-01-01

SEDSAT-1 is designed to be a low cost scientific satellite which is to be used to perform a minimum of five tasks which include: (1) the acquisition of a number of important parameters associated with the tethering processes from the payloads perspective (such as accelerations incurred and imaging data of the tether during deployment), (2) to act as a remote sensing platform for making measurements of the Earth's Atmosphere (allowing research to be performed in such areas as vertical lightning observation, visible light spectrography, and cloud cover studies, (3) to act as a general purpose amateur radio communication satellite relaying information back to earth, (4) to demonstrate the feasibility of the deployment in low earth orbit of advanced technology such as the Gallium Arsenide Solar Cells, Nickel Metal Hydride batteries, and multi-chip module technology and, (5) to support student's active participation in applying the disciplines of engineering and science to space-based hardware platforms. The project includes the Three-axis Accelerometer System, TAS, Experiment which is designed to report the accelerations that the satellite undergoes during the tethering operations and during the second phase of the mission when the free floating satellite comes in contact with orbit debris. The SEASIS (SEDS Earth, Atmosphere, and Space Imaging System) is another SEDSAT experiment designed to provide images of the tether during its deployment and the earth during the second phase of the mission. To control these experiments and virtually all other satellite operations the Command Data System, CDS is employed. This system utilizes a moderate complexity micro-controller controlled by tasks operating under a real-time operating system to dynamically monitor and control the satellite. The scope of this researchers efforts has been in the general area of coordinating and assisting the student researchers with the development of the CDS and ground station interfaces. This included the low level CDS hardware design and the formulization of a general software plan and schedule for both the CDS and ground station portions of the project.

Configurable Multi-Purpose Processor

NASA Technical Reports Server (NTRS)

Valencia, J. Emilio; Forney, Chirstopher; Morrison, Robert; Birr, Richard

2010-01-01

Advancements in technology have allowed the miniaturization of systems used in aerospace vehicles. This technology is driven by the need for next-generation systems that provide reliable, responsive, and cost-effective range operations while providing increased capabilities such as simultaneous mission support, increased launch trajectories, improved launch, and landing opportunities, etc. Leveraging the newest technologies, the command and telemetry processor (CTP) concept provides for a compact, flexible, and integrated solution for flight command and telemetry systems and range systems. The CTP is a relatively small circuit board that serves as a processing platform for high dynamic, high vibration environments. The CTP can be reconfigured and reprogrammed, allowing it to be adapted for many different applications. The design is centered around a configurable field-programmable gate array (FPGA) device that contains numerous logic cells that can be used to implement traditional integrated circuits. The FPGA contains two PowerPC processors running the Vx-Works real-time operating system and are used to execute software programs specific to each application. The CTP was designed and developed specifically to provide telemetry functions; namely, the command processing, telemetry processing, and GPS metric tracking of a flight vehicle. However, it can be used as a general-purpose processor board to perform numerous functions implemented in either hardware or software using the FPGA s processors and/or logic cells. Functionally, the CTP was designed for range safety applications where it would ultimately become part of a vehicle s flight termination system. Consequently, the major functions of the CTP are to perform the forward link command processing, GPS metric tracking, return link telemetry data processing, error detection and correction, data encryption/ decryption, and initiate flight termination action commands. Also, the CTP had to be designed to survive and operate in a launch environment. Additionally, the CTP was designed to interface with the WFF (Wallops Flight Facility) custom-designed transceiver board which is used in the Low Cost TDRSS Transceiver (LCT2) also developed by WFF. The LCT2 s transceiver board demodulates commands received from the ground via the forward link and sends them to the CTP, where they are processed. The CTP inputs and processes data from the inertial measurement unit (IMU) and the GPS receiver board, generates status data, and then sends the data to the transceiver board where it is modulated and sent to the ground via the return link. Overall, the CTP has combined processing with the ability to interface to a GPS receiver, an IMU, and a pulse code modulation (PCM) communication link, while providing the capability to support common interfaces including Ethernet and serial interfaces boarding a relatively small-sized, lightweight package.

Low-cost real-time infrared scene generation for image projection and signal injection

NASA Astrophysics Data System (ADS)

Buford, James A., Jr.; King, David E.; Bowden, Mark H.

1998-07-01

As cost becomes an increasingly important factor in the development and testing of Infrared sensors and flight computer/processors, the need for accurate hardware-in-the- loop (HWIL) simulations is critical. In the past, expensive and complex dedicated scene generation hardware was needed to attain the fidelity necessary for accurate testing. Recent technological advances and innovative applications of established technologies are beginning to allow development of cost-effective replacements for dedicated scene generators. These new scene generators are mainly constructed from commercial-off-the-shelf (COTS) hardware and software components. At the U.S. Army Aviation and Missile Command (AMCOM) Missile Research, Development, and Engineering Center (MRDEC), researchers have developed such a dynamic IR scene generator (IRSG) built around COTS hardware and software. The IRSG is used to provide dynamic inputs to an IR scene projector for in-band seeker testing and for direct signal injection into the seeker or processor electronics. AMCOM MRDEC has developed a second generation IRSG, namely IRSG2, using the latest Silicon Graphics Incorporated (SGI) Onyx2 with Infinite Reality graphics. As reported in previous papers, the SGI Onyx Reality Engine 2 is the platform of the original IRSG that is now referred to as IRSG1. IRSG1 has been in operation and used daily for the past three years on several IR projection and signal injection HWIL programs. Using this second generation IRSG, frame rates have increased from 120 Hz to 400 Hz and intensity resolution from 12 bits to 16 bits. The key features of the IRSGs are real time missile frame rates and frame sizes, dynamic missile-to-target(s) viewpoint updated each frame in real-time by a six-degree-of- freedom (6DOF) system under test (SUT) simulation, multiple dynamic objects (e.g. targets, terrain/background, countermeasures, and atmospheric effects), latency compensation, point-to-extended source anti-aliased targets, and sensor modeling effects. This paper provides a comparison between the IRSG1 and IRSG2 systems and focuses on the IRSG software, real time features, and database development tools.

OSG-GEM: Gene Expression Matrix Construction Using the Open Science Grid.

PubMed

Poehlman, William L; Rynge, Mats; Branton, Chris; Balamurugan, D; Feltus, Frank A

2016-01-01

High-throughput DNA sequencing technology has revolutionized the study of gene expression while introducing significant computational challenges for biologists. These computational challenges include access to sufficient computer hardware and functional data processing workflows. Both these challenges are addressed with our scalable, open-source Pegasus workflow for processing high-throughput DNA sequence datasets into a gene expression matrix (GEM) using computational resources available to U.S.-based researchers on the Open Science Grid (OSG). We describe the usage of the workflow (OSG-GEM), discuss workflow design, inspect performance data, and assess accuracy in mapping paired-end sequencing reads to a reference genome. A target OSG-GEM user is proficient with the Linux command line and possesses basic bioinformatics experience. The user may run this workflow directly on the OSG or adapt it to novel computing environments.

OSG-GEM: Gene Expression Matrix Construction Using the Open Science Grid

PubMed Central

Poehlman, William L.; Rynge, Mats; Branton, Chris; Balamurugan, D.; Feltus, Frank A.

2016-01-01

High-throughput DNA sequencing technology has revolutionized the study of gene expression while introducing significant computational challenges for biologists. These computational challenges include access to sufficient computer hardware and functional data processing workflows. Both these challenges are addressed with our scalable, open-source Pegasus workflow for processing high-throughput DNA sequence datasets into a gene expression matrix (GEM) using computational resources available to U.S.-based researchers on the Open Science Grid (OSG). We describe the usage of the workflow (OSG-GEM), discuss workflow design, inspect performance data, and assess accuracy in mapping paired-end sequencing reads to a reference genome. A target OSG-GEM user is proficient with the Linux command line and possesses basic bioinformatics experience. The user may run this workflow directly on the OSG or adapt it to novel computing environments. PMID:27499617

A concept to standardize raw biosignal transmission for brain-computer interfaces.

PubMed

Breitwieser, Christian; Neuper, Christa; Müller-Putz, Gernot R

2011-01-01

With this concept we introduced the attempt of a standardized interface called TiA to transmit raw biosignals. TiA is able to deal with multirate and block-oriented data transmission. Data is distinguished by different signal types (e.g., EEG, EOG, NIRS, …), whereby those signals can be acquired at the same time from different acquisition devices. TiA is built as a client-server model. Multiple clients can connect to one server. Information is exchanged via a control- and a separated data connection. Control commands and meta information are transmitted over the control connection. Raw biosignal data is delivered using the data connection in a unidirectional way. For this purpose a standardized handshaking protocol and raw data packet have been developed. Thus, an abstraction layer between hardware devices and data processing was evolved facilitating standardization.

High-Speed Noninvasive Eye-Tracking System

NASA Technical Reports Server (NTRS)

Talukder, Ashit; LaBaw, Clayton; Michael-Morookian, John; Monacos, Steve; Serviss, Orin

2007-01-01

The figure schematically depicts a system of electronic hardware and software that noninvasively tracks the direction of a person s gaze in real time. Like prior commercial noninvasive eye-tracking systems, this system is based on (1) illumination of an eye by a low-power infrared light-emitting diode (LED); (2) acquisition of video images of the pupil, iris, and cornea in the reflected infrared light; (3) digitization of the images; and (4) processing the digital image data to determine the direction of gaze from the centroids of the pupil and cornea in the images. Relative to the prior commercial systems, the present system operates at much higher speed and thereby offers enhanced capability for applications that involve human-computer interactions, including typing and computer command and control by handicapped individuals,and eye-based diagnosis of physiological disorders that affect gaze responses.

Controlled impact demonstration on-board (interior) photographic system

NASA Technical Reports Server (NTRS)

May, C. J.

1986-01-01

Langley Research Center (LaRC) was responsible for the design, manufacture, and integration of all hardware required for the photographic system used to film the interior of the controlled impact demonstration (CID) B-720 aircraft during actual crash conditions. Four independent power supplies were constructed to operate the ten high-speed 16 mm cameras and twenty-four floodlights. An up-link command system, furnished by Ames Dryden Flight Research Facility (ADFRF), was necessary to activate the power supplies and start the cameras. These events were accomplished by initiation of relays located on each of the photo power pallets. The photographic system performed beyond expectations. All four power distribution pallets with their 20 year old Minuteman batteries performed flawlessly. All 24 lamps worked. All ten on-board high speed (400 fps) 16 mm cameras containing good resolution film data were recovered.

STS-81 launch view

NASA Image and Video Library

1998-06-15

STS081-S-005 (12 Jan. 1997) --- Lighting up an early morning sky, the Space Shuttle Atlantis lifts off from Pad 39B to begin the new year of space missions for NASA's shuttle fleet. Launch occurred at 4:27:23 a.m. (EST), Jan. 12, 1997. Now on their way for a docking mission with Russia's Mir Space Station are a crew of six astronauts and a SPACEHAB Double Module (DM), along with a large supply of food, water, hardware and other materials for Mir. Astronaut Jerry M. Linenger, now onboard Atlantis, will trade places with John E. Blaha, cosmonaut guest researcher, onboard Mir since mid September 1996. Along with Linenger, other crewmembers now aboard Atlantis are astronauts Michael A. Baker, commander; Brent W. Jett, Jr., pilot; and mission specialists John M. Grunsfeld, Marsha S. Ivins and Peter J. K. (Jeff) Wisoff.

Closed loop performance of a brushless dc motor powered electromechanical actuator for flight control applications. [computerized simulation for Shuttle Orbiter applications

NASA Technical Reports Server (NTRS)

Demerdash, N. A.; Nehl, T. W.

1980-01-01

A comprehensive digital model for the analysis and possible optimization of the closed loop dynamic (instantaneous) performance of a power conditioner fed, brushless dc motor powered, electromechanical actuator system (EMA) is presented. This model was developed for the simulation of the dynamic performance of an actual prototype EMA built for NASA-JSC as a possible alternative to hydraulic actuators for consideration in Space Shuttle Orbiter applications. Excellent correlation was achieved between numerical model simulation and experimental test results obtained from the actual hardware. These results include: various current and voltage waveforms in the machine-power conditioner (MPC) unit, flap position as well as other control loop variables in response to step commands of change of flap position. These results with consequent conclusions are detailed in the paper.

A motion sensing-based framework for robotic manipulation.

PubMed

Deng, Hao; Xia, Zeyang; Weng, Shaokui; Gan, Yangzhou; Fang, Peng; Xiong, Jing

2016-01-01

To data, outside of the controlled environments, robots normally perform manipulation tasks operating with human. This pattern requires the robot operators with high technical skills training for varied teach-pendant operating system. Motion sensing technology, which enables human-machine interaction in a novel and natural interface using gestures, has crucially inspired us to adopt this user-friendly and straightforward operation mode on robotic manipulation. Thus, in this paper, we presented a motion sensing-based framework for robotic manipulation, which recognizes gesture commands captured from motion sensing input device and drives the action of robots. For compatibility, a general hardware interface layer was also developed in the framework. Simulation and physical experiments have been conducted for preliminary validation. The results have shown that the proposed framework is an effective approach for general robotic manipulation with motion sensing control.

Gravity Probe B spacecraft description

NASA Astrophysics Data System (ADS)

Bennett, Norman R.; Burns, Kevin; Katz, Russell; Kirschenbaum, Jon; Mason, Gary; Shehata, Shawky

2015-11-01

The Gravity Probe B spacecraft, developed, integrated, and tested by Lockheed Missiles & Space Company and later Lockheed Martin Corporation, consisted of structures, mechanisms, command and data handling, attitude and translation control, electrical power, thermal control, flight software, and communications. When integrated with the payload elements, the integrated system became the space vehicle. Key requirements shaping the design of the spacecraft were: (1) the tight mission timeline (17 months, 9 days of on-orbit operation), (2) precise attitude and translational control, (3) thermal protection of science hardware, (4) minimizing aerodynamic, magnetic, and eddy current effects, and (5) the need to provide a robust, low risk spacecraft. The spacecraft met all mission requirements, as demonstrated by dewar lifetime meeting specification, positive power and thermal margins, precision attitude control and drag-free performance, reliable communications, and the collection of more than 97% of the available science data.

Veg-01 Plant Harvest

NASA Image and Video Library

2014-06-10

Commander Steve Swanson harvests plants for the VEG-01 investigation. He is harvesting them on the Maintenance Work Area (MWA) in the Node 2/Harmony. The Veg-01 hardware validation test investigation utilizes the Veggie facility on ISS. This investigation will assess on-orbit function and performance of the Veggie,and focus on the growth and development of Outredgeous Lettuce (Lactuca sativa ) seedlings in the spaceflight environment and the effects of the spaceflight environment on composition of microbial flora on the Veggie-grown plants and the Veggie facility. Lettuce plants are harvested on-orbit, frozen at <-80oC and returned to the ground for post-flight evaluation. Microbial sampling swabs will be taken of the Veggie facility and plant material, frozen and returned to the ground for environmental microbiological examination. Rooting pillows and water sample syringes will also be returned for microbial sampling and root analysis.

NASA Tech Briefs, August 2008

NASA Technical Reports Server (NTRS)

2008-01-01

Customizable Digital Receivers for Radar Two-Camera Acquisition and Tracking of a Flying Target Visual Data Analysis for Satellites A Data Type for Efficient Representation of Other Data Types Hand-Held Ultrasonic Instrument for Reading Matrix Symbols Broadband Microstrip-to-Coplanar Strip Double-Y Balun A Topographical Lidar System for Terrain-Relative Navigation Programmable Low-Voltage Circuit Breaker and Tester Electronic Switch Arrays for Managing Microbattery Arrays Topics covered include: Lower-Dark-Current, Higher-Blue-Response CMOS Imagers; Fabricating Large-Area Sheets of Single-Layer Graphene by CVD; Support for Diagnosis of Custom Computer Hardware; Providing Goal-Based Autonomy for Commanding a Spacecraft; Dynamic Method for Identifying Collected Sample Mass; Optimal Planning and Problem-Solving; Attitude-Control Algorithm for Minimizing Maneuver Execution Errors; Grants Document-Generation System; Heat-Storage Modules Containing LiNO3 3H2O and Graphite Foam; Precipitation-Strengthened, High-Temperature, High-Force Shape Memory Alloys; Improved Relief Valve Would Be Less Susceptible to Failure; Safety Modification of Cam-and-Groove Hose Coupling; Using Composite Materials in a Cryogenic Pump; Using Electronic Noses to Detect Tumors During Neurosurgery; Producing Newborn Synchronous Mammalian Cells; Smaller, Lower-Power Fast-Neutron Scintillation Detectors; Rotationally Vibrating Electric-Field Mill; Estimating Hardness from the USDC Tool-Bit Temperature Rise; Particle-Charge Spectrometer; Automated Production of Movies on a Cluster of Computers; FIDO-Class Development Rover; and Tone-Based Command of Deep Space Probes Using Ground Antennas.

Multimodal interaction for human-robot teams

NASA Astrophysics Data System (ADS)

Burke, Dustin; Schurr, Nathan; Ayers, Jeanine; Rousseau, Jeff; Fertitta, John; Carlin, Alan; Dumond, Danielle

2013-05-01

Unmanned ground vehicles have the potential for supporting small dismounted teams in mapping facilities, maintaining security in cleared buildings, and extending the team's reconnaissance and persistent surveillance capability. In order for such autonomous systems to integrate with the team, we must move beyond current interaction methods using heads-down teleoperation which require intensive human attention and affect the human operator's ability to maintain local situational awareness and ensure their own safety. This paper focuses on the design, development and demonstration of a multimodal interaction system that incorporates naturalistic human gestures, voice commands, and a tablet interface. By providing multiple, partially redundant interaction modes, our system degrades gracefully in complex environments and enables the human operator to robustly select the most suitable interaction method given the situational demands. For instance, the human can silently use arm and hand gestures for commanding a team of robots when it is important to maintain stealth. The tablet interface provides an overhead situational map allowing waypoint-based navigation for multiple ground robots in beyond-line-of-sight conditions. Using lightweight, wearable motion sensing hardware either worn comfortably beneath the operator's clothing or integrated within their uniform, our non-vision-based approach enables an accurate, continuous gesture recognition capability without line-of-sight constraints. To reduce the training necessary to operate the system, we designed the interactions around familiar arm and hand gestures.