Sample records for full space qualification

  1. 14 CFR Appendix C to Part 60 - Qualification Performance Standards for Helicopter Full Flight Simulators

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Qualification Performance Standards for Helicopter Full Flight Simulators C Appendix C to Part 60 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE Pt. 60, App....

  2. 14 CFR Appendix C to Part 60 - Qualification Performance Standards for Helicopter Full Flight Simulators

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Qualification Performance Standards for Helicopter Full Flight Simulators C Appendix C to Part 60 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE Pt. 60, App....

  3. 14 CFR Appendix C to Part 60 - Qualification Performance Standards for Helicopter Full Flight Simulators

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Qualification Performance Standards for Helicopter Full Flight Simulators C Appendix C to Part 60 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE Pt. 60, App....

  4. 14 CFR Appendix C to Part 60 - Qualification Performance Standards for Helicopter Full Flight Simulators

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Qualification Performance Standards for Helicopter Full Flight Simulators C Appendix C to Part 60 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE Pt. 60, App....

  5. 14 CFR Appendix C to Part 60 - Qualification Performance Standards for Helicopter Full Flight Simulators

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Qualification Performance Standards for Helicopter Full Flight Simulators C Appendix C to Part 60 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE Pt. 60, App....

  6. NASA's Space Launch System Booster Passes Major Milestone on Journey to Mars (QM-2)

    NASA Image and Video Library

    2016-06-28

    A booster for the most powerful rocket in the world, NASA’s Space Launch System (SLS), was fired up Tuesday, June 28 at 11:05 a.m. EDT for a second qualification ground test at Orbital ATK's test facilities in Promontory, Utah. This was the last full-scale test for the booster before SLS is ready in 2018 for the first uncrewed test flight with NASA’s Orion spacecraft, marking a key milestone on the agency’s Journey to Mars. The booster was tested at a cold motor conditioning target of 40 degrees Fahrenheit –the colder end of its accepted propellant temperature range. When ignited, temperatures inside the booster reached nearly 6,000 degrees. The two-minute, full-duration ground qualification test provided NASA with critical data on 82 qualification objectives that will support certification of the booster for flight. Engineers now will evaluate test data captured by more than 530 instrumentation channels on the booster.

  7. 46 CFR 57.05-3 - Limited space qualifications.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 46 Shipping 2 2012-10-01 2012-10-01 false Limited space qualifications. 57.05-3 Section 57.05-3... Performance Qualifications § 57.05-3 Limited space qualifications. When a welder is to be qualified for welding or torch brazing of piping on board ship in a limited or restricted space, the space restrictions...

  8. 46 CFR 57.05-3 - Limited space qualifications.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... 46 Shipping 2 2014-10-01 2014-10-01 false Limited space qualifications. 57.05-3 Section 57.05-3... Performance Qualifications § 57.05-3 Limited space qualifications. When a welder is to be qualified for welding or torch brazing of piping on board ship in a limited or restricted space, the space restrictions...

  9. 46 CFR 57.05-3 - Limited space qualifications.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 46 Shipping 2 2011-10-01 2011-10-01 false Limited space qualifications. 57.05-3 Section 57.05-3... Performance Qualifications § 57.05-3 Limited space qualifications. When a welder is to be qualified for welding or torch brazing of piping on board ship in a limited or restricted space, the space restrictions...

  10. 46 CFR 57.05-3 - Limited space qualifications.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 46 Shipping 2 2013-10-01 2013-10-01 false Limited space qualifications. 57.05-3 Section 57.05-3... Performance Qualifications § 57.05-3 Limited space qualifications. When a welder is to be qualified for welding or torch brazing of piping on board ship in a limited or restricted space, the space restrictions...

  11. The past as prologue - A look at historical flight qualifications for space nuclear systems

    NASA Technical Reports Server (NTRS)

    Bennett, Gary L.

    1992-01-01

    Currently the U.S. is sponsoring production of radioisotope thermoelectric generators (RTGs) for the Cassini mission to Saturn; the SP-100 space nuclear reactor power system for NASA applications; a thermionic space reactor program for DoD applications as well as early work on nuclear propulsion. In an era of heightened public concern about having successful space ventures it is important that a full understanding be developed of what it means to 'flight qualify' a space nuclear system. As a contribution to the ongoing work this paper reviews several qualification programs, including the general-purpose heat source radioisotope thermoelectric generators (GPHS-RTGs) as developed for the Galileo and Ulysses missions, the SNAP-10A space reactor, the Nuclear Engine for Rocket Vehicle Applications (NERVA), the F-1 chemical engine used on the Saturn-V, and the Space Shuttle Main Engines (SSMEs). Similarities and contrasts are noted.

  12. The past as prologue - A look at historical flight qualifications for space nuclear systems

    NASA Astrophysics Data System (ADS)

    Bennett, Gary L.

    Currently the U.S. is sponsoring production of radioisotope thermoelectric generators (RTGs) for the Cassini mission to Saturn; the SP-100 space nuclear reactor power system for NASA applications; a thermionic space reactor program for DoD applications as well as early work on nuclear propulsion. In an era of heightened public concern about having successful space ventures it is important that a full understanding be developed of what it means to 'flight qualify' a space nuclear system. As a contribution to the ongoing work this paper reviews several qualification programs, including the general-purpose heat source radioisotope thermoelectric generators (GPHS-RTGs) as developed for the Galileo and Ulysses missions, the SNAP-10A space reactor, the Nuclear Engine for Rocket Vehicle Applications (NERVA), the F-1 chemical engine used on the Saturn-V, and the Space Shuttle Main Engines (SSMEs). Similarities and contrasts are noted.

  13. 47 CFR 25.140 - Qualifications of Fixed-Satellite space station licensees.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... 47 Telecommunication 2 2013-10-01 2013-10-01 false Qualifications of Fixed-Satellite space station... CARRIER SERVICES SATELLITE COMMUNICATIONS Applications and Licenses Space Stations § 25.140 Qualifications of Fixed-Satellite space station licensees. (a) [Reserved] (b) Each applicant for a space station...

  14. A Shuttle Story: Latchup Qualification of a Truly Commercial Instrument

    NASA Technical Reports Server (NTRS)

    Swift, G.; Edmonds, L.; O'Conner, M.; Smith, L.; Tubbs, E.

    1998-01-01

    Destructive single event effects (DSEE) are a main concern for pioneers attempting to use COTS (commercial-off-the-shelf) devices in space, so a COTS instrument full of such devices is particulary scary.

  15. 47 CFR 25.140 - Qualifications of fixed-satellite space station licensees.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 47 Telecommunication 2 2011-10-01 2011-10-01 false Qualifications of fixed-satellite space station... CARRIER SERVICES SATELLITE COMMUNICATIONS Applications and Licenses Space Stations § 25.140 Qualifications of fixed-satellite space station licensees. (a) New fixed-satellites shall comply with the...

  16. 47 CFR 25.140 - Qualifications of fixed-satellite space station licensees.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 47 Telecommunication 2 2010-10-01 2010-10-01 false Qualifications of fixed-satellite space station... CARRIER SERVICES SATELLITE COMMUNICATIONS Applications and Licenses Space Stations § 25.140 Qualifications of fixed-satellite space station licensees. (a) New fixed-satellites shall comply with the...

  17. 47 CFR 25.140 - Qualifications of fixed-satellite space station licensees.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... 47 Telecommunication 2 2012-10-01 2012-10-01 false Qualifications of fixed-satellite space station... CARRIER SERVICES SATELLITE COMMUNICATIONS Applications and Licenses Space Stations § 25.140 Qualifications of fixed-satellite space station licensees. (a) New fixed-satellites shall comply with the...

  18. 14 CFR 60.27 - Automatic loss of qualification and procedures for restoration of qualification.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Automatic loss of qualification and procedures for restoration of qualification. 60.27 Section 60.27 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  19. 14 CFR 60.29 - Other losses of qualification and procedures for restoration of qualification.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Other losses of qualification and procedures for restoration of qualification. 60.29 Section 60.29 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  20. 14 CFR 60.27 - Automatic loss of qualification and procedures for restoration of qualification.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Automatic loss of qualification and procedures for restoration of qualification. 60.27 Section 60.27 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  1. 14 CFR 60.29 - Other losses of qualification and procedures for restoration of qualification.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Other losses of qualification and procedures for restoration of qualification. 60.29 Section 60.29 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  2. 14 CFR 60.29 - Other losses of qualification and procedures for restoration of qualification.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Other losses of qualification and procedures for restoration of qualification. 60.29 Section 60.29 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  3. 14 CFR 60.29 - Other losses of qualification and procedures for restoration of qualification.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Other losses of qualification and procedures for restoration of qualification. 60.29 Section 60.29 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  4. 14 CFR 60.27 - Automatic loss of qualification and procedures for restoration of qualification.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Automatic loss of qualification and procedures for restoration of qualification. 60.27 Section 60.27 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  5. 14 CFR 60.29 - Other losses of qualification and procedures for restoration of qualification.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Other losses of qualification and procedures for restoration of qualification. 60.29 Section 60.29 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  6. 14 CFR 60.27 - Automatic loss of qualification and procedures for restoration of qualification.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Automatic loss of qualification and procedures for restoration of qualification. 60.27 Section 60.27 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  7. 14 CFR 60.27 - Automatic loss of qualification and procedures for restoration of qualification.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Automatic loss of qualification and procedures for restoration of qualification. 60.27 Section 60.27 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  8. Open-Source RTOS Space Qualification: An RTEMS Case Study

    NASA Technical Reports Server (NTRS)

    Zemerick, Scott

    2017-01-01

    NASA space-qualification of reusable off-the-shelf real-time operating systems (RTOSs) remains elusive due to several factors notably (1) The diverse nature of RTOSs utilized across NASA, (2) No single NASA space-qualification criteria, lack of verification and validation (V&V) analysis, or test beds, and (3) different RTOS heritages, specifically open-source RTOSs and closed vendor-provided RTOSs. As a leader in simulation test beds, the NASA IV&V Program is poised to help jump-start and lead the space-qualification effort of the open source Real-Time Executive for Multiprocessor Systems (RTEMS) RTOS. RTEMS, as a case-study, can be utilized as an example of how to qualify all RTOSs, particularly the reusable non-commercial (open-source) ones that are gaining usage and popularity across NASA. Qualification will improve the overall safety and mission assurance of RTOSs for NASA-agency wide usage. NASA's involvement in space-qualification of an open-source RTOS such as RTEMS will drive the RTOS industry toward a more qualified and mature open-source RTOS product.

  9. A Motor Drive Electronics Assembly for Mars Curiosity Rover: An Example of Assembly Qualification for Extreme Environments

    NASA Technical Reports Server (NTRS)

    Kolawa, Elizabeth; Chen, Yuan; Mojarradi, Mohammad M.; Weber, Carissa Tudryn; Hunter, Don J.

    2013-01-01

    This paper describes the technology development and infusion of a motor drive electronics assembly for Mars Curiosity Rover under space extreme environments. The technology evaluation and qualification as well as space qualification of the assembly are detailed and summarized. Because of the uncertainty of the technologies operating under the extreme space environments and that a high level reliability was required for this assembly application, both component and assembly board level qualifications were performed.

  10. Space Qualification Issues in Acousto-optic and Electro-optic Devices

    NASA Technical Reports Server (NTRS)

    Prasad, Narasimha S.; Taylor, Edward W.; Trivedi, Sudhir; Kutcher, Sue; Soos, Jolanta

    2007-01-01

    Satellite and space-based applications of photonic devices and systems require operational reliability in the harsh environment of space for extended periods of time. This in turn requires every component of the systems and their packaging to meet space qualifications. Acousto- and electro-optical devices form the major components of many current space based optical systems, which is the focus of this paper. The major space qualification issues are related to: mechanical stability, thermal effects and operation of the devices in the naturally occurring space radiation environment. This paper will discuss acousto- and electro-optic materials and devices with respect to their stability against mechanical vibrations, thermal cycling in operating and non-operating conditions and device responses to space ionizing and displacement radiation effects. Selection of suitable materials and packaging to meet space qualification criteria will also be discussed. Finally, a general roadmap for production and testing of acousto- and electro-optic devices will be discussed.

  11. NASA Electronic Parts and Packaging (NEPP): Space Qualification Guidelines of Optoelectronic and Photonic Devices for Optical Communication Systems

    NASA Technical Reports Server (NTRS)

    Kim, Quiesup

    2001-01-01

    Key elements of space qualification of opto-electric and photonic optical devices were overviewed. Efforts were concentrated on the reliability concerns of the devices needed for potential applications in space environments. The ultimate goal for this effort is to gradually establish enough data to develop a space qualification plan of newly developed specific photonic parts using empirical and numerical models to assess the life-time and degradation of the devices for potential long term space missions.

  12. 14 CFR 60.15 - Initial qualification requirements.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Initial qualification requirements. 60.15 Section 60.15 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.15...

  13. 14 CFR 60.15 - Initial qualification requirements.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Initial qualification requirements. 60.15 Section 60.15 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.15...

  14. 14 CFR 60.7 - Sponsor qualification requirements.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Sponsor qualification requirements. 60.7 Section 60.7 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.7...

  15. 14 CFR 60.7 - Sponsor qualification requirements.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Sponsor qualification requirements. 60.7 Section 60.7 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.7...

  16. 14 CFR 60.7 - Sponsor qualification requirements.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Sponsor qualification requirements. 60.7 Section 60.7 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.7...

  17. 14 CFR 60.15 - Initial qualification requirements.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Initial qualification requirements. 60.15 Section 60.15 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.15...

  18. 14 CFR 60.7 - Sponsor qualification requirements.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Sponsor qualification requirements. 60.7 Section 60.7 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.7...

  19. 14 CFR 60.15 - Initial qualification requirements.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Initial qualification requirements. 60.15 Section 60.15 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.15...

  20. 14 CFR 60.4 - Qualification Performance Standards.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Qualification Performance Standards. 60.4 Section 60.4 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.4...

  1. 14 CFR 60.4 - Qualification Performance Standards.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Qualification Performance Standards. 60.4 Section 60.4 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.4...

  2. 14 CFR 60.15 - Initial qualification requirements.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Initial qualification requirements. 60.15 Section 60.15 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.15...

  3. 14 CFR 60.4 - Qualification Performance Standards.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Qualification Performance Standards. 60.4 Section 60.4 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.4...

  4. 14 CFR 60.4 - Qualification Performance Standards.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Qualification Performance Standards. 60.4 Section 60.4 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.4...

  5. 14 CFR 60.4 - Qualification Performance Standards.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Qualification Performance Standards. 60.4 Section 60.4 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.4...

  6. 14 CFR 121.439 - Pilot qualification: Recent experience.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Pilot qualification: Recent experience. 121.439 Section 121.439 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... Pilot qualification: Recent experience. (a) No certificate holder may use any person nor may any person...

  7. 14 CFR 121.439 - Pilot qualification: Recent experience.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Pilot qualification: Recent experience. 121.439 Section 121.439 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... Pilot qualification: Recent experience. (a) No certificate holder may use any person nor may any person...

  8. 14 CFR 125.285 - Pilot qualifications: Recent experience.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Pilot qualifications: Recent experience. 125.285 Section 125.285 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... Requirements § 125.285 Pilot qualifications: Recent experience. (a) No certificate holder may use any person...

  9. 14 CFR 125.285 - Pilot qualifications: Recent experience.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Pilot qualifications: Recent experience. 125.285 Section 125.285 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... Requirements § 125.285 Pilot qualifications: Recent experience. (a) No certificate holder may use any person...

  10. 14 CFR 125.285 - Pilot qualifications: Recent experience.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Pilot qualifications: Recent experience. 125.285 Section 125.285 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... Requirements § 125.285 Pilot qualifications: Recent experience. (a) No certificate holder may use any person...

  11. Qualification and Lessons Learned with Space Flight Fiber Optic Components

    NASA Technical Reports Server (NTRS)

    Ott, Melanie

    2007-01-01

    This presentation covers lessons learned during the design, development, manufacturing and qualification of space flight fiber optic components. Changes at NASA, including short-term projects and decreased budgets have brought about changes to vendors and parts. Most photonics for NASA needs are now commercial off the shelf (COTS) products. The COTS Tecnology Assurance approach for space flight and qualification plans are outlined.

  12. 14 CFR 91.1089 - Qualifications: Check pilots (aircraft) and check pilots (simulator).

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Qualifications: Check pilots (aircraft) and check pilots (simulator). 91.1089 Section 91.1089 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... RULES Fractional Ownership Operations Program Management § 91.1089 Qualifications: Check pilots...

  13. 14 CFR 91.1089 - Qualifications: Check pilots (aircraft) and check pilots (simulator).

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Qualifications: Check pilots (aircraft) and check pilots (simulator). 91.1089 Section 91.1089 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... RULES Fractional Ownership Operations Program Management § 91.1089 Qualifications: Check pilots...

  14. 14 CFR 60.16 - Additional qualifications for a currently qualified FSTD.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Additional qualifications for a currently qualified FSTD. 60.16 Section 60.16 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE...

  15. 14 CFR 60.16 - Additional qualifications for a currently qualified FSTD.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Additional qualifications for a currently qualified FSTD. 60.16 Section 60.16 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE...

  16. 14 CFR 60.16 - Additional qualifications for a currently qualified FSTD.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Additional qualifications for a currently qualified FSTD. 60.16 Section 60.16 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE...

  17. 14 CFR 60.16 - Additional qualifications for a currently qualified FSTD.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Additional qualifications for a currently qualified FSTD. 60.16 Section 60.16 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE...

  18. Space qualified hybrid superconductor/semiconductor planar oscillator circuit

    NASA Technical Reports Server (NTRS)

    Miranda, F. A.; Chorey, C. M.; Romanofsky, R. R.; Bhasin, K. B.

    1995-01-01

    We report on the space qualification of a hybrid superconductor/semiconductor planar local oscillator (LO) at 8.4 GHz. This oscillator was designed, fabricated, and tested as a component for the High Temperature Superconductivity Space Experiment 2 (HTSSE-2). The LO consisted of a GaAs MESFET and microstrip circuitry patterned onto a YBa2Cu3O(7-delta) high temperature superconducting (HTS) thin film on a 1.0 x 1.0 sq cm lanthanum aluminate (LaAlO3) substrate. At 77 K, this oscillator achieved power output levels up to 10 dBm into a 50 Ohm load. When incorporated into a full cryogenic receiver, the LO provided output powers within 0.0-3.0 dBm with less than 50 mW of dc power dissipation. Space qualification data on the sensitivity of the HTS films to the processing steps involved in the fabrication of HTS-based components are presented. Data on ohmic contacts, strength of wire bonds made to such contacts, and aging effects as well as vibration test results are discussed.

  19. Basic space payload fastener

    NASA Technical Reports Server (NTRS)

    Vranish, J. M.; Gorevan, Stephen

    1995-01-01

    A new basic space fastener has been developed and tested by the GSFC. The purposes of this fastener are to permit assembly and servicing in space by astronauts and/or robots and to facilitate qualification of payloads on Earth prior to launch by saving time and money during the systems integration and component testing and qualification processes. The space fastener is a rework of the basic machine screw such that crossthreading is impossible; it is self-locking and will not work its way out during launch (vibration proof); it will not wear out despite repeated use; it occupies a small foot print which is comparable to its machine screw equivalent, and it provides force and exhibits strength comparable to its machine screw equivalent. Construction is ultra-simple and cost effective and the principle is applicable across the full range of screw sizes ranging from a #10 screw to 2.5 cm (1 in) or more. In this paper, the fastener principles of operation will be discussed along with test results and construction details. The new fastener also has considerable potential in the commercial sector. A few promising applications will be presented.

  20. 14 CFR 119.67 - Management personnel: Qualifications for operations conducted under part 121 of this chapter.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... or Part 135 of This Chapter § 119.67 Management personnel: Qualifications for operations conducted... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Management personnel: Qualifications for operations conducted under part 121 of this chapter. 119.67 Section 119.67 Aeronautics and Space FEDERAL...

  1. 14 CFR 119.71 - Management personnel: Qualifications for operations conducted under part 135 of this chapter.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... or Part 135 of This Chapter § 119.71 Management personnel: Qualifications for operations conducted... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Management personnel: Qualifications for operations conducted under part 135 of this chapter. 119.71 Section 119.71 Aeronautics and Space FEDERAL...

  2. 14 CFR Appendix D to Part 60 - Qualification Performance Standards for Helicopter Flight Training Devices

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Qualification Performance Standards for Helicopter Flight Training Devices D Appendix D to Part 60 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE Pt. 60, App...

  3. 14 CFR Appendix D to Part 60 - Qualification Performance Standards for Helicopter Flight Training Devices

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Qualification Performance Standards for Helicopter Flight Training Devices D Appendix D to Part 60 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE Pt. 60, App...

  4. 14 CFR Appendix D to Part 60 - Qualification Performance Standards for Helicopter Flight Training Devices

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Qualification Performance Standards for Helicopter Flight Training Devices D Appendix D to Part 60 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE Pt. 60, App...

  5. 14 CFR Appendix D to Part 60 - Qualification Performance Standards for Helicopter Flight Training Devices

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Qualification Performance Standards for Helicopter Flight Training Devices D Appendix D to Part 60 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE Pt. 60, App...

  6. 14 CFR Appendix D to Part 60 - Qualification Performance Standards for Helicopter Flight Training Devices

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Qualification Performance Standards for Helicopter Flight Training Devices D Appendix D to Part 60 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE Pt. 60, App...

  7. 14 CFR 121.915 - Continuing qualification curriculum.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Continuing qualification curriculum. 121... Continuing qualification curriculum. Each continuing qualification curriculum must contain training and... training device as approved in the certificate holder's curriculum that must be completed during each...

  8. Qualification Strategies of Field Programmable Gate Arrays (FPGAs) for Space Application

    NASA Technical Reports Server (NTRS)

    Sheldon, Douglas; Schone, Harald

    2005-01-01

    This viewgraph document reviews the issue of using Field Programmable Gate Arrays (FPGAs) in Space Application, and the some of the strategies for qualifying the FPGA. Qualification and risk management of such complex systems requires new approaches. The paper presents a matrix approach to qualification has been presented that: - Complements historical specifications - Highlights the importance of device physics as a cornerstone to qualification. - Provides levels of risk management that expressly document trade offs. - Stresses the role of the FPGA vendor as team member in the development of modern spacecraft.

  9. Impact of the Europeanisation of Education: Qualifications Frameworks in Europe

    ERIC Educational Resources Information Center

    Mikulec, Borut

    2017-01-01

    This article examines the influence of the European qualifications framework--a key European lifelong learning policy instrument for improving employability, comparability and mobility in the European educational space--on the establishment of national qualifications frameworks in Europe. The European qualifications framework and national…

  10. A Motor Drive Electronics Assembly for Mars Curiosity Rover: An Example of Assembly Qualification for Extreme Environments

    NASA Technical Reports Server (NTRS)

    Kolawa, Elizabeth; Chen, Yuan; Mojarradi, Mohammad M.; Tudryn Weber, Carissa

    2013-01-01

    In this paper, the technology development and infusion of the motor drive electronics assembly, along with the technology qualification and space qualification, is described and detailed. The process is an example of the qualification methodology for extreme environmen

  11. 14 CFR 121.439 - Pilot qualification: Recent experience.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Pilot qualification: Recent experience. 121... Pilot qualification: Recent experience. Link to an amendment published at 78 FR 67841, Nov. 12, 2013. (a... qualification: Recent experience. (f) Deviation authority based upon designation of related aircraft in...

  12. 14 CFR 417.311 - Flight safety crew roles and qualifications.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Flight safety crew roles and qualifications. 417.311 Section 417.311 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... the knowledge, skills, and abilities needed to operate the flight safety system hardware in accordance...

  13. 14 CFR 417.311 - Flight safety crew roles and qualifications.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Flight safety crew roles and qualifications. 417.311 Section 417.311 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... the knowledge, skills, and abilities needed to operate the flight safety system hardware in accordance...

  14. 14 CFR 121.453 - Flight engineer qualifications.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Flight engineer qualifications. 121.453... REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Crewmember Qualifications § 121.453 Flight engineer qualifications. (a) No certificate holder may use any person nor may any person serve as a flight engineer on an...

  15. 14 CFR 121.453 - Flight engineer qualifications.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Flight engineer qualifications. 121.453... REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Crewmember Qualifications § 121.453 Flight engineer qualifications. (a) No certificate holder may use any person nor may any person serve as a flight engineer on an...

  16. 14 CFR 121.453 - Flight engineer qualifications.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Flight engineer qualifications. 121.453... REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Crewmember Qualifications § 121.453 Flight engineer qualifications. (a) No certificate holder may use any person nor may any person serve as a flight engineer on an...

  17. 14 CFR 121.453 - Flight engineer qualifications.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Flight engineer qualifications. 121.453... REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Crewmember Qualifications § 121.453 Flight engineer qualifications. (a) No certificate holder may use any person nor may any person serve as a flight engineer on an...

  18. 14 CFR 121.453 - Flight engineer qualifications.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Flight engineer qualifications. 121.453... REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Crewmember Qualifications § 121.453 Flight engineer qualifications. (a) No certificate holder may use any person nor may any person serve as a flight engineer on an...

  19. Performance Assessment of Refractory Concrete Used on the Space Shuttle's Launch Pad

    NASA Technical Reports Server (NTRS)

    Trejo, David; Calle, Luz Marina; Halman, Ceki

    2005-01-01

    The John F. Kennedy Space Center (KSC) maintains several facilities for launching space vehicles. During recent launches it has been observed that the refractory concrete materials that protect the steel-framed flame duct are breaking away from this base structure and are being projected at high velocities. There is significant concern that these projected pieces can strike the launch complex or space vehicle during the launch, jeopardizing the safety of the mission. A qualification program is in place to evaluate the performance of different refractory concretes and data from these tests have been used to assess the performance of the refractory concretes. However, there is significant variation in the test results, possibly making the existing qualification test program unreliable. This paper will evaluate data from past qualification tests, identify potential key performance indicators for the launch complex, and will recommend a new qualification test program that can be used to better qualify refractory concrete.

  20. DFL, Canada's Space AIT Facilities - Current and Planned Capabilities

    NASA Astrophysics Data System (ADS)

    Singhal, R.; Mishra, S.; Choueiry, E.; Dumoulin, J.; Ahmed, S.

    2004-08-01

    The David Florida Laboratory (DFL) of the Canadian Space Agency is the Canadian national ISO 9001:2000 registered facility for the assembly, integration, and (environmental) testing of space hardware. This paper briefly describes the three main qualification facilities: Structural Qualification Facilities (SQF); Radio Frequency Qualification Facilities (RFQF); and Thermal Qualification Facilities (TQF). The paper also describes the planned/new upgrades/improvements to the DFL's existing capabilities. These include: cylindrical near-field antenna measurement system, current capabilities in multi-frequency multi-band passive intermodulation (PIM) measurement; combined thermal/vibration test facility, improvement in efficiency and performance of the photogrammetry capability, acquisition of an additional mass properties measurement system for small and micro-satellites; combined control and data acquisition system for all existing thermal vacuum facilities, plus a new automatic thermal control system and hypobaric chamber.

  1. 14 CFR 121.445 - Pilot in command airport qualification: Special areas and airports.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Pilot in command airport qualification... Qualifications § 121.445 Pilot in command airport qualification: Special areas and airports. (a) The... any person serve, as pilot in command to or from an airport determined to require special airport...

  2. 14 CFR 121.445 - Pilot in command airport qualification: Special areas and airports.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Pilot in command airport qualification... Qualifications § 121.445 Pilot in command airport qualification: Special areas and airports. (a) The... any person serve, as pilot in command to or from an airport determined to require special airport...

  3. 14 CFR 121.445 - Pilot in command airport qualification: Special areas and airports.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Pilot in command airport qualification... Qualifications § 121.445 Pilot in command airport qualification: Special areas and airports. (a) The... any person serve, as pilot in command to or from an airport determined to require special airport...

  4. 14 CFR 121.445 - Pilot in command airport qualification: Special areas and airports.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Pilot in command airport qualification... Qualifications § 121.445 Pilot in command airport qualification: Special areas and airports. (a) The... any person serve, as pilot in command to or from an airport determined to require special airport...

  5. 14 CFR 121.445 - Pilot in command airport qualification: Special areas and airports.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Pilot in command airport qualification... Qualifications § 121.445 Pilot in command airport qualification: Special areas and airports. (a) The... any person serve, as pilot in command to or from an airport determined to require special airport...

  6. 14 CFR 121.913 - Qualification curriculum.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Qualification curriculum. 121.913 Section 121.913 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED... list of and text describing the knowledge requirements, subject materials, job skills, and...

  7. 14 CFR 121.913 - Qualification curriculum.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Qualification curriculum. 121.913 Section 121.913 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED... list of and text describing the knowledge requirements, subject materials, job skills, and...

  8. Historical flight qualifications of space nuclear systems

    NASA Astrophysics Data System (ADS)

    Bennett, Gary L.

    1997-01-01

    An overview is presented of the qualification programs for the general-purpose heat source radioisotope thermoelectric generators (GPHS-RTGs) as developed for the Galileo and Ulysses missions; the SNAP-10A space reactor; the Nuclear Engine for Rocket Vehicle Applications (NERVA); the F-1 chemical rocket engine used on the Saturn-V Apollo lunar missions; and the Space Shuttle Main Engines (SSMEs). Some similarities and contrasts between the qualification testing employed on these five programs will be noted. One common thread was that in each of these successful programs there was an early focus on component and subsystem tests to uncover and correct problems.

  9. Space Shuttle Solid Rocket Motor (SRM) development and qualification

    NASA Technical Reports Server (NTRS)

    Lund, R. K.; Brinton, B. C.

    1980-01-01

    The configuration of reusable solid propellant motors for the space shuttle vehicle is delineated and traces their design evolution. Also presented are the summary results of the first two of the three qualification motor firings designated QM-1 and QM-2.

  10. Brief, Why the Launch Equipment Test Facility Needs a Laser Tracker

    NASA Technical Reports Server (NTRS)

    Yue, Shiu H.

    2011-01-01

    The NASA Kennedy Space Center Launch Equipment Test Facility (LETF) supports a wide spectrum of testing and development activities. This capability was originally established in the 1970's to allow full-scale qualification of Space Shuttle umbilicals and T-O release mechanisms. The LETF has leveraged these unique test capabilities to evolve into a versatile test and development area that supports the entire spectrum of operational programs at KSC. These capabilities are historically Aerospace related, but can certainly can be adapted for other industries. One of the more unique test fixtures is the Vehicle Motion Simulator or the VMS. The VMS simulates all of the motions that a launch vehicle will experience from the time of its roll-out to the launch pad, through roughly the first X second of launch. The VMS enables the development and qualification testing of umbilical systems in both pre-launch and launch environments. The VMS can be used to verify operations procedures, clearances, disconnect systems performance &margins, and vehicle loads through processing flow motion excursions.

  11. 14 CFR 60.19 - Inspection, continuing qualification evaluation, and maintenance requirements.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Inspection, continuing qualification evaluation, and maintenance requirements. 60.19 Section 60.19 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  12. 14 CFR 60.19 - Inspection, continuing qualification evaluation, and maintenance requirements.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Inspection, continuing qualification evaluation, and maintenance requirements. 60.19 Section 60.19 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  13. 14 CFR 60.19 - Inspection, continuing qualification evaluation, and maintenance requirements.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Inspection, continuing qualification evaluation, and maintenance requirements. 60.19 Section 60.19 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  14. 14 CFR 60.19 - Inspection, continuing qualification evaluation, and maintenance requirements.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Inspection, continuing qualification evaluation, and maintenance requirements. 60.19 Section 60.19 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  15. 14 CFR 60.19 - Inspection, continuing qualification evaluation, and maintenance requirements.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Inspection, continuing qualification evaluation, and maintenance requirements. 60.19 Section 60.19 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  16. Photovoltaic Engineering Testbed Designed for Calibrating Photovoltaic Devices in Space

    NASA Technical Reports Server (NTRS)

    Landis, Geoffrey A.

    2002-01-01

    Accurate prediction of the performance of solar arrays in space requires that the cells be tested in comparison with a space-flown standard. Recognizing that improvements in future solar cell technology will require an ever-increasing fidelity of standards, the Photovoltaics and Space Environment Branch at the NASA Glenn Research Center, in collaboration with the Ohio Aerospace Institute, designed a prototype facility to allow routine calibration, measurement, and qualification of solar cells on the International Space Station, and then the return of the cells to Earth for laboratory use. For solar cell testing, the Photovoltaic Engineering Testbed (PET) site provides a true air-mass-zero (AM0) solar spectrum. This allows solar cells to be accurately calibrated using the full spectrum of the Sun.

  17. Qualification of silicon pore optics

    NASA Astrophysics Data System (ADS)

    Wille, Eric; Bavdaz, Marcos; Fransen, Sebastiaan; Collon, Maximilien; Ackermann, Marcelo; Guenther, Ramses; Chatbi, Abdelhakim; Vacanti, Giuseppe; Vervest, Mark; van Baren, Coen; Haneveld, Jeroen; Riekerink, Mark Olde; Koelewijn, Arenda; Kampf, Dirk; Zuknik, Karl-Heinz; Reutlinger, Arnd

    2014-07-01

    Silicon Pore Optics (SPO) are the enabling technology for ESA's second large class mission in the Cosmic Vision programme. As for every space hardware, a critical qualification process is required to verify the suitability of the SPO mirror modules surviving the launch loads and maintaining their performance in the space environment. We present recent design modifications to further strengthen the mounting system (brackets and dowel pins) against mechanical loads. The progress of a formal qualification test campaign with the new mirror module design is shown. We discuss mechanical and thermal limitations of the SPO technology and provide recommendations for the mission design of the next X-ray Space Observatory.

  18. The Development of a GaAs MMIC Reliability and Space Qualification Guide

    NASA Technical Reports Server (NTRS)

    Ponchak, G.; Kayali, S.; Huang, H-C.

    1994-01-01

    This paper discusses the need for a space qualification guide, provides a brief description of some common GaAs failure mechanisms, the approach that the NASA MMIC Reliability Assurance Program is following to develop the guide, and the status of the program.

  19. Space qualification of silicon carbide for mirror applications: progress and future objectives

    NASA Astrophysics Data System (ADS)

    Palusinski, Iwona A.; Ghozeil, Isaac

    2006-09-01

    Production of optical silicon carbide (SiC) for mirror applications continues to evolve and there are renewed plans to use this material in future space-based systems. While SiC has the potential for rapid and cost-effective manufacturing of large, lightweight, athermal optical systems, this material's use in mirror applications is relatively new and has limited flight heritage. This combination of drivers stresses the necessity for a space qualification program for this material. Successful space qualification will require independent collaboration to absorb the high cost of executing this program while taking advantage of each contributing group's laboratory expertise to develop a comprehensive SiC database. This paper provides an overview of the trends and progress in the production of SiC, and identifies future objectives such as non-destructive evaluation and space-effects modeling to ensure proper implementation of this material into future space-based systems.

  20. Space Station Freedom as an engineering experiment station: An overview

    NASA Technical Reports Server (NTRS)

    Rose, M. Frank

    1992-01-01

    In this presentation, the premise that Space Station Freedom has great utility as an engineering experiment station will be explored. There are several modes in which it can be used for this purpose. The most obvious are space qualification, process development, in space satellite repair, and materials engineering. The range of engineering experiments which can be done at Space Station Freedom run the gamut from small process oriented experiments to full exploratory development models. A sampling of typical engineering experiments are discussed in this session. First and foremost, Space Station Freedom is an elaborate experiment itself, which, if properly instrumented, will provide engineering guidelines for even larger structures which must surely be built if humankind is truly 'outward bound.' Secondly, there is the test, evaluation and space qualification of advanced electric thruster concepts, advanced power technology and protective coatings which must of necessity be tested in the vacuum of space. The current approach to testing these technologies is to do exhaustive laboratory simulation followed by shuttle or unmanned flights. Third, the advanced development models of life support systems intended for future space stations, manned mars missions, and lunar colonies can be tested for operation in a low gravity environment. Fourth, it will be necessary to develop new protective coatings, establish construction techniques, evaluate new materials to be used in the upgrading and repair of Space Station Freedom. Finally, the industrial sector, if it is ever to build facilities for the production of commercial products, must have all the engineering aspects of the process evaluated in space prior to a commitment to such a facility.

  1. 14 CFR 60.14 - Special equipment and personnel requirements for qualification of the FSTD.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Special equipment and personnel requirements for qualification of the FSTD. 60.14 Section 60.14 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  2. 14 CFR 60.14 - Special equipment and personnel requirements for qualification of the FSTD.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Special equipment and personnel requirements for qualification of the FSTD. 60.14 Section 60.14 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  3. 14 CFR 60.14 - Special equipment and personnel requirements for qualification of the FSTD.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Special equipment and personnel requirements for qualification of the FSTD. 60.14 Section 60.14 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  4. 14 CFR 60.14 - Special equipment and personnel requirements for qualification of the FSTD.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Special equipment and personnel requirements for qualification of the FSTD. 60.14 Section 60.14 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  5. 14 CFR 60.14 - Special equipment and personnel requirements for qualification of the FSTD.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Special equipment and personnel requirements for qualification of the FSTD. 60.14 Section 60.14 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  6. AlGaN UV LED and Photodiodes Radiation Hardness and Space Qualifications and Their Applications in Space Science and High Energy Density Physics

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

    Sun, K. X.

    2011-05-31

    This presentation provides an overview of robust, radiation hard AlGaN optoelectronic devices and their applications in space exploration & high energy density physics. Particularly, deep UV LED and deep UV photodiodes are discussed with regard to their applications, radiation hardness and space qualification. AC charge management of UV LED satellite payload instruments, which were to be launched in late 2012, is covered.

  7. 14 CFR 135.247 - Pilot qualifications: Recent experience.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Pilot qualifications: Recent experience... Flight Crewmember Requirements § 135.247 Pilot qualifications: Recent experience. (a) No certificate holder may use any person, nor may any person serve, as pilot in command of an aircraft carrying...

  8. 14 CFR 135.247 - Pilot qualifications: Recent experience.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Pilot qualifications: Recent experience... Flight Crewmember Requirements § 135.247 Pilot qualifications: Recent experience. (a) No certificate holder may use any person, nor may any person serve, as pilot in command of an aircraft carrying...

  9. Southern Impact Testing Alliance (SITA)

    NASA Technical Reports Server (NTRS)

    Hubbs, Whitney; Roebuck, Brian; Zwiener, Mark; Wells, Brian

    2009-01-01

    Efforts to form this Alliance began in 2008 to showcase the impact testing capabilities within the southern United States. Impact testing customers can utilize SITA partner capabilities to provide supporting data during all program phases-materials/component/ flight hardware design, development, and qualification. This approach would allow programs to reduce risk by providing low cost testing during early development to flush out possible problems before moving on to larger scale1 higher cost testing. Various SITA partners would participate in impact testing depending on program phase-materials characterization, component/subsystem characterization, full-scale system testing for qualification. SITA partners would collaborate with the customer to develop an integrated test approach during early program phases. Modeling and analysis validation can start with small-scale testing to ensure a level of confidence for the next step large or full-scale conclusive test shots. Impact Testing Facility (ITF) was established and began its research in spacecraft debris shielding in the early 1960's and played a malor role in the International Space Station debris shield development. As a result of return to flight testing after the loss of STS-107 (Columbia) MSFC ITF realized the need to expand their capabilities beyond meteoroid and space debris impact testing. MSFC partnered with the Department of Defense and academic institutions as collaborative efforts to gain and share knowledge that would benefit the Space Agency as well as the DoD. MSFC ITF current capabilities include: Hypervelocity impact testing, ballistic impact testing, and environmental impact testing.

  10. Historical flight qualifications of space nuclear systems

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

    Bennett, G.L.

    1997-01-01

    An overview is presented of the qualification programs for the general-purpose heat source radioisotope thermoelectric generators (GPHS-RTGs) as developed for the Galileo and Ulysses missions; the SNAP-10A space reactor; the Nuclear Engine for Rocket Vehicle Applications (NERVA); the F-1 chemical rocket engine used on the Saturn-V Apollo lunar missions; and the Space Shuttle Main Engines (SSMEs). Some similarities and contrasts between the qualification testing employed on these five programs will be noted. One common thread was that in each of these successful programs there was an early focus on component and subsystem tests to uncover and correct problems. {copyright} {italmore » 1997 American Institute of Physics.}« less

  11. Design, Qualification, and On Orbit Performance of the CALIPSO Aerosol Lidar Transmitter

    NASA Technical Reports Server (NTRS)

    Hovis, Floyd E.; Witt, Greg; Sullivan, Edward T.; Le, Khoa; Weimer, Carl; Applegate, Jeff; Luck, William S., Jr.; Verhapen, Ron; Cisewski, Michael S.

    2007-01-01

    The laser transmitter for the CALIPSO aerosol lidar mission has been operating on orbit as planned since June 2006. This document discusses the optical and laser system design and qualification process that led to this success. Space-qualifiable laser design guidelines included the use of mature laser technologies, the use of alignment sensitive resonator designs, the development and practice of stringent contamination control procedures, the operation of all optical components at appropriately derated levels, and the proper budgeting for the space-qualification of the electronics and software.

  12. Space Shuttle solid rocket motor /SRM/ development and qualification

    NASA Technical Reports Server (NTRS)

    Lund, R. K.; Brinton, B. C.

    1980-01-01

    The configuration of the reusable Space Shuttle solid rocket motors is described. In addition, their design evolution is reviewed, noting that the requirement that certain components be recovered, refurbished, and used on as many as 20 flights dictated a conservative design approach, the validity of which has been proven by successful testing of all development and qualification motors. Aspects discussed include ballistics, the motor case, nozzle, nozzle materials, and the ignition system. Finally, summary results of the first two of three qualification motor firings designated QM-1 and QM-2 are presented.

  13. 14 CFR 121.437 - Pilot qualification: Certificates required.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Pilot qualification: Certificates required... Pilot qualification: Certificates required. (a) No pilot may act as pilot in command of an aircraft (or... pilots) unless he holds an airline transport pilot certificate and an appropriate type rating for that...

  14. 14 CFR 121.437 - Pilot qualification: Certificates required.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Pilot qualification: Certificates required... Pilot qualification: Certificates required. (a) No pilot may act as pilot in command of an aircraft (or... pilots) unless he holds an airline transport pilot certificate and an appropriate type rating for that...

  15. 14 CFR 121.439 - Pilot qualification: Recent experience.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Pilot qualification: Recent experience. 121... Pilot qualification: Recent experience. (a) No certificate holder may use any person nor may any person serve as a required pilot flight crewmember, unless within the preceding 90 days, that person has made...

  16. 14 CFR 121.439 - Pilot qualification: Recent experience.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Pilot qualification: Recent experience. 121... Pilot qualification: Recent experience. (a) No certificate holder may use any person nor may any person serve as a required pilot flight crewmember, unless within the preceding 90 days, that person has made...

  17. 14 CFR 125.285 - Pilot qualifications: Recent experience.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Pilot qualifications: Recent experience... Requirements § 125.285 Pilot qualifications: Recent experience. (a) No certificate holder may use any person, nor may any person serve, as a required pilot flight crewmember unless within the preceding 90...

  18. 14 CFR 125.285 - Pilot qualifications: Recent experience.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Pilot qualifications: Recent experience... Requirements § 125.285 Pilot qualifications: Recent experience. (a) No certificate holder may use any person, nor may any person serve, as a required pilot flight crewmember unless within the preceding 90...

  19. Development of optimized PPP insulated pipe-cable systems in the commercial voltage range

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

    Allam, E.M.; McKean, A.L.

    1992-05-01

    The primary objectives of this project included the development of an alternate domestic source of Paper-Polypropylene-Paper (PPP) laminate and the development of optimized designs for PPP-insulated pipe-type cable systems in the commercial voltage range. The development of a domestic source of PPP laminate was successfully completed. This laminate was utilized throughout the program for fabrication of full-size prototype cables submitted for laboratory qualification tests. Selected cables at rated voltages of 138, 230 and 345kV have been designed, fabricated and subjected to the series of qualification tests leading to full laboratory qualification. An optimized design of 2000 kcmil, 345kV cable insulatedmore » with 600 mils of domestic PPP laminate was fabricated and successfully passed all laboratory qualification tests. This cable design was subsequently installed at Waltz Mill to undergo the series of field tests leading to full commercial qualification.« less

  20. Development of optimized PPP insulated pipe-cable systems in the commercial voltage range. Final report

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

    Allam, E.M.; McKean, A.L.

    1992-05-01

    The primary objectives of this project included the development of an alternate domestic source of Paper-Polypropylene-Paper (PPP) laminate and the development of optimized designs for PPP-insulated pipe-type cable systems in the commercial voltage range. The development of a domestic source of PPP laminate was successfully completed. This laminate was utilized throughout the program for fabrication of full-size prototype cables submitted for laboratory qualification tests. Selected cables at rated voltages of 138, 230 and 345kV have been designed, fabricated and subjected to the series of qualification tests leading to full laboratory qualification. An optimized design of 2000 kcmil, 345kV cable insulatedmore » with 600 mils of domestic PPP laminate was fabricated and successfully passed all laboratory qualification tests. This cable design was subsequently installed at Waltz Mill to undergo the series of field tests leading to full commercial qualification.« less

  1. Space Qualification Test of a-Silicon Solar Cell Modules

    NASA Technical Reports Server (NTRS)

    Kim, Q.; Lawton, R. A.; Manion, S. J.; Okuno, J. O.; Ruiz, R. P.; Vu, D. T.; Kayali, S. A.; Jeffrey, F. R.

    1997-01-01

    The basic requirement of solar cell modules for space applications are generally described in MIL-S-83576 for the specific needs of the USAF. However, the specifications of solar cells intended for use on space terrestrial applications are not well defined. Therefore this qualification test effort was concentrated on critical areas specific to the microseismometer probe which is intended to be included in the Mars microprobe programs.

  2. Space Shuttle Orbiter - Leading edge structural design/analysis and material allowables

    NASA Technical Reports Server (NTRS)

    Johnson, D. W.; Curry, D. M.; Kelly, R. E.

    1986-01-01

    Reinforced Carbon-Carbon (RCC), a structural composite whose development was targeted for the high temperature reentry environments of reusable space vehicles, has successfully demonstrated that capability on the Space Shuttle Orbiter. Unique mechanical properties, particularly at elevated temperatures up to 3000 F, make this material ideally suited for the 'hot' regions of multimission space vehicles. Design allowable characterization testing, full-scale development and qualification testing, and structural analysis techniques will be presented herein that briefly chart the history of the RCC material from infancy to eventual multimission certification for the Orbiter. Included are discussions pertaining to the development of the design allowable data base, manipulation of the test data into usable forms, and the analytical verification process.

  3. 14 CFR 60.37 - FSTD qualification on the basis of a Bilateral Aviation Safety Agreement (BASA).

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false FSTD qualification on the basis of a Bilateral Aviation Safety Agreement (BASA). 60.37 Section 60.37 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  4. 14 CFR 60.37 - FSTD qualification on the basis of a Bilateral Aviation Safety Agreement (BASA).

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false FSTD qualification on the basis of a Bilateral Aviation Safety Agreement (BASA). 60.37 Section 60.37 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  5. 14 CFR 60.37 - FSTD qualification on the basis of a Bilateral Aviation Safety Agreement (BASA).

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false FSTD qualification on the basis of a Bilateral Aviation Safety Agreement (BASA). 60.37 Section 60.37 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  6. 14 CFR 60.37 - FSTD qualification on the basis of a Bilateral Aviation Safety Agreement (BASA).

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false FSTD qualification on the basis of a Bilateral Aviation Safety Agreement (BASA). 60.37 Section 60.37 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  7. 14 CFR 60.37 - FSTD qualification on the basis of a Bilateral Aviation Safety Agreement (BASA).

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false FSTD qualification on the basis of a Bilateral Aviation Safety Agreement (BASA). 60.37 Section 60.37 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND...

  8. 14 CFR Appendix B to Part 60 - Qualification Performance Standards for Airplane Flight Training Devices

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Qualification Performance Standards for Airplane Flight Training Devices B Appendix B to Part 60 Aeronautics and Space FEDERAL AVIATION... encourages the use of electronic media for all communication, including any record, report, request, test, or...

  9. 14 CFR Appendix B to Part 60 - Qualification Performance Standards for Airplane Flight Training Devices

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Qualification Performance Standards for Airplane Flight Training Devices B Appendix B to Part 60 Aeronautics and Space FEDERAL AVIATION... encourages the use of electronic media for all communication, including any record, report, request, test, or...

  10. 14 CFR Appendix B to Part 60 - Qualification Performance Standards for Airplane Flight Training Devices

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Qualification Performance Standards for Airplane Flight Training Devices B Appendix B to Part 60 Aeronautics and Space FEDERAL AVIATION... encourages the use of electronic media for all communication, including any record, report, request, test, or...

  11. 14 CFR Appendix B to Part 60 - Qualification Performance Standards for Airplane Flight Training Devices

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Qualification Performance Standards for Airplane Flight Training Devices B Appendix B to Part 60 Aeronautics and Space FEDERAL AVIATION... encourages the use of electronic media for all communication, including any record, report, request, test, or...

  12. 14 CFR Appendix B to Part 60 - Qualification Performance Standards for Airplane Flight Training Devices

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Qualification Performance Standards for Airplane Flight Training Devices B Appendix B to Part 60 Aeronautics and Space FEDERAL AVIATION... encourages the use of electronic media for all communication, including any record, report, request, test, or...

  13. 14 CFR 61.4 - Qualification and approval of flight simulators and flight training devices.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... for certain flight training devices. (b) Any device used for flight training, testing, or checking... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Qualification and approval of flight simulators and flight training devices. 61.4 Section 61.4 Aeronautics and Space FEDERAL AVIATION...

  14. 14 CFR 61.4 - Qualification and approval of flight simulators and flight training devices.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... for certain flight training devices. (b) Any device used for flight training, testing, or checking... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Qualification and approval of flight simulators and flight training devices. 61.4 Section 61.4 Aeronautics and Space FEDERAL AVIATION...

  15. 14 CFR 61.4 - Qualification and approval of flight simulators and flight training devices.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... for certain flight training devices. (b) Any device used for flight training, testing, or checking... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Qualification and approval of flight simulators and flight training devices. 61.4 Section 61.4 Aeronautics and Space FEDERAL AVIATION...

  16. 14 CFR 61.4 - Qualification and approval of flight simulators and flight training devices.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... for certain flight training devices. (b) Any device used for flight training, testing, or checking... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Qualification and approval of flight simulators and flight training devices. 61.4 Section 61.4 Aeronautics and Space FEDERAL AVIATION...

  17. 14 CFR 61.4 - Qualification and approval of flight simulators and flight training devices.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... for certain flight training devices. (b) Any device used for flight training, testing, or checking... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Qualification and approval of flight simulators and flight training devices. 61.4 Section 61.4 Aeronautics and Space FEDERAL AVIATION...

  18. VQSEC Home Page

    Science.gov Websites

    Complex Water Impact Visitor Information Validation and Qualification Sciences Experimental Complex Our the problem space. The Validation and Qualification Sciences Experimental Complex (VQSEC) at Sandia

  19. Providing Pressurized Gasses to the International Space Station (ISS): Developing a Composite Overwrapped Pressure Vessel (COPV) for the Safe Transport of Oxygen and Nitrogen

    NASA Technical Reports Server (NTRS)

    Kezirian, Michael; Cook, Anthony; Dick, Brandon; Phoenix, S. Leigh

    2012-01-01

    To supply oxygen and nitrogen to the International Space Station, a COPV tank is being developed to meet requirements beyond that which have been flown. In order to "Ship Full' and support compatibility with a range of launch site operations, the vessel was designed for certification to International Standards (ISO) that have a different approach than current NASA certification approaches. These requirements were in addition to existing NASA certification standards had to be met. Initial risk-reduction development tests have been successful. Qualification is in progress.

  20. 14 CFR 125.281 - Pilot-in-command qualifications.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Pilot-in-command qualifications. 125.281... Requirements § 125.281 Pilot-in-command qualifications. No certificate holder may use any person, nor may any person serve, as pilot in command of an airplane unless that person— (a) Holds at least a commercial...

  1. 14 CFR 61.55 - Second-in-command qualifications.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Second-in-command qualifications. 61.55...-in-command qualifications. (a) A person may serve as a second-in-command of an aircraft type certificated for more than one required pilot flight crewmember or in operations requiring a second-in-command...

  2. 14 CFR 125.283 - Second-in-command qualifications.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Second-in-command qualifications. 125.283... Requirements § 125.283 Second-in-command qualifications. No certificate holder may use any person, nor may any person serve, as second in command of an airplane unless that person— (a) Holds at least a commercial...

  3. 14 CFR 125.283 - Second-in-command qualifications.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Second-in-command qualifications. 125.283... Requirements § 125.283 Second-in-command qualifications. No certificate holder may use any person, nor may any person serve, as second in command of an airplane unless that person— (a) Holds at least a commercial...

  4. 14 CFR 135.245 - Second in command qualifications.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Second in command qualifications. 135.245... Crewmember Requirements § 135.245 Second in command qualifications. (a) Except as provided in paragraph (b), no certificate holder may use any person, nor may any person serve, as second in command of an...

  5. 14 CFR 135.243 - Pilot in command qualifications.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Pilot in command qualifications. 135.243... Crewmember Requirements § 135.243 Pilot in command qualifications. (a) No certificate holder may use a person, nor may any person serve, as pilot in command in passenger-carrying operations— (1) Of a turbojet...

  6. 14 CFR 125.281 - Pilot-in-command qualifications.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Pilot-in-command qualifications. 125.281... Requirements § 125.281 Pilot-in-command qualifications. No certificate holder may use any person, nor may any person serve, as pilot in command of an airplane unless that person— (a) Holds at least a commercial...

  7. 14 CFR 125.283 - Second-in-command qualifications.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Second-in-command qualifications. 125.283... Requirements § 125.283 Second-in-command qualifications. No certificate holder may use any person, nor may any person serve, as second in command of an airplane unless that person— (a) Holds at least a commercial...

  8. 14 CFR 121.443 - Pilot in command qualification: Route and airports.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Pilot in command qualification: Route and... Pilot in command qualification: Route and airports. (a) Each certificate holder shall provide a system... to the pilot in command and appropriate flight operation personnel. The system must also provide an...

  9. 14 CFR 125.283 - Second-in-command qualifications.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Second-in-command qualifications. 125.283... Requirements § 125.283 Second-in-command qualifications. No certificate holder may use any person, nor may any person serve, as second in command of an airplane unless that person— (a) Holds at least a commercial...

  10. 14 CFR 135.243 - Pilot in command qualifications.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Pilot in command qualifications. 135.243... Crewmember Requirements § 135.243 Pilot in command qualifications. (a) No certificate holder may use a person, nor may any person serve, as pilot in command in passenger-carrying operations— (1) Of a turbojet...

  11. 14 CFR 61.55 - Second-in-command qualifications.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Second-in-command qualifications. 61.55...-in-command qualifications. (a) A person may serve as a second-in-command of an aircraft type certificated for more than one required pilot flight crewmember or in operations requiring a second-in-command...

  12. 14 CFR 135.243 - Pilot in command qualifications.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Pilot in command qualifications. 135.243... Crewmember Requirements § 135.243 Pilot in command qualifications. (a) No certificate holder may use a person, nor may any person serve, as pilot in command in passenger-carrying operations— (1) Of a turbojet...

  13. 14 CFR 135.245 - Second in command qualifications.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Second in command qualifications. 135.245... Crewmember Requirements § 135.245 Second in command qualifications. (a) Except as provided in paragraph (b), no certificate holder may use any person, nor may any person serve, as second in command of an...

  14. 14 CFR 135.245 - Second in command qualifications.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Second in command qualifications. 135.245... Crewmember Requirements § 135.245 Second in command qualifications. (a) Except as provided in paragraph (b), no certificate holder may use any person, nor may any person serve, as second in command of an...

  15. 14 CFR 121.443 - Pilot in command qualification: Route and airports.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Pilot in command qualification: Route and... Pilot in command qualification: Route and airports. (a) Each certificate holder shall provide a system... to the pilot in command and appropriate flight operation personnel. The system must also provide an...

  16. 14 CFR 135.243 - Pilot in command qualifications.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Pilot in command qualifications. 135.243... Crewmember Requirements § 135.243 Pilot in command qualifications. (a) No certificate holder may use a person, nor may any person serve, as pilot in command in passenger-carrying operations— (1) Of a turbojet...

  17. 14 CFR 135.245 - Second in command qualifications.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Second in command qualifications. 135.245... Crewmember Requirements § 135.245 Second in command qualifications. (a) Except as provided in paragraph (b), no certificate holder may use any person, nor may any person serve, as second in command of an...

  18. 14 CFR 61.55 - Second-in-command qualifications.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Second-in-command qualifications. 61.55...-in-command qualifications. (a) A person may serve as a second-in-command of an aircraft type certificated for more than one required pilot flight crewmember or in operations requiring a second-in-command...

  19. 14 CFR 125.283 - Second-in-command qualifications.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Second-in-command qualifications. 125.283... Requirements § 125.283 Second-in-command qualifications. No certificate holder may use any person, nor may any person serve, as second in command of an airplane unless that person— (a) Holds at least a commercial...

  20. 14 CFR 135.243 - Pilot in command qualifications.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Pilot in command qualifications. 135.243... Crewmember Requirements § 135.243 Pilot in command qualifications. (a) No certificate holder may use a person, nor may any person serve, as pilot in command in passenger-carrying operations— (1) Of a turbojet...

  1. 14 CFR 125.281 - Pilot-in-command qualifications.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Pilot-in-command qualifications. 125.281... Requirements § 125.281 Pilot-in-command qualifications. No certificate holder may use any person, nor may any person serve, as pilot in command of an airplane unless that person— (a) Holds at least a commercial...

  2. 14 CFR 125.281 - Pilot-in-command qualifications.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Pilot-in-command qualifications. 125.281... Requirements § 125.281 Pilot-in-command qualifications. No certificate holder may use any person, nor may any person serve, as pilot in command of an airplane unless that person— (a) Holds at least a commercial...

  3. 14 CFR 125.281 - Pilot-in-command qualifications.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Pilot-in-command qualifications. 125.281... Requirements § 125.281 Pilot-in-command qualifications. No certificate holder may use any person, nor may any person serve, as pilot in command of an airplane unless that person— (a) Holds at least a commercial...

  4. 14 CFR 121.443 - Pilot in command qualification: Route and airports.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Pilot in command qualification: Route and... Pilot in command qualification: Route and airports. (a) Each certificate holder shall provide a system... to the pilot in command and appropriate flight operation personnel. The system must also provide an...

  5. 14 CFR 61.55 - Second-in-command qualifications.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Second-in-command qualifications. 61.55...-in-command qualifications. (a) A person may serve as a second-in-command of an aircraft type certificated for more than one required pilot flight crewmember or in operations requiring a second-in-command...

  6. 14 CFR 121.443 - Pilot in command qualification: Route and airports.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Pilot in command qualification: Route and... Pilot in command qualification: Route and airports. (a) Each certificate holder shall provide a system... to the pilot in command and appropriate flight operation personnel. The system must also provide an...

  7. 14 CFR 135.245 - Second in command qualifications.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Second in command qualifications. 135.245... Crewmember Requirements § 135.245 Second in command qualifications. (a) Except as provided in paragraph (b), no certificate holder may use any person, nor may any person serve, as second in command of an...

  8. 14 CFR 121.443 - Pilot in command qualification: Route and airports.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Pilot in command qualification: Route and... Pilot in command qualification: Route and airports. (a) Each certificate holder shall provide a system... to the pilot in command and appropriate flight operation personnel. The system must also provide an...

  9. 14 CFR 121.411 - Qualifications: Check airmen (airplane) and check airmen (simulator).

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Qualifications: Check airmen (airplane) and... § 121.411 Qualifications: Check airmen (airplane) and check airmen (simulator). Link to an amendment... airman (airplane) is a person who is qualified, and permitted, to conduct flight checks or instruction in...

  10. Space Shuttle Flight Support Motor no. 1 (FSM-1)

    NASA Technical Reports Server (NTRS)

    Hughes, Phil D.

    1990-01-01

    Space Shuttle Flight Support Motor No. 1 (FSM-1) was static test fired on 15 Aug. 1990 at the Thiokol Corporation Static Test Bay T-24. FSM-1 was a full-scale, full-duration static test fire of a redesigned solid rocket motor. FSM-1 was the first of seven flight support motors which will be static test fired. The Flight Support Motor program validates components, materials, and manufacturing processes. In addition, FSM-1 was the full-scale motor for qualification of Western Electrochemical Corporation ammonium perchlorate. This motor was subjected to all controls and documentation requirements CTP-0171, Revision A. Inspection and instrumentation data indicate that the FSM-1 static test firing was successful. The ambient temperature during the test was 87 F and the propellant mean bulk temperature was 82 F. Ballistics performance values were within the specified requirements. The overall performance of the FSM-1 components and test equipment was nominal.

  11. From space qualified fiber optic gyroscope to generic fiber optic solutions available for space application

    NASA Astrophysics Data System (ADS)

    Buret, Thomas; Ramecourt, David; Napolitano, Fabien

    2017-11-01

    The aim of this article is to present how the qualification of the Fiber Optic Gyroscope technology from IXSEA has been achieved through the qualification of a large range of optical devices and related manufacturing processes. These qualified optical devices and processes, that are now fully mastered by IXSEA through vertical integration of the technology, can be used for other space optical sensors. The example of the SWARM project will be discussed.

  12. 14 CFR 121.411 - Qualifications: Check airmen (airplane) and check airmen (simulator).

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Qualifications: Check airmen (airplane) and... § 121.411 Qualifications: Check airmen (airplane) and check airmen (simulator). (a) For the purposes of this section and § 121.413: (1) A check airman (airplane) is a person who is qualified, and permitted...

  13. 14 CFR 121.411 - Qualifications: Check airmen (airplane) and check airmen (simulator).

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Qualifications: Check airmen (airplane) and... § 121.411 Qualifications: Check airmen (airplane) and check airmen (simulator). (a) For the purposes of this section and § 121.413: (1) A check airman (airplane) is a person who is qualified, and permitted...

  14. 14 CFR 121.411 - Qualifications: Check airmen (airplane) and check airmen (simulator).

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Qualifications: Check airmen (airplane) and... § 121.411 Qualifications: Check airmen (airplane) and check airmen (simulator). (a) For the purposes of this section and § 121.413: (1) A check airman (airplane) is a person who is qualified, and permitted...

  15. 14 CFR 121.411 - Qualifications: Check airmen (airplane) and check airmen (simulator).

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Qualifications: Check airmen (airplane) and... § 121.411 Qualifications: Check airmen (airplane) and check airmen (simulator). (a) For the purposes of this section and § 121.413: (1) A check airman (airplane) is a person who is qualified, and permitted...

  16. MEMS Reliability Assurance Guidelines for Space Applications

    NASA Technical Reports Server (NTRS)

    Stark, Brian (Editor)

    1999-01-01

    This guide is a reference for understanding the various aspects of microelectromechanical systems, or MEMS, with an emphasis on device reliability. Material properties, failure mechanisms, processing techniques, device structures, and packaging techniques common to MEMS are addressed in detail. Design and qualification methodologies provide the reader with the means to develop suitable qualification plans for the insertion of MEMS into the space environment.

  17. Space Technology-5 Lithium-Ion Battery Design, Qualification and Integration and Testing

    NASA Technical Reports Server (NTRS)

    Rao, Gopalakishna M.; Stewart, Karen; Ameen, Syed; Banfield, Peter K.

    2005-01-01

    This document is a viewgraph presentation that reviews the Lithium Ion Battery for the Space Technology-5 (ST-5) mission. Included in the document is a review of the ST-5 Mission, a review of the battery requirements, a description of the battery and the battery materials. The testing and the integration and qualification data is reviewed.

  18. Qualification testing of fiber-based laser transmitters and on-orbit validation of a commercial laser system

    NASA Astrophysics Data System (ADS)

    Wright, M. W.; Wilkerson, M. W.; Tang, R. R.

    2017-11-01

    Qualification testing of fiber based laser transmitters is required for NASA's Deep Space Optical Communications program to mature the technology for space applications. In the absence of fully space qualified systems, commercial systems have been investigated in order to demonstrate the robustness of the technology. To this end, a 2.5 W fiber based laser source was developed as the transmitter for an optical communications experiment flown aboard the ISS as a part of a technology demonstration mission. The low cost system leveraged Mil Standard design principles and Telcordia certified components to the extent possible and was operated in a pressure vessel with active cooling. The laser was capable of high rate modulation but was limited by the mission requirements to 50 Mbps for downlinking stored video from the OPALS payload, externally mounted on the ISS. Environmental testing and space qualification of this unit will be discussed along with plans for a fully space qualified laser transmitter.

  19. An update on the Deep Space 1 power system: SCARLET integration and test results

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

    Allen, D.M.; Murphy, D.M.

    1998-07-01

    The Solar Concentrator Arrays with Refractive Linear Element Technology (SCARLET) system for the Deep Space 1 (DS1) spacecraft have been completed and delivered to JPL for integration with the spacecraft. This paper describes the array assembly, the qualification test program, and the results of the qualification tests. The array will provide power to the DS1 spacecraft and its NSTAR ion electric propulsion system. Launch is scheduled for October, 1998 from Kennedy Space Center, FL.

  20. Implementation and Qualifications Lessons Learned for Space Flight Photonic Components

    NASA Technical Reports Server (NTRS)

    Ott, Melanie N.

    2010-01-01

    This slide presentation reviews the process for implementation and qualification of space flight photonic components. It discusses the causes for most common anomalies for the space flight components, design compatibility, a specific failure analysis of optical fiber that occurred in a cable in 1999-2000, and another ExPCA connector anomaly involving pins that broke off. It reviews issues around material selection, quality processes and documentation, and current projects that the Photonics group is involved in. The importance of good documentation is stressed.

  1. QM-8 final performance evaluation report: SEALS, volume 4

    NASA Technical Reports Server (NTRS)

    Nelsen, L. V.

    1989-01-01

    The Space Shuttle Redesigned Solid Rocket Motor (RSRM) static test of Qualification Motor-8 (QM-8) was conducted. The QM-8 test article was the fifth full-scale, full-duration test, and the third qualification motor to incorporate the redesigned case field joint and nozzle-to-case joint. This was the second static test conducted in the T-97 test facility, which is equipped with actuators for inducing external side loads to a 360 degree external tank (ET) attach ring during test motor operation, and permits heating/cooling of an entire motor. The QM-8 motor was cooled to a temperature which ensured that the maximum propellant mean bulk temperature (PMBT) of 40 F was achieved at firing. All test results are not included, but rather, the performance of the metal case, field joints, and nozzle-to-case joint is addressed. The involvement is studied of the Structural Applications and Structural Design Groups with the QM-8 test which includes: assembly procedures of the field and nozzle-to-case joints, joint leak check results, structural test results, and post-test inspection evaluations.

  2. Throttling Impacts on Hall Thruster Performance, Erosion, and Qualification for NASA Science Missions

    NASA Technical Reports Server (NTRS)

    Dankanich, John W.; DeHoyos, Amado

    2007-01-01

    With the SMART-1, Department of Defense, and commercial industry successes in Hall thruster technologies, NASA has started considering Hall thrusters for science missions. The recent Discovery proposals included a Hall thruster science mission and the In-Space Propulsion Project is investing in Hall thruster technologies. As the confidence in Hall thrusters improve, ambitious multi-thruster missions are being considered. Science missions often require large throttling ranges due to the 1/r(sup 2) power drop-off from the sun. Deep throttling of Hall thrusters will impact the overall system performance. Also, Hall thrusters can be throttled with both current and voltage, impacting erosion rates and performance. Last, electric propulsion thruster lifetime qualification has previously been conducted with long duration full power tests. Full power tests may not be appropriate for NASA science missions, and a combination of lifetime testing at various power levels with sufficient analysis is recommended. Analyses of various science missions and throttling schemes using the Aerojet BPT-4000 and NASA 103M HiVHAC thruster are presented.

  3. CNES reliability approach for the qualification of MEMS for space

    NASA Astrophysics Data System (ADS)

    Pressecq, Francis; Lafontan, Xavier; Perez, Guy; Fortea, Jean-Pierre

    2001-10-01

    This paper describes the reliability approach performs at CNES to evaluate MEMS for space application. After an introduction and a detailed state of the art on the space requirements and on the use of MEMS for space, different approaches for taking into account MEMS in the qualification phases are presented. CNES proposes improvement to theses approaches in term of failure mechanisms identification. Our approach is based on a design and test phase deeply linked with a technology study. This workflow is illustrated with an example: the case of a variable capacitance processed with MUMPS process is presented.

  4. Equivalent electron fluence for space qualification of shallow junction heteroface GaAs solar cells

    NASA Technical Reports Server (NTRS)

    Wilson, J. W.; Stock, L. V.

    1984-01-01

    It is desirable to perform qualification tests prior to deployment of solar cells in space power applications. Such test procedures are complicated by the complex mixture of differing radiation components in space which are difficult to simulate in ground test facilities. Although it has been shown that an equivalent electron fluence ratio cannot be uniquely defined for monoenergetic proton exposure of GaAs shallow junction cells, an equivalent electron fluence test can be defined for common spectral components of protons found in space. Equivalent electron fluence levels for the geosynchronous environment are presented.

  5. Fabrication of fuel pin assemblies, phase 3

    NASA Technical Reports Server (NTRS)

    Keeton, A. R.; Stemann, L. G.

    1972-01-01

    Five full size and eight reduced length fuel pins were fabricated for irradiation testing to evaluate design concepts for a fast spectrum lithium cooled compact space power reactor. These assemblies consisted of uranium mononitride fuel pellets encased in a T-111 (Ta-8W-2Hf) clad with a tungsten barrier separating fuel and clad. Fabrication procedures were fully qualified by process development and assembly qualification tests. Detailed specifications and procedures were written for the fabrication and assembly of prototype fuel pins.

  6. VEGA, the European small launcher: Development status, future perspectives, and applications

    NASA Astrophysics Data System (ADS)

    Bianchi, Stefano; VEGA Integrated Project Team (IPT)

    2008-07-01

    This paper presents a technical and programmatic overview of the VEGA launch system program currently in development for the European Space Agency, which includes the development and qualification activities of the small launcher VEGA, of the ground infrastructure, and of all the launcher elements. Several programmatic milestones have been successfully achieved so far: most subsystems have gone through the critical design review or qualification review. The launcher system critical design review has been performed during spring 2007 as well. Concerning propulsion, all the three development models of the solid rocket motors have been successfully tested between December 2005 and December 2006. The first qualification model engine of the liquid propulsion upper module has successfully completed its firing campaign and the test campaign for the second model has just started. The liquid upper stage AVUM engine has been tested as well. The VEGA ground segment program has entered its final lapse by completing the detailed design of the various subsystems. The installation phase in the launch range site (Kourou, French Guyane) is in full swing. The integration of the Mobile Gantry, necessary to integrate the launcher, is almost completed as for the main structure.

  7. NARC Rayon Replacement Program for the RSRM Nozzle, Phase IV Qualification and Implementation Status

    NASA Technical Reports Server (NTRS)

    Haddock, M. Reed; Wendel, Gary M.; Cook, Roger V.

    2005-01-01

    The Space Shuttle NARC Rayon Replacement Program has down-selected Enka rayon as a replacement for the obsolete NARC rayon in the nozzle carbon cloth phenolic (CCP) ablative insulators. Full qualification testing of the Enka rayon-based carbon cloth phenolic is underway, including processing, thmal/structural properties, and hot-fire subscale tests. Required thermal-structural capabilities, together with confidence in erosio/char performance in simulated and subscale hot fire tests such as Wright-Patterson Air Force Base Laser Hardened Materials Evaluation Laboratory testing, NASA-MSFC 24-inch motor tests, NASA-MSFC Solid Fuel Torch - Super Sonic Blast Tube, NASA-MSFC Plasma Torch Test Bed, ATK Thiokol Forty Pound Charge and NASA-MSFC MNASA justified the testing of the new Enka-rayon candidate on full-scale static test motors. The first RSRM full-scale static test motor nozzle, fabricated using the new Enka rayon-based CCP, was successfully demonstrated in June 2004. Two additional static test motors are planned with the new Enka rayon in the next two years along with additional A-basis property characterization. Process variation or "corner-of-the-box" testing together with cured and uncured aging studies are also planned as some of the pre-flight implementation activities with 5-year cured aging studies over-lapping flight hardware fabrication.

  8. Qualification Tests of Micro-camera Modules for Space Applications

    NASA Astrophysics Data System (ADS)

    Kimura, Shinichi; Miyasaka, Akira

    Visual capability is very important for space-based activities, for which small, low-cost space cameras are desired. Although cameras for terrestrial applications are continually being improved, little progress has been made on cameras used in space, which must be extremely robust to withstand harsh environments. This study focuses on commercial off-the-shelf (COTS) CMOS digital cameras because they are very small and are based on an established mass-market technology. Radiation and ultrahigh-vacuum tests were conducted on a small COTS camera that weighs less than 100 mg (including optics). This paper presents the results of the qualification tests for COTS cameras and for a small, low-cost COTS-based space camera.

  9. Building the Qualification File of EGNOS with DOORS

    NASA Astrophysics Data System (ADS)

    Fabre, J.

    2008-08-01

    EGNOS, the European Satellite-Based Augmentation System (SBAS) to GPS, is getting to its final deployment and being initially operated towards qualification and certification to reach operational capability by 2008/2009. A very important milestone in the development process is the System Qualification Review (QR). As the verification phase aims at demonstrating that the EGNOS System design meets the applicable requirements, the QR declares the completion of verification activities. The main document to present at QR is a consolidated, consistent and complete Qualification file. The information included shall give confidence to the QR reviewers that the performed qualification activities are completed. Therefore, an important issue for the project team is to focus on synthetic and consistent information, and to make the presentation as clear as possible. Traceability to applicable requirements shall be systematically presented. Moreover, in order to support verification justification, reference to details shall be available, and the reviewer shall have the possibility to link automatically to the documents including this detailed information. In that frame, Thales Alenia Space has implemented a strong support in terms of methodology and tool, to provide to System Engineering and Verification teams a single reference technical database, in which all team members consult the applicable requirements, compliance, justification, design data and record the information necessary to build the final Qualification file. This paper presents the EGNOS context, the Qualification file contents, and the methodology implemented, based on Thales Alenia Space practices and in line with ECSS. Finally, it shows how the Qualification file is built in a DOORS environment.

  10. Preparing America for Deep Space Exploration Episode 16: Exploration On The Move

    NASA Image and Video Library

    2018-02-22

    Preparing America for Deep Space Exploration Episode 16: Exploration On The Move NASA is pressing full steam ahead toward sending humans farther than ever before. Take a look at the work being done by teams across the nation for NASA’s Deep Space Exploration System, including the Space Launch System, Orion, and Exploration Ground Systems programs, as they continue to propel human spaceflight into the next generation. Highlights from the fourth quarter of 2017 included Orion parachute drop tests at the Yuma Proving Ground in Arizona; the EM-1 Crew Module move from Cleanroom to Workstation at Kennedy Space Center; Crew Training, Launch Pad Evacuation Scenario, and Crew Module Vibration and Legibility Testing at NASA’s Johnson Space Center; RS-25 Rocket Engine Testing at Stennis Space Center; Core Stage Engine Section arrival, Core Stage Pathfinder; LH2 Qualification Tank; Core Stage Intertank Umbilical lift at Mobile Launcher; Crew Access Arm move to Mobile Launcher; Water Flow Test at Launch Complex 39-B.

  11. Development of electrical test procedures for qualification of spacecraft against EID. Volume 2: Review and specification of test procedures

    NASA Technical Reports Server (NTRS)

    Wilkenfeld, J. M.; Harlacher, B. L.; Mathews, D.

    1982-01-01

    A combined experimental and analytical program to develop system electrical test procedures for the qualification of spacecraft against damage produced by space-electron-induced discharges (EID) occurring on spacecraft dielectric outer surfaces is described. A review and critical evaluation of possible approaches to qualify spacecraft against space electron-induced discharges (EID) is presented. A variety of possible schemes to simulate EID electromagnetic effects produced in spacecraft was studied. These techniques form the principal element of a provisional, recommended set of test procedures for the EID qualification spacecraft. Significant gaps in our knowledge about EID which impact the final specification of an electrical test to qualify spacecraft against EID are also identified.

  12. Managing Risk for Thermal Vacuum Testing of the International Space Station Radiators

    NASA Technical Reports Server (NTRS)

    Carek, Jerry A.; Beach, Duane E.; Remp, Kerry L.

    2000-01-01

    The International Space Station (ISS) is designed with large deployable radiator panels that are used to reject waste heat from the habitation modules. Qualification testing of the Heat Rejection System (HRS) radiators was performed using qualification hardware only. As a result of those tests, over 30 design changes were made to the actual flight hardware. Consequently, a system level test of the flight hardware was needed to validate its performance in the final configuration. A full thermal vacuum test was performed on the flight hardware in order to demonstrate its ability to deploy on-orbit. Since there is an increased level of risk associated with testing flight hardware, because of cost and schedule limitations, special risk mitigation procedures were developed and implemented for the test program, This paper introduces the Continuous Risk Management process that was utilized for the ISS HRS test program. Testing was performed in the Space Power Facility at the NASA Glenn Research Center, Plum Brook Station located in Sandusky, Ohio. The radiator system was installed in the 100-foot diameter by 122-foot tall vacuum chamber on a special deployment track. Radiator deployments were performed at several thermal conditions similar to those expected on-orbit using both the primary deployment mechanism and the back-up deployment mechanism. The tests were highly successful and were completed without incident.

  13. 14 CFR Appendix A to Part 60 - Qualification Performance Standards for Airplane Full Flight Simulators

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    .... Qualification Performance Standards (§ 60.4). 5. Quality Management System (§ 60.5). 6. Sponsor Qualification... inquiries on system compatibility, and minimum system requirements are also included on the NSP Web site. d... Flight Guidance Systems. (15) AC 120-57, as amended, Surface Movement Guidance and Control System (SMGCS...

  14. Commercial Parts Technology Qualification Processes

    NASA Technical Reports Server (NTRS)

    Cooper, Mark S.

    2013-01-01

    Many high-reliability systems, including space systems, use selected commercial parts (including Plastic Encapsulated Microelectronics or PEMs) for unique functionality, small size, low weight, high mechanical shock resistance, and other factors. Predominantly this usage is subjected to certain 100% tests (typically called screens) and certain destructive tests usually (but not always) performed on the flight lot (typically called qualification tests). Frequently used approaches include those documented in EEE-INST-002 and JPL DocID62212 (which are sometimes modified by the particular aerospace space systems manufacturer). In this study, approaches from these documents and several space systems manufacturers are compared to approaches from a launch systems manufacturer (SpaceX), an implantable medical electronics manufacturer (Medtronics), and a high-reliability transport system process (automotive systems). In the conclusions section, these processes are outlined for all of these cases and presented in tabular form. Then some simple comparisons are made. In this introduction section, the PEM technology qualification process is described, as documented in EEE-INST-002 (written by the Goddard Space Flight Center, GSFC), as well as the somewhat modified approach employed at the Jet Propulsion Laboratory (JPL). Approaches used at several major NASA contractors are also described

  15. Development of Magneto-Resistive Angular Position Sensors for Space Applications

    NASA Astrophysics Data System (ADS)

    Hahn, Robert; Langendorf, Sven; Seifart, Klaus; Slatter, Rolf; Olberts, Bastian; Romera, Fernando

    2015-09-01

    Magnetic microsystems in the form of magneto- resistive (MR) sensors are firmly established in automobiles and industrial applications. They measure path, angle, electrical current, or magnetic fields. MR technology opens up new sensor possibilities in space applications and can be an enabling technology for optimal performance, high robustness and long lifetime at reasonable costs. In a recent assessment study performed by HTS GmbH and Sensitec GmbH under ESA Contract a market survey has confirmed that space industry has a very high interest in novel, contactless position sensors based on MR technology. Now, a detailed development stage is pursued, to advance the sensor design up to Engineering Qualification Model (EQM) level and to perform qualification testing for a representative pilot space application.The paper briefly reviews the basics of magneto- resistive effects and possible sensor applications and describes the key benefits of MR angular sensors with reference to currently operational industrial and space applications. The results of the assessment study are presented and potential applications and uses of contactless magneto-resistive angular sensors for spacecraft are identified. The baseline mechanical and electrical sensor design will be discussed. An outlook on the EQM development and qualification tests is provided.

  16. Nuclear Cryogenic Propulsion Stage Fuel Design and Fabrication

    NASA Technical Reports Server (NTRS)

    Hickman, Robert; Broadway, Jeramie; Mireles, Omar; Webb, Jon; Qualls, Lou

    2012-01-01

    Nuclear Cryogenic Propulsion Stage (NCPS) is a game changing technology for space exploration. Goal of assessing the affordability and viability of an NCPS includes these overall tasks: (1) Pre-conceptual design of the NCPS and architecture integration (2) NCPS Fuel Design and Testing (3) Nuclear Thermal Rocket Element Environmental Simulator (NTREES) (4) Affordable NCPS Development and Qualification Strategy (5) Second Generation NCPS Concepts. There is a critical need for fuels development. Fuel task objectives are to demonstrate capabilities and critical technologies using full scale element fabrication and testing.

  17. Nuclear Cryogenic Propulsion Stage Fuel Design and Fabrication

    NASA Technical Reports Server (NTRS)

    Hickman, Robert; Broadway, Jeramie; Mireles, Omar; Webb, Jon; Qualls, Lou

    2012-01-01

    Nuclear Cryogenic Propulsion Stage (NCPS) is a game changing technology for space exploration. Goal of assessing the affordability and viability of an NCPS includes thses overall tasks: (1) Pre-conceptual design of the NCPS and architecture integration (2) NCPS Fuel Design and Testing (3) Nuclear Thermal Rocket Element Environmental Simulator (NTREES) (4) Affordable NCPS Development and Qualification Strategy (5) Second Generation NCPS Concepts. There is a critical need for fuels development. Fuel task objectives are to demonstrate capabilities and critical technologies using full scale element fabrication and testing.

  18. Overview of RICOR tactical cryogenic refrigerators for space missions

    NASA Astrophysics Data System (ADS)

    Riabzev, Sergey; Filis, Avishai; Livni, Dorit; Regev, Itai; Segal, Victor; Gover, Dan

    2016-05-01

    Cryogenic refrigerators represent a significant enabling technology for Earth and Space science enterprises. Many of the space instruments require cryogenic refrigeration to enable the use of advanced detectors to explore a wide range of phenomena from space. RICOR refrigerators involved in various space missions are overviewed in this paper, starting in 1994 with "Clementine" Moon mission, till the latest ExoMars mission launched in 2016. RICOR tactical rotary refrigerators have been incorporated in many space instruments, after passing qualification, life time, thermal management testing and flight acceptance. The tactical to space customization framework includes an extensive characterization and qualification test program to validate reliability, the design of thermal interfacing with a detector, vibration export control, efficient heat dissipation in a vacuum environment, robustness, mounting design, compliance with outgassing requirements and strict performance screening. Current RICOR development is focused on dedicated ultra-long-life, highly reliable, space cryogenic refrigerator based on a Pulse Tube design

  19. Dialogic Spaces: A Critical Policy Development Perspective of Educational Leadership Qualifications

    ERIC Educational Resources Information Center

    Smith, Déirdre; Kelly, Darron; Allard, Carson

    2017-01-01

    The critical exploration of policy development processes employed to construct leadership qualifications is the focus of this inquiry. This exploration is made through specific application of the necessary conditions of Habermasian "practical discourse" to current dialogic procedures used to develop policies for principal, supervisory…

  20. Optical fiber technology for space: challenges of development and qualification

    NASA Astrophysics Data System (ADS)

    Goepel, Michael

    2017-11-01

    Using fiber optical components and assemblies for space flight applications brings several challenges for the design and the qualification process. Good knowledge of the system and environmental requirements is needed to derive design decisions and select suitable components for the fiber optical subsystem. Furthermore, the manufacturing process and integration limitations are providing additional constraints, which have to be considered at the beginning of the design phase. Besides Commercial off the shelf (COTS) components, custom made parts are often necessary.

  1. Space flight requirements for fiber optic components: qualification testing and lessons learned

    NASA Astrophysics Data System (ADS)

    Ott, Melanie N.; Jin, Xiaodan Linda; Chuska, Richard; Friedberg, Patricia; Malenab, Mary; Matuszeski, Adam

    2006-04-01

    "Qualification" of fiber optic components holds a very different meaning than it did ten years ago. In the past, qualification meant extensive prolonged testing and screening that led to a programmatic method of reliability assurance. For space flight programs today, the combination of using higher performance commercial technology, with shorter development schedules and tighter mission budgets makes long term testing and reliability characterization unfeasible. In many cases space flight missions will be using technology within years of its development and an example of this is fiber laser technology. Although the technology itself is not a new product the components that comprise a fiber laser system change frequently as processes and packaging changes occur. Once a process or the materials for manufacturing a component change, even the data that existed on its predecessor can no longer provide assurance on the newer version. In order to assure reliability during a space flight mission, the component engineer must understand the requirements of the space flight environment as well as the physics of failure of the components themselves. This can be incorporated into an efficient and effective testing plan that "qualifies" a component to specific criteria defined by the program given the mission requirements and the component limitations. This requires interaction at the very initial stages of design between the system design engineer, mechanical engineer, subsystem engineer and the component hardware engineer. Although this is the desired interaction what typically occurs is that the subsystem engineer asks the components or development engineers to meet difficult requirements without knowledge of the current industry situation or the lack of qualification data. This is then passed on to the vendor who can provide little help with such a harsh set of requirements due to high cost of testing for space flight environments. This presentation is designed to guide the engineers of design, development and components, and vendors of commercial components with how to make an efficient and effective qualification test plan with some basic generic information about many space flight requirements. Issues related to the physics of failure, acceptance criteria and lessons learned will also be discussed to assist with understanding how to approach a space flight mission in an ever changing commercial photonics industry.

  2. Space Flight Requirements for Fiber Optic Components; Qualification Testing and Lessons Learned

    NASA Technical Reports Server (NTRS)

    Ott, Melanie N.; Jin, Xiaodan Linda; Chuska, Richard; Friedberg, Patricia; Malenab, Mary; Matuszeski, Adam

    2007-01-01

    "Qualification" of fiber optic components holds a very different meaning than it did ten years ago. In the past, qualification meant extensive prolonged testing and screening that led to a programmatic method of reliability assurance. For space flight programs today, the combination of using higher performance commercial technology, with shorter development schedules and tighter mission budgets makes long term testing and reliability characterization unfeasible. In many cases space flight missions will be using technology within years of its development and an example of this is fiber laser technology. Although the technology itself is not a new product the components that comprise a fiber laser system change frequently as processes and packaging changes occur. Once a process or the materials for manufacturing a component change, even the data that existed on its predecessor can no longer provide assurance on the newer version. In order to assure reliability during a space flight mission, the component engineer must understand the requirements of the space flight environment as well as the physics of failure of the components themselves. This can be incorporated into an efficient and effective testing plan that "qualifies" a component to specific criteria defined by the program given the mission requirements and the component limitations. This requires interaction at the very initial stages of design between the system design engineer, mechanical engineer, subsystem engineer and the component hardware engineer. Although this is the desired interaction what typically occurs is that the subsystem engineer asks the components or development engineers to meet difficult requirements without knowledge of the current industry situation or the lack of qualification data. This is then passed on to the vendor who can provide little help with such a harsh set of requirements due to high cost of testing for space flight environments. This presentation is designed to guide the engineers of design, development and components, and vendors of commercial components with how to make an efficient and effective qualification test plan with some basic generic information about many space flight requirements. Issues related to the physics of failure, acceptance criteria and lessons learned will also be discussed to assist with understanding how to approach a space flight mission in an ever changing commercial photonics industry.

  3. 14 CFR 91.1091 - Qualifications: Flight instructors (aircraft) and flight instructors (simulator).

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... (aircraft) and flight instructors (simulator). 91.1091 Section 91.1091 Aeronautics and Space FEDERAL... Qualifications: Flight instructors (aircraft) and flight instructors (simulator). (a) For the purposes of this... aircraft, in a flight simulator, or in a flight training device for a particular type, class, or category...

  4. 14 CFR 91.1091 - Qualifications: Flight instructors (aircraft) and flight instructors (simulator).

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... (aircraft) and flight instructors (simulator). 91.1091 Section 91.1091 Aeronautics and Space FEDERAL... Qualifications: Flight instructors (aircraft) and flight instructors (simulator). (a) For the purposes of this... aircraft, in a flight simulator, or in a flight training device for a particular type, class, or category...

  5. 14 CFR 91.1091 - Qualifications: Flight instructors (aircraft) and flight instructors (simulator).

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... (aircraft) and flight instructors (simulator). 91.1091 Section 91.1091 Aeronautics and Space FEDERAL... Qualifications: Flight instructors (aircraft) and flight instructors (simulator). (a) For the purposes of this... aircraft, in a flight simulator, or in a flight training device for a particular type, class, or category...

  6. 14 CFR 91.1091 - Qualifications: Flight instructors (aircraft) and flight instructors (simulator).

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... (aircraft) and flight instructors (simulator). 91.1091 Section 91.1091 Aeronautics and Space FEDERAL... Qualifications: Flight instructors (aircraft) and flight instructors (simulator). (a) For the purposes of this... aircraft, in a flight simulator, or in a flight training device for a particular type, class, or category...

  7. 14 CFR 121.412 - Qualifications: Flight instructors (airplane) and flight instructors (simulator).

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... (airplane) and flight instructors (simulator). 121.412 Section 121.412 Aeronautics and Space FEDERAL... OPERATIONS Training Program § 121.412 Qualifications: Flight instructors (airplane) and flight instructors... section and § 121.414: (1) A flight instructor (airplane) is a person who is qualified to instruct in an...

  8. 14 CFR 121.412 - Qualifications: Flight instructors (airplane) and flight instructors (simulator).

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... (airplane) and flight instructors (simulator). 121.412 Section 121.412 Aeronautics and Space FEDERAL... OPERATIONS Training Program § 121.412 Qualifications: Flight instructors (airplane) and flight instructors (simulator). (a) For the purposes of this section and § 121.414: (1) A flight instructor (airplane) is a...

  9. 14 CFR 121.412 - Qualifications: Flight instructors (airplane) and flight instructors (simulator).

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... (airplane) and flight instructors (simulator). 121.412 Section 121.412 Aeronautics and Space FEDERAL... OPERATIONS Training Program § 121.412 Qualifications: Flight instructors (airplane) and flight instructors (simulator). (a) For the purposes of this section and § 121.414: (1) A flight instructor (airplane) is a...

  10. 14 CFR 121.412 - Qualifications: Flight instructors (airplane) and flight instructors (simulator).

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... (airplane) and flight instructors (simulator). 121.412 Section 121.412 Aeronautics and Space FEDERAL... OPERATIONS Training Program § 121.412 Qualifications: Flight instructors (airplane) and flight instructors (simulator). (a) For the purposes of this section and § 121.414: (1) A flight instructor (airplane) is a...

  11. 14 CFR Appendix E to Part 60 - Qualification Performance Standards for Quality Management Systems for Flight Simulation Training...

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... Quality Management Systems for Flight Simulation Training Devices E Appendix E to Part 60 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION...—Qualification Performance Standards for Quality Management Systems for Flight Simulation Training Devices Begin...

  12. 14 CFR 121.412 - Qualifications: Flight instructors (airplane) and flight instructors (simulator).

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... (airplane) and flight instructors (simulator). 121.412 Section 121.412 Aeronautics and Space FEDERAL... OPERATIONS Training Program § 121.412 Qualifications: Flight instructors (airplane) and flight instructors (simulator). (a) For the purposes of this section and § 121.414: (1) A flight instructor (airplane) is a...

  13. Compatibility of Space Nuclear Power Plant Materials in an Inert He/Xe Working Gas Containing Reactive Impurities

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

    MM Hall

    2006-01-31

    A major materials selection and qualification issue identified in the Space Materials Plan is the potential for creating materials compatibility problems by combining dissimilar reactor core, Brayton Unit and other power conversion plant materials in a recirculating, inert He/Xe gas loop containing reactive impurity gases. Reported here are results of equilibrium thermochemical analyses that address the compatibility of space nuclear power plant (SNPP) materials in high temperature impure He gas environments. These studies provide early information regarding the constraints that exist for SNPP materials selection and provide guidance for establishing test objectives and environments for SNPP materials qualification testing.

  14. Implementation of COTs Hardware in Non-Critical Space Applications: A Brief Tutorial

    NASA Technical Reports Server (NTRS)

    Yoder, Geoffrey L.

    2004-01-01

    Approaches used for manned applications include limited items such as CD-players evaluated for safety to high criticality applications where the COTs hardware is evaluated on a case-by-case basis for the application and commensurate screening and qualification testing. COTS hardware is successfully implemented in both the International Space Station and Space Shuttle but requires evaluation and modifications for the application. Screening and qualification of COTs hardware used in critical applications may need to be more extensive and stringent than traditional military screening. Evaluation for: a) Suitability for the application; b) Safety; c) Reliability and maintainability; and d) Workmanship.

  15. NASA Space Mechanisms Handbook and Reference Guide Expanded Into CD-ROM Set

    NASA Technical Reports Server (NTRS)

    Fusaro, Robert L.

    2002-01-01

    Several NASA missions suffered failures and anomalies due to problems in applying space mechanisms technology to specific projects. Research shows that engineers often lack either adequate knowledge of mechanism design or sufficient understanding of how mechanisms affect sensitive systems. The Space Mechanisms Project conducted a Lessons Learned study and published a Space Mechanisms Handbook to help space industry engineers avoid recurring design, qualification, and application problems. The Space Mechanisms Handbook written at the NASA Glenn Research Center details the state-of-the-art in space mechanisms design as of 1998. NASA's objective in developing this Space Mechanisms Handbook was to provide readily accessible information on such areas as space mechanisms design, mechanical component availability and use, testing and qualification of mechanical systems, and a listing of worldwide space mechanisms experts and testing facilities in the United States. This handbook has been expanded into a two-volume CD-ROM set in an Adobe Acrobat format. In addition to the handbook, the CD's include (1) the two volume Space Mechanisms Lessons Learned Study, (2) proceedings from all the NASA hosted Aerospace Mechanisms Symposia held through the year 2000, (3) the Space Materials Handbook, (4) the Lubrication Handbook for the Space Industry, (5) the Structural & Mechanical Systems Long-Life Assurance Design Guidelines, (6) the Space Environments and Effects Source-Book, (7) the Spacecraft Deployable Appendages manual, (8) the Fastener Design Manual, (9) A Manual for Pyrotechnic Design, Development and Qualification, (10) the Report on Alternative Devices to Pyrotechnics on Spacecraft, and (11) Gearing (a manual). In addition, numerous other papers on tribology and lubrication are included.This technical summary of the project provides information on how to obtain the handbook and related information.

  16. 29 CFR 515.3 - Qualifications of the State agency.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... UTILIZATION OF STATE AGENCIES FOR INVESTIGATIONS AND INSPECTIONS § 515.3 Qualifications of the State agency... be under the direction of an executive who gives full time to the work of the agency. The agency...

  17. Enlisted Personnel Allocation System

    DTIC Science & Technology

    1989-03-01

    hierarchy is further subdivided into two characteristic groupings: intelligence qualifications and physical qualifications. 41 I I 7 -, S- ie p if- i - LL...weighted as 30% of the applicant’s Intelligence Qualifications score). As shown in Figure 6, a step function generates a score based on the...34 There is no aritificial time window imposed on any MOS. Any open training date within the full DEP horizon may be recommended by the optimization

  18. Qualification of Electrical Ground Support Equipment for New Space Programs

    NASA Technical Reports Server (NTRS)

    SotoToro, Felix A.; Vu, Bruce T.; Hamilton, Mark S.

    2011-01-01

    With the Space Shuttle program coming to an end, the National Aeronautics and Space Administration (NASA) is moving to a new space flight program that will allow expeditions beyond low earth orbit. The space vehicles required to comply with these missions will be carrying heavy payloads. This implies that the Earth departure stage capabilities must be of higher magnitudes, given the current propulsion technology. The engineering design of the new flight hardware comes with some structural, thermal, propulsion and other subsystems' challenges. Meanwhile, the necessary ground support equipment (GSE) used to test, validate, verify and process the flight hardware must withstand the new program specifications. This paper intends to provide the qualification considerations during implementation of new electrical GSE for space programs. A team of engineers was formed to embark on this task, and facilitate the logistics process and ensure that the electrical, mechanical and fluids subsystems conduct the proper level of testing. Ultimately, each subsystem must certify that each piece of ground support equipment used in the field is capable of withstanding the strenuous vibration, acoustics, environmental, thermal and Electromagnetic Interference (EMf) levels experienced during pre-launch, launch and post-launch activities. The benefits of capturing and sharing these findings will provide technical, cost savings and schedule impacts infon11ation to both the technical and management community. Keywords: Qualification; Testing; Ground Support Equipment; Electromagnetic Interference Testing; Vibration Testing; Acoustic Testing; Power Spectral Density.

  19. Findings from the Supersonic Qualification Program of the Mars Science Laboratory Parachute System

    NASA Technical Reports Server (NTRS)

    Sengupta, Anita; Steltzner, Adam; Witkowski, Allen; Candler, Graham; Pantano, Carlos

    2009-01-01

    In 2012, the Mars Science Laboratory Mission (MSL) will deploy NASA's largest extra-terrestrial parachute, a technology integral to the safe landing of its advanced robotic explorer on the surface. The supersonic parachute system is a mortar deployed 21.5 m disk-gap-band (DGB) parachute, identical in geometric scaling to the Viking era DGB parachutes of the 1970's. The MSL parachute deployment conditions are Mach 2.3 at a dynamic pressure of 750 Pa. The Viking Balloon Launched Decelerator Test (BLDT) successfully demonstrated a maximum of 700 Pa at Mach 2.2 for a 16.1 m DGB parachute in its AV4 flight. All previous Mars deployments have derived their supersonic qualification from the Viking BLDT test series, preventing the need for full scale high altitude supersonic testing. The qualification programs for Mars Pathfinder, Mars Exploration Rover, and Phoenix Scout Missions were all limited to subsonic structural qualification, with supersonic performance and survivability bounded by the BLDT qualification. The MSL parachute, at the edge of the supersonic heritage deployment space and 33% larger than the Viking parachute, accepts a certain degree of risk without addressing the supersonic environment in which it will deploy. In addition, MSL will spend up to 10 seconds above Mach 1.5, an aerodynamic regime that is associated with a known parachute instability characterized by significant canopy projected area fluctuation and dynamic drag variation. This aerodynamic instability, referred to as "area oscillations" by the parachute community has drag performance, inflation stability, and structural implications, introducing risk to mission success if not quantified for the MSL parachute system. To minimize this risk and as an alternative to a prohibitively expensive high altitude test program, a multi-phase qualification program using computation simulation validated by subscale test was developed and implemented for MSL. The first phase consisted of 2% of fullscale supersonic wind tunnel testing of a rigid DGB parachute with entry-vehicle to validate two high fidelity computational fluid dynamics (CFD) tools. The computer codes utilized Large Eddy Simulation and Detached Eddy Simulation numerical approaches to accurately capture the turbulent wake of the entry vehicle and its coupling to the parachute bow-shock. The second phase was the development of fluid structure interaction (FSI) computational tools to predict parachute response to the supersonic flow field. The FSI development included the integration of the CFD from the first phase with a finite element structural model of the parachute membrane and cable elements. In this phase, a 4% of full-scale supersonic flexible parachute test program was conducted to provide validation data to the FSI code and an empirical dataset of the MSL parachute in a flight-like environment. The final phase is FSI simulations of the full-scale MSL parachute in a Mars type deployment. Findings from this program will be presented in terms of code development and validation, empirical findings from the supersonic testing, and drag performance during supersonic operation.

  20. A shuttle and space station manipulator system for assembly, docking, maintenance, cargo handling and spacecraft retrieval (preliminary design). Volume 3: Concept analysis. Part 2: Development program

    NASA Technical Reports Server (NTRS)

    1972-01-01

    A preliminary estimate is presented of the resources required to develop the basic general purpose walking boom manipulator system. It is assumed that the necessary full scale zero g test facilities will be available on a no cost basis. A four year development effort is also assumed and it is phased with an estimated shuttle development program since the shuttle will be developed prior to the space station. Based on delivery of one qualification unit and one flight unit and without including any ground support equipment or flight test support it is estimated (within approximately + or - 25%) that a total of 3551 man months of effort and $17,387,000 are required.

  1. RL10A-3-3B high mixture ratio qualification program

    NASA Technical Reports Server (NTRS)

    Vogel, T.; Varella, D.; Smith, C.

    1987-01-01

    The results of the high mixture ratio qualification testing of the RL10 engine for the Shuttle/Centaur program are presented. The objective of the engine qualification test was to demonstrate the suitability of the RL10A-3-3B engine for space vehicle flight by subjecting it to the testing specified in RL10A-3-3B Model Specification Number 2295 dated February 1986. The applicable section of the specification is presented. Due to payload volume advantages which can be achieved by increasing the operating mixture ratio of the RL10, a decision was made to qualify the engine to run at a higher mixture ratio. A program was created to qualify the RL10 engine for operation at 15,000 pounds thrust and a nominal 6.0 to 1 mixture ratio. This model of the engine was designated the RL10A-3-3B. The qualification program included three test series as follows: (1) hardware durability and limits test in which the engine completed 23 firings and 4605.7 seconds with 1588.7 seconds at less than 6.6 mixture ratio; (2) preliminary qualification test in which the engine completed 26 firings and 5750 seconds; and (3) qualification test in which the engine completed 26 hot firings and 5693.4 seconds with 905.9 seconds at 6.7 mixture ratio. Several changes in engine hardware were required for operation of the RL10A-3-3B engine in the Space Shuttle which include a duel pressure switch ignition, an oxidizer flow control, and helium plumbing changes.

  2. Validation of Commercial Fiber Optic Components for Aerospace Environments

    NASA Technical Reports Server (NTRS)

    Ott, Melanie N.

    2005-01-01

    Full qualification for commercial photonic parts as defined by the Military specification system in the past, is not feasible. Due to changes in the photonic components industry and the Military specification system that NASA had relied upon so heavily in the past, an approach to technology validation of commercial off the shelf parts had to be devised. This approach involves knowledge of system requirements, environmental requirements and failure modes of the particular components under consideration. Synthesizing the criteria together with the major known failure modes to formulate a test plan is an effective way of establishing knowledge based "qualification". Although this does not provide the type of reliability assurance that the Military specification system did in the past, it is an approach that allows for increased risk mitigation. The information presented will introduce the audience to the technology validation approach that is currently applied at NASA for the usage of commercial-off-the-shelf (COTS) fiber optic components for space flight environments. The focus will be on how to establish technology validation criteria for commercial fiber products such that continued reliable performance is assured under the harsh environmental conditions of typical missions. The goal of this presentation is to provide the audience with an approach to formulating a COTS qualification test plan for these devices. Examples from past NASA missions will be discussed.

  3. General presentation including new structure

    NASA Astrophysics Data System (ADS)

    Soons, A.

    2002-12-01

    Electrical, electronic and electro-mechanical components play an essential role in the functional performance, quality, life cycle and costs of space systems. Their standardisation, product specification, development, evaluation, qualification and procurement must be based on a coherent and efficient approach, paying due attention to present and prospective European space policies and must be commensurate with user needs, market developments and technology trends. The European Space Components Coordination (ESCC) is established with the objective of harmonising the efforts concerning the various aspects of EEE space components by ESA. European national and international public space organisations, the component manufacturers and the user industries. The goal of the ESCC is to improve the availability of strategic EEE space components with the required performance and at affordable costs for institutional and commercial space programmes. It is the objective of ESCC to achieve this goal by harmonising the resources and development efforts for space components in the ESA Member States and by providing a single and unified system for the standardisation, product specification, evaluation, qualification and procurement of European EEE space components and for the certification of components and component manufacturers.

  4. The Social Space of Educational Strategies: Exploring Patterns of Enrolment, Efficiency and Completion among Swedish Students in Undergraduate Programmes with Professional Qualifications

    ERIC Educational Resources Information Center

    Carlhed, Carina

    2017-01-01

    The aim of the study was to analyse enrolment patterns, and study efficiency and completion among students in programmes with professional qualifications, using microdata from Statistics Sweden. The programmes were Architecture, Medicine, Nursing, Law, Social work, Psychology, andEngineering (year 2001-2002, n = 15,918). Using the concepts from…

  5. Qualification of Bonding Process of Temperature Sensors to Extreme Temperature Deep Space Missions

    NASA Technical Reports Server (NTRS)

    Ramesham, Rajeshuni; Kitiyakara, Amarit; Redick, Richard; Sunada, Eric T.

    2011-01-01

    A process has been explored based on the state-of-the-art technology to bond the platinum resistance thermometer (PRT) on to potential aerospace material such as a flat aluminum surface and a flexible copper tube to simulate coaxial cable for the flight applications. Primarily, PRTs were inserted into a metal plated copper braid to avoid stresses on the sensor while attaching the sensor with braid to the base material for long duration deep space missions. Appropriate pretreatment has been implemented in this study to enhance the adhesion of the PRTs to the base material. NuSil product has been chosen in this research to attach PRT to the base materials. The resistance (approx.1.1 k(Omega)) of PRTs has been electrically monitored continuously during the qualification thermal cycling testing from -150 C to +120 C and -100 C to -35 C. The test hardware has been thermal cycled three times the mission life per JPL design principles for JUNO project. No PRT failures were observed during and after the PRT thermal cycling qualification test for extreme temperature environments. However, there were some failures associated with staking of the PRT pig tails as a result of thermal cycling qualification test.

  6. Results of qualification tests on water-level sensing instruments, 1987

    USGS Publications Warehouse

    Olive, T.E.

    1989-01-01

    The U.S. Geological Survey 's Hydrologic Instrumentation Facility at the Stennis Space Center, Mississippi, conducts qualification tests on water level sensing instruments. Instrument systems, which meet or exceed the Survey 's minimum performance requirements, are placed on the Survey 's Qualified Products List. The qualification tests conducted in 1987 added two instrument systems to the Survey 's Qualified Products List. One system met requirements for use at a daily-discharge station , and the other system met requirements for a special-case station. The report is prepared for users of hydrologic instruments. The report provides a list of instrument features, describes the instrument systems, summarizes test procedures, and presents test results for the two instrument systems that met the Survey 's minimum performance standards for the 1987 round of qualification tests. (USGS)

  7. 42 CFR 493.1483 - Standard: Cytotechnologist qualifications.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... person examining cytology slide preparations must meet the qualifications of § 493.1449 (b) or (k), or... laboratory directed by a pathologist or other physician providing cytology services; and (iii) Completed 2..., have full-time experience of at least 2 years or equivalent examining cytology slide preparations...

  8. 42 CFR 493.1483 - Standard: Cytotechnologist qualifications.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... person examining cytology slide preparations must meet the qualifications of § 493.1449 (b) or (k), or... laboratory directed by a pathologist or other physician providing cytology services; and (iii) Completed 2..., have full-time experience of at least 2 years or equivalent examining cytology slide preparations...

  9. 42 CFR 493.1483 - Standard: Cytotechnologist qualifications.

    Code of Federal Regulations, 2014 CFR

    2014-10-01

    ... person examining cytology slide preparations must meet the qualifications of § 493.1449 (b) or (k), or... laboratory directed by a pathologist or other physician providing cytology services; and (iii) Completed 2..., have full-time experience of at least 2 years or equivalent examining cytology slide preparations...

  10. 42 CFR 493.1483 - Standard: Cytotechnologist qualifications.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... person examining cytology slide preparations must meet the qualifications of § 493.1449 (b) or (k), or... laboratory directed by a pathologist or other physician providing cytology services; and (iii) Completed 2..., have full-time experience of at least 2 years or equivalent examining cytology slide preparations...

  11. 42 CFR 493.1483 - Standard: Cytotechnologist qualifications.

    Code of Federal Regulations, 2012 CFR

    2012-10-01

    ... person examining cytology slide preparations must meet the qualifications of § 493.1449 (b) or (k), or... laboratory directed by a pathologist or other physician providing cytology services; and (iii) Completed 2..., have full-time experience of at least 2 years or equivalent examining cytology slide preparations...

  12. Fatigue qualification of high thickness composite rotor components

    NASA Astrophysics Data System (ADS)

    Raggi, M.; Mariani, U.; Zaffaroni, G.

    Fatigue qualification aspects of composite rotor components are presented according with the safe life procedure usually applied by helicopter manufacturers. Test activities are identified at three levels of specimen complexity: coupon, structural element and full scale component. Particular attention is given to high thickness laminates qualification as far as environmental exposure is concerned. A practical approach for an accelerated conditioning procedure is described. The application to a main rotor tension link is presented showing the negligible effect of the moisture absorption on its fatigue strength.

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

    NASA Technical Reports Server (NTRS)

    Scheidegger, Noemy; Ferris, Mark; Phillips, Nigel

    2014-01-01

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

  14. Thermography During Thermal Test of the Gaia Deployable Sunshield Assembly Qualification Model in the ESTEC Large Space Simulator

    NASA Astrophysics Data System (ADS)

    Simpson, R.; Broussely, M.; Edwards, G.; Robinson, D.; Cozzani, A.; Casarosa, G.

    2012-07-01

    The National Physical Laboratory (NPL) and The European Space Research and Technology Centre (ESTEC) have performed for the first time successful surface temperature measurements using infrared thermal imaging in the ESTEC Large Space Simulator (LSS) under vacuum and with the Sun Simulator (SUSI) switched on during thermal qualification tests of the GAIA Deployable Sunshield Assembly (DSA). The thermal imager temperature measurements, with radiosity model corrections, show good agreement with thermocouple readings on well characterised regions of the spacecraft. In addition, the thermal imaging measurements identified potentially misleading thermocouple temperature readings and provided qualitative real-time observations of the thermal and spatial evolution of surface structure changes and heat dissipation during hot test loadings, which may yield additional thermal and physical measurement information through further research.

  15. Results of qualification tests on water-level sensing instruments, 1986

    USGS Publications Warehouse

    Holland, Randolph R.; Rapp, Donald H.

    1988-01-01

    This report presents to users of hydrological instrumentation and U.S. Geological Survey procurement personnel a list of instruments that have met or exceeded the Survey 's minimum performance requirements for water level sensing instruments. The Hydrologic Instrumentation Facility at the National Space Technology Laboratories, Mississippi conducted qualification tests on four instrument systems. The data collected are summarized, brief system descriptions are given, qualification testing purposes and procedures are summarized, and results are given for each of the three systems that met performance requirements. The fourth system was returned to the manufacturer , because in preliminary testing the instrument system did not perform properly according to the manufacturer 's operating procedures. As a result of the qualification tests, the three systems that met performance requirements have been included on the Survey 's Qualified Products List. (USGS)

  16. RTEMS CENTRE- RTEMS Improvement

    NASA Astrophysics Data System (ADS)

    Silva, Helder; Constantino, Alexandre; Freitas, Daniel; Coutinho, Manuel; Faustino, Sergio; Sousa, Jose; Dias, Luis; Zulianello, Marco

    2010-08-01

    During the last two years, EDISOFT's RTEMS CENTRE team [1], jointly with the European Space Agency and with the support of the worldwide RTEMS community [2], have been developing an activity to facilitate the qualification of the real-time operating system RTEMS (Real-Time Operating System for Multiprocessor Systems). This paper intends to give a high level visibility of the progress and the results obtained in the RTEMS Improvement [3] activity. The primary objective [4] of the project is to improve the RTEMS product, its documentation and to facilitate the qualification of RTEMS for future space missions, taking into consideration the specific operational requirements. The sections below provide a brief overview of the RTEMS operating system and the activities performed in the RTEMS Improvement project, which includes the selection of API managers to be qualified, the tailoring process, the requirements analysis, the reverse engineering and design of the RTEMS, the quality assurance process, the ISVV activities, the test campaign, the results obtained, the criticality analysis and the facilitation of qualification process.

  17. Space Qualification Test of a-Silicon Solar Cell Modules

    NASA Technical Reports Server (NTRS)

    Kim, Q.; Lawton, R. A.; Manion, S. J.; Okuno, J. O.; Ruiz, R. P.; Vu, D. T.; Vu, D. T.; Kayali, S. A.; Jeffrey, F. R.

    2004-01-01

    The basic requirements of solar cell modules for space applications are generally described in MIL-S-83576 for the specific needs of the USAF. However, the specifications of solar cells intended for use on space terrestrial applications are not well defined. Therefore, this qualifications test effort was concentrated on critical areas specific to the microseismometer probe which is intended to be included in the Mars microprobe programs. Parameters that were evaluated included performance dependence on: illuminating angles, terrestrial temperatures, lifetime, as well as impact landing conditions. Our qualification efforts were limited to these most critical areas of concern. Most of the tested solar cell modules have met the requirements of the program except the impact tests. Surprisingly, one of the two single PIN 2 x 1 amorphous solar cell modules continued to function even after the 80000G impact tests. The output power parameters, Pout, FF, Isc and Voc, of the single PIN amorphous solar cell module were found to be 3.14 mW, 0.40, 9.98 mA and 0.78 V, respectively. These parameters are good enough to consider the solar module as a possible power source for the microprobe seismometer. Some recommendations were made to improve the usefulness of the amorphous silicon solar cell modules in space terrestrial applications, based on the results obtained from the intensive short term lab test effort.

  18. Intermediate eXperimental Vehicle Jettison Mechanism Engineering and Test

    NASA Astrophysics Data System (ADS)

    Caldirola, L.; Schmid, B.

    2015-09-01

    The IXV (Intermediate eXperimental Vehicle) is a project of the European Space Agency that aims to develop an autonomous atmospheric re-entry system. A flight model has been launched on a Vega rocket on the 11th of February 2015 and after descending from an altitude of 420km splashed down in the Pacific Ocean. In the frame of this project RUAG space has developed the entire cold structure and the mechanisms able to eject the panels closing the parachute and floatation balloons bays. Panels ejection allows respectively parachutes deployment, reducing the IXV re-entry speed from Mach 1.5 to few meters per second just before the splash down, and buoyancy balloons inflation which let the vehicle float on the sea surface until arrival of the recovery ship.Such panels and the relevant mechanisms had to be designed not only to guarantee the correct external aerodynamic shape needed for the flight performance, but also to provide enough stiffness and strength to the IXV structure, being capable of transfer high shear loads.Moreover the floatation doors design enclosed both the hold down and release mechanism, based on a non- explosive separation nut, and the jettison springs, therefore particular attention had to be put to prevent any damage to the panel during the release which could have potentially led to jamming of the panel itself which jeopardise the floatation balloon deployment. The chosen design was therefore based on a spherical joint, so that shear load can be withstand and bending moment on the jettison-able panels limited at the same time.Test activities have been performed at mechanism level for environmental and preliminary functional qualification, subsystem level, including dummy panel jettison and full scale IXV drop test, to complete the functional qualification and system level test to close qualification campaign.The purpose of this paper is to present the mechanism design and the activities performed to qualify at component and sub-system level the jettison mechanism of the floatation balloons doors.

  19. Lightweight thermally efficient composite feedlines for the space tug cryogenic propulsion system

    NASA Technical Reports Server (NTRS)

    Spond, D. E.

    1975-01-01

    Six liquid hydrogen feedline design concepts were developed for the cryogenic space tug. The feedlines include composite and all-metal vacuum jacketed and nonvacuum jacketed concepts, and incorporate the latest technological developments in the areas of thermally efficient vacuum jacket end closures and standoffs, radiation shields in the vacuum annulus, thermal coatings, and lightweight dissimilar metal flanged joints. The feedline design concepts are evaluated on the basis of thermal performance, weight, cost, reliability, and reusability. Design concepts were proved in a subscale test program. Detail design was completed on the most promising composite feedline concept and an all-metal feedline. Three full scale curved composite feedlines and one all-metal feedline assembly were fabricated and subjected to a test program representative of flight hardware qualification. The test results show that composite feedline technology is fully developed. Composite feedlines are ready for space vehicle application and offer significant reduction in weights over the conventional all-metal feedlines presently used.

  20. 46 CFR 57.05-3 - Limited space qualifications.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) MARINE ENGINEERING WELDING AND BRAZING... welding or torch brazing of piping on board ship in a limited or restricted space, the space restrictions shown in connection with Figure 57.05-3(a) or (b) shall be used when welding and brazing the test joint...

  1. Photovoltaic Engineering Testbed: A Facility for Space Calibration and Measurement of Solar Cells on the International Space Station

    NASA Technical Reports Server (NTRS)

    Landis, Geoffrey A.; Bailey, Sheila G.; Jenkins, Phillip; Sexton, J. Andrew; Scheiman, David; Christie, Robert; Charpie, James; Gerber, Scott S.; Johnson, D. Bruce

    2001-01-01

    The Photovoltaic Engineering Testbed ("PET") is a facility to be flown on the International Space Station to perform calibration, measurement, and qualification of solar cells in the space environment and then returning the cells to Earth for laboratory use. PET will allow rapid turnaround testing of new photovoltaic technology under AM0 conditions.

  2. Video of SLS Liquid Hydrogen Tank Qualification Structural Test Article Being Moved to Cell E at NASA’s Michoud Assembly Facility

    NASA Image and Video Library

    2017-06-29

    This video shows the Space Launch System liquid hydrogen tank structural qualification test article being moved to Building 110, Cell at NASA's Michoud Assembly Facility in New Orleans. The rocket's liquid hydrogen tank, which is the propellant tank that joins to the engine section of the 212-foot tall core stage, will carry cryogenic liquid hydrogen that propels the rocket. This test article build at Michoud is being prepared for testing at NASA's Marshall Space Flight Center in Huntsville, Alabama. There, it will be subjected to millions of pounds of force during testing to ensure the hardware can withstand the incredible stresses of launch.

  3. International Space Station United States Laboratory Module Water Recovery Management Subsystem Verification from Flight 5A to Stage ULF2

    NASA Technical Reports Server (NTRS)

    Williams, David E.; Labuda, Laura

    2009-01-01

    The International Space Station (ISS) Environmental Control and Life Support (ECLS) system comprises of seven subsystems: Atmosphere Control and Supply (ACS), Atmosphere Revitalization (AR), Fire Detection and Suppression (FDS), Temperature and Humidity Control (THC), Vacuum System (VS), Water Recovery and Management (WRM), and Waste Management (WM). This paper provides a summary of the nominal operation of the United States (U.S.) Laboratory Module WRM design and detailed element methodologies utilized during the Qualification phase of the U.S. Laboratory Module prior to launch and the Qualification of all of the modification kits added to it from Flight 5A up and including Stage ULF2.

  4. Space Shuttle external tank: Today - DDT & E: Tomorrow - Production

    NASA Technical Reports Server (NTRS)

    Norton, A. M.; Tanner, E. J.

    1979-01-01

    The External Tank (ET) is the structural backbone of the Space Shuttle. The ET is discussed relative to its role; its design as a highly efficient Shuttle element; the liquid oxygen tank - a thin shelled monocoque; the intertank - the forward structural connection; the liquid hydrogen tank structure - the connection with the Orbiter; the ET structural verification; the propulsion system - a variety of functions; the electrical subsystem; electrical subsystem qualification; the thermal protection system; and other related problems. To date the qualification programs have been extremely successful and are almost complete, and the first flight tank has been delivered. Tomorrow's objectives will concentrate on establishing the facilities, tools and processes to achieve a production rate of 24 ETs/year.

  5. The Impact of Part-Time Jobs in Years 12 and 13 on Qualification Achievement.

    ERIC Educational Resources Information Center

    Payne, Joan

    2003-01-01

    Presents data from nationally representative sample of the England/Wales Youth Cohort Study, describing patterns of paid work among full-time students in Years 12/13 working for qualifications. Shows paid work of a few hours has negligible impact on "A" level grades, but long working hours significantly reduce grades. (BT)

  6. Qualification of an evaluated butterfly-packaged DFB laser designed for space applications

    NASA Astrophysics Data System (ADS)

    Tornow, S.; Stier, C.; Buettner, T.; Laurent, T.; Kneier, M.; Bru, J.; Lien, Y.

    2017-11-01

    An extended qualification program has proven the quality of a previously evaluated semiconductor laser diode, which is intended to be used in a subsystem for the GAIA mission. We report on results of several reliability tests performed in subgroups. The requirements of the procurement specification with respect to reliability and desired manufacturing processes were confirmed. This is an example for successful collaboration between component supplier, system integrator and payload responsible party.

  7. 14 CFR 60.31 - Recordkeeping and reporting.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Recordkeeping and reporting. 60.31 Section 60.31 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.31...

  8. 14 CFR 60.3 - Definitions.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Definitions. 60.3 Section 60.3 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.3 Definitions. In addition to...

  9. 14 CFR 60.3 - Definitions.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Definitions. 60.3 Section 60.3 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.3 Definitions. In addition to...

  10. 14 CFR 60.31 - Recordkeeping and reporting.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Recordkeeping and reporting. 60.31 Section 60.31 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.31...

  11. 14 CFR 60.3 - Definitions.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Definitions. 60.3 Section 60.3 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.3 Definitions. In addition to...

  12. 14 CFR 60.31 - Recordkeeping and reporting.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Recordkeeping and reporting. 60.31 Section 60.31 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.31...

  13. 14 CFR 60.31 - Recordkeeping and reporting.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Recordkeeping and reporting. 60.31 Section 60.31 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.31...

  14. 14 CFR 60.3 - Definitions.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Definitions. 60.3 Section 60.3 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.3 Definitions. In addition to...

  15. 14 CFR 60.3 - Definitions.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Definitions. 60.3 Section 60.3 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.3 Definitions. In addition to...

  16. 14 CFR 60.31 - Recordkeeping and reporting.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Recordkeeping and reporting. 60.31 Section 60.31 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.31...

  17. Infrared Heater Used in Qualification Testing of International Space Station Radiators

    NASA Technical Reports Server (NTRS)

    Ziemke, Robert A.

    2004-01-01

    Two heat rejection radiator systems for the International Space Station (ISS) have undergone thermal vacuum qualification testing at the NASA Glenn Research Center (GRC), Plum Brook Station, Sandusky, Ohio. The testing was performed in the Space Power Facility (SPF), the largest thermal vacuum chamber in the world. The heat rejection system radiator was tested first; it removes heat from the ISS crew living quarters. The second system tested was the photovoltaic radiator (PVR), which rejects heat from the ISS photovoltaic arrays and the electrical power-conditioning equipment. The testing included thermal cycling, hot- and cold-soaked deployments, thermal gradient deployments, verification of the onboard heater controls, and for the PVR, thermal performance tests with ammonia flow. Both radiator systems are orbital replacement units for ease of replacement on the ISS. One key to the success of these tests was the performance of the infrared heater system. It was used in conjunction with a gaseous-nitrogen-cooled cryoshroud in the SPF vacuum chamber to achieve the required thermal vacuum conditions for the qualification tests. The heater, which was designed specifically for these tests, was highly successful and easily met the test requirements. This report discusses the heating requirements, the heater design features, the design approach, and the mathematical basis of the design.

  18. Development of a Magneto-Resistive Angular Position Sensor for Space Mechanisms

    NASA Technical Reports Server (NTRS)

    Hahn, Robert; Schmidt, Tilo; Seifart, Klaus; Olberts, Bastian; Romera, Fernando

    2016-01-01

    Magnetic microsystems in the form of magneto-resistive (MR) sensors are firmly established in automobiles and industrial applications. They are used to measure travel, angle, electrical current, or magnetic fields. MR technology opens up new sensor possibilities in space applications and can be an enabling technology for optimal performance, high robustness and long lifetime at reasonable costs. In some science missions, the technology is already applied, however, the designs are proprietary and case specific, for instance in case of the angular sensors used for JPL/NASA's Mars rover Curiosity [1]. Since 2013 HTS GmbH and Sensitec GmbH have teamed up to develop and qualify a standardized yet flexible to use MR angular sensor for space mechanisms. Starting with a first assessment study and market survey performed under ESA contract, a very strong industry interest in novel, contactless position measurement means was found. Currently a detailed and comprehensive development program is being performed by HTS and Sensitec. The objective of this program is to advance the sensor design up to Engineering Qualification Model level and to perform qualification testing for a representative space application. The paper briefly reviews the basics of magneto-resistive effects and possible sensor applications and describes the key benefits of MR angular sensors with reference to currently operational industrial and space applications. The key applications and specification are presented and the preliminary baseline mechanical and electrical design will be discussed. An outlook on the upcoming development and test stages as well as the qualification program will be provided.

  19. Laser Development for Interferometry in Space

    NASA Technical Reports Server (NTRS)

    Numata, Kenji; Camp, Jordan

    2012-01-01

    We are developing a laser (master oscillator) and optical amplifier for interferometric space missions, including the gravitational-wave missions NGO and OpTIIX experiment on the international space station. Our system is based on optical fiber and semiconductor laser technologies, which have evolved dramatically in the past decade. We will report on the latest status of the development work, including noise measurements and space qualification tests.

  20. 14 CFR 60.20 - Logging FSTD discrepancies.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Logging FSTD discrepancies. 60.20 Section 60.20 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.20 Logging...

  1. 14 CFR 60.5 - Quality management system.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Quality management system. 60.5 Section 60.5 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.5 Quality...

  2. 14 CFR 60.5 - Quality management system.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Quality management system. 60.5 Section 60.5 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.5 Quality...

  3. 14 CFR 60.20 - Logging FSTD discrepancies.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Logging FSTD discrepancies. 60.20 Section 60.20 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.20 Logging...

  4. 14 CFR 60.20 - Logging FSTD discrepancies.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Logging FSTD discrepancies. 60.20 Section 60.20 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.20 Logging...

  5. 14 CFR 60.5 - Quality management system.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Quality management system. 60.5 Section 60.5 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.5 Quality...

  6. 14 CFR 60.5 - Quality management system.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Quality management system. 60.5 Section 60.5 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.5 Quality...

  7. 14 CFR 60.17 - Previously qualified FSTDs.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Previously qualified FSTDs. 60.17 Section 60.17 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.17 Previously...

  8. 14 CFR 60.17 - Previously qualified FSTDs.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Previously qualified FSTDs. 60.17 Section 60.17 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.17 Previously...

  9. 14 CFR 60.20 - Logging FSTD discrepancies.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Logging FSTD discrepancies. 60.20 Section 60.20 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.20 Logging...

  10. 14 CFR 60.17 - Previously qualified FSTDs.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Previously qualified FSTDs. 60.17 Section 60.17 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.17 Previously...

  11. 14 CFR 60.20 - Logging FSTD discrepancies.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Logging FSTD discrepancies. 60.20 Section 60.20 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.20 Logging...

  12. 14 CFR 60.17 - Previously qualified FSTDs.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Previously qualified FSTDs. 60.17 Section 60.17 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.17 Previously...

  13. 14 CFR 60.17 - Previously qualified FSTDs.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Previously qualified FSTDs. 60.17 Section 60.17 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.17 Previously...

  14. SULTAN measurement and qualification: ITER-US-LLNL-NMARTOVETSKY- 092008

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

    Martovetsky, N N

    2006-09-21

    Measuring the characteristics of full scale ITER CICC at SULTAN is the critical qualification test. If volt-ampere characteristic (VAC) or volt-temperature characteristic (VTC) are distorted, the criterion of 10 uV/m may not be a valid criterion to judge the conductor performance. Only measurements with a clear absence or low signals from the current distribution should be considered as quantitatively representative, although in some obvious circumstances one can judge if a conductor will meet or fail ITER requirements. SULTAN full scale ITER CICC testing should be done with all measures taken to ensure uniform current redistribution. A full removal of Crmore » plating in the joint area and complete solder filling of the joints (with provision of the central channel for helium flow) should be mandatory for DC qualification samples for ITER. Also, T and I should be increased slowly that an equilibrium could be established for accurate measurement of Tcs, Ic and N. It is also desirable to go up in down in current and/or temperature (within stable range) to make sure that the equilibrium is reached.« less

  15. Space Shuttle Crawler Transporter Truck Shoe Qualification Tests and Analyses for Return-to-Flight

    NASA Technical Reports Server (NTRS)

    Margasahayam, Ravi N.; Meyer, Karl A.; Burton, Roy C.; Gosselin, Armand M.

    2005-01-01

    A vital element to Launch Complex 39 (LC39) and NASA's Kennedy Space Center (KSC) mobile launch transfer operation is a 3 million kilogram behemoth known as the Crawler Transporter (CT). Built in the 1960's, two CT's have accumulated over 1700+ miles each and have been used for the Apollo and the Space Shuttle programs. Recent observation of fatigue cracks on the CT shoes led to a comprehensive engineering, structural and metallurgical evaluation to assess the root cause that necessitated procurement of over 1000 new shoes. This paper documents the completed dynamic and compression tests on the old and new shoes respectively, so as to certify them for Space Shuttle's return-to-flight (RTF). Measured strain data from the rollout tests was used to develop stress/loading spectra and static equivalent load for qualification testing of the new shoes. Additionally, finite element analysis (FEA) was used to conduct sensitivity analyses of various contact parameters and structural characteristics for acceptance of new shoes.

  16. The Returns to Completion or Partial Completion of a Qualification in the Trades. Research Report

    ERIC Educational Resources Information Center

    Lu, Tham

    2015-01-01

    Many students do not complete full qualifications in the vocational education and training (VET) system because their intention is to obtain only the particular skills they require. This can be achieved through the acquisition of skill sets; these enable flexibility in training to quickly respond to changes in the labour market. Skill sets may…

  17. Qualification of Commercial XIPS(R) Ion Thrusters for NASA Deep Space Missions

    NASA Technical Reports Server (NTRS)

    Goebel, Dan M.; Polk, James E.; Wirz, Richard E.; Snyder, J.Steven; Mikellides, Ioannis G.; Katz, Ira; Anderson, John

    2008-01-01

    Electric propulsion systems based on commercial ion and Hall thrusters have the potential for significantly reducing the cost and schedule-risk of Ion Propulsion Systems (IPS) for deep space missions. The large fleet of geosynchronous communication satellites that use solar electric propulsion (SEP), which will approach 40 satellites by year-end, demonstrates the significant level of technical maturity and spaceflight heritage achieved by the commercial IPS systems. A program to delta-qualify XIPS(R) ion thrusters for deep space missions is underway at JPL. This program includes modeling of the thruster grid and cathode life, environmental testing of a 25-centimeter electromagnetic (EM) thruster over DAWN-like vibe and temperature profiles, and wear testing of the thruster cathodes to demonstrate the life and benchmark the model results. This paper will present the delta-qualification status of the XIPS thruster and discuss the life and reliability with respect to known failure mechanisms.

  18. The human role in space. Volume 2: Research analysis and technology report

    NASA Technical Reports Server (NTRS)

    1984-01-01

    The human role in space was studied. The role and the degree of direct involvement of humans that will be required in future space missions are investigated. Valid criteria for allocating functional activities between humans and machines were established. The technology requirements, economics, and benefits of the human presence in space was examined. Topics discussed include: human qualifications for space activities; specific project assessments; technology requirements and tasks; and generalization on human roles in space.

  19. The Role of Space Experiments in the Radiation Qualification of Electronic and Photonic Devices and Systems

    NASA Technical Reports Server (NTRS)

    Buchner, S.; LaBel, K.; Barth, J.; Campbell, A.

    2005-01-01

    Space experiments are occasionally launched to study the effects of radiation on electronic and photonic devices. This begs the following questions: Are space experiments necessary? Do the costs justify the benefits? How does one judge success of space experiment? What have we learned from past space experiments? How does one design a space experiment? This viewgraph presentation provides information on the usefulness of space and ground tests for simulating radiation damage to spacecraft components.

  20. Mars MetNet Mission - Martian Atmospheric Observational Post Network

    NASA Astrophysics Data System (ADS)

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

    2016-10-01

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

  1. 14 CFR 60.23 - Modifications to FSTDs.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Modifications to FSTDs. 60.23 Section 60.23 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.23 Modifications to FSTDs. (a...

  2. 14 CFR 60.11 - FSTD use.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false FSTD use. 60.11 Section 60.11 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.11 FSTD use. No person may use...

  3. 14 CFR 60.23 - Modifications to FSTDs.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Modifications to FSTDs. 60.23 Section 60.23 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.23 Modifications to FSTDs. (a...

  4. 14 CFR 60.23 - Modifications to FSTDs.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Modifications to FSTDs. 60.23 Section 60.23 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.23 Modifications to FSTDs. (a...

  5. 14 CFR 60.23 - Modifications to FSTDs.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Modifications to FSTDs. 60.23 Section 60.23 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.23 Modifications to FSTDs. (a...

  6. 14 CFR 60.11 - FSTD use.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false FSTD use. 60.11 Section 60.11 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.11 FSTD use. No person may use...

  7. 14 CFR 60.11 - FSTD use.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false FSTD use. 60.11 Section 60.11 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.11 FSTD use. No person may use...

  8. 14 CFR 60.9 - Additional responsibilities of the sponsor.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Additional responsibilities of the sponsor. 60.9 Section 60.9 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.9...

  9. 14 CFR 60.9 - Additional responsibilities of the sponsor.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Additional responsibilities of the sponsor. 60.9 Section 60.9 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.9...

  10. 14 CFR 60.23 - Modifications to FSTDs.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Modifications to FSTDs. 60.23 Section 60.23 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.23 Modifications to FSTDs. (a...

  11. 14 CFR 60.11 - FSTD use.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false FSTD use. 60.11 Section 60.11 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.11 FSTD use. No person may use...

  12. 14 CFR 60.9 - Additional responsibilities of the sponsor.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Additional responsibilities of the sponsor. 60.9 Section 60.9 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.9...

  13. 14 CFR 60.9 - Additional responsibilities of the sponsor.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Additional responsibilities of the sponsor. 60.9 Section 60.9 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.9...

  14. 14 CFR 60.11 - FSTD use.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false FSTD use. 60.11 Section 60.11 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.11 FSTD use. No person may use...

  15. 14 CFR 60.9 - Additional responsibilities of the sponsor.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Additional responsibilities of the sponsor. 60.9 Section 60.9 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE § 60.9...

  16. Space Qualification Testing of a Shape Memory Alloy Deployable CubeSat Antenna

    DTIC Science & Technology

    2016-09-15

    the SMA deployment in the space environment. The HCT QHA successfully passed all required NASA General Environmental Verification Standards space... NASA /JPL parabolic deployable antenna design [28] .................. 19 Figure 11. SERC and NASA /JPL parabolic antenna prototype [28...19 Figure 12. SERC and NASA /JPL parabolic antenna stowed configuration [28] ............. 20 Figure 13. JPL KaPDA antenna [29

  17. SP-100 flight qualification testing assessment

    NASA Technical Reports Server (NTRS)

    Jeanmougin, Nanette M.; Moore, Roger M.; Wait, David L.; Jacox, Michael G.

    1988-01-01

    The SP-100 is a compact space power system driven by a nuclear reactor that provides 100 kWe to the user at 200 VDC. The thermal energy generated by the nuclear reactor is converted into electrical energy by passive thermoelectric devices. Various options for tailoring the MIL-STD-1540B guidelines to the SP-100 nuclear power system are discussed. This study aids in selecting the appropriate qualification test program based on the cost, schedule, and test effectiveness of the various options.

  18. Differential labour market impacts from disability onset.

    PubMed

    Polidano, Cain; Vu, Ha

    2015-03-01

    We estimate the causal labour market impacts of disability onset by gender, age and education levels up to 4 years after onset using longitudinal data from the Household Income and Labour Dynamics Australia survey and difference-in-difference propensity score matching techniques. We find lasting negative impacts on employment, especially full-time employment, which is due more to reduced movement into full-time employment than downshifting from full-time to part-time work following onset. Those without post-school education qualifications are particularly vulnerable to the impacts of onset and are more likely to be out of work and on income support than those with qualifications up to 4 years after onset, due in part because they have greater difficulty adjusting. Copyright © 2013 John Wiley & Sons, Ltd.

  19. Radiation Effects on Optoelectronic Devices in Space Missions

    NASA Technical Reports Server (NTRS)

    Johnston, Allan H.

    2006-01-01

    Radiation degradation of optoelectronic devices is discussed, including effects on optical emitters, detectors and optocouplers. The importance of displacement damage is emphasized, including the limitations of non-ionizing energy loss (NIEL) in normalizing damage. Failures of optoelectronics in fielded space systems are discussed, along with testing and qualification methods.

  20. Locating Post-16 Professionalism: Public Spaces as Dissenting Spaces

    ERIC Educational Resources Information Center

    Dennis, Carol Azumah

    2015-01-01

    Locating post-16 professionalism explores the ways in which teachers in the UK and the USA engaged in digitally mediated communication incidentally narrate their professional selves during extended exchanges about the process of post-qualification registration. Drawing on a theoretical framework derived from participatory democracy, the study is…

  1. Performance of the GLAS Laser Transmitter in Space

    NASA Technical Reports Server (NTRS)

    Yu, Anthony W.; Afzal, Robert S.; Dallas, Joseph L.; Melak, Anthony; Mamakos, William

    2006-01-01

    The Geoscience Laser Altimeter System (GLAS), launched in January 2003, is a laser altimeter and lidar for the Earth Observing System's (EOS) ICESat mission. The laser transmitter requirements, design and qualification test results and in-flight performance for this space-based remote sensing instrument is summarized and presented.

  2. Appendange deployment mechanism for the Hubble Space Telescope program

    NASA Technical Reports Server (NTRS)

    Greenfield, H. T.

    1985-01-01

    The key requirements, a design overview, development testing (qualification levels), and two problems and their solutions resolved during the mechanism development testing phase are presented. The mechanism described herein has demonstrated its capability to deploy/restow two large Hubble Space Telescope deployable appendages in a varying but controlled manner.

  3. Qualification and issues with space flight laser systems and components

    NASA Astrophysics Data System (ADS)

    Ott, Melanie N.; Coyle, D. B.; Canham, John S.; Leidecker, Henning W., Jr.

    2006-02-01

    The art of flight quality solid-state laser development is still relatively young, and much is still unknown regarding the best procedures, components, and packaging required for achieving the maximum possible lifetime and reliability when deployed in the harsh space environment. One of the most important issues is the limited and unstable supply of quality, high power diode arrays with significant technological heritage and market lifetime. Since Spectra Diode Labs Inc. ended their involvement in the pulsed array business in the late 1990's, there has been a flurry of activity from other manufacturers, but little effort focused on flight quality production. This forces NASA, inevitably, to examine the use of commercial parts to enable space flight laser designs. System-level issues such as power cycling, operational derating, duty cycle, and contamination risks to other laser components are some of the more significant unknown, if unquantifiable, parameters that directly effect transmitter reliability. Designs and processes can be formulated for the system and the components (including thorough modeling) to mitigate risk based on the known failures modes as well as lessons learned that GSFC has collected over the past ten years of space flight operation of lasers. In addition, knowledge of the potential failure modes related to the system and the components themselves can allow the qualification testing to be done in an efficient yet, effective manner. Careful test plan development coupled with physics of failure knowledge will enable cost effect qualification of commercial technology. Presented here will be lessons learned from space flight experience, brief synopsis of known potential failure modes, mitigation techniques, and options for testing from the system level to the component level.

  4. Qualification and Issues with Space Flight Laser Systems and Components

    NASA Technical Reports Server (NTRS)

    Ott, Melanie N.; Coyle, D. Barry; Canham, John S.; Leidecker, Henning W.

    2006-01-01

    The art of flight quality solid-state laser development is still relatively young, and much is still unknown regarding the best procedures, components, and packaging required for achieving the maximum possible lifetime and reliability when deployed in the harsh space environment. One of the most important issues is the limited and unstable supply of quality, high power diode arrays with significant technological heritage and market lifetime. Since Spectra Diode Labs Inc. ended their involvement in the pulsed array business in the late 1990's, there has been a flurry of activity from other manufacturers, but little effort focused on flight quality production. This forces NASA, inevitably, to examine the use of commercial parts to enable space flight laser designs. System-level issues such as power cycling, operational derating, duty cycle, and contamination risks to other laser components are some of the more significant unknown, if unquantifiable, parameters that directly effect transmitter reliability. Designs and processes can be formulated for the system and the components (including thorough modeling) to mitigate risk based on the known failures modes as well as lessons learned that GSFC has collected over the past ten years of space flight operation of lasers. In addition, knowledge of the potential failure modes related to the system and the components themselves can allow the qualification testing to be done in an efficient yet, effective manner. Careful test plan development coupled with physics of failure knowledge will enable cost effect qualification of commercial technology. Presented here will be lessons learned from space flight experience, brief synopsis of known potential failure modes, mitigation techniques, and options for testing from the system level to the component level.

  5. Qualification and Issues with Space Flight Laser Systems and Components

    NASA Technical Reports Server (NTRS)

    Ott, Melanie N.; Coyle, D. Barry; Canham, John S.; Leidecker, Henning W.

    2006-01-01

    The art of flight quality solid-state laser development is still relatively young, and much is still unknown regarding the best procedures, components, and packaging required for achieving the maximum possible lifetime and reliability when deployed in the harsh space environment. One of the most important issues is the limited and unstable supply of quality, high power diode arrays with significant technological heritage and market lifetime. Since Spectra Diode Labs Inc. ended their involvement in the pulsed array business in the late 199O's, there has been a flurry of activity from other manufacturers, but little effort focused on flight quality production. This forces NASA, inevitably, to examine the use of commercial parts to enable space flight laser designs. System-level issues such as power cycling, operational derating, duty cycle, and contamination risks to other laser components are some of the more significant unknown, if unquantifiable, parameters that directly effect transmitter reliability. Designs and processes can be formulated for the system and the components (including thorough modeling) to mitigate risk based on the known failures modes as well as lessons learned that GSFC has collected over the past ten years of space flight operation of lasers. In addition, knowledge of the potential failure modes related to the system and the components themselves can allow the qualification testing to be done in an efficient yet, effective manner. Careful test plan development coupled with physics of failure knowledge will enable cost effect qualification of commercial technology. Presented here will be lessons learned from space flight experience, brief synopsis of known potential failure modes, mitigation techniques, and options for testing from the system level to the component level.

  6. Structural Qualification Testing of the WindSat Payload Using Sine Bursts Near Structural Resonance

    NASA Technical Reports Server (NTRS)

    Pontius, Jim; Barnes, Donald; Broduer, Steve (Technical Monitor)

    2001-01-01

    Sine burst tests are often used for structural qualification of space flight hardware. In most instances, the driving frequency of the shaker is specified far below the structure's first resonant mode, such that the entire test article sees uniform acceleration. For large structures, this limits qualification testing to lower parts of the structure, or else it over-tests the lower structure to achieve qualification of the upper structure. The WindSat payload, a 10.5 foot tall graphite/epoxy, titanium, and aluminum radiometer, experiences accelerations at the six foot diameter reflector nearly four times that at the spacecraft interface. Due to size of the payload, the number of bonded joints, and the lightweight reflector support structure design and construction, using static pull testing to qualify all of the bonded joints in the upper structure would result in large, expensive, and extensive test fixturing. Sine burst testing near the first two structural resonant modes was performed on the WindSat payload to achieve the correct load factor distribution up the stack for structural qualification. In this presentation, how finite element method (FEM) sine burst predictions were used in conjunction with low level random and sine burst tests to achieve correct qualification test load factor distribution on the WindSat payload is discussed. Also presented is the risk mitigation approach for using the uncorrelated FEM in this procedure.

  7. Laser Development for Gravitational-Wave Interferometry in Space

    NASA Technical Reports Server (NTRS)

    Numata, Kenji; Camp, Jordan

    2012-01-01

    We are reporting on our development work on laser (master oscillator) and optical amplifier systems for gravitational-wave interferometry in space. Our system is based on the mature, wave-guided optics technologies, which have advantages over bulk, crystal-based, free-space optics. We are investing in a new type of compact, low-noise master oscillator, called the planar-waveguide external cavity diode laser. We made measurements, including those of noise, and performed space-qualification tests.

  8. Back on Track: Exploring How a Further Education College Re-Motivates Learners to Re-Sit Previously Failed Qualifications at GCSE

    ERIC Educational Resources Information Center

    Anderson, Nadia; Peart, Sheine

    2016-01-01

    Underachievement at GCSE level has significant effects on an individual's life chances. Each year, around half of 16-year-olds leave school without having achieved a full level-2 qualification (five GCSEs at A*-C including English and maths). Many of these students enrol on a programme of study at local further education (FE) colleges. Recent…

  9. Conduct and Results of YF-16 RPRV Stall/Spin Drop Model Tests

    DTIC Science & Technology

    1977-04-01

    Bomb Recovery System Tests Iron Bird Recovery System Tests Captive Flights Typical Flight Operations Flight Planning and Pilot Training...helicopter tow qualification test, one model tow qualification test, three Iron Bird parachute recovery system verification tests, three captive tests...Corresponding Full-Scale YF-16 Altitude -Reference 1: Woodcock , Robert J., Some Notes on Free-Flight Model Seal- ing, AFFDL-TM-73-123-FCC, Air Force Flight

  10. [Postdoctoral lecturer thesis in medicine: academic competence or career booster?].

    PubMed

    Sorg, H; Betzler, C; Grieswald, C; Schwab, C G G; Tilkorn, D J; Hauser, J

    2016-06-01

    The postdoctoral lecturer thesis in medicine represents an essential success factor for the career of a physician; however, there is controversial discussion on whether this reflects academic competence or is more a career booster. In this context we conducted a survey among postdoctoral medical lecturers with the aim to evaluate the significance of this qualification. The online survey was performed using a questionnaire requesting biographical parameters and subjective ratings of topics concerning the postdoctoral lecturer thesis. Overall 628 questionnaires were included in the study. The significance of the postdoctoral qualification was rated high in 68.6 % and was seen to be necessary for professional advancement in 71.0 %. The chances of obtaining a full professorship after achieving a postdoctoral qualification were rated moderate to low (68.1 %); nevertheless, 92.3 % would do it again and 86.5 % would recommend it to colleagues. Accordingly, 78.8 % were against its abolishment. Wishes for reforms included standardized federal regulations, reduced dependency on professors and more transparency. The postdoctoral lecturer qualification in medicine is highly valued and the majority of responders did not want it to be abolished. Although the chances for a full professorship were only rated low, successful graduation seems to be beneficial for the career; however, there is a need for substantial structural and international changes.

  11. Space Shuttle SRM development. [Solid Rocket Motors

    NASA Technical Reports Server (NTRS)

    Brinton, B. C.; Kilminster, J. C.

    1979-01-01

    The successful static test of the fourth Development Space Shuttle Solid Rocket Motor (SRM) in February 1979 concluded the development testing phase of the SRM Project. Qualification and flight motors are currently being fabricated, with the first qualification motor to be static tested. Delivered thrust-time traces on all development motors were very close to predicted values, and both specific and total impulse exceeded specification requirements. 'All-up' static tests conducted with a solid rocket booster equipment on development motors achieved all test objectives. Transportation and support equipment concepts have been proven, baselining is complete, and component reusability has been demonstrated. Evolution of the SRM transportation support equipment, and special test equipment designs are reviewed, and development activities discussed. Handling and processing aspects of large, heavy components are described.

  12. The MICROSCOPE inertial sensor: qualification status

    NASA Astrophysics Data System (ADS)

    Santos Rodrigues, Manuel; Touboul, Pierre; Liorzou, Francoise; Bodoville, Guillaume

    The payload of the MICROSCOPE space mission embarks two pairs of test-masses, made of Platinum Rhodium alloy and Titanium alloy, that are used to perform the test of the Uni-versality of free fall, i.e. of the Equivalence Principle (EP). These cylindrical test-masses are at the core of the inertial sensors used to perform the full drag-free and attitude control of the satellite. Based on electrostatic space accelerometers developed in ONERA, the payload has been designed with challenging technologies for the electronics and for the sensor core. Following a very specific development plan, the payload is currently in the qualification phase, by being integrated after a long period of challenging accurate production and metrology. The results obtained for the driving components of the expected performance will be addressed. In particular, the micrometric metrology of the instrument core, made in gold coated silica, will be presented: the specific ultra-sonic machining processes, optimized for this production, indeed exhibit a few micrometers accuracy. Similar accuracy is obtained for the geometry of the test-masses, produced and controlled in collaboration with the PTB, Physikalisch-Technische Bundesanstalt. This accurate geometry and the specific selected shape is mandatory to balance the mass moment of inertia for gravity gradient rejection and to highly decouple the instru-ment measurement axes. The first results of the flight model electronics will be also presented demonstrating micro-volt low noise and weak thermal sensitivity in good agreement with the requirements. At last, the development status of the payload will be mentioned insisting on the coming milestones.

  13. Overview of Materials Qualification Needs for Metal Additive Manufacturing

    NASA Astrophysics Data System (ADS)

    Seifi, Mohsen; Salem, Ayman; Beuth, Jack; Harrysson, Ola; Lewandowski, John J.

    2016-03-01

    This overview highlights some of the key aspects regarding materials qualification needs across the additive manufacturing (AM) spectrum. AM technology has experienced considerable publicity and growth in the past few years with many successful insertions for non-mission-critical applications. However, to meet the full potential that AM has to offer, especially for flight-critical components (e.g., rotating parts, fracture-critical parts, etc.), qualification and certification efforts are necessary. While development of qualification standards will address some of these needs, this overview outlines some of the other key areas that will need to be considered in the qualification path, including various process-, microstructure-, and fracture-modeling activities in addition to integrating these with lifing activities targeting specific components. Ongoing work in the Advanced Manufacturing and Mechanical Reliability Center at Case Western Reserve University is focusing on fracture and fatigue testing to rapidly assess critical mechanical properties of some titanium alloys before and after post-processing, in addition to conducting nondestructive testing/evaluation using micro-computerized tomography at General Electric. Process mapping studies are being conducted at Carnegie Mellon University while large area microstructure characterization and informatics (EBSD and BSE) analyses are being conducted at Materials Resources LLC to enable future integration of these efforts via an Integrated Computational Materials Engineering approach to AM. Possible future pathways for materials qualification are provided.

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

    NASA Technical Reports Server (NTRS)

    1973-01-01

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

  15. Full Spectrum Information Operations and the Information Professional Officer Intermediate Qualification Process: Filling the Gap to Ensure the Continued Leadership of the Information Professional Community in the Area of Information Dominance

    DTIC Science & Technology

    2005-09-01

    information dominance . This thesis provides recommended line items for injection into the IP IQ in the appropriate format with discussions and definitions that address the specific line items. The thesis also provides further recommendations for the continuing improvement and refinement of the IP qualification process, especially in the area of

  16. Haine v. Leves, 7 April 1987.

    PubMed

    1987-01-01

    The Court ruled that where pupils coming from within a local community were segregated into single sex schools with differences in their curricula that resulted in a variation in educational qualification such that the school qualification of boys for tertiary education and employment was greater than that of girls, the Equal Opportunity Tribunal could conclude that the girls were being discriminated against under Section 31A of the Anti-Discrimination Act 1977. full text

  17. RTEMS CENTRE- Support and Maintenance CENTRE to RTEMS Operating System

    NASA Astrophysics Data System (ADS)

    Silva, H.; Constantino, A.; Coutunho, M.; Freitas, D.; Faustino, S.; Mota, M.; Colaço, P.; Zulianello, M.

    2008-08-01

    RTEMS stands for Real-Time Operating System for Multiprocessor Systems. It is a full featured Real Time Operating System that supports a variety of open APIs and interface standards. It provides a high performance environment for embedded applications, including a fixed-priority preemptive/non-preemptive scheduler, a comprehensive set of multitasking operations and a large range of supported architectures. Support and maintenance CENTRE to RTEMS operating system (RTEMS CENTRE) is a joint initiative of ESA-Portugal Task force, aiming to build a strong technical competence in the space flight (on- board) software, to offer support, maintenance and improvements to RTEMS. This paper provides a high level description of the current and future activities of the RTEMS CENTRE. It presents a brief description of the RTEMS operating system, a description of the tools developed and distributed to the community [1] and the improvements to be made to the operating system, including facilitation for the qualification of RTEMS (4.8.0) [2] for the space missions.

  18. Results of 2007 test beam of AMS-02 Electromagnetic Calorimeter

    NASA Astrophysics Data System (ADS)

    di Falco, Stefano

    2010-01-01

    The AMS-02 experiment will be delivered by the Space Shuttle Discovery to the ISS in summer 2010. The main goals of the experiment are search for antimatter and dark matter, high precision measurement of charged cosmic ray spectra and fluxes and study of gamma rays, in the GeV to TeV energy range. In AMS-02 the Electromagnetic Calorimeter (ECAL) is required to measure e+,e- and gamma energy and to discriminate electromagnetic showers from hadronic cascades. ECAL is based on a lead/scintillating fiber sandwich, providing a 3D imaging reconstruction of the showers. The electronics equipping the detector has low power consumption, low noise, large dynamic range readout and full double redundancy. The calorimeter successfully got through several space qualification tests concerning the mechanical and thermal stability, the electromagnetic compatibility and radiation hardness. The ECAL Flight Model was calibrated during Summer 2007 in a test beam at CERN, using 6-250 GeV electron and proton beams: angular and energy resolutions, obtained from these data, are reported.

  19. Booster Test for Space Launch System Rocket

    NASA Image and Video Library

    2016-06-26

    The test area where the second and final qualification motor (QM-2) test for the Space Launch System’s booster is seen Sunday, June 26, 2016, at Orbital ATK Propulsion Systems test facilities in Promontory, Utah. The test is scheduled for Tuesday, June 28 at 10:05 a.m. EDT (8:05 a.m. MDT). Photo Credit: (NASA/Bill Ingalls)

  20. Preliminary Report: Issues in selection and training for long duration space flight

    NASA Technical Reports Server (NTRS)

    Akins, F. R.

    1979-01-01

    Based on previous experience with crew selection, three important avenues of consideration for future missions are discussed: technical qualifications and expertise; medical fitness and ability to tolerate the various conditions of space; and psychological considerations including personality structure, motivation, intelligence, leadership potential, group compatibility, etc. Primary emphasis was given to the psychological considerations.

  1. OSIRIS-REx Visible And Infrared Spectrometer - OVIRS

    NASA Technical Reports Server (NTRS)

    Hair, Jason

    2016-01-01

    Goddard Space Flight Center: Overall Instrument Responsibility; Instrument Scientist and Deputy Instrument Scientist; Management Systems Engineering; Mechanical Hardware; Harness Assemblies; SIDECAR Assembly Code; OVIRS Integration and Environmental Qualification; OVIRS Performance Testing, Calibration and Characterization.

  2. REACT: Resettable Hold Down and Release Actuator for Space Applications

    NASA Astrophysics Data System (ADS)

    Nava, Nestor; Collado, Marcelo; Cabás, Ramiro

    2014-07-01

    A new HDRA based on SMA technology, called REACT, has been designed for development of loads and appendixes in space applications. This design involves a rod supported by spheres that block its axial movement during a preload application. The rod shape allows misalignment and blocks the rotation around axial axis for a proper installation of the device. Because of the high preload requirements for this type of actuators, finite element analysis (FEA) has been developed in order to check the structure resistance. The results of the FEA have constrained the REACT design, in terms of dimensions, materials, and shape of the mechanical parts. A complete test campaign for qualification of REACT is proposed. Several qualification models are intended to be built for testing in parallel. Therefore, it is a way to demonstrate margins which allows getting some statistics.

  3. Support for life-cycle product reuse in NASA's SSE

    NASA Technical Reports Server (NTRS)

    Shotton, Charles

    1989-01-01

    The Software Support Environment (SSE) is a software factory for the production of Space Station Freedom Program operational software. The SSE is to be centrally developed and maintained and used to configure software production facilities in the field. The PRC product TTCQF provides for an automated qualification process and analysis of existing code that can be used for software reuse. The interrogation subsystem permits user queries of the reusable data and components which have been identified by an analyzer and qualified with associated metrics. The concept includes reuse of non-code life-cycle components such as requirements and designs. Possible types of reusable life-cycle components include templates, generics, and as-is items. Qualification of reusable elements requires analysis (separation of candidate components into primitives), qualification (evaluation of primitives for reusability according to reusability criteria) and loading (placing qualified elements into appropriate libraries). There can be different qualifications for different installations, methodologies, applications and components. Identifying reusable software and related components is labor-intensive and is best carried out as an integrated function of an SSE.

  4. Integration and Environmental Qualification Testing of Spacecraft Structures in Support of the Naval Postgraduate School CubeSat Launcher Program

    DTIC Science & Technology

    2009-06-01

    2 3. Space Access Challenges to the CubeSat Community........ 3 B. NPSCUL/NPSCUL-LITE PROGRAM HISTORY TO DATE...Astronautics, AIAA Space 2008 Conference and Exhibition, 2008. 3 3. Space Access Challenges to the CubeSat Community In less than ten years since... challenges to space access for CubeSats.5 Launch of a CubeSat aboard US launch vehicles from US launch facilities would allow CubeSats of a sensitive nature

  5. Clock Technology Development in the Laser Cooling and Atomic Physics (LCAP) Program

    NASA Technical Reports Server (NTRS)

    Seidel, Dave; Thompson, R. J.; Klipstein, W. M.; Kohel, J.; Maleki, L.

    2000-01-01

    This paper presents the Laser Cooling and Atomic Physics (LCAP) program. It focuses on clock technology development. The topics include: 1) Overview of LCAP Flight Projects; 2) Space Clock 101; 3) Physics with Clocks in microgravity; 4) Space Clock Challenges; 5) LCAP Timeline; 6) International Space Station (ISS) Science Platforms; 7) ISS Express Rack; 8) Space Qualification of Components; 9) Laser Configuration; 10) Clock Rate Comparisons: GPS Carrier Phase Frequency Transfer; and 11) ISS Model Views. This paper is presented in viewgraph form.

  6. Continuous Improvement in Battery Testing at the NASA/JSC Energy System Test Area

    NASA Technical Reports Server (NTRS)

    Boyd, William; Cook, Joseph

    2003-01-01

    The Energy Systems Test Area (ESTA) at the Lyndon B. Johnson Space Center in Houston, Texas conducts development and qualification tests to fulfill Energy System Division responsibilities relevant to ASA programs and projects. EST A has historically called upon a variety of fluid, mechanical, electrical, environmental, and data system capabilities spread amongst five full-service facilities to test human and human supported spacecraft in the areas of propulsion systems, fluid systems, pyrotechnics, power generation, and power distribution and control systems. Improvements at ESTA are being made in full earnest of offering NASA project offices an option to choose a thorough test regime that is balanced with cost and schedule constraints. In order to continue testing of enabling power-related technologies utilized by the Energy System Division, an especially proactive effort has been made to increase the cost effectiveness and schedule responsiveness for battery testing. This paper describes the continuous improvement in battery testing at the Energy Systems Test Area being made through consolidation, streamlining, and standardization.

  7. Space reactor fuel element testing in upgraded TREAT

    NASA Astrophysics Data System (ADS)

    Todosow, M.; Bezler, P.; Ludewig, H.; Kato, W. Y.

    The testing of candidate fuel elements at prototypic operating conditions with respect to temperature, power density, hydrogen coolant flow rate, etc.; a crucial component in the development and qualification of nuclear rocket engines based on the Particle Bed Reactor (PBR); NERVA-derivative; and other concepts are discussed. Such testing may be performed at existing reactors, or at new facilities. A scoping study has been performed to assess the feasibility of testing PBR based fuel elements at the TREAT reactor. Initial results suggest that full-scale PBR elements could be tested at an average energy deposition of approximately 60-80 MW-s/L in the current TREAT reactor. If the TREAT reactor was upgraded to include fuel elements with a higher temperature limit, average energy deposition of approximately 100 MW/L may be achievable.

  8. Space reactor fuel element testing in upgraded TREAT

    NASA Astrophysics Data System (ADS)

    Todosow, Michael; Bezler, Paul; Ludewig, Hans; Kato, Walter Y.

    1993-01-01

    The testing of candidate fuel elements at prototypic operating conditions with respect to temperature, power density, hydrogen coolant flow rate, etc., is a crucial component in the development and qualification of nuclear rocket engines based on the Particle Bed Reactor (PBR), NERVA-derivative, and other concepts. Such testing may be performed at existing reactors, or at new facilities. A scoping study has been performed to assess the feasibility of testing PBR based fuel elements at the TREAT reactor. Initial results suggests that full-scale PBR elements could be tested at an average energy deposition of ˜60-80 MW-s/L in the current TREAT reactor. If the TREAT reactor was upgraded to include fuel elements with a higher temperture limit, average energy deposition of ˜100 MW/L may be achievable.

  9. Assembly of 5.5-Meter Diameter Developmental Barrel Segments for the Ares I Upper Stage

    NASA Technical Reports Server (NTRS)

    Carter, Robert W.

    2011-01-01

    Full scale assembly welding of Ares I Upper Stage 5.5-Meter diameter cryogenic tank barrel segments has been performed at the Marshall Space Flight Center (MSFC). One full-scale developmental article produced under the Ares 1 Upper Stage project is the Manufacturing Demonstration Article (MDA) Barrel. This presentation will focus on the welded assembly of this barrel section, and associated lessons learned. Among the MDA articles planned on the Ares 1 Program, the Barrel was the first to be completed, primarily because the process of manufacture from piece parts (barrel panels) utilized the most mature friction stir process planned for use on the Ares US program: Conventional fixed pin Friction Stir Welding (FSW). This process is in use on other space launch systems, including the Shuttle s External Tank, the Delta IV common booster core, the Delta II, and the Atlas V rockets. The goals for the MDA Barrel development were several fold: 1) to prove out Marshall Space Flight Center s new Vertical Weld Tool for use in manufacture of cylindrical barrel sections, 2) to serve as a first run for weld qualification to a new weld specification, and 3) to provide a full size cylindrical section for downstream use in precision cleaning and Spray-on Foam Insulation development. The progression leading into the welding of the full size barrel included sub scale panel welding, subscale cylinder welding, a full length confidence weld, and finally, the 3 seamed MDA barrel processing. Lessons learned on this MDA program have been carried forward into the production tooling for the Ares 1 US Program, and in the use of the MSFC VWT in processing other large scale hardware, including two 8.4 meter diameter Shuttle External Tank barrel sections that are currently being used in structural analysis to validate shell buckling models.

  10. Design and Qualification of the AMS-02 Flight Cryocoolers

    NASA Technical Reports Server (NTRS)

    Shirey, Kimberly; Banks,Stuart; Boyle, Rob; Unger, Reuven

    2005-01-01

    Four commercial Sunpower M87N Stirling-cycle cryocoolers will be used to extend the lifetime of the Alpha Magnetic Spectrometer-02 (AMS-02) experiment. The cryocoolers will be mounted to the AMS-02 vacuum case using a structure that will thermally and mechanically decouple the cryocooler from the vacuum case. This paper discusses modifications of the Sunpower M87N cryocooler to make it acceptable for space flight applications and suitable for use on AMS-02. Details of the flight model qualification test program are presented. AMS-02 is a state-of-the-art particle physics detector containing a large superfluid helium-cooled superconducting magnet. Highly sensitive detector plates inside the magnet measure a particle's speed, mass, charge, and direction. The AMS-02 experiment, which will be flown as an attached payload on the International Space Station, will study the properties and origin of cosmic particles and nuclei including antimatter and dark matter. Two engineering model cryocoolers have been under test at NASA Goddard since November 2001. Qualification testing of the engineering model cryocooler bracket assembly including random vibration and thermal vacuum testing was completed at the end of April 2005. The flight cryocoolers were received in December 2003. Acceptance testing of the flight cryocooler bracket assemblies began in May 2005 .

  11. Techniques for control of long-term reliability of complex integrated circuits. I - Reliability assurance by test vehicle qualification.

    NASA Technical Reports Server (NTRS)

    Van Vonno, N. W.

    1972-01-01

    Development of an alternate approach to the conventional methods of reliability assurance for large-scale integrated circuits. The product treated is a large-scale T squared L array designed for space applications. The concept used is that of qualification of product by evaluation of the basic processing used in fabricating the product, providing an insight into its potential reliability. Test vehicles are described which enable evaluation of device characteristics, surface condition, and various parameters of the two-level metallization system used. Evaluation of these test vehicles is performed on a lot qualification basis, with the lot consisting of one wafer. Assembled test vehicles are evaluated by high temperature stress at 300 C for short time durations. Stressing at these temperatures provides a rapid method of evaluation and permits a go/no go decision to be made on the wafer lot in a timely fashion.

  12. Evaluation and qualification of commercial opto-electronic components for the MOHA subsystem in ESA's SMOS mission

    NASA Astrophysics Data System (ADS)

    Gutierrez, Francisco; Cordero, Enrique; Sánchez, Carolina; Barbero, Juan; Mosberger, Martin; Boehle, Peter; Tornell, Manuel; Lundmark, Karin

    2017-11-01

    A dedicated evaluation and qualification campaign has been performed on several optical COTS components in order to use them on ESA's SMOS mission. The evaluation phase consisted of a set of critical tests and analyses and led to the selection of the flight lot component. After selection of the components, one lot of each component has been qualified for the SMOS mission. The overall approach is presented together with a summary of all activities performed. The whole task has been handled in a joint effort between ESA, EADS CASA Espacio (prime contractor), Contraves Space AG (MOHA subsystem), TECNOLOGICA SA (component qualification experts) and the respective manufacturers, each party providing their specific know-how. Test results are presented and the issues discovered and lessons learned are addressed. Special emphasis is given to particular tests for which dedicated setups had to be designed due to the unavailability of standard equipment.

  13. 77 FR 55837 - Information Collection Being Reviewed by the Federal Communications Commission

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-09-11

    ..., Satellite Network Stations and Space Stations. Form No.: FCC Form 312; Schedule S. Type of Review: Extension... determine the technical and legal qualifications of applicants or licensees to operate a station, transfer...

  14. Rover Low Gain Antenna Qualification for Deep Space Thermal Environments

    NASA Technical Reports Server (NTRS)

    Ramesham, Rajeshuni; Amaro, Luis R.; Brown, Paula R.; Usiskin, Robert; Prater, Jack L.

    2013-01-01

    A method to qualify the Rover Low Gain Antenna (RLGA) for use during the Mars Science Laboratory (MSL) mission has been devised. The RLGA antenna must survive all ground operations, plus the nominal 670 Martian sol mission that includes the summer and winter seasons of the Mars thermal environment. This qualification effort was performed to verify that the RLGA design, its bonding, and packaging processes are adequate. The qualification test was designed to demonstrate a survival life of three times more than all expected ground testing, plus a nominal 670 Martian sol missions. Baseline RF tests and a visual inspection were performed on the RLGA hardware before the start of the qualification test. Functional intermittent RF tests were performed during thermal chamber breaks over the course of the complete qualification test. For the return loss measurements, the RLGA antenna was moved to a test area. A vector network analyzer was calibrated over the operational frequency range of the antenna. For the RLGA, a simple return loss measurement was performed. A total of 2,010 (3 670 or 3 times mission thermal cycles) thermal cycles was performed. Visual inspection of the RLGA hardware did not show any anomalies due to the thermal cycling. The return loss measurement results of the RLGA antenna after the PQV (Package Qualification and Verification) test did not show any anomalies. The antenna pattern data taken before and after the PQV test at the uplink and downlink frequencies were unchanged. Therefore, the developed design of RLGA is qualified for a long-duration MSL mission.

  15. Fabrication and Qualification of Coated Chip-on-Board Technology for Miniaturized Space Systems

    NASA Technical Reports Server (NTRS)

    Maurer, R. H.; Le, B. Q.; Nhan, E.; Lew, A. L.; Darrin, M. Ann Garrison

    1997-01-01

    The results of a study carried out in order to manufacture and verify the quality of chip-on-board (COB) packaging technology are presented. The COB, designed for space applications, was tested under environmental stresses, temperature cycling, and temperature-humidity-bias. Both robustness in space applications and in environmental protection on the ground-complete reliability without hermeticity were searched for. The epoxy-parylene combinations proved to be superior to other materials tested.

  16. Cryogenic wheel mechanisms for the Mid-Infrared Instrument (MIRI) of the James Webb Space Telescope (JWST): detailed design and test results from the qualification program

    NASA Astrophysics Data System (ADS)

    Krause, O.; Birkmann, S.; Blümchen, T.; Böhm, A.; Ebert, M.; Grözinger, U.; Henning, Th.; Hofferbert, R.; Huber, A.; Lemke, D.; Rohloff, R.-R.; Scheithauer, S.; Gross, T.; Luichtel, G.; Stein, C.; Stott, R.; Übele, M.; Amiaux, J.; Auguères, J.-L.; Glauser, A.; Zehnder, A.; Meijers, M.; Jager, R.; Parr-Burrman, P.; Wright, G.

    2008-07-01

    The Mid-Infrared Instrument (MIRI) of the James Webb Space Telescope, scheduled for launch in 2013, will provide a variety of observing modes such as broad/narrow-band imaging, coronagraphy and low/medium resolution spectroscopy. One filter wheel and two dichroic-grating wheel mechanisms allow to configure the instrument between the different observing modes and wavelength ranges. The main requirements for the three mechanisms with up to 18 positions on the wheel include: (1) reliable operation at T ~ 7 K, (2) optical precision, (3) low power dissipation, (4) high vibration capability, (5) functionality at 6 K < T < 300 K and (6) long lifetime (5-10 years). To meet these stringent requirement, a space-proven mechanism design based on the European ISO mission and consisting of a central bearing carrying the optical wheels, a central torque motor for wheel actuation, a ratchet system for precise and powerless positioning and a magnetoresistive position sensor has been selected. We present here the detailed design of the flight models and report results from the extensive component qualification.

  17. Thermal vacuum life test facility for radioisotope thermoelectric generators

    NASA Astrophysics Data System (ADS)

    Deaton, R. L.; Goebel, C. J.; Amos, W. R.

    In the late 1970's, the Department of Energy (DOE) assigned Monsanto Research Corporation, Mound Facility, now operated by EG and G Mound Applied Technologies, the responsibility for assembling and testing General Purpose Heat Source (GPHS) radioisotope thermoelectric generators (RTGs). Assembled and tested were five RTGs, which included four flight units and one non-flight qualification unit. Figure 1 shows the RTG, which was designed by General Electric AstroSpace Division (GE/ASD) to produce 285 W of electrical power. A detailed description of the processes for RTG assembly and testing is presented by Amos and Goebel (1989). The RTG performance data are described by Bennett, et al., (1986). The flight units will provide electrical power for the National Aeronautics and Space Administration's (NASA) Galileo mission to Jupiter (two RTGs) and the joint NASA/European Space Agency (ESA) Ulysses mission to study the polar regions of the sun (one RTG). The remaining flight unit will serve as the spare for both missions, and a non-flight qualification unit was assembled and tested to ensure that performance criteria were adequately met.

  18. Space qualification of an automotive microcontroller for the DREAMS-P/H pressure and humidity instrument on board the ExoMars 2016 Schiaparelli lander

    NASA Astrophysics Data System (ADS)

    Nikkanen, T.; Schmidt, W.; Harri, A.-M.; Genzer, M.; Hieta, M.; Haukka, H.; Kemppinen, O.

    2015-10-01

    Finnish Meteorological Institute (FMI) has developed a novel kind of pressure and humidity instrument for the Schiaparelli Mars lander, which is a part of the ExoMars 2016 mission of the European Space Agency (ESA) [1]. The DREAMS-P pressure instrument and DREAMS-H humidity instrument are part of the DREAMS science package on board the lander. DREAMS-P (seen in Fig. 1 and DREAMS-H were evolved from earlier planetary pressure and humidity instrument designs by FMI with a completely redesigned control and data unit. Instead of using the conventional approach of utilizing a space grade processor component, a commercial off the shelf microcontroller was selected for handling the pressure and humidity measurements. The new controller is based on the Freescale MC9S12XEP100 16-bit automotive microcontroller. Coordinated by FMI, a batch of these microcontroller units (MCUs) went through a custom qualification process in order to accept the component for spaceflight on board a Mars lander.

  19. The state-of-the-art of dc power distribution systems/components for space applications

    NASA Technical Reports Server (NTRS)

    Krauthamer, S.

    1988-01-01

    This report is a survey of the state of the art of high voltage dc systems and components. This information can be used for consideration of an alternative secondary distribution (120 Vdc) system for the Space Station. All HVdc components have been prototyped or developed for terrestrial, aircraft, and spacecraft applications, and are applicable for general space application with appropriate modification and qualification. HVdc systems offer a safe, reliable, low mass, high efficiency and low EMI alternative for Space Station secondary distribution.

  20. FRTL-5 experiment during ENEIDE mission

    NASA Astrophysics Data System (ADS)

    Meli, A.; Perrella, G.; Toller, M.; Zambito, A. M.; Spelat, R.; Moretti, M.; Ferro, F.; Curcio, F.; Ambesi-Impiombato, F. S.

    2007-09-01

    The FRTL-5 experiment was performed during the 10 day Italian Soyuz Mission "ENEIDE" (from April 15 to April 25, 2005) on the International Space Station. The main objectives were: 1) the validation of the FRTL5 cells as a biological system to evaluate space environment effects; 2) the investigation of the space environment-related pathophysiological mechanisms of cellular damage and/or behaviour; 3) to verify if fastgrowing cells could be differently sensitive to space environment-related effects as compared to cells in physiological standby. Because of the limited available space in the dedicated facilities and the restrictive requirements imposed by ESA, RSA and NASA, and because no pre-qualified equipment existed, all of the equipment and the procedures have been subjected to structural failure test and to severe qualification tests. Results were: 1) all the qualification procedures and tests were successful 2) Overall cell number is lower in the cultures exposed to space environment as compared to the controls reproducing the temperature conditions during the ENEIDE mission; 3) This phenomenon is most likely related to a slower growth rate in proliferative state; 4) This slow growth rate is: a) reversible, as demonstrated by the results of the growth curves, the plating and cloning efficiencies measured on the samples once they have been returned to our laboratory in Udine; b) mostly related to space effects as indicated by additional control in a clinostat. More experiments of this kind are needed to verify and validate these data and to investigate the molecular mechanisms underling the phenomenon.

  1. Cesic: optomechanical technology last development results and new HBCesic highly light weighted space mirror development including corrective function 7th international conference on space optics, october 2008

    NASA Astrophysics Data System (ADS)

    Devilliers, Christophe; Kroedel, Mathias

    2017-11-01

    Thales-Alenia-Space and ECM has developed a new SiC ceramic composite to produce very lightweight space mirrors and structure. Cesicmade by ECM has been selected for its own intrinsic properties ( high specific Young modulus, high conductivity , low CTE, high strength for a ceramics) and its large manufacturing capabilities. Recently a full monolithic space instrument for earth observation, with a monolithic Cesicstructure and with Cesicmirrors has been designed, manufactured and space qualified and is now ready for launch. The Cesictelescope assembly has been tested under shock environment, vibration loads, and full qualification thermal environment. All these qualification tests were done directly on the flight model. Extensive development has been also performed to design, size, manufacture and test a very light weight reflector shell made as a single part. This 1 meter reflective shell has an areal density of less than 10 Kg/m2 has been manufactured with its surface grounded to the bi parabolic shape. Such challenging areal density has requested a very thin skin associated with a ribs thickness of less than 2mm. In order to demonstrate the high stability and strength of Cesicthe reflector has been tested successfully under very aggressive environment up to 350°C and also an acoustic test with flight representative levels was successfully performed. To produce future very lightweight space mirrors ECM develop with the support of Thales-Alenia-Space since some years an improved version of Cesicceramic, called HB-Cesic©. HB-Cesicmade by ECM is developed for its higher intrinsic properties, Young modulus, strength and especially its direct polishing capabilities down to 3 nm micro-roughness. One of the major targets for this development was also to overcome size limitations of the C/C raw material of currently around 1x1 m to produce mirror up to 3,5 m diameter out of a single C/C raw material block. Under ESA study a 600 mm mirror with a surface density of only 18 Kg/m2 has been designed, sized and manufactured and is currently under polishing at SESO. The polishing to a micro-roughness of far less than 20 nm RMS without expensive overcoatings has been already validated on mirrors up to 800 mm. This 600 mm mirror will be polished to a WFE of less than 20 nm, and afterwards the mirror will be tested under cryogenic environment to measure the WFE evolution between ambient and cryo. The mirror is equipped with a system for focus and astigmatism modification. During the cryo test this system will be activated at cryo temperature to also demonstrate the function of this system. This correction system is developed for future large mirrors for interferometric nulling or aperture synthesis missions like the Darwin mission . For such missions very large and very lightweight mirrors up to 3,5 m diameter with an areal density of less than 25 Kg/m2 are required and thank to the HBCesictechnology such performance is now feasible.

  2. Thin film cell development workshop report

    NASA Technical Reports Server (NTRS)

    Woodyard, James R.

    1991-01-01

    The Thin Film Development Workshop provided an opportunity for those interested in space applications of thin film cells to debate several topics. The unique characteristics of thin film cells as well as a number of other issues were covered during the discussions. The potential of thin film cells, key research and development issues, manufacturing issues, radiation damage, substrates, and space qualification of thin film cells were discussed.

  3. Booster Test for Space Launch System Rocket

    NASA Image and Video Library

    2016-06-26

    The test area where the second and final qualification motor (QM-2) test for the Space Launch System’s booster is seen through the window of a camera bunker, Sunday, June 26, 2016, at Orbital ATK Propulsion Systems test facilities in Promontory, Utah. The test is scheduled for Tuesday, June 28 at 10:05 a.m. EDT (8:05 a.m. MDT). Photo Credit: (NASA/Bill Ingalls)

  4. Parts Engineering Experiences, Philosophies and Trends

    NASA Technical Reports Server (NTRS)

    Shaw, Harry; Day, John H. (Technical Monitor)

    2000-01-01

    This document is the presentation viewgraphs of the NASA presentations to NASDA, outlining the philosophy and trends of the experiences with engineering parts. Included in the presentations: are (1) the assurance of COTS boards for Space flight, and (2) Peer Review for Ice, Cloud and land Elevation Satellite (ICESat) GPS flight receivers EEE parts. The emphasis is on the methods for qualification of available parts for space flight.

  5. An Initiative Toward Reliable Long-Duration Operation of Diode Lasers in Space

    NASA Technical Reports Server (NTRS)

    Tratt, David M.; Amzajerdian, Farzin; Stephen, Mark A.; Shapiro, Andrew A.

    2006-01-01

    This viewgraph presentation reviews the workings of the Laser Diode Arrays (LDA) working group. The group facilitates focused interaction between the LDA user and provider communities and it will author standards document for the specification and qualification of LDA's for operation in the space environment. It also reviews the NASA test and evaluation facilities that are available to the community.

  6. The variable polarity plasma arc welding process: Its application to the Space Shuttle external tank

    NASA Technical Reports Server (NTRS)

    Nunes, A. C., Jr.; Bayless, O. E., Jr.; Jones, C. S., III; Munafo, A. P.; Wilson, W. A.

    1983-01-01

    The technical history of the variable polarity plasma arc (VPPA) welding process being introduced as a partial replacement for the gas shielded tungsten arc process in assembly welding of the space shuttle external tank is described. Interim results of the weld strength qualification studies, and plans for further work on the implementation of the VPPA process are included.

  7. 14 CFR 61.195 - Flight instructor limitations and qualifications.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... that flight instructor has determined the student's flight preparation, planning, equipment, and... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Flight instructor limitations and... TRANSPORTATION (CONTINUED) AIRMEN CERTIFICATION: PILOTS, FLIGHT INSTRUCTORS, AND GROUND INSTRUCTORS Flight...

  8. 14 CFR 61.195 - Flight instructor limitations and qualifications.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... that flight instructor has determined the student's flight preparation, planning, equipment, and... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Flight instructor limitations and... TRANSPORTATION (CONTINUED) AIRMEN CERTIFICATION: PILOTS, FLIGHT INSTRUCTORS, AND GROUND INSTRUCTORS Flight...

  9. 14 CFR 61.195 - Flight instructor limitations and qualifications.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... that flight instructor has determined the student's flight preparation, planning, equipment, and... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Flight instructor limitations and... TRANSPORTATION (CONTINUED) AIRMEN CERTIFICATION: PILOTS, FLIGHT INSTRUCTORS, AND GROUND INSTRUCTORS Flight...

  10. 14 CFR 61.195 - Flight instructor limitations and qualifications.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... that flight instructor has determined the student's flight preparation, planning, equipment, and... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Flight instructor limitations and... TRANSPORTATION (CONTINUED) AIRMEN CERTIFICATION: PILOTS, FLIGHT INSTRUCTORS, AND GROUND INSTRUCTORS Flight...

  11. 14 CFR 61.195 - Flight instructor limitations and qualifications.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... that flight instructor has determined the student's flight preparation, planning, equipment, and... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Flight instructor limitations and... TRANSPORTATION (CONTINUED) AIRMEN CERTIFICATION: PILOTS, FLIGHT INSTRUCTORS, AND GROUND INSTRUCTORS Flight...

  12. NASA SLS Booster Nozzle Plug Pieces Fly During Test

    NASA Image and Video Library

    2016-06-28

    On June 28, a test version of the booster that will help power NASA's new rocket, the Space Launch System, fired up at nearly 6,000 degrees Fahrenheit for a successful, two-minute qualification test at Orbital ATK's test facilities in Promontory, Utah. This video shows the booster's nozzle plug intentionally breaking apart. The smoky ring coming off the booster is condensed water vapor created by a pressure difference between the motor gas and normal air. The nozzle plug is an environmental barrier to prevent heat, dust and moisture from getting inside the booster before it ignites. The plug isn't always part of a static test but was included on this one due to changes made to the hardware. The foam on the plug is denser than previous NASA launch vehicles, as the engines are now in the same plane as the boosters. A numbered grid was placed on the exterior of the plug before the test so the pieces retrieved could support plug breakup assessment and reconstruction. Along with video, collecting the pieces helps determine the size and speed of them when they break apart. Nozzle plug pieces were found as far as 1,500 to 2,000 feet away from the booster. This is the last full-scale qualification test for the booster before the first, uncrewed flight of SLS with the Orion spacecraft in 2018.

  13. Performance study of the gamma-ray bursts polarimeter POLAR

    NASA Astrophysics Data System (ADS)

    Sun, J. C.; Wu, B. B.; Bao, T. W.; Batsch, T.; Bernasconi, T.; Britvitch, I.; Cadoux, F.; Cernuda, I.; Chai, J. Y.; Dong, Y. W.; Gauvin, N.; Hajdas, W.; He, J. J.; Kole, M.; Kong, M. N.; Kong, S. W.; Lechanoine-Leluc, C.; Li, Lu; Liu, J. T.; Liu, X.; Marcinkowski, R.; Orsi, S.; Pohl, M.; Produit, N.; Rapin, D.; Rutczynska, A.; Rybka, D.; Shi, H. L.; Song, L. M.; Szabelski, J.; Wang, R. J.; Wen, X.; Xiao, H. L.; Xiong, S. L.; Xu, H. H.; Xu, M.; Zhang, L.; Zhang, L. Y.; Zhang, S. N.; Zhang, X. F.; Zhang, Y. J.; Zwolinska, A.

    2016-07-01

    The Gamma-ray Burst Polarimeter-POLAR is a highly sensitive detector which is dedicated to the measurement of GRB's polarization with a large effective detection area and a large field of view (FOV). The optimized performance of POLAR will contribute to the capture and measurement of the transient sources like GRBs and Solar Flares. The detection energy range of POLAR is 50 keV 500 keV, and mainly dominated by the Compton scattering effect. POLAR consists of 25 detector modular units (DMUs), and each DMU is composed of low Z material Plastic Scintillators (PS), multi-anode photomultipliers (MAPMT) and multi-channel ASIC Front-end Electronics (FEE). POLAR experiment is an international collaboration project involving China, Switzerland and Poland, and is expected to be launched in September in 2016 onboard the Chinese space laboratory "Tiangong-2 (TG-2)". With the efforts from the collaborations, POLAR has experienced the Demonstration Model (DM) phase, Engineering and Qualification Model (EQM) phase, Qualification Model (QM) phase, and now a full Flight Model (FM) of POLAR has been constructed. The FM of POLAR has passed the environmental acceptance tests (thermal cycling, vibration, shock and thermal vacuum tests) and experienced the calibration tests with both radioactive sources and 100% polarized Gamma-Ray beam at ESRF after its construction. The design of POLAR, Monte-Carlo simulation analysis, as well as the performance test results will all be introduced in this paper.

  14. Qualification flight tests of the Viking decelerator system.

    NASA Technical Reports Server (NTRS)

    Moog, R. D.; Bendura, R. J.; Timmons, J. D.; Lau, R. A.

    1973-01-01

    The Balloon Launched Decelerator Test (BLDT) series conducted at White Sands Missile Range (WSMR) during July and August of 1972 flight qualified the NASA Viking '75 decelerator system at conditions bracketing those expected for Mars. This paper discusses the decelerator system design requiremnts, compares the test results with prior work, and discusses significant considerations leading to successful qualification in earth's atmosphere. The Viking decelerator system consists of a single-stage mortar-deployed 53-foot nominal diameter disk-gap-band parachute. Full-scale parachutes were deployed behind a full-scale simulated Viking vehicle at Mach numbers from 0.47 to 2.18 and dynamic pressures from 6.9 to 14.6 psf. Analyses show that the system is qualified with sufficient margin to perform successfully for the Viking mission.

  15. Back-illuminated large area frame transfer CCDs for space-based hyper-spectral imaging applications

    NASA Astrophysics Data System (ADS)

    Philbrick, Robert H.; Gilmore, Angelo S.; Schrein, Ronald J.

    2016-07-01

    Standard offerings of large area, back-illuminated full frame CCD sensors are available from multiple suppliers and they continue to be commonly deployed in ground- and space-based applications. By comparison the availability of large area frame transfers CCDs is sparse, with the accompanying 2x increase in die area no doubt being a contributing factor. Modern back-illuminated CCDs yield very high quantum efficiency in the 290 to 400 nm band, a wavelength region of great interest in space-based instruments studying atmospheric phenomenon. In fast framing (e.g. 10 - 20 Hz), space-based applications such as hyper-spectral imaging, the use of a mechanical shutter to block incident photons during readout can prove costly and lower instrument reliability. The emergence of large area, all-digital visible CMOS sensors, with integrate while read functionality, are an alternative solution to CCDs; but, even after factoring in reduced complexity and cost of support electronics, the present cost to implement such novel sensors is prohibitive to cost constrained missions. Hence, there continues to be a niche set of applications where large area, back-illuminated frame transfer CCDs with high UV quantum efficiency, high frame rate, high full well, and low noise provide an advantageous solution. To address this need a family of large area frame transfer CCDs has been developed that includes 2048 (columns) x 256 (rows) (FT4), 2048 x 512 (FT5), and 2048 x 1024 (FT6) full frame transfer CCDs; and a 2048 x 1024 (FT7) split-frame transfer CCD. Each wafer contains 4 FT4, 2 FT5, 2 FT6, and 2 FT7 die. The designs have undergone radiation and accelerated life qualification and the electro-optical performance of these CCDs over the wavelength range of 290 to 900 nm is discussed.

  16. The BepiColombo Spacecraft: The Mercury Transfer Module Structure Qualification Test Campaign Description

    NASA Astrophysics Data System (ADS)

    Martin Zurdo, M. J.

    2012-07-01

    The BepiColombo is a space mission to Mercury (ESA in cooperation with Japan Aerospace Exploration Agency). The spacecraft consist of three different structures: two orbiters responsible for the scientific mission (MPO and MMO) and one service module, Mercury Transfer Module (MTM), which provides propulsion and services during the journey to Mercury. Taking into account only the MTM structure, the companies involved are ASTRIUM GERMANY acting as the prime contractor and ASTRIUM UK acting as the co- prime contractor company. EADS CASA Espacio (ECE) in Spain is the company responsible for the final design, manufacturing and qualification of the MTM structure. The test campaign specimen is the MTM core structure, which corresponds to the central cone with the structure floors, shear panels and tank support structure. This test campaign qualifies the primary load path and its primary interfaces; the rest of the MTM structure is qualified by system level vibration test. In order to qualify the MTM structure, three different kinds of qualification tests have been performed: stiffness test, global strength test and local tests in different specific areas. The most relevant test during the campaign is the global strength test case, in which several external loads are introduced (different interfaces) simulating the load introduction for a selected critical flight case. There are two important items in the qualification test campaign: 1. The instrumentation of the structure, with two main functions: to control the specimen under test loads, and to demonstrate the qualification of the structure. 2. The set-up structure, designed by ECE to allow the correct load introduction on each testing case during the whole test campaign. This paper describes the MTM structure test campaign from the definition of the loads applied in each test to the qualification of the complete structure.

  17. Associations between contractual status, part-time work, and intent to leave among professional caregivers for older people: results of a national cross-sectional survey in Japan.

    PubMed

    Kachi, Yuko; Inoue, Kazuo; Toyokawa, Satoshi

    2010-08-01

    Despite a growing number of studies on leaving the organization or long-term care among professional caregivers for older people, little is known about the impact of types of employment on leaving. To examine the association between the type of employment and intent to leave among Japanese professional caregivers. Secondary analysis of data from the 2006 Working Conditions Survey in Long-term Care, a nationally representative cross-sectional survey done in Japan. 10,107 professional caregivers aged 18 years and older. Predictor of intent to leave was type of employment (full-time permanent, full-time precarious, and part-time precarious). Precarious work was defined as employment that failed to meet the standard of full-time permanent employment, including fixed-term, temporary agency, and part-time work. Covariates included demographics, home or facility care, tenure in the profession, national qualification for caregivers, having other jobs, overtime work, and night shift work. We used multinomial logit models to estimate the strength of the association between the type of employment and intent to leave and to explore the possible mechanisms explaining this association. In the unadjusted model, when compared to part-time precarious workers, full-time permanent workers (OR=2.37; 95% CI=2.06, 2.72) and full-time precarious workers (OR=2.41; 95% CI=2.01, 2.88) were more likely to report intent to leave. After adjustment for covariates, these odds ratios were attenuated, but nevertheless remained significant. Overtime work greatly attenuated these odds ratios in both full-time precarious and full-time permanent workers, and having national qualification for caregivers only did in the case of full-time permanent workers. In contrast to people in other professions, full-time caregivers are more likely to have intent to leave than part-time caregivers. This study highlights the importance of policy strategies for retaining full-time workers by reducing their overtime work and rewarding caregivers who have national qualifications. Copyright (c) 2010 Elsevier Ltd. All rights reserved.

  18. Space reactor fuel element testing in upgraded TREAT

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

    Todosow, M.; Bezler, P.; Ludewig, H.

    1993-01-14

    The testing of candidate fuel elements at prototypic operating conditions with respect to temperature, power density, hydrogen coolant flow rate, etc., a crucial component in the development and qualification of nuclear rocket engines based on the Particle Bed Reactor (PBR), NERVA-derivative, and other concepts. Such testing may be performed at existing reactors, or at new facilities. A scoping study has been performed to assess the feasibility of testing PBR based fuel elements at the TREAT reactor. initial results suggest that full-scale PBR, elements could be tested at an average energy deposition of {approximately}60--80 MW-s/L in the current TREAT reactor. Ifmore » the TREAT reactor was upgraded to include fuel elements with a higher temperature limit, average energy deposition of {approximately}100 MW/L may be achievable.« less

  19. Space reactor fuel element testing in upgraded TREAT

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

    Todosow, M.; Bezler, P.; Ludewig, H.

    1993-05-01

    The testing of candidate fuel elements at prototypic operating conditions with respect to temperature, power density, hydrogen coolant flow rate, etc., a crucial component in the development and qualification of nuclear rocket engines based on the Particle Bed Reactor (PBR), NERVA-derivative, and other concepts. Such testing may be performed at existing reactors, or at new facilities. A scoping study has been performed to assess the feasibility of testing PBR based fuel elements at the TREAT reactor. initial results suggest that full-scale PBR, elements could be tested at an average energy deposition of {approximately}60--80 MW-s/L in the current TREAT reactor. Ifmore » the TREAT reactor was upgraded to include fuel elements with a higher temperature limit, average energy deposition of {approximately}100 MW/L may be achievable.« less

  20. Ball Aerospace Advances in 35 K Cooling-The SB235E Cryocooler

    NASA Astrophysics Data System (ADS)

    Lock, J. S.; Glaister, D. S.; Gully, W.; Hendershott, P.; Marquardt, E.

    2008-03-01

    This paper describes the design, development, testing and performance of the Ball Aerospace & Technologies Corp. SB235E, a 2-stage long life space cryocooler optimized for 2 cooling loads. The SB235E model is designed to provide simultaneous cooling at 35 K (typically for HgCdTe detectors) and 85 K (typically for optics). The SB235E is a higher capacity model derivative of the SB235. Initial testing of the SB235E has shown performance of 2.13 W at 35 K and 8.14 W at 85 K for 200 W power at 289 K rejection temperature. These data equate to Carnot efficiency of 0.175 or nearly twice that of other published space cryocooler data. Qualification testing has been completed including full performance mapping and vibration export. Performance mapping with the cold-stage temperature varying from 20 K to 80 K and mid-stage temperature varying from 85 K to 175 K are presented. Two engineering models of the SB235E are currently in build.

  1. Space shuttle redesigned solid rocket motor Certificate of Qualification (COQ) data report

    NASA Technical Reports Server (NTRS)

    Duersch, Fred, Jr.

    1990-01-01

    The Space Shuttle Redesigned Solid Rocket Motor (RSRM) Certification Program provides confidence that the RSRM and its components/subsystems meet or exceed Mission Oriented Requirements when manufactured per design requirements and specified/approved processes. Certification is based on documented results of tests, analyses, inspections, similarity, and demonstrations. Evidencing information is provided to certify that each RSRM component/subsystem satisfies design, mission related requirements and objectives.

  2. Booster Test for Space Launch System Rocket

    NASA Image and Video Library

    2016-06-26

    The quench system arm and nozzle are seen at the test area where the second and final qualification motor (QM-2) test for the Space Launch System’s booster will take place, Sunday, June 26, 2016, at Orbital ATK Propulsion Systems test facilities in Promontory, Utah. The test is scheduled for Tuesday, June 28 at 10:05 a.m. EDT (8:05 a.m. MDT). Photo Credit: (NASA/Bill Ingalls)

  3. Qualification of Engineering Camera for Long-Duration Deep Space Missions

    NASA Technical Reports Server (NTRS)

    Ramesham, Rajeshuni; Maki, Justin N.; Pourangi, Ali M.; Lee, Steven W.

    2012-01-01

    Qualification and verification of advanced electronic packaging and interconnect technologies, and various other types of hardware elements for the Mars Exploration Rover s Spirit and Opportunity (MER)/Mars Science Laboratory (MSL) flight projects, has been performed to enhance the mission assurance. The qualification of hardware (engineering camera) under extreme cold temperatures has been performed with reference to various Mars-related project requirements. The flight-like packages, sensors, and subassemblies have been selected for the study to survive three times the total number of expected diurnal temperature cycles resulting from all environmental and operational exposures occurring over the life of the flight hardware, including all relevant manufacturing, ground operations, and mission phases. Qualification has been performed by subjecting above flight-like hardware to the environmental temperature extremes, and assessing any structural failures or degradation in electrical performance due to either overstress or thermal cycle fatigue. Engineering camera packaging designs, charge-coupled devices (CCDs), and temperature sensors were successfully qualified for MER and MSL per JPL design principles. Package failures were observed during qualification processes and the package redesigns were then made to enhance the reliability and subsequent mission assurance. These results show the technology certainly is promising for MSL, and especially for longterm extreme temperature missions to the extreme temperature conditions. The engineering camera has been completely qualified for the MSL project, with the proven ability to survive on Mars for 2010 sols, or 670 sols times three. Finally, the camera continued to be functional, even after 2010 thermal cycles.

  4. Dual wound dc brush motor gearhead

    NASA Technical Reports Server (NTRS)

    Henson, Barrie W.

    1986-01-01

    The design requirements, the design, development tests and problems, the qualification and life test and the findings of the strip examination of a dual wound DC brushed motor gearhead are described. It is the only space qualified dual wound dc brushed motor gearhead in Europe.

  5. 9th Annual Systems Engineering Conference: Volume 2 Tuesday

    DTIC Science & Technology

    2006-10-26

    Laboratory, Ben-Gurion University of the Negev Jacob Herscovitz Space systems Directorate RAFAEL jacobh@rafael.co.il A Pragmatic Focus in Managing...Maintainability Tests •Environmental Qualification Tests – Humidity, Salt Fog, Shock, Vibration, Rain UE, Rain CE, Solar Radiation , Icing, Fluid

  6. The Geoscience Laser Altimeter System Laser Transmitter

    NASA Technical Reports Server (NTRS)

    Afzal, R. S.; Dallas, J. L.; Yu, A. W.; Mamakos, W. A.; Lukemire, A.; Schroeder, B.; Malak, A.

    2000-01-01

    The Geoscience Laser Altimeter System (GLAS), scheduled to launch in 2001, is a laser altimeter and lidar for tile Earth Observing System's (EOS) ICESat mission. The laser transmitter requirements, design and qualification test results for this space- based remote sensing instrument are presented.

  7. Extreme Radiation Hardness and Space Qualification of AlGaN Optoelectronic Devices

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

    Sun, Ke-Xun; Balakrishnan, Kathik; Hultgren, Eric

    2010-09-21

    Unprecedented radiation hardness and environment robustness are required in the new generation of high energy density physics (HEDP) experiments and deep space exploration. National Ignition Facility (NIF) break-even shots will have a neutron yield of 1015 or higher. The Europa Jupiter System Mission (EJSM) mission instruments will be irradiated with a total fluence of 1012 protons/cm2 during the space journey. In addition, large temperature variations and mechanical shocks are expected in these applications under extreme conditions. Hefty radiation and thermal shields are required for Si and GaAs based electronics and optoelectronics devices. However, for direct illumination and imaging applications, shieldingmore » is not a viable option. It is an urgent task to search for new semiconductor technologies and to develop radiation hard and environmentally robust optoelectronic devices. We will report on our latest systematic experimental studies on radiation hardness and space qualifications of AlGaN optoelectronic devices: Deep UV Light Emitting Diodes (DUV LEDs) and solarblind UV Photodiodes (PDs). For custom designed AlGaN DUV LEDs with a central emission wavelength of 255 nm, we have demonstrated its extreme radiation hardness up to 2x1012 protons/cm2 with 63.9 MeV proton beams. We have demonstrated an operation lifetime of over 26,000 hours in a nitrogen rich environment, and 23,000 hours of operation in vacuum without significant power drop and spectral shift. The DUV LEDs with multiple packaging styles have passed stringent space qualifications with 14 g random vibrations, and 21 cycles of 100K temperature cycles. The driving voltage, current, emission spectra and optical power (V-I-P) operation characteristics exhibited no significant changes after the space environmental tests. The DUV LEDs will be used for photoelectric charge management in space flights. For custom designed AlGaN UV photodiodes with a central response wavelength of 255 nm, we have demonstrated its extreme radiation hardness using a 65 MeV proton beam line. The solar-blind AlGaN photodiodes retained ~50% responsivity up to 3x1012 protons/cm2 fluence. The Stanford-NSTec-SETI team will continue to develop radiation hard optoelectronic devices for applications under extreme conditions.« less

  8. 14 CFR 60.35 - Specific full flight simulator compliance requirements.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE... the extent necessary for the training, testing, and/or checking that comprise the simulation portion...

  9. 14 CFR 60.35 - Specific full flight simulator compliance requirements.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE... the extent necessary for the training, testing, and/or checking that comprise the simulation portion...

  10. 14 CFR 60.35 - Specific full flight simulator compliance requirements.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE... the extent necessary for the training, testing, and/or checking that comprise the simulation portion...

  11. 14 CFR 60.35 - Specific full flight simulator compliance requirements.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE... the extent necessary for the training, testing, and/or checking that comprise the simulation portion...

  12. 14 CFR 60.35 - Specific full flight simulator compliance requirements.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... TRANSPORTATION (CONTINUED) AIRMEN FLIGHT SIMULATION TRAINING DEVICE INITIAL AND CONTINUING QUALIFICATION AND USE... the extent necessary for the training, testing, and/or checking that comprise the simulation portion...

  13. Electrical, Electronic and Electromechanical (EEE) Parts in the New Space Paradigm: When is Better the Enemy of Good Enough?

    NASA Technical Reports Server (NTRS)

    La Bel, Kenneth A.; Sampson, Michael J.

    2016-01-01

    As the space business rapidly evolves to accommodate a lower cost model of development and operation via concepts such as commercial space and small spacecraft (aka, CubeSats), traditional EEE parts screening and qualification methods are being scrutinized under a risk-reward trade space. In this presentation, two basic concepts will be the overarching theme: 1) The movement from complete risk aversion EEE parts methods to managing and/or accepting risk via alternate approaches; and, 2) A discussion of over-design focusing on both electrical design performance and bounding margins.

  14. Electrical, Electronic and Electromechanical (EEE) Parts in the New Space Paradigm: When is Better the Enemy of Good Enough?

    NASA Technical Reports Server (NTRS)

    LaBel, Kenneth A.; Sampson, Michael J.

    2016-01-01

    As the space business rapidly evolves to accommodate a lower cost model of development and operation via concepts such as commercial space and small spacecraft (aka, CubeSats), traditional EEE parts screening and qualification methods are being scrutinized under a risk-reward trade space. In this presentation, two basic concepts will be the overarching theme: 1) The movement from complete risk aversion EEE parts methods to managing and or accepting risk via alternate approaches; and, 2) A discussion of over-design focusing on both electrical design performance and bounding margins.

  15. State-of-the art of dc components for secondary power distribution of Space Station Freedom

    NASA Technical Reports Server (NTRS)

    Krauthamer, Stanley; Gangal, Mukund; Das, Radhe S. L.

    1991-01-01

    120-V dc secondary power distribution has been selected for Space Station Freedom. State-of-the art components and subsystems are examined in terms of performance, size, and topology. One of the objectives of this work is to inform Space Station users what is available in power supplies and power control devices. The other objective is to stimulate interest in the component industry so that more focused product development can be started. Based on results of this study, it is estimated that, with some redesign, modifications, and space qualification, may of these components may be applied to Space Station needs.

  16. Development of electrical test procedures for qualification of spacecraft against EID. Volume 1: The CAN test and other relevant data

    NASA Technical Reports Server (NTRS)

    Wilkenfeld, J. M.; Judge, R. J. R.; Harlacher, B. L.

    1982-01-01

    A combined experimental and analytical program to develop system electrical test procedures for the qualification of spacecraft against damage produced by space-electron-induced discharges (EID) occurring on spacecraft dielectric outer surfaces is described. The data on the response of a simple satellite model, called CAN, to electron-induced discharges is presented. The experimental results were compared to predicted behavior and to the response of the CAN to electrical injection techniques simulating blowoff and arc discharges. Also included is a review of significant results from other ground tests and the P78-2 program to form a data base from which is specified those test procedures which optimally simulate the response of spacecraft to EID. The electrical and electron spraying test data were evaluated to provide a first-cut determination of the best methods for performance of electrical excitation qualification tests from the point of view of simulation fidelity.

  17. Modification Of The Manufacturing Process Of A Composite Structure- From System Needs To Elementary Tests

    NASA Astrophysics Data System (ADS)

    Touzard, Jerome; Veilleraud, Frederic; Collias, Michael

    2012-07-01

    The SYLDA5 structure (SYstème de Lancement Double Ariane 5 - Ariane 5 dual launch system) is a lightweight carbon composite structure designed and manufactured by Astrium Space Transportation at Les Mureaux premises. In order to improve the manufacturing process of t he SYLDA5, a proposal was made by SYLDA5 technical team to change the manufacturing process of the composite sandwich parts. The SYLDA5 is however one of the main contributors in the dynamic behaviour of the upper part of Ariane 5 launcher and plays an important role in the qualification of the launcher. The present paper describes the overall qualification logic retained, from System requirements to material tests and to global System qualification, in a classical V- type design cycle. It demonstrates the necessity to take into account System needs when modifying a part of it, especially when the System is qualified with actual characteristics of t he parts that may not be defined in product’s initial requirements.

  18. Advanced Key Technologies for Hot Control Surfaces in Space Re- Entry Vehicles

    NASA Astrophysics Data System (ADS)

    Dogigli, Michael; Pradier, Alain; Tumino, Giorgio

    2002-01-01

    (1)MAN Technologie AG, D- 86153 Augsburg, Germany (2,3) ESA, 2200 Noordwijk ZH, The Netherlands Current space re-entry vehicles (e.g. X-38 vehicle 201, the prototype of the International Space Station's Crew Return Vehicle (CRV)) require advanced control surfaces (so called body flaps). Such control surfaces allow the design of smaller and lighter vehicles as well as faster re-entries (compared to the US Shuttle). They are designed as light-weight structures that need no metallic parts, need no mass or volume consuming heat sinks to protect critical components (e.g. bearings) and that can be operated at temperatures of more than 1600 "C in air transferring high mechanical loads (dynamic 40 kN, static 70 kN) at the same time. Because there is a need for CRV and also for Reusable Launch Vehicles (RLV) in future, the European Space Agency (ESA) felt compelled to establish a "Future European Space Transportation and Investigation Program,, (FESTIP) and a "General Support for Technology Program,, (GSTP). One of the main goals of these programs was to develop and qualify key-technologies that are able to master the above mentioned challenging requirements for advanced hot control surfaces and that can be applied for different vehicles. In 1996 MAN Technologie has started the development of hot control surfaces for small lifting bodies in the national program "Heiü Strukturen,,. One of the main results of this program was that especially the following CMC (Ceramic Matrix Composite) key technologies need to be brought up to space flight standard: Complex CMC Structures, CMC Bearings, Metal-to-CMC Joining Technologies, CMC Fasteners, Oxidation Protection Systems and Static and Dynamic Seals. MAN Technologie was contracted by ESA to continue the development and qualification of these key technologies in the frame of the FESTIP and the GSTP program. Development and qualification have successfully been carried out. The key technologies have been applied for the X-38 vehicle 201 body flaps that have been designed, manufactured and qualified also by MAN Technologie in the frame of the national TETRA program ("Technologien fu zuku ftige Raum-Transportsysteme,,). A set of two body flaps will be delivered to NASA at the beginning of 2002 to be integrated into the vehicle 201. Based on development- and qualification tests, the paper describes main technical properties and features of these key technologies that at the same time represent the status of the art. In a qualification test (simultaneous application of thermal and mechanical loads with bearing movements in oxidising atmosphere) of a full scaled CMC bearing, five complete re-entries have been simulated successfully. The paper informs about applied mechanical load and temperature histories as well as about the number of intermittent bearing movements. The paper further informs about the complex CMC attachment structures (attachment of bearing into the body flap and load introduction) that have been qualified together with the CMC bearing. The attachment of the body flap to the vehicle's aft structure has also been qualified by tests in which also four re- entries have been simulated successfully. The attachment in principle is an interfacing structure between the "hot" (1600 "C) CMC body flap and the "cold,, (175 "C) metallic vehicle's aft structure that is able to transfer high me- chanical loads at high temperatures and minimise the heat flux through interfacing components in such way that the temperature difference of 1600 "C 175 "C = 1425 "C is brought down over a structure-length of only 200 mm. The paper informs about applied mechanical load and temperature histories and about the safety margins that have been demonstrated by rupture tests. Mechanical load carrying capacity and thermal resistance of ceramic fasteners have been demonstrated in several development tests which cover tension-, shear-, fatigue- and self locking-tests as well as tests with fastener assemblies representative for the body flaps. The reliability of these fasteners has also been demonstrated in the bearing and body flap qualification tests. In a comprehensive development test campaign, oxidation protection systems as well as repair methods have been developed and successfully applied for the body flap structure and components that reliably can be protected at least for four re-entries. The development of key technologies is continued in the national ASTRA program ("Basistechnologien fu keramische Hochtemperatur-Komponenten,,) and in international programs that among others focus on to improve the reusability of high temperature CMC components for RLVs.

  19. Guidelines for Selection, Screening and Qualification of Low-Voltage Commercial Multilayer Ceramic Capacitors for Space Programs

    NASA Technical Reports Server (NTRS)

    Teverovsky, Alexander A.

    2012-01-01

    This document has been developed in the course of NASA Electronic Parts and Packaging (NEPP) program and is not an official endorsement of the insertion of commercial capacitors in space programs or an established set of requirements for their testing. The purpose of this document is to suggest possible ways for selection, screening, and qualification of commercial capacitors for NASA projects and open discussions in the parts engineering community related to the use of COTS ceramic capacitors. This guideline is applicable to commercial surface mount chip, simple parallel plate design, multi-layer ceramic capacitors (MLCCs) rated to voltages of 100V and less. Parts with different design, e.g. low inductance ceramic capacitors (LICA), land grid array (LGA) etc., might need additional testing and tailoring of the requirements described in this document. Although the focus of this document is on commercial MLCCs, many procedures discussed below would be beneficial for military-grade capacitors

  20. Polishing, coating and integration of SiC mirrors for space telescopes

    NASA Astrophysics Data System (ADS)

    Rodolfo, Jacques

    2017-11-01

    In the last years, the technology of SiC mirrors took an increasingly significant part in the field of space telescopes. Sagem is involved in the JWST program to manufacture and test the optical components of the NIRSpec instrument. The instrument is made of 3 TMAs and 4 plane mirrors made of SiC. Sagem is in charge of the CVD cladding, the polishing, the coating of the mirrors and the integration and testing of the TMAs. The qualification of the process has been performed through the manufacturing and testing of the qualification model of the FOR TMA. This TMA has shown very good performances both at ambient and during the cryo test. The polishing process has been improved for the manufacturing of the flight model. This improvement has been driven by the BRDF performance of the mirror. This parameter has been deeply analysed and a model has been built to predict the performance of the mirrors. The existing Dittman model have been analysed and found to be optimistic.

  1. Study Methods to Characterize and Implement Thermography Nondestructive Evaluation (NDE)

    NASA Technical Reports Server (NTRS)

    Walker, James L.

    1998-01-01

    The limits and conditions under which an infrared thermographic nondestructive evaluation can be utilized to assess the quality of aerospace hardware is demonstrated in this research effort. The primary focus of this work is on applying thermography to the inspection of advanced composite structures such as would be found in the International Space Station Instrumentation Racks, Space Shuttle Cargo Bay Doors, Bantam RP-1 tank or RSRM Nose Cone. Here, the detection of delamination, disbond, inclusion and porosity type defects are of primary interest. In addition to composites, an extensive research effort has been initiated to determine how well a thermographic evaluation can detect leaks and disbonds in pressurized metallic systems "i.e. the Space Shuttle Main Engine Nozzles". In either case, research into developing practical inspection procedures was conducted and thermographic inspections were performed on a myriad of test samples, subscale demonstration articles and "simulated" flight hardware. All test samples were fabricated as close to their respective structural counterparts as possible except with intentional defects for NDE qualification. As an added benefit of this effort to create simulated defects, methods were devised for defect fabrication that may be useful in future NDE qualification ventures.

  2. Proton and gamma irradiation of Fabry-Perot quantum cascade lasers for space qualification

    DOE PAGES

    Myers, Tanya L.; Cannon, Bret D.; Brauer, Carolyn S.; ...

    2015-01-20

    Fabry-Perot quantum cascade lasers (QCLs) were characterized following irradiation by high energy (64 MeV) protons and Cobalt-60 gamma rays. Seven QCLs were exposed to radiation dosages that are typical for a space mission in which the total accumulated dosages from both radiation sources varied from 20 krad(Si) to 46.3 krad(Si). In conclusion, the QCLs did not show any measurable changes in threshold current or slope efficiency suggesting the suitability of QCLs for use in space-based missions.

  3. Testing and Qualifying Linear Integrated Circuits for Radiation Degradation in Space

    NASA Technical Reports Server (NTRS)

    Johnston, Allan H.; Rax, Bernard G.

    2006-01-01

    This paper discusses mechanisms and circuit-related factors that affect the degradation of linear integrated circuits from radiation in space. For some circuits there is sufficient degradation to affect performance at total dose levels below 4 krad(Si) because the circuit design techniques require higher gain for the pnp transistors that are the most sensitive to radiation. Qualification methods are recommended that include displacement damage as well as ionization damage.

  4. MNASA as a Test for Carbon Fiber Thermal Barrier Development

    NASA Technical Reports Server (NTRS)

    Bauer, Paul; McCool, Alex (Technical Monitor)

    2001-01-01

    A carbon fiber rope thermal barrier is being evaluated as a replacement for the conventional room temperature vulcanizing (RTV) thermal barrier that is currently used to protect o-rings in Reusable Solid Rocket Motor (RSRM) nozzle joints. Performance requirements include its ability to cool any incoming, hot propellant gases that fill and pressurize the nozzle joints, filter slag and particulates, and to perform adequately in various joint assembly conditions as well as dynamic flight motion. Modified National Aeronautics and Space Administration (MNASA) motors, with their inherent and unique ability to replicate select RSRM internal environment features, were an integral step in the development path leading to full scale RSRM static test demonstration of the carbon fiber rope (CFR) joint concept. These 1/4 scale RSRM motors serve to bridge the gap between the other classes of subscale test motors (extremely small and moderate duration, or small scale and short duration) and the critical asset RSRM static test motors. A series of MNASA tests have been used to demonstrate carbon fiber rope performance and have provided rationale for implementation into a full-scale static motor and flight qualification.

  5. Organizational characteristics influencing nursing home social service directors' qualifications: a national study.

    PubMed

    Simons, Kelsey V

    2006-11-01

    This research sought to identify organizational characteristics associated with the amount of professional qualifications among a nationally representative sample of nursing home social service directors. A self-administered survey was sent to directors in 675 facilities randomly sampled from a federal database, excluding facilities with fewer than 120 beds that are not required to staff a full-time social worker. The response rate was 45 percent (N = 299). Univariate results showed that most respondents possessed a social work degree, most lacked licensure, and few were clinically supervised. A multiple regression analysis found that nonprofit, independently owned facilities in rural areas staffed social service directors who were significantly more qualified than directors in for-profit, chain-affiliated facilities in urban and suburban areas. Facilities with fewer psychosocial deficiencies and higher occupancy rates employed social service directors with greater qualifications. The implications of these findings for social work education, practice, policy, and research are discussed.

  6. Development and qualification of additively manufactured parts for space

    NASA Astrophysics Data System (ADS)

    O'Brien, Michael J.

    2018-02-01

    Additive manufacturing (commonly called "3D printing") fabricates the desired final part directly from the input CAD (Computer Aided Design) file by depositing and fusing layer upon layer of the source material. New engineering designs are possible in which a single optimized part with novel topology can replace several traditional parts. The complex physics of metal deposition leads to variations in quality and to new flaws and residual stresses not seen in traditional manufacturing. Additive manufacturing currently has gaps in knowledge. Mission assurance will require: qualification and certification standards; sharing of data in handbooks; predictive models relating processing, microstructure and properties; and development of closed loop process control and non-destructive evaluation to reduce variability.

  7. Space Technology: Game Changing Development Deep Space Engine (DSE) 100 lbf and 5 lbf Thruster Development and Qualification

    NASA Technical Reports Server (NTRS)

    Barnett, Gregory

    2017-01-01

    Science mission studies require spacecraft propulsion systems that are high-performance, lightweight, and compact. Highly matured technology and low-cost, short development time of the propulsion system are also very desirable. The Deep Space Engine (DSE) 100-lbf thruster is being developed to meet these needs. The overall goal of this game changing technology project is to qualify the DSE thrusters along with 5-lbf attitude control thrusters for space flight and for inclusion in science and exploration missions. The aim is to perform qualification tests representative of mission duty cycles. Most exploration missions are constrained by mass, power and cost. As major propulsion components, thrusters are identified as high-risk, long-lead development items. NASA spacecraft primarily rely on 1960s' heritage in-space thruster designs and opportunities exist for reducing size, weight, power, and cost through the utilization of modern materials and advanced manufacturing techniques. Advancements in MON-25/MMH hypergolic bipropellant thrusters represent a promising avenue for addressing these deficiencies with tremendous mission enhancing benefits. DSE is much lighter and costs less than currently available thrusters in comparable thrust classes. Because MON-25 propellants operate at lower temperatures, less power is needed for propellant conditioning for in-space propulsion applications, especially long duration and/or deep-space missions. Reduced power results in reduced mass for batteries and solar panels. DSE is capable of operating at a wide propellant temperature range (between -22 F and 122 F) while a similar existing thruster operates between 45 F and 70 F. Such a capability offers robust propulsion operation as well as flexibility in design. NASA's Marshall Space Flight Center evaluated available operational Missile Defense Agency heritage thrusters suitable for the science and lunar lander propulsion systems.

  8. Design and fabrication of an autonomous rendezvous and docking sensor using off-the-shelf hardware

    NASA Technical Reports Server (NTRS)

    Grimm, Gary E.; Bryan, Thomas C.; Howard, Richard T.; Book, Michael L.

    1991-01-01

    NASA Marshall Space Flight Center (MSFC) has developed and tested an engineering model of an automated rendezvous and docking sensor system composed of a video camera ringed with laser diodes at two wavelengths and a standard remote manipulator system target that has been modified with retro-reflective tape and 830 and 780 mm optical filters. TRW has provided additional engineering analysis, design, and manufacturing support, resulting in a robust, low cost, automated rendezvous and docking sensor design. We have addressed the issue of space qualification using off-the-shelf hardware components. We have also addressed the performance problems of increased signal to noise ratio, increased range, increased frame rate, graceful degradation through component redundancy, and improved range calibration. Next year, we will build a breadboard of this sensor. The phenomenology of the background scene of a target vehicle as viewed against earth and space backgrounds under various lighting conditions will be simulated using the TRW Dynamic Scene Generator Facility (DSGF). Solar illumination angles of the target vehicle and candidate docking target ranging from eclipse to full sun will be explored. The sensor will be transportable for testing at the MSFC Flight Robotics Laboratory (EB24) using the Dynamic Overhead Telerobotic Simulator (DOTS).

  9. Automated personnel data base system specifications, Task V. Final report

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

    Bartley, H.J.; Bocast, A.K.; Deppner, F.O.

    1978-11-01

    The full title of this study is 'Development of Qualification Requirements, Training Programs, Career Plans, and Methodologies for Effective Management and Training of Inspection and Enforcement Personnel.' Task V required the development of an automated personnel data base system for NRC/IE. This system is identified as the NRC/IE Personnel, Assignment, Qualifications, and Training System (PAQTS). This Task V report provides the documentation for PAQTS including the Functional Requirements Document (FRD), the Data Requirements Document (DRD), the Hardware and Software Capabilities Assessment, and the Detailed Implementation Schedule. Specific recommendations to facilitate implementation of PAQTS are also included.

  10. Commercial Spacewalking: Designing an EVA Qualification Program for Space Tourism

    NASA Technical Reports Server (NTRS)

    Gast, Matthew A.

    2010-01-01

    In the near future, accessibility to space will be opened to anyone with the means and the desire to experience the weightlessness of microgravity, and to look out upon both the curvature of the Earth and the blackness of space, from the protected, shirt-sleeved environment of a commercial spacecraft. Initial forays will be short-duration, suborbital flights, but the experience and expertise of half a century of spaceflight will soon produce commercial vehicles capable of achieving low Earth orbit. Even with the commercial space industry still in its infancy, and manned orbital flight a number of years away, there is little doubt that there will one day be a feasible and viable market for those courageous enough to venture outside the vehicle and into the void, wearing nothing but a spacesuit, armed with nothing but preflight training. What that Extravehicular Activity (EVA) preflight training entails, however, is something that has yet to be defined. A number of significant factors will influence the composition of a commercial EVA training program, but a fundamental question remains: 'what minimum training guidelines must be met to ensure a safe and successful commercial spacewalk?' Utilizing the experience gained through the development of NASA's Skills program - designed to qualify NASA and International Partner astronauts for EVA aboard the International Space Station - this paper identifies the attributes and training objectives essential to the safe conduct of an EVA, and attempts to conceptually design a comprehensive training methodology meant to represent an acceptable qualification standard.

  11. Advanced Computational Modeling Approaches for Shock Response Prediction

    NASA Technical Reports Server (NTRS)

    Derkevorkian, Armen; Kolaini, Ali R.; Peterson, Lee

    2015-01-01

    Motivation: (1) The activation of pyroshock devices such as explosives, separation nuts, pin-pullers, etc. produces high frequency transient structural response, typically from few tens of Hz to several hundreds of kHz. (2) Lack of reliable analytical tools makes the prediction of appropriate design and qualification test levels a challenge. (3) In the past few decades, several attempts have been made to develop methodologies that predict the structural responses to shock environments. (4) Currently, there is no validated approach that is viable to predict shock environments overt the full frequency range (i.e., 100 Hz to 10 kHz). Scope: (1) Model, analyze, and interpret space structural systems with complex interfaces and discontinuities, subjected to shock loads. (2) Assess the viability of a suite of numerical tools to simulate transient, non-linear solid mechanics and structural dynamics problems, such as shock wave propagation.

  12. PROGRESS IN DESIGN OF THE INSTRUMENTATION AND CONTROL OF THE TOKAMAK COOLING WATER SYSTEM

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

    Korsah, Kofi; DeVan, Bill; Ashburn, David

    This paper discusses progress in the design of the control, interlock and safety systems of the Tokamak Cooling Water System (TCWS) for the ITER fusion reactor. The TCWS instrumentation and control (I&C) is one of approximately 200 separate plant I&C systems (e.g., vacuum system I&C, magnets system I&C) that interface to a common central I&C system through standardized networks. Several aspects of the I&C are similar to the I&C of fission-based power plants. However, some of the unique features of the ITER fusion reactor and the TCWS (e.g., high quasi-static magnetic field, need for baking and drying as well asmore » cooling operations), also demand some unique safety and qualification considerations. The paper compares the design strategy/guidelines of the TCWS I&C and the I&C of conventional nuclear power plants. Issues such as safety classifications, independence between control and safety systems, sensor sharing, redundancy, voting schemes, and qualification methodologies are discussed. It is concluded that independence and separation requirements are similar in both designs. However, the voting schemes for safety systems in nuclear power plants typically use 2oo4 (i.e., 4 divisions of safety I&C, any 2 of which is sufficient to trigger a safety action), while 2oo3 voting logic - within each of 2 independent trains - is used in the TCWS I&C. It is also noted that 2oo3 voting is also acceptable in nuclear power plants if adequate risk assessment and reliability is demonstrated. Finally, while qualification requirements provide similar guidance [e.g., both IEC 60780 (invoked in ITER-space), and IEEE 323 (invoked in fission power plant space) provide similar guidance], an important qualification consideration is the susceptibility of I&C to the magnetic fields of ITER. Also, the radiation environments are different. In the case of magnetic fields the paper discusses some options that are being considered.« less

  13. Linear Actuator System for the NASA Docking System

    NASA Technical Reports Server (NTRS)

    Dick, Brandon N.; Oesch, Christopher; Rupp, Timothy W.

    2017-01-01

    The Linear Actuator System (LAS) is a major sub-system within the NASA Docking System (NDS). The NDS Block 1 will be used on the Boeing Crew Space Transportation (CST-100) system to achieve docking with the International Space Station. Critical functions in the Soft Capture aspect of docking are performed by the LAS. This paper describes the general function of the LAS, the system's key requirements and technical challenges, and the development and qualification approach for the system.

  14. jsc2017e038547

    NASA Image and Video Library

    2017-03-30

    jsc2017e038547 (March 30, 2017) --- At the Gagarin Cosmonaut Training Center in Star City, Russia, Expedition 51 crewmembers Jack Fischer of NASA (left) and Fyodor Yurchikhin of the Russian Federal Space Agency (Roscosmos, right) flash broad smiles March 30 as they begin final crew qualification exams. They will launch April 20 on the Soyuz MS-04 spacecraft from the Baikonur Cosmodrome in Kazakhstan for a four and a half month mission on the International Space Station. Credit: NASA/Rob Navias

  15. jsc2012e238678

    NASA Image and Video Library

    2012-11-28

    At the Gagarin Cosmonaut Training Center in Star City, Russia, Expedition 34/35 Soyuz Commander Roman Romanenko listens to a question from reporters during the second of two days of flight qualification exams Nov. 28, 2012. He and his crewmates, Flight Engineer Chris Hadfield of the Canadian Space Agency and NASA Flight Engineer Tom Marshburn are preparing for launch Dec. 19 to the International Space Station from the Baikonur Cosmodrome in Kazakhstan aboard the Soyuz TMA-07M spacecraft. NASA/Stephanie Stoll

  16. High Power Laser Diode Array Qualification and Guidelines for Space Flight Environments

    NASA Technical Reports Server (NTRS)

    Ott, Melanie N.; Eegholm, Niels; Stephen, Mark; Leidecker, Henning; Plante, Jeannette; Meadows, Byron; Amzajerdian, Farzin; Jamison, Tracee; LaRocca, Frank

    2006-01-01

    High-power laser diode arrays (LDAs) are used for a variety of space-based remote sensor laser programs as an energy source for diode-pumped solid-state lasers. LDAs have been flown on NASA missions including MOLA, GLAS and MLA and have continued to be viewed as an important part of the laser-based instrument component suite. There are currently no military or NASA-grade, -specified, or - qualified LDAs available for "off-the-shelf" use by NASA programs. There has also been no prior attempt to define a standard screening and qualification test flow for LDAs for space applications. Initial reliability studies have also produced good results from an optical performance and stability standpoint. Usage experience has shown, howeve that the current designs being offered may be susceptible to catastrophic failures due to their physical construction (packaging) combined with the electro-optical operational modes and the environmental factors of space application. design combined with operational mode was at the root of the failures which have greatly reduced the functionality of the GLAS instrument. The continued need for LDAs for laser-based science instruments and past catastrophic failures of this part type demand examination of LDAs in a manner which enables NASA to select, buy, validate and apply them in a manner which poses as little risk to the success of the mission as possible.

  17. Flight telerobotic servicer legacy

    NASA Astrophysics Data System (ADS)

    Shattuck, Paul L.; Lowrie, James W.

    1992-11-01

    The Flight Telerobotic Servicer (FTS) was developed to enhance and provide a safe alternative to human presence in space. The first step for this system was a precursor development test flight (DTF-1) on the Space Shuttle. DTF-1 was to be a pathfinder for manned flight safety of robotic systems. The broad objectives of this mission were three-fold: flight validation of telerobotic manipulator (design, control algorithms, man/machine interfaces, safety); demonstration of dexterous manipulator capabilities on specific building block tasks; and correlation of manipulator performance in space with ground predictions. The DTF-1 system is comprised of a payload bay element (7-DOF manipulator with controllers, end-of-arm gripper and camera, telerobot body with head cameras and electronics module, task panel, and MPESS truss) and an aft flight deck element (force-reflecting hand controller, crew restraint, command and display panel and monitors). The approach used to develop the DTF-1 hardware, software and operations involved flight qualification of components from commercial, military, space, and R controller, end-of-arm tooling, force/torque transducer) and the development of the telerobotic system for space applications. The system is capable of teleoperation and autonomous control (advances state of the art); reliable (two-fault tolerance); and safe (man-rated). Benefits from the development flight included space validation of critical telerobotic technologies and resolution of significant safety issues relating to telerobotic operations in the Shuttle bay or in the vicinity of other space assets. This paper discusses the lessons learned and technology evolution that stemmed from developing and integrating a dexterous robot into a manned system, the Space Shuttle. Particular emphasis is placed on the safety and reliability requirements for a man-rated system as these are the critical factors which drive the overall system architecture. Other topics focused on include: task requirements and operational concepts for servicing and maintenance of space platforms; origins of technology for dexterous robotic systems; issues associated with space qualification of components; and development of the industrial base to support space robotics.

  18. 14 CFR 183.49 - Authorized functions.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Authorized functions. 183.49 Section 183.49... functions. (a) Consistent with an ODA Holder's qualifications, the Administrator may delegate any function... ODA Unit may perform only those functions, and is subject to the limitations, listed in the ODA Holder...

  19. 14 CFR 121.921 - Training devices and simulators.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... devices and simulators. (a) Each flight training device or airplane simulator that will be used in an AQP... device or flight simulator qualification level: (1) Required evaluation of individual or crew proficiency... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Training devices and simulators. 121.921...

  20. 14 CFR 121.921 - Training devices and simulators.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... devices and simulators. (a) Each flight training device or airplane simulator that will be used in an AQP... device or flight simulator qualification level: (1) Required evaluation of individual or crew proficiency... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Training devices and simulators. 121.921...

  1. 14 CFR 121.921 - Training devices and simulators.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... devices and simulators. (a) Each flight training device or airplane simulator that will be used in an AQP... device or flight simulator qualification level: (1) Required evaluation of individual or crew proficiency... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Training devices and simulators. 121.921...

  2. 14 CFR 121.921 - Training devices and simulators.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... devices and simulators. (a) Each flight training device or airplane simulator that will be used in an AQP... device or flight simulator qualification level: (1) Required evaluation of individual or crew proficiency... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Training devices and simulators. 121.921...

  3. Teaching Astronomy in UK Schools

    ERIC Educational Resources Information Center

    Roche, Paul; Roberts, Sarah; Newsam, Andy; Barclay, Charles

    2012-01-01

    This article attempts to summarise the good, bad and (occasionally) ugly aspects of teaching astronomy in UK schools. It covers the most common problems reported by teachers when asked about covering the astronomy/space topics in school. Particular focus is given to the GCSE Astronomy qualification offered by Edexcel (which is currently the…

  4. 14 CFR § 1253.550 - Sex as a bona fide occupational qualification.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 5 2014-01-01 2014-01-01 false Sex as a bona fide occupational... ADMINISTRATION NONDISCRIMINATION ON THE BASIS OF SEX IN EDUCATION PROGRAMS OR ACTIVITIES RECEIVING FEDERAL FINANCIAL ASSISTANCE Discrimination on the Basis of Sex in Employment in Education Programs or Activities...

  5. Expedition 31 Preflight

    NASA Image and Video Library

    2012-04-24

    Expedition 31 NASA backup crew member Kevin Ford, left, Oleg Novitskiy and Evgeny Tarelkin, third from left, select International Space Station Russian segment event simulation test cards for their final qualification test in preparation for flight, Tuesday, April 24, 2012 at the Gagarin Cosmonaut Training Center in Star City, Russia. Photo Credit: (NASA/Carla Cioffi)

  6. Spartan Auxiliary Mount Panel (SPAM): A Metal Matrix Composite Honeycomb Panel for Space Flight Use

    NASA Technical Reports Server (NTRS)

    Segal, Kenneth N.; Stevens, Edward J.

    1998-01-01

    This presentation focus on the use of metal matrix composite (MMC) material option in spaceflight hardware applications. It addresses the important questions and issues such as: what is SPAM; why the use of MMC; design requirements and flexibility; qualification testing; and flight concerns.

  7. 14 CFR 121.434 - Operating experience, operating cycles, and consolidation of knowledge and skills.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... consolidation of knowledge and skills. 121.434 Section 121.434 Aeronautics and Space FEDERAL AVIATION... Qualifications § 121.434 Operating experience, operating cycles, and consolidation of knowledge and skills. (a... of knowledge and skills, required by this section, except as follows: (1) Crewmembers other than...

  8. Sustaining the Leaders of Children's Centres: The Role of Leadership Mentoring

    ERIC Educational Resources Information Center

    John, Karen

    2008-01-01

    Leadership mentoring is a central component of the National Professional Qualification in Integrated Centre Leadership (NPQICL), which is designed to develop robust, creative and courageous children's centre leaders. Mentoring provides a safe, supportive and confidential space in which leaders can discuss the challenges of leading their centres.…

  9. On-Orbit Measurement of Next Generation Space Solar Cell Technology on the International Space Station

    NASA Technical Reports Server (NTRS)

    Wolford, David S.; Myers, Matthew G.; Prokop, Norman F.; Krasowski, Michael J.; Parker, David S.; Cassidy, Justin C.; Davies, William E.; Vorreiter, Janelle O.; Piszczor, Michael F.; McNatt, Jeremiah S.

    2014-01-01

    On-orbit measurements of new photovoltaic (PV) technologies for space power are an essential step in the development and qualification of advanced solar cells. NASA Glenn Research Center will fly and measure several solar cells attached to NASA Goddards Robotic Refueling Mission (RRM), expected to be launched in 2014. Industry and government partners have provided advanced PV devices for evaluation of performance and environmental durability. The experiment is completely self-contained, providing its own power and internal data storage. Several new cell technologies including Inverted Metamorphic Multi-junction and four-junction cells will be tested.

  10. Controls-Structures Interaction (CSI) technology program summary. Earth orbiting platforms program area of the space platforms technology program

    NASA Technical Reports Server (NTRS)

    Newsom, Jerry R.

    1991-01-01

    Control-Structures Interaction (CSI) technology embraces the understanding of the interaction between the spacecraft structure and the control system, and the creation and validation of concepts, techniques, and tools, for enabling the interdisciplinary design of an integrated structure and control system, rather than the integration of a structural design and a control system design. The goal of this program is to develop validated CSI technology for integrated design/analysis and qualification of large flexible space systems and precision space structures. A description of the CSI technology program is presented.

  11. Solar Simulation for the CREST Preflight Thermal-Vacuum Test at B-2

    NASA Technical Reports Server (NTRS)

    Ziemke, Robert A.

    2013-01-01

    In June 2011, the multi-university sponsored Cosmic Ray Electron Synchrotron Telescope (CREST) has undergone thermal-vacuum qualification testing at the NASA Glenn Research Center (GRC), Plum Brook Station, Sandusky, Ohio. The testing was performed in the B- 2 Space Propulsion Facility vacuum chamber. The CREST was later flown over the Antarctic region as the payload of a stratospheric balloon. Solar simulation was provided by a system of planar infrared lamp arrays specifically designed for CREST. The lamp arrays, in conjunction with a liquid-nitrogen-cooled cryoshroud, achieved the required thermal conditions for the qualification tests. This report focuses on the design and analysis of the planar arrays based on first principles. Computational spreadsheets are included in the report.

  12. Development of an Electrostatically Clean Solar Array Panel

    NASA Technical Reports Server (NTRS)

    Stern, Theodore G.; Krumweide, Duane; Gaddy, Edward; Katz, Ira

    2000-01-01

    The results of design, analysis, and qualification of an Electrostatically Clean Solar Array (ECSA) panel are described. The objective of the ECSA design is to provide an electrostatic environment that does not interfere with sensitive instruments on scientific spacecraft. The ECSA design uses large, ITO-coated coverglasses that cover multiple solar cells, an aperture grid that covers the intercell areas, stress-relieved interconnects for connecting the aperture grid to the coverglasses, and edge clips to provides an electromagnetically shielded enclosure for the solar array active circuitry. Qualification coupons were fabricated and tested for photovoltaic response, conductivity, and survivability to launch acoustic and thermal cycling environments simulating LEO and GEO missions. The benefits of reducing solar panel interaction with the space environment are also discussed.

  13. A 30% bandwidth tunerless SIS mixer of quantum-limited sensitivity for Herschel / HIFI Band 1

    NASA Astrophysics Data System (ADS)

    Salez, Morvan; Delorme, Yan; Peron, I.; Lecomte, Benoit; Dauplay, Frederic; Boussaha, Faouzi; Spatazza, J.; Feret, A.; Krieg, J. M.; Schuster, Karl-Friedrich

    2003-02-01

    We report on the status of the development of a 30% bandwidth tunerless SIS double-sideband mixer for the "Band 1" (480 GHz-630 GHz) channel of the heterodyne instrument (HIFI) of ESA"s Herschel Space Observatory, scheduled for launch in 2007. After exposing the main features of our mixer design, we present the performance achieved by the demonstration mixer, measured via Fourier Transform Spectroscopy and heterodyne Y factor calibrations. We infer from a preliminary mixer analysis that the mixer has very low, quantum-limited noise and low conversion loss. We also report on some pre-qualification tests, as we currently start to manufacture the qualification models and design the last iteration of masks for SIS junction production.

  14. A Handbook of Flight Simulation Fidelity Required for Human Factors Research

    DOT National Transportation Integrated Search

    1995-12-01

    This report examines relevant literature for guidelines relative to the use of : flight simulators, ranging from full mission to part-task trainers, in addition : to requirements for flight crew experience and qualifications. Both sets of : guideline...

  15. International Space Station Atmosphere Control and Supply, Atmosphere Revitalization, and Water Recovery and Management Subsystem - Verification for Node 1

    NASA Technical Reports Server (NTRS)

    Williams, David E.

    2007-01-01

    The International Space Station (ISS) Node 1 Environmental Control and Life Support (ECLS) System is comprised of five subsystems: Atmosphere Control and Supply (ACS), Atmosphere Revitalization (AR), Fire Detection and Suppression (FDS), Temperature and Humidity Control (THC), and Water Recovery and Management (WRM). This paper provides a summary of the nominal operation of the Node 1 ACS, AR, and WRM design and detailed Element Verification methodologies utilized during the Qualification phase for Node 1.

  16. Payload test philosophy. [implications of STS development at Goddard Space Flight Center

    NASA Technical Reports Server (NTRS)

    Arman, A.

    1979-01-01

    The implications of STS development for payload testing at the Goddard Space Flight Center are reviewed. The biggest impact of STS may be that instead of testing the entire payload, most of the testing may have to be limited to the subsystem or subassembly level. Particular consideration is given to the Goddard protoflight concept in which the test is geared to the design qualification levels, the test durations being those that are expected during the actual launch sequence.

  17. Qualification of Coatings for Launch Facilities and Ground Support Equipment Through the NASA Corrosion Technology Laboratory

    NASA Technical Reports Server (NTRS)

    Kolody, Mark R.; Curran, Jerome P.; Calle, Luz Marina

    2014-01-01

    Corrosion protection at NASA's Kennedy Space Center is a high priority item. The launch facilities at the Kennedy Space Center are located approximately 1000 feet from the Atlantic Ocean where they are exposed to salt deposits, high humidity, high UV degradation, and acidic exhaust from solid rocket boosters. These assets are constructed from carbon steel, which requires a suitable coating to provide long-term protection to reduce corrosion and its associated costs.

  18. Expedition 31 Preflight

    NASA Image and Video Library

    2012-04-23

    Expedition 31 NASA Flight Engineer Joe Acaba, far left, Expedition 31 Soyuz Commander Gennady Padalka and Flight Engineer Sergei Revin, third from left, select International Space Station Russian segment event simulation test cards for their final qualification test in preparation for launch, Monday, April 23, 2012 at the Gagarin Cosmonaut Training Center in Star City, Russia. Padalka, Acaba and Revin are set to launch May 15 from the Baikonur Cosmodrome in their Soyuz TMA-04M spacecraft to the International Space Station. Photo Credit: (NASA/Carla Cioffi)

  19. Application of Digital Radiography to Weld Inspection for the Space Shuttle External Fuel Tank

    NASA Technical Reports Server (NTRS)

    Ussery, Warren

    2009-01-01

    This slide presentation reviews NASA's use of digital radiography to inspect the welds of the external tanks used to hold the cryogenic fuels for the Space Shuttle Main Engines. NASA has had a goal of replacing a significant portion of film used to inspect the welds, with digital radiography. The presentation reviews the objectives for converting to a digital system from film, the characteristics of the digital system, the Probability of detection study, the qualification and implementation of the system.

  20. jsc2012e238680

    NASA Image and Video Library

    2012-11-28

    The next trio of residents that will launch to the International Space Station clasp hands for reporters and photojournalists at the Gagarin Cosmonaut Training Center in Star City, Russia Nov. 28, 2012 during the second of two days of flight qualification exams. Expedition 34/35 Flight Engineer Chris Hadfield of the Canadian Space Agency (left), Soyuz Commander Roman Romanenko (center) and NASA Flight Engineer Tom Marshburn (right) are scheduled to launch Dec. 19 from the Baikonur Cosmodrome in Kazakhstan on the Soyuz TMA-07M spacecraft. NASA/Stephanie Stoll

  1. jsc2012e238676

    NASA Image and Video Library

    2012-11-28

    At the Gagarin Cosmonaut Training Center in Star City, Russia, Expedition 34/35 Flight Engineer Tom Marshburn of NASA signs in for the second of two days of flight qualification exams Nov. 28, 2012. He and his crewmates are preparing for launch Dec. 19 to the International Space Station from the Baikonur Cosmodrome in Kazakhstan aboard the Soyuz TMA-07M spacecraft. Looking on behind Marshburn are Soyuz Commander Roman Romanenko (left) and Flight Engineer Chris Hadfield of the Canadian Space Agency (partially hidden). NASA/Stephanie Stoll

  2. jsc2012e238679

    NASA Image and Video Library

    2012-11-28

    The next trio of residents that will launch to the International Space Station fielded questions from reporters at the Gagarin Cosmonaut Training Center in Star City, Russia Nov. 28, 2012 during the second of two days of flight qualification exams. Expedition 34/35 Flight Engineer Chris Hadfield of the Canadian Space Agency (left), Soyuz Commander Roman Romanenko (center) and NASA Flight Engineer Tom Marshburn (right) are scheduled to launch Dec. 19 from the Baikonur Cosmodrome in Kazakhstan on the Soyuz TMA-07M spacecraft. NASA/Stephanie Stoll

  3. jsc2012e238677

    NASA Image and Video Library

    2012-11-28

    The next trio of residents that will launch to the International Space Station fielded questions from reporters at the Gagarin Cosmonaut Training Center in Star City, Russia Nov. 28, 2012 during the second of two days of flight qualification exams. Expedition 34/35 Flight Engineer Chris Hadfield of the Canadian Space Agency (left), Soyuz Commander Roman Romanenko (center) and NASA Flight Engineer Tom Marshburn (right) are scheduled to launch Dec. 19 from the Baikonur Cosmodrome in Kazakhstan on the Soyuz TMA-07M spacecraft. NASA/Stephanie Stoll

  4. jsc2012e238675

    NASA Image and Video Library

    2012-11-28

    At the Gagarin Cosmonaut Training Center in Star City, Russia, Expedition 34/35 Flight Engineer Chris Hadfield of the Canadian Space Agency signs in for the second of two days of flight qualification exams Nov. 28, 2012. He and his crewmates are preparing for launch Dec. 19 to the International Space Station from the Baikonur Cosmodrome in Kazakhstan aboard the Soyuz TMA-07M spacecraft. Looking on behind Hadfield are NASA Flight Engineer Tom Marshburn (left) and Soyuz Commander Roman Romanenko (right). NASA/Stephanie Stoll

  5. The careers of women graduates from St Mary's Hospital Medical School, London, 1961--72.

    PubMed

    Shaw, H E

    1979-07-01

    The careers of women doctors who qualified from St Mary's Hospital Medical School between 1961 and 1972 inclusive have been studied. Thirty-eight per cent were in full-time work, 47% were working part-time, and 15% were not practising medicine at the time of the survey. Those working full-time were predominantly single women and married women with no children. With the birth of children most women stopped working for a time, and 38% of those whose children were all under school age were not working. However, 90% returned to medicine, usually to part-time jobs that were compatible with family responsibilities. Eighty-six per cent of the respondents held one or more postgraduate qualifications. More of those with higher qualifications were in full-time work than was the case for women with a basic medical degree only, and fewer were not practising medicine. An equal proportion of single and married women intended to make their career in general practice. Fewer married women than single women chose a hospital career, because the possibilities of part-time work in this field were seen as limited.

  6. The DOE/NASA SRG110 Program Overview

    NASA Astrophysics Data System (ADS)

    Shaltens, R. K.; Richardson, R. L.

    2005-12-01

    The Department of Energy is developing the Stirling Radioisotope Generator (SRG110) for NASAs Science Mission Directorate for potential surface and deep space missions. The SRG110 is one of two new radioisotope power systems (RPSs) currently being developed for NASA space missions, and is capable of operating in a range of planetary atmospheres and in deep space environments. It has a mass of approximately 27 kg and produces more than 125We(dc) at beginning of mission (BOM), with a design lifetime of fourteen years. Electrical power is produced by two (2) free-piston Stirlings convertor heated by two General Purpose Heat Source (GPHS) modules. The complete SRG110 system is approximately 38 cm x 36 cm and 76 cm long. The SRG110 generator is being designed in 3 stages: Engineering Model, Qualification Generator, and Flight Generator. Current plans call for the Engineering Model to be fabricated and tested by October 2006. Completion of testing of the Qualification Generator is scheduled for mid-2009. This development is being performed by Lockheed Martin, Valley Forge, PA and Infinia Corporation, Kennewick, WA under contract to the Department of Energy, Germantown, Md. Glenn Research Center, Cleveland, Ohio is providing independent testing and support for the technology transition for the SRG110 Program.

  7. Space reliability technology - A historical perspective

    NASA Technical Reports Server (NTRS)

    Cohen, H.

    1984-01-01

    The progressive improvements in reliability of launch vehicles is traced from the Vanguard rocket to the STS. The Vanguard, built with minimal redundancy and a high mass ratio, was used as an operational vehicle midway through its test program in an attempt to meet the perceived challenge represented by the Sputnik. The fourth Vanguard failed due to inadequate contamination prevention and lack of inspection ports. Automatic firing sequences were adopted for the Titan rockets, which were an order of magnitude larger than the Vanguard and therefore had room for interior inspections. Qualification testing and reporting were introduced for components, along with X ray inspection of fuel tank welds. Dual systems were added for flight critical components when the Titan became man-rated for the Gemini program. Designs incorporated full failure mode effects and criticality analyses for the Apollo program, which exposed the limits of applicability of numerical reliability models. Fault tree analyses and program milestone reviews were initiated. The worth of man-in-the-loop in space activities for reliability was demonstrated with the rescue of Skylab after solar panel and meteoroid shield failures. It is now the reliability of the payload, rather than the vehicle, that is questioned for Shuttle launches.

  8. Glide back booster wind tunnel model testing

    NASA Astrophysics Data System (ADS)

    Pricop, M. V.; Cojocaru, M. G.; Stoica, C. I.; Niculescu, M. L.; Neculaescu, A. M.; Persinaru, A. G.; Boscoianu, M.

    2017-07-01

    Affordable space access requires partial or ideally full launch vehicle reuse, which is in line with clean environment requirement. Although the idea is old, the practical use is difficult, requiring very large technology investment for qualification. Rocket gliders like Space Shuttle have been successfullyoperated but the price and correspondingly the energy footprint were found not sustainable. For medium launchers, finally there is a very promising platform as Falcon 9. For very small launchers the situation is more complex, because the performance index (payload to start mass) is already small, versus medium and heavy launchers. For partial reusable micro launchers this index is even smaller. However the challenge has to be taken because it is likely that in a multiyear effort, technology is going to enable the performance recovery to make such a system economically and environmentally feasible. The current paper is devoted to a small unitary glide back booster which is foreseen to be assembled in a number of possible configurations. Although the level of analysis is not deep, the solution is analyzed from the aerodynamic point of view. A wind tunnel model is designed, with an active canard, to enablea more efficient wind tunnel campaign, as a national level premiere.

  9. 14 CFR 135.338 - Qualifications: Flight instructors (aircraft) and flight instructors (simulator).

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... (aircraft) and flight instructors (simulator). 135.338 Section 135.338 Aeronautics and Space FEDERAL... instructors (aircraft) and flight instructors (simulator). (a) For the purposes of this section and § 135.340... flight simulator, or in a flight training device for a particular type, class, or category aircraft. (2...

  10. 14 CFR 135.338 - Qualifications: Flight instructors (aircraft) and flight instructors (simulator).

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... (aircraft) and flight instructors (simulator). 135.338 Section 135.338 Aeronautics and Space FEDERAL... instructors (aircraft) and flight instructors (simulator). (a) For the purposes of this section and § 135.340... flight simulator, or in a flight training device for a particular type, class, or category aircraft. (2...

  11. 14 CFR 135.338 - Qualifications: Flight instructors (aircraft) and flight instructors (simulator).

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... (aircraft) and flight instructors (simulator). 135.338 Section 135.338 Aeronautics and Space FEDERAL... instructors (aircraft) and flight instructors (simulator). (a) For the purposes of this section and § 135.340... flight simulator, or in a flight training device for a particular type, class, or category aircraft. (2...

  12. 14 CFR 135.338 - Qualifications: Flight instructors (aircraft) and flight instructors (simulator).

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... (aircraft) and flight instructors (simulator). 135.338 Section 135.338 Aeronautics and Space FEDERAL... instructors (aircraft) and flight instructors (simulator). (a) For the purposes of this section and § 135.340... flight simulator, or in a flight training device for a particular type, class, or category aircraft. (2...

  13. 14 CFR 1253.550 - Sex as a bona fide occupational qualification.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 5 2011-01-01 2010-01-01 true Sex as a bona fide occupational... NONDISCRIMINATION ON THE BASIS OF SEX IN EDUCATION PROGRAMS OR ACTIVITIES RECEIVING FEDERAL FINANCIAL ASSISTANCE Discrimination on the Basis of Sex in Employment in Education Programs or Activities Prohibited § 1253.550 Sex as...

  14. 14 CFR 1253.550 - Sex as a bona fide occupational qualification.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 5 2013-01-01 2013-01-01 false Sex as a bona fide occupational... NONDISCRIMINATION ON THE BASIS OF SEX IN EDUCATION PROGRAMS OR ACTIVITIES RECEIVING FEDERAL FINANCIAL ASSISTANCE Discrimination on the Basis of Sex in Employment in Education Programs or Activities Prohibited § 1253.550 Sex as...

  15. 14 CFR 1253.550 - Sex as a bona fide occupational qualification.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 5 2010-01-01 2010-01-01 false Sex as a bona fide occupational... NONDISCRIMINATION ON THE BASIS OF SEX IN EDUCATION PROGRAMS OR ACTIVITIES RECEIVING FEDERAL FINANCIAL ASSISTANCE Discrimination on the Basis of Sex in Employment in Education Programs or Activities Prohibited § 1253.550 Sex as...

  16. 14 CFR 1253.550 - Sex as a bona fide occupational qualification.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 5 2012-01-01 2012-01-01 false Sex as a bona fide occupational... NONDISCRIMINATION ON THE BASIS OF SEX IN EDUCATION PROGRAMS OR ACTIVITIES RECEIVING FEDERAL FINANCIAL ASSISTANCE Discrimination on the Basis of Sex in Employment in Education Programs or Activities Prohibited § 1253.550 Sex as...

  17. Boeing CST-100 Heat Shield Testing

    NASA Image and Video Library

    2017-05-31

    A heat shield is used during separation test activities with Boeing's Starliner structural test article. The test article is undergoing rigorous qualification testing at the company's Huntington Beach Facility in California. Boeing’s CST-100 Starliner will launch on the Atlas V rocket to the International Space Station as part of NASA’s Commercial Crew Program.

  18. 14 CFR 121.434 - Operating experience, operating cycles, and consolidation of knowledge and skills.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Operating experience, operating cycles, and... Qualifications § 121.434 Operating experience, operating cycles, and consolidation of knowledge and skills. (a... position, the operating experience, operating cycles, and the line operating flight time for consolidation...

  19. Standard payload computer for the international space station

    NASA Astrophysics Data System (ADS)

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

    1999-01-01

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

  20. Delivery of Colloid Micro-Newton Thrusters for the Space Technology 7 Mission

    NASA Technical Reports Server (NTRS)

    Ziemer, John K.; Randolph, Thomas M.; Franklin, Garth W.; Hruby, Vlad; Spence, Douglas; Demmons, Nathaniel; Roy, Thomas; Ehrbar, Eric; Zwahlen, Jurg; Martin, Roy; hide

    2008-01-01

    Two flight-qualified clusters of four Colloid Micro-Newton Thruster (CMNT) systems have been delivered to the Jet Propulsion Laboratory (JPL). The clusters will provide precise spacecraft control for the drag-free technology demonstration mission, Space Technology 7 (ST7). The ST7 mission is sponsored by the NASA New Millennium Program and will demonstrate precision formation flying technologies for future missions such as the Laser Interferometer Space Antenna (LISA) mission. The ST7 disturbance reduction system (DRS) will be on the ESA LISA Pathfinder spacecraft using the European gravitational reference sensor (GRS) as part of the ESA LISA Technology Package (LTP). Developed by Busek Co. Inc., with support from JPL in design and testing, the CMNT has been developed over the last six years into a flight-ready and flight-qualified microthruster system, the first of its kind. Recent flight-unit qualification tests have included vibration and thermal vacuum environmental testing, as well as performance verification and acceptance tests. All tests have been completed successfully prior to delivery to JPL. Delivery of the first flight unit occurred in February of 2008 with the second unit following in May of 2008. Since arrival at JPL, the units have successfully passed through mass distribution, magnetic, and EMI/EMC measurements and tests as part of the integration and test (I&T) activities including the integrated avionics unit (IAU). Flight software sequences have been tested and validated with the full flight DRS instrument successfully to the extent possible in ground testing, including full functional and 72 hour autonomous operations tests. Delivery of the cluster assemblies along with the IAU to ESA for integration into the LISA Pathfinder spacecraft is planned for the summer of 2008 with a planned launch and flight demonstration in late 2010.

  1. Testing of a femtosecond pulse laser in outer space

    PubMed Central

    Lee, Joohyung; Lee, Keunwoo; Jang, Yoon-Soo; Jang, Heesuk; Han, Seongheum; Lee, Sang-Hyun; Kang, Kyung-In; Lim, Chul-Woo; Kim, Young-Jin; Kim, Seung-Woo

    2014-01-01

    We report a test operation of an Er-doped fibre femtosecond laser which was conducted for the first time in outer space. The fibre-based ultrashort pulse laser payload was designed to meet space-use requirements, undergone through ground qualification tests and finally launched into a low-earth orbit early in 2013. Test results obtained during a one-year mission lifetime confirmed stable mode-locking all the way through although the radiation induced attenuation (RIA) in the Er-doped gain fibre caused an 8.6% reduction in the output power. This successful test operation would help facilitate diverse scientific and technological applications of femtosecond lasers in space and earth atmosphere in the near future. PMID:24875665

  2. Testing of a femtosecond pulse laser in outer space.

    PubMed

    Lee, Joohyung; Lee, Keunwoo; Jang, Yoon-Soo; Jang, Heesuk; Han, Seongheum; Lee, Sang-Hyun; Kang, Kyung-In; Lim, Chul-Woo; Kim, Young-Jin; Kim, Seung-Woo

    2014-05-30

    We report a test operation of an Er-doped fibre femtosecond laser which was conducted for the first time in outer space. The fibre-based ultrashort pulse laser payload was designed to meet space-use requirements, undergone through ground qualification tests and finally launched into a low-earth orbit early in 2013. Test results obtained during a one-year mission lifetime confirmed stable mode-locking all the way through although the radiation induced attenuation (RIA) in the Er-doped gain fibre caused an 8.6% reduction in the output power. This successful test operation would help facilitate diverse scientific and technological applications of femtosecond lasers in space and earth atmosphere in the near future.

  3. The Hubble Space Telescope Scientific Instruments

    NASA Technical Reports Server (NTRS)

    Moore, J. V.

    1986-01-01

    The paper describes the status of the five Scientific Instruments (SI's) to be flown on the Hubble Space Telescope (HST) which is planned to be launched by the Space Transportation System in the last half of 1986. Concentration is on the testing experience for each of the instruments both at the instrument level and in conjunction with the other instruments and subsystems of the HST. Since the Acceptance/Flight Qualification Program of the HST is currently underway a description of the test and verification plans to be accomplished prior to shipment to the Kennedy Space Center (KSC) and pre-launch tests plans prior to launch are provided. The paper concludes with a brief description of anticipated orbital performance.

  4. An environmental testing facility for Space Station Freedom power management and distribution hardware

    NASA Technical Reports Server (NTRS)

    Jackola, Arthur S.; Hartjen, Gary L.

    1992-01-01

    The plans for a new test facility, including new environmental test systems, which are presently under construction, and the major environmental Test Support Equipment (TSE) used therein are addressed. This all-new Rocketdyne facility will perform space simulation environmental tests on Power Management and Distribution (PMAD) hardware to Space Station Freedom (SSF) at the Engineering Model, Qualification Model, and Flight Model levels of fidelity. Testing will include Random Vibration in three axes - Thermal Vacuum, Thermal Cycling and Thermal Burn-in - as well as numerous electrical functional tests. The facility is designed to support a relatively high throughput of hardware under test, while maintaining the high standards required for a man-rated space program.

  5. Operation of commercially-based microcomputer technology in a space radiation environment

    NASA Astrophysics Data System (ADS)

    Yelverton, J. N.

    This paper focuses on detection and recovery techniques that should enable the reliable operation of commercially-based microprocessor technology in the harsh radiation environment of space and at high altitudes. This approach is especially significant in light of the current shift in emphasis (due to cost) from space hardened Class-S parts qualification to a more direct use of commercial parts. The method should offset some of the concern that the newer high density state-of-the-art RISC and CISC microprocessors can be used in future space applications. Also, commercial aviation, should benefit, since radiation induced transients are a new issue arising from the increased quantities of microcomputers used in aircraft avionics.

  6. Management of the camera electronics programme for the World Space Observatory ultraviolet WUVS instrument

    NASA Astrophysics Data System (ADS)

    Patel, Gayatri; Clapp, Matthew; Salter, Mike; Waltham, Nick; Beardsley, Sarah

    2016-08-01

    World Space Observatory Ultraviolet (WSO-UV) is a major international collaboration led by Russia and will study the universe at ultraviolet wavelengths between 115 nm and 320 nm. The WSO Ultraviolet Spectrograph (WUVS) subsystem is led by a consortium of Russian institutes and consists of three spectrographs. RAL Space is contracted by e2v technologies Ltd to provide the CCD readout electronics for each of the three WUVS channels. The programme involves the design, manufacturing, assembly and testing of each Camera Electronics Box (CEB), its associated Interconnection Module (ICM), Electrical Ground Support Equipment (EGSE) and harness. An overview of the programme will be presented, from the initial design phase culminating in the development of an Engineering Model (EM) through qualification whereby an Engineering Qualification Model (EQM) will undergo environmental testing to characterize the performance of the CEB against the space environment, to the delivery of the Flight Models (FMs). The paper will discuss the challenges faced managing a large, dynamic project. This includes managing significant changes in fundamental requirements mid-programme as a result of external political issues which forced a complete re-design of an existing CEB with extensive space heritage but containing many ITAR controlled electronic components to a new, more efficient solution, free of ITAR controlled parts. The methodology and processes used to ensure the demanding schedule is maintained through each stage of the project will be presented including an insight into planning, decision-making, communication, risk management, and resource management; all essential to the continued success of the programme.

  7. Photonic Component Qualification and Implementation Activities at NASA Goddard Space Flight Center

    NASA Technical Reports Server (NTRS)

    Ott, Melanie N.; Jin, Xiaodan Linda; Chuska, Richard F.; LaRocca, Frank V.; MacMurphy, Shawn L.; Matuszeski, Adam J.; Zellar, Ronald S.; Friedberg, Patricia R.; Malenab, Mary C.

    2006-01-01

    The photonics group in Code 562 at NASA Goddard Space Flight Center supports a variety of space flight programs at NASA including the: International Space Station (ISS), Shuttle Return to Flight Mission, Lunar Reconnaissance Orbiter (LRO), Express Logistics Carrier, and the NASA Electronic Parts and Packaging Program (NEPP). Through research, development, and testing of the photonic systems to support these missions much information has been gathered on practical implementations for space environments. Presented here are the highlights and lessons learned as a result of striving to satisfy the project requirements for high performance and reliable commercial optical fiber components for space flight systems. The approach of how to qualify optical fiber components for harsh environmental conditions, the physics of failure and development lessons learned will be discussed.

  8. International Space Station (ISS) Internal Active Thermal Control System (IATCS) New Biocide Selection, Qualification and Implementation

    NASA Technical Reports Server (NTRS)

    Wilson, Mark E.; Cole, Harold E.; Rector, Tony; Steele, John; Varsik, Jerry

    2011-01-01

    The Internal Active Thermal Control System (IATCS) aboard the International Space Station (ISS) is primarily responsible for the removal of heat loads from payload and system racks. The IATCS is a water based system which works in conjunction with the EATCS (External ATCS), an ammonia based system, which are interfaced through a heat exchanger to facilitate heat transfer. On-orbit issues associated with the aqueous coolant chemistry began to occur with unexpected increases in CO2 levels in the cabin. This caused an increase in total inorganic carbon (TIC), a reduction in coolant pH, increased corrosion, and precipitation of nickel phosphate. These chemical changes were also accompanied by the growth of heterotrophic bacteria that increased risk to the system and could potentially impact crew health and safety. Studies were conducted to select a biocide to control microbial growth in the system based on requirements for disinfection at low chemical concentration (effectiveness), solubility and stability, material compatibility, low toxicity to humans, compatibility with vehicle environmental control and life support systems (ECLSS), ease of application, rapid on-orbit measurement, and removal capability. Based on these requirements, ortho-phthalaldehyde (OPA), an aromatic dialdehyde compound, was selected for qualification testing. This paper presents the OPA qualification test results, development of hardware and methodology to safely apply OPA to the system, development of a means to remove OPA, development of a rapid colorimetric test for measurement of OPA, and the OPA on-orbit performance for controlling the growth of microorganisms in the ISS IATCS since November 3, 2007.

  9. The ARA Mark 3 solar array design and development

    NASA Technical Reports Server (NTRS)

    vanHassel, Rob H. A.

    1996-01-01

    The ARA (Advanced Rigid Array) Mark3 solar array of Fokker Space BV is currently in its final stages of qualification (wing tests to be completed in March, 1996; unit/part tests in April, 1996). With regard to its predecessor, the ARA Mark2, the design has not only been improved in terms of mechanical and electrical performance, but also with regard to production cost and throughput time. This 'state of the art' array is designed to fit the needs of a wide variety of geostationary telecommunications satellites and is qualified for launch on the complete range of medium/large size commercial launchers (Ariane IV & V, Atlas, Delta, Proton, Long March, H2). The first mission to fly the new ARA Mk3 array is Hot Bird 2 (customer: Eutelsat, prime contractor: Matra Marconi Space; launch: mid-1996). In this configuration, its end of life (EOL) power-to-mass ratio is 42 W/kg, with an operational life of more than 12 years. The main mechanisms on a solar array are typically found in the deployment system and in the hold down and release system. During the design and development phase of these mechanisms, extensive engineering and qualification tests have been performed. This paper presents the key design features of these mechanisms and the improvements that were made with regard to their predecessors. It also describes the qualification philosophy on unit/part and wing level. Finally, some of the development items that turned out to be critical, as well as the lessons learned from them, are discussed.

  10. International Space Station (ISS) Internal Active Thermal Control System (IATCS) New Biocide Selection, Qualification and Implementation

    NASA Technical Reports Server (NTRS)

    Wilson, Mark E.; Cole, Harold; Rector, Tony; Steele, John; Varsik, Jerry

    2010-01-01

    The Internal Active Thermal Control System (IATCS) aboard the International Space Station (ISS) is primarily responsible for the removal of heat loads from payload and system racks. The IATCS is a water based system which works in conjunction with the EATCS (External ATCS), an ammonia based system, which are interfaced through a heat exchanger to facilitate heat transfer. On-orbit issues associated with the aqueous coolant chemistry began to occur with unexpected increases in CO2 levels in the cabin. This caused an increase in total inorganic carbon (TIC), a reduction in coolant pH, increased corrosion, and precipitation of nickel phosphate. These chemical changes were also accompanied by the growth of heterotrophic bacteria that increased risk to the system and could potentially impact crew health and safety. Studies were conducted to select a biocide to control microbial growth in the system based on requirements for disinfection at low chemical concentration (effectiveness), solubility and stability, material compatibility, low toxicity to humans, compatibility with vehicle environmental control and life support systems (ECLSS), ease of application, rapid on-orbit measurement, and removal capability. Based on these requirements, ortho-phthalaldehyde (OPA), an aromatic dialdehyde compound, was selected for qualification testing. This paper presents the OPA qualification test results, development of hardware and methodology to safely apply OPA to the system, development of a means to remove OPA, development of a rapid colorimetric test for measurement of OPA, and the OPA on-orbit performance for controlling the growth of microorganisms in the ISS IATCS since November 3, 2007.

  11. Characterization, performance and optimization of PVDF as a piezoelectric film for advanced space mirror concepts.

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

    Jones, Gary D.; Assink, Roger Alan; Dargaville, Tim Richard

    2005-11-01

    Piezoelectric polymers based on polyvinylidene fluoride (PVDF) are of interest for large aperture space-based telescopes as adaptive or smart materials. Dimensional adjustments of adaptive polymer films depend on controlled charge deposition. Predicting their long-term performance requires a detailed understanding of the piezoelectric material features, expected to suffer due to space environmental degradation. Hence, the degradation and performance of PVDF and its copolymers under various stress environments expected in low Earth orbit has been reviewed and investigated. Various experiments were conducted to expose these polymers to elevated temperature, vacuum UV, {gamma}-radiation and atomic oxygen. The resulting degradative processes were evaluated. Themore » overall materials performance is governed by a combination of chemical and physical degradation processes. Molecular changes are primarily induced via radiative damage, and physical damage from temperature and atomic oxygen exposure is evident as depoling, loss of orientation and surface erosion. The effects of combined vacuum UV radiation and atomic oxygen resulted in expected surface erosion and pitting rates that determine the lifetime of thin films. Interestingly, the piezo responsiveness in the underlying bulk material remained largely unchanged. This study has delivered a comprehensive framework for material properties and degradation sensitivities with variations in individual polymer performances clearly apparent. The results provide guidance for material selection, qualification, optimization strategies, feedback for manufacturing and processing, or alternative materials. Further material qualification should be conducted via experiments under actual space conditions.« less

  12. A Summary of DOD-Sponsored Research Performed at NASA Langley's Impact Dynamics Research Facility

    NASA Technical Reports Server (NTRS)

    Jackson, Karen E.; Boitnott, Richard L.; Fasanella, Edwin L.; Jones, Lisa E.; Lyle, Karen H.

    2004-01-01

    The Impact Dynamics Research Facility (IDRF) is a 240-ft.-high gantry structure located at NASA Langley Research Center in Hampton, Virginia. The IDRF was originally built in the early 1960's for use as a Lunar Landing Research Facility. As such, the facility was configured to simulate the reduced gravitational environment of the Moon, allowing the Apollo astronauts to practice lunar landings under realistic conditions. In 1985, the IDRF was designated a National Historic Landmark based on its significant contributions to the Apollo Moon Landing Program. In the early 1970's the facility was converted into its current configuration as a full-scale crash test facility for light aircraft and rotorcraft. Since that time, the IDRF has been used to perform a wide variety of impact tests on full-scale aircraft, airframe components, and space vehicles in support of the General Aviation (GA) aircraft industry, the U.S. Department of Defense (DOD), the rotorcraft industry, and the NASA Space program. The objectives of this paper are twofold: to describe the IDRF facility and its unique capabilities for conducting structural impact testing, and to summarize the impact tests performed at the IDRF in support of the DOD. These tests cover a time period of roughly 2 1/2 decades, beginning in 1975 with the full-scale crash test of a CH-47 Chinook helicopter, and ending in 1999 with the external fuel system qualification test of a UH-60 Black Hawk helicopter. NASA officially closed the IDRF in September 2003; consequently, it is important to document the past contributions made in improved human survivability and impact tolerance through DOD-sponsored research performed at the IDRF.

  13. [Assessment of the significance and the requirements of medical postdoctoral lecture qualifications in Germany by the assessment committees].

    PubMed

    Sorg, Heiko; Krämer, Robert; Grieswald, Christoph; Schwab, Christian G G; Thönnes, Simon; Reinke, Julia M; Hauser, Jörg; Tilkorn, Daniel J

    2016-10-01

    The postdoctoral medical lecture qualification (Habilitation) represents the highest academic qualification in Germany, which is successfully completed by approximately 850 candidates in medicine and health sciences per year. However, there is only a limited number of respective academic positions available. In addition, structures in education and society have changed over the last years, challenging the importance of this specific German qualification. The aim of this study was to elicit the opinions of members of German habilitation committees concerning the requirements, processes and the overall importance of the postdoctoral medical lecture qualification. Furthermore we wanted to evaluate potential needs for reforms. The online survey was conducted asking for biographic parameters, subjective ratings and potential needs for reforms concerning the postdoctoral medical lecture qualification (PLQ). The PLQ was rated high in significance by 71.3 % of the committee members. According to the medical understanding of the Humboldt triad (research, teaching, patient care), research (94.3 %) and teaching (89.7 %) have been rated as the most important requirements for a PLQ. Asked for the motivation to undertake a PLQ, 91.0 % of the members gave the joy of doing research, 78.2 % the joy of teaching and 65.5 % better career prospects perspectives as their reason. The recognition of a Ph.D. degree as being equivalent to a German PQL was clearly rejected by the survey respondents (58.6 %: no equivalence). The majority is against the abolition of the German PLQ. However, there is a definite desire for reform, preferably concerning internal obstacles such as the dependence on full professors, more transparency in the PLQ process, but also the demand for a federal standard PLQ regulation. From the committee members' point of view the German PLQ has still a role to play and, despite controversy, is still regarded as a timely qualification. However, there is clear-cut evidence for local, national and international reforms in order to create equality of opportunity for the candidates and to open up suitable career options. Copyright © 2016. Published by Elsevier GmbH.

  14. Performance and Environmental Test Results of the High Voltage Hall Accelerator Engineering Development Unit

    NASA Technical Reports Server (NTRS)

    Kamhawi, Hani; Haag, Thomas; Huang, Wensheng; Shastry, Rohit; Pinero, Luis; Peterson, Todd; Mathers, Alex

    2012-01-01

    NASA Science Mission Directorate's In-Space Propulsion Technology Program is sponsoring the development of a 3.5 kW-class engineering development unit Hall thruster for implementation in NASA science and exploration missions. NASA Glenn and Aerojet are developing a high fidelity high voltage Hall accelerator that can achieve specific impulse magnitudes greater than 2,700 seconds and xenon throughput capability in excess of 300 kilograms. Performance, plume mappings, thermal characterization, and vibration tests of the high voltage Hall accelerator engineering development unit have been performed. Performance test results indicated that at 3.9 kW the thruster achieved a total thrust efficiency and specific impulse of 58%, and 2,700 sec, respectively. Thermal characterization tests indicated that the thruster component temperatures were within the prescribed material maximum operating temperature limits during full power thruster operation. Finally, thruster vibration tests indicated that the thruster survived the 3-axes qualification full-level random vibration test series. Pre and post-vibration test performance mappings indicated almost identical thruster performance. Finally, an update on the development progress of a power processing unit and a xenon feed system is provided.

  15. Center for Advanced Space Propulsion

    NASA Technical Reports Server (NTRS)

    1995-01-01

    The Center for Advanced Space Propulsion (CASP) is part of the University of Tennessee-Calspan Center for Aerospace Research (CAR). It was formed in 1985 to take advantage of the extensive research faculty and staff of the University of Tennessee and Calspan Corporation. It is also one of sixteen NASA sponsored Centers established to facilitate the Commercial Development of Space. Based on investigators' qualifications in propulsion system development, and matching industries' strong intent, the Center focused its efforts in the following technical areas: advanced chemical propulsion, electric propulsion, AI/Expert systems, fluids management in microgravity, and propulsion materials processing. This annual report focuses its discussion in these technical areas.

  16. Laser transmitter for Lidar In-Space Technology Experiment

    NASA Technical Reports Server (NTRS)

    Chang, John; Cimolino, Marc; Petros, Mulugeta

    1991-01-01

    The Lidar In-Space Technology Experiment (LITE) Laser Transmitter Module (LTM) flight laser optical architecture has been space qualified by extensive testing at the system, subsystem and component level. The projected system output performance has been verified using an optically and electrically similar breadboard version of the laser. Parasitic lasing was closely examined and completely suppressed after design changes were implemented and tested. Oscillator and amplifier type heads were separately tested to 150 million shots. Critical subassemblies have undergone environmental testing to Shuttle qualification levels. A superior three color anti-reflection coating was developed and tested for use on 14 surfaces after the final amplifier.

  17. AGR-3/4 Final Data Qualification Report for ATR Cycles 151A through 155B-1

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

    Pham, Binh T.

    2015-03-01

    This report provides the qualification status of experimental data for the entire Advanced Gas Reactor 3/4 (AGR 3/4) fuel irradiation. AGR-3/4 is the third in a series of planned irradiation experiments conducted in the Advanced Test Reactor (ATR) at Idaho National Laboratory (INL) for the AGR Fuel Development and Qualification Program, which supports development of the advanced reactor technology under the INL ART Technology Development Office (TDO). The main objective of AGR-3/4 irradiation is to provide a known source of fission products for subsequent transport through compact matrix and structural graphite materials due to the presence of designed-to-fail fuel particles.more » Full power irradiation of the AGR 3/4 test began on December 14, 2011 (ATR Cycle 151A), and was completed on April 12, 2014 (end of ATR Cycle 155B) after 369.1 effective full power days of irradiation. The AGR-3/4 test was in the reactor core for eight of the ten ATR cycles between 151A and 155B. During the unplanned outage cycle, 153A, the experiment was removed from the ATR northeast flux trap (NEFT) location and stored in the ATR canal. This was to prevent overheating of fuel compacts due to higher than normal ATR power during the subsequent Powered Axial Locator Mechanism cycle, 153B. The AGR 3/4 test was inserted back into the ATR NEFT location during the outage of ATR Cycle 154A on April 26, 2013. Therefore, the AGR-3/4 irradiation data received during these 2 cycles (153A and 153B) are irrelevant and their qualification status isnot included in this report. Additionally, during ATR Cycle 152A the ATR core ran at low power for a short enough duration that the irradiation data are not used for physics and thermal calculations. However, the qualification status of irradiation data for this cycle is still covered in this report. As a result, this report includes data from 8 ATR Cycles: 151A, 151B, 152A, 152B, 154A, 154B, 155A, and 155B, as recorded in the Nuclear Data Management and Analysis System (NDMAS). The AGR 3/4 data streams addressed in this report include thermocouple (TC) temperatures, sweep gas data (flow rates, pressure, and moisture content), and Fission Product Monitoring System (FPMS) data (release rates, release to birth rate ratios [R/Bs], and particle failure counts) for each of the twelve capsules in the AGR 3/4 experiment. During Outage Cycle 155A, fourteen flow meters were installed downstream from fourteen FPMS monitors to measure flows from the monitors; qualification status of these data are also included in the report. The final data qualification status for these data streams is determined by a Data Review Committee (DRC) composed of AGR technical leads, Sitewide Quality Assurance (QA), and NDMAS analysts. For ATR Cycles 151A through 154B, the DRC convened on February 12, 2014, reviewed the data acquisition process, and considered whether the data met the requirements for data collection as specified in QA approved INL ART TDO data collection plans. The DRC also examined the results of NDMAS data testing and statistical analyses, and confirmed the qualification status of the data as given in this report. The qualification status of AGR-3/4 irradiation data during the first six cycles were previously reported in INL/EXT-14-31186 document. This report presents data qualification status for the entire AGR-3/4 irradiation.« less

  18. The Geoscience Laser Altimeter System (GLAS) Laser Transmitter

    NASA Technical Reports Server (NTRS)

    Afzal, Robert S.; Yu, Anthony W.; Dallas, Joseph L.; Melak, Anthony; Lukemir, Alan; Ramos-Izqueirdo, L.; Mamakos, William

    2007-01-01

    The Geoscience Laser Altimeter System (GLAS), launched in January 2003, is a laser altimeter and lidar for the Earth Observing System's (EOS) ICESat mission. GLAS accommodates three, sequentially operated, diode-pumped, solid-state, Nd:YAG laser transmitters. The laser transmitter requirements, design and qualification test results for this space-based remote sensing instrument is summarized and presented

  19. Sensor Data Qualification for Autonomous Operation of Space Systems

    NASA Technical Reports Server (NTRS)

    Maul, William A.; Melcher, Kevin J.; Chicatelli, Amy K.; Sowers, T. Shane

    2006-01-01

    NASA's new Exploration initiative for both robotic and manned missions will require higher levels of reliability, autonomy and reconfiguration capability to make the missions safe, successful and affordable. Future systems will require diagnostic reasoning to assess the health of the system in order to maintain the system s functionality. The diagnostic reasoning and assessment will involve data qualification, fault detection, fault isolation and remediation control. A team of researchers at the NASA Glenn Research Center is currently working on a Sensor Data Qualification (SDQ) system that will support these critical evaluation processes, for both automated and human-in-the-loop applications. Data qualification is required as a first step so that critical safety and operational decisions are based on good data. The SDQ system would monitor a network of related sensors to determine the health of individual sensors within that network. Various diagnostic systems such as the Caution and Warning System would then use the sensor health information with confidence. The proposed SDQ technology will be demonstrated on a variety of subsystems that are relevant to NASA s Exploration systems, which currently include an electrical power system and a cryogenic fluid management system. The focus of this paper is the development and demonstration of a SDQ application for a prototype power distribution unit that is representative of a Crew Exploration Vehicle electrical power system; this provides a unique and relevant environment in which to demonstrate the feasibility of the SDQ technology.

  20. Space qualified laser sources

    NASA Astrophysics Data System (ADS)

    Heine, Frank; Schwander, Thomas; Lange, Robert; Smutny, Berry

    2006-04-01

    Tesat-Spacecom has developed a series of fiber coupled single frequency lasers for space applications ranging from onboard metrology for space borne FTIR spectrometers to step tunable seed lasers for LIDAR applications. The cw-seed laser developed for the ESA AEOLUS Mission shows a 3* 10 -11 Allen variance from 1 sec time intervals up to 1000 sec. Q-switched lasers with stable beam pointing under space environments are another field of development. One important aspect of a space borne laser system is a reliable fiber coupled laser diode pump source around 808nm. A dedicated development concerning chip design and packaging yielded in a 5*10 6h MTTF (mean time to failure) for the broad area emitters. Qualification and performance test results for the different laser assemblies will be presented and their application in the different space programs.

  1. International Space Station Environmental Control and Life Support System: Verification for the Pressurized Mating Adapters

    NASA Technical Reports Server (NTRS)

    Williams, David E.

    2007-01-01

    The International Space Station (ISS) Pressurized Mating Adapters (PMAs) Environmental Control and Life Support (ECLS) System is comprised of three subsystems: Atmosphere Control and Supply (ACS), Temperature and Humidity Control (THC), and Water Recovery and Management (WRM). PMA 1 and PMA 2 flew to ISS on Flight 2A and PMA 3 flew to ISS on Flight 3A. This paper provides a summary of the PMAs ECLS design and the detailed Element Verification methodologies utilized during the Qualification phase for the PMAs.

  2. International Space Station Temperature and Humidity Control Subsystem Verification for Node 1

    NASA Technical Reports Server (NTRS)

    Williams, David E.

    2007-01-01

    The International Space Station (ISS) Node 1 Environmental Control and Life Support (ECLS) System is comprised of five subsystems: Atmosphere Control and Supply (ACS), Atmosphere Revitalization (AR), Fire Detection and Suppression (FDS), Temperature and Humidity Control (THC), and Water Recovery and Management (WRM). This paper provides a summary of the nominal operation of the Node 1 THC subsystem design. The paper will also provide a discussion of the detailed Element Verification methodologies for nominal operation of the Node 1 THC subsystem operations utilized during the Qualification phase.

  3. jsc2012e094088

    NASA Image and Video Library

    2012-06-19

    (19 June 2012) --- Expedition 32/33 backup crew members Tom Marshburn of NASA (left), Soyuz Commander Roman Romanenko (center) and Chris Hadfield of the Canadian Space Agency walked to a Soyuz simulator as they prepared for their final Soyuz qualification test June 19, 2012 at the Gagarin Cosmonaut Training Center in Star City, Russia. Expedition 32 Soyuz Commander Yuri Malenchenko and Flight Engineers Suni Williams and Aki Hoshide practiced similar scenarios nearby in advance of their final approval for launch to the International Space Station, scheduled for July 15, 2012. Photo credit: NASA

  4. jsc2012e238682

    NASA Image and Video Library

    2012-11-28

    At the Gagarin Cosmonaut Training Center in Star City, Russia, trainers eyed a bank of monitors as the Expedition 34/35 crew conducted the second of two days of flight qualification exams Nov. 28, 2012 in a Soyuz spacecraft simulator. NASA Flight Engineer Tom Marshburn of NASA, Soyuz Commander Roman Romanenko and Flight Engineer Chris Hadfield of the Canadian Space Agency are preparing for launch Dec. 19 from the Baikonur Cosmodrome in Kazakhstan in their Soyuz TMA-07M spacecraft, bound for a 5-month mission on the International Space Station. NASA/Stephanie Stoll

  5. jsc2012e238681

    NASA Image and Video Library

    2012-11-28

    At the Gagarin Cosmonaut Training Center in Star City, Russia, Expedition 34/35 Soyuz Commander Roman Romanenko studies a flight data file manual in front of a Soyuz spacecraft simulator Nov. 28, 2012 as he and his crewmates conducted the second of two days of flight qualification exams. Romanenko, NASA Flight Engineer Tom Marshburn and Flight Engineer Chris Hadfield of the Canadian Space Agency are scheduled to launch Dec. 19 from the Baikonur Cosmodrome in Kazakhstan on the Soyuz TMA-07M spacecraft, bound for a 5-month mission on the International Space Station. NASA/Stephanie Stoll

  6. Linear Actuator System for the NASA Docking System

    NASA Technical Reports Server (NTRS)

    Dick, Brandon; Oesch, Chris

    2017-01-01

    The Linear Actuator System (LAS) is a major sub-system within the NASA Docking System (NDS). The NDS Block 1 will be used on the Boeing Crew Space Transportation (CST-100) system to achieve docking with the International Space Station. Critical functions in the Soft Capture aspect of docking are performed by the LAS, which implements the Soft Impact Mating and Attenuation Concept (SIMAC). This paper describes the general function of the LAS, the system's key requirements and technical challenges, and the development and qualification approach for the system.

  7. Development of liquid crystal based adaptive optical elements for space applications

    NASA Astrophysics Data System (ADS)

    Geday, M. A.; Quintana, X.; Otón, E.; Cerrolaza, B.; Lopez, D.; Garcia de Quiro, F.; Manolis, I.; Short, A.

    2017-11-01

    In this paper we present the results obtained within the context of the ESA-funded project Programmable Optoelectronic Adaptive Element (AO/1-5476/07/NL/EM). The objective of this project is the development of adaptive (reconfigurable) optical elements for use in space applications and the execution of preliminary qualification tests in the relevant environment. The different designs and materials that have been considered and manufactured for a 2D beam steerer based on passive matrix liquid crystal programmable blaze grating will described and discussed.

  8. Thermo-optical vacuum testing of IRNSS laser retroreflector array qualification model

    NASA Astrophysics Data System (ADS)

    Porcelli, L.; Boni, A.; Ciocci, E.; Contessa, S.; Dell'Agnello, S.; Delle Monache, G.; Intaglietta, N.; Martini, M.; Mondaini, C.; Patrizi, G.; Salvatori, L.; Tibuzzi, M.; Lops, C.; Cantone, C.; Tuscano, P.; Maiello, M.; Venkateswaran, R.; Chakraborty, P.; Ramana Reddy, C. V.; Sriram, K. V.

    2017-09-01

    We describe the activities performed by SCF_Lab (Satellite/lunar/GNSS laser ranging/altimetry and cube/microsat Characterization Facilities Laboratory) of INFN-LNF for the thermo-optical vacuum testing activity of a IRNSS (Indian Regional Navigation Satellite System) LRA (Laser Retroreflector Array), under contract for ISRO-LEOS. To our knowledge, this is the first publication on the characterization of the optical performance of an LRA operating at about 36,000 km altitude (typical of regional GNSS segments, namely QZSS, COMPASS-G) executed in fully representative, carefully lab-simulated space conditions. In particular, this is the only such publication concerning IRNSS. Since laser ranging to its altitude is more challenging than to GNSS altitudes (from about 19,100 km for GLONASS to about 23,200 km for Galileo), comparative measurements were long awaited by ILRS (International Laser Ranging Service) and we present measurements of the absolute laser return to ground stations of the ILRS in terms of lidar OCS (Optical Cross Section) at the IRNSS relevant value of velocity aberration, in turn derived from measurements of the full FFDP (Far Field Diffraction Pattern) over a very large range of velocity aberrations. These measurements were acquired: (i) on a full-size qualification model of a IRNSS CCR (Cube Corner Retroreflector) LRA that ISRO-LEOS provided to INFN-LNF; (ii) during the lab-simulation of a 1/4 orbit segment, in which the LRA CCRs are exposed to the perturbation of the sun heat at varying angles, from grazing incidence (90° with respect to the direction perpendicular to the plane of array), up to the perpendicular to the LRA, with a same time variation consistent with the actual space orbit. In this 1/4 orbit condition, the LRA experiences potentially large thermal degradations of the OCS, depending on the detailed thermal and mechanical design of the LRA. Since all GNSS constellations have different LRA designs or configurations, this is another reason of the interest in the laboratory optical performance of the IRNSS designs. In fact, we tested two different IRNSS LRA configurations, without and with an auxiliary cover. The latter of the configurations is designed to give a somewhat increased performance. We also measured FFDPs and OCS: (1) in-air isothermal conditions (thus obtaining the LRA nominal performance); (2) in space conditions at a low, stationary value of the LRA bulk temperature; (3) in space conditions at a high, stationary value of the LRA bulk temperature (Figs. S1-S18, available in the online supplementary material for this paper). In all these three cases, we measured FFDPs and OCS at the following laser incidence angles: (a) normal to the LRA plane; (b) +9° to the normal to the LRA plane; (c) -9° to the normal to the LRA plane. This is the first time, to our knowledge, that the measurements (not simulations) at ±9° (values requested by ISRO-LEOS) are published for GNSS LRAs. Finally, we point out that we measured full-FFDP and OCS of single CCRs, for maximum diagnostic value and performance validation at subelement level. For all these reasons, the articulate and variate set of tests of the IRNSS LRA reported in this paper is unique.

  9. Testing in Support of Space Fission System Development and Qualification

    NASA Technical Reports Server (NTRS)

    Houts, Mike; Bragg-Sitton, Shannon; Garber, Anne; Godfrey, Tom; Martin, Jim; Pearson, Boise; Webster, Kenny

    2007-01-01

    Extensive data would be required for the qualification of a fission surface power (FSP) system. The strategy for qualifying a FSP system could have a significant programmatic impact. This paper explores potential options that could be used for qualifying FSP systems, including cost-effective means for obtaining required data. three methods for obtaining qualification data are analysis, non-nuclear testing, and nuclear testing. It has been over 40 years since the US qualified a space reactor for launch. During that time, advances have been made related to all three methods. Perhaps the greatest advancement has occurred in the area of computational tools for design and analysis. Tools that have been developed, coupled with modem computers, would have a significant impact on a FSP qualification. This would be especially true for systems with materials and fuels operating well within temperature, irradiation damage, and burnup limits. The ability to perform highly realistic non-nuclear testing has also advanced throughout the past four decades. Instrumented thermal simulators were developed during the 1970s and 1980s to assist in the development, operation, and assessment of terrestrial fission systems. Instrumented thermal simulators optimized for assisting in the development, operation, and assessment of modem FSP systems have been under development (and utilized) since 1998. These thermal simulators enable heat from fission to be closely mimicked (axial power profile, radial power profile, temperature, heat flux, etc.} and extensive data to be taken from the core region. Both steady-state and transient operation can be tested. For transient testing, reactivity feedback is calculated (or measured in cold/warm criticals) based on reactor temperature and/or dimensional changes. Pin power during a transient is then calculated based on the reactivity feedback that would occur given measured values of temperature and/or dimensional change. In this way nonnuclear testing can be used to provide very realistic information related to nuclear operation. Non-nuclear testing can be used at all levels, including component, subsystem, and integrated system testing. Realistic non-nuclear testing is most useful for systems operating within known temperature, irradiation damage, and burnup capabilities.

  10. Instructions for Plastic Encapsulated Microcircuit(PEM) Selection, Screening and Qualification.

    NASA Technical Reports Server (NTRS)

    King, Terry; Teverovsky, Alexander; Leidecker, Henning

    2002-01-01

    The use of Plastic Encapsulated Microcircuits (PEMs) is permitted on NASA Goddard Space Flight Center (GSFC) spaceflight applications, provided each use is thoroughly evaluated for thermal, mechanical, and radiation implications of the specific application and found to meet mission requirements. PEMs shall be selected for their functional advantage and availability, not for cost saving; the steps necessary to ensure reliability usually negate any initial apparent cost advantage. A PEM shall not be substituted for a form, fit and functional equivalent, high reliability, hermetic device in spaceflight applications. Due to the rapid change in wafer-level designs typical of commercial parts and the unknown traceability between packaging lots and wafer lots, lot specific testing is required for PEMs, unless specifically excepted by the Mission Assurance Requirements (MAR) for the project. Lot specific qualification, screening, radiation hardness assurance analysis and/or testing, shall be consistent with the required reliability level as defined in the MAR. Developers proposing to use PEMs shall address the following items in their Performance Assurance Implementation Plan: source selection (manufacturers and distributors), storage conditions for all stages of use, packing, shipping and handling, electrostatic discharge (ESD), screening and qualification testing, derating, radiation hardness assurance, test house selection and control, data collection and retention.

  11. Electrical, Electronic and Electromechanical (EEE) Parts in the New Space Paradigm: When is Better the Enemy of Good Enough?

    NASA Technical Reports Server (NTRS)

    LaBel, Kenneth A.; Sampson, Michael J.

    2017-01-01

    As the space business rapidly evolves to accommodate a lower cost model of development and operation via concepts such as commercial space and small spacecraft (aka, CubeSats and swarms), traditional EEE parts screening and qualification methods are being scrutinized under a risk-reward trade space. In this presentation, two basic concepts will be discussed: (1) The movement from complete risk aversion EEE parts methods to managing and/or accepting risk via alternate approaches; and, (2) A discussion of emerging assurance methods to reduce overdesign as well emerging model based mission assurance (MBMA) concepts. center dot Example scenarios will be described as well as consideration for trading traditional versus alternate methods.

  12. jsc2017e135207 - At the Gagarin Cosmonaut Training Center in Star City, Russia, Expedition 54-55 prime crewmember Norishige Kanai of the Japan Aerospace Exploration Space Agency (JAXA) listens to a reporters’ question Nov. 29 as part of the crew’s fin

    NASA Image and Video Library

    2017-11-29

    jsc2017e135207 - At the Gagarin Cosmonaut Training Center in Star City, Russia, Expedition 54-55 prime crewmember Norishige Kanai of the Japan Aerospace Exploration Space Agency (JAXA) listens to a reporters’ question Nov. 29 as part of the crew’s final qualification exam activities. Kanai, Scott Tingle of NASA and Anton Shkaplerov of the Russian Federal Space Agency (Roscosmos) will launch Dec. 17 on the Soyuz MS-07 spacecraft from the Baikonur Cosmodrome in Kazakhstan for a five-month mission on the International Space Station...NASA/Elizabeth Weissinger.

  13. Optical Fiber Assemblies for Space Flight from the NASA Goddard Space Flight Center, Photonics Group

    NASA Technical Reports Server (NTRS)

    Ott, Melanie N.; Thoma, William Joe; LaRocca, Frank; Chuska, Richard; Switzer, Robert; Day, Lance

    2009-01-01

    The Photonics Group at NASA Goddard Space Flight Center in the Electrical Engineering Division of the Advanced Engineering and Technologies Directorate has been involved in the design, development, characterization, qualification, manufacturing, integration and anomaly analysis of optical fiber subsystems for over a decade. The group supports a variety of instrumentation across NASA and outside entities that build flight systems. Among the projects currently supported are: The Lunar Reconnaissance Orbiter, the Mars Science Laboratory, the James Webb Space Telescope, the Express Logistics Carrier for the International Space Station and the NASA Electronic Parts. and Packaging Program. A collection of the most pertinent information gathered during project support over the past year in regards to space flight performance of optical fiber components is presented here. The objective is to provide guidance for future space flight designs of instrumentation and communication systems.

  14. Psychological considerations in future space missions

    NASA Technical Reports Server (NTRS)

    Helmreich, R. L.; Wilhelm, J. A.; Runge, T. E.

    1980-01-01

    Issues affecting human psychological adjustments to long space missions are discussed. Noting that the Shuttle flight crewmembers will not have extensive flight qualification requirements, the effects of a more heterogeneous crew mixture than in early space flights is considered to create possibilities of social conflicts. Routine space flight will decrease the novelty of a formerly unique experience, and the necessity of providing personal space or other mechanisms for coping with crowded, permanently occupied space habitats is stressed. Women are noted to display more permeable personal space requirements. The desirability of planning leisure activities is reviewed, and psychological test results for female and male characteristics are cited to show that individuals with high scores in both traditionally male and female attributes are most capable of effective goal-oriented behavior and interpersonal relationships. Finally, it is shown that competitiveness is negatively correlated with the success of collaborative work and the social climate of an environment.

  15. Use of Shuttle Heritage Hardware in Space Launch System (SLS) Application-Structural Assessment

    NASA Technical Reports Server (NTRS)

    Aggarwal, Pravin; Booker, James N.

    2018-01-01

    NASA is moving forward with the development of the next generation system of human spaceflight to meet the Nation's goals of human space exploration. To meet these goals, NASA is aggressively pursuing the development of an integrated architecture and capabilities for safe crewed and cargo missions beyond low-Earth orbit. Two important tenets critical to the achievement of NASA's strategic objectives are Affordability and Safety. The Space Launch System (SLS) is a heavy-lift launch vehicle being designed/developed to meet these goals. The SLS Block 1 configuration (Figure 1) will be used for the first Exploration Mission (EM-1). It utilizes existing hardware from the Space Shuttle inventory, as much as possible, to save cost and expedite the schedule. SLS Block 1 Elements include the Core Stage, "Heritage" Boosters, Heritage Engines, and the Integrated Spacecraft and Payload Element (ISPE) consisting of the Launch Vehicle Stage Adapter (LVSA), the Multi-Purpose Crew Vehicle (MPCV) Stage Adapter (MSA), and an Interim Cryogenic Propulsion Stage (ICPS) for Earth orbit escape and beyond-Earth orbit in-space propulsive maneuvers. When heritage hardware is used in a new application, it requires a systematic evaluation of its qualification. In addition, there are previously-documented Lessons Learned (Table -1) in this area cautioning the need of a rigorous evaluation in any new application. This paper will exemplify the systematic qualification/assessment efforts made to qualify the application of Heritage Solid Rocket Booster (SRB) hardware in SLS. This paper describes the testing and structural assessment performed to ensure the application is acceptable for intended use without having any adverse impact to Safety. It will further address elements such as Loads, Material Properties and Manufacturing, Testing, Analysis, Failure Criterion and Factor of Safety (FS) considerations made to reach the conclusion and recommendation.

  16. OCCUPATIONS IN THE CARE AND REHABILITATION OF THE MENTALLY RETARDED.

    ERIC Educational Resources Information Center

    BOSS, MILTON R.; GREGG, RANDOLPH M.

    TWENTY-SEVEN FULL TIME OCCUPATIONS INVOLVING DIAGNOSIS, CARE, AND REHABILITATION OF THE MENTALLY RETARDED ARE DISCUSSED. FOR EACH, AN OCCUPATIONAL DEFINITION, THE NEEDED QUALIFICATIONS, AND SOME INDICATION OF THE NECESSARY WORKER TRAIT REQUIREMENTS SUCH AS APTITUDES, INTERESTS, TEMPERAMENT, AND PHYSICAL DEMANDS AND WORKING CONDITIONS ARE…

  17. Tenure Wild Cards

    ERIC Educational Resources Information Center

    Zemsky, Robert

    2008-01-01

    The circumstances of tenure have changed and will likely continue to change, perhaps even dramatically. The proportion of university and college faculty members with full academic qualifications--which usually means those with earned doctorates--who either have tenure or are serving a probationary period for tenure has been declining steadily over…

  18. Battery Resistance Analysis of ISS Power System

    NASA Technical Reports Server (NTRS)

    Newstadt, Gregory E.

    2004-01-01

    The computer package, SPACE (Systems Power Analysis for Capability Evaluation) was created by the members of LT-9D to perform power analysis and modeling of the electrical power system on the International Space Station (ISS). Written in FORTRAN, SPACE comprises thousands of lines of code and has been used profficiently in analyzing missions to the ISS. LT-9D has also used its expertise recently to investigate the batteries onboard the Hubble telescope. During the summer of 2004, I worked with the members of LT-9D, under the care of Dave McKissock. Solar energy will power the ISS through eight solar arrays when the ISS is completed, although only two arrays are currently connected. During the majority of the periods of sunlight, the solar arrays provide enough energy for the ISS. However, rechargeable Nickel-Hydrogen batteries are used during eclipse periods or at other times when the solar arrays cannot be used (at docking for example, when the arrays are turned so that they will not be damaged by the Shuttle). Thirty-eight battery cells are connected in series, which make up an ORU (Orbital Replacement Unit). An ISS "battery" is composed of two ORUs. a great deal of time into finding the best way to represent them in SPACE. During my internship, I investigated the resistance of the ISS batteries. SPACE constructs plots of battery charge and discharge voltages vs. time using a constant current. To accommodate for a time-varying current, the voltages are adjusted using the formula, DeltaV = DeltaI * Cell Resistance. To enhance our model of the battery resistance, my research concentrated on several topics: investigating the resistance of a qualification unit battery (using data gathered by LORAL), comparing the resistance of the qualification unit to SPACE, looking at the internal resistance and wiring resistance, and examining the impact of possible recommended changes to SPACE. The ISS batteries have been found to be very difficult to model, and LT-9D has dedicated

  19. Low-Power Operation and Plasma Characterization of a Qualification Model SPT-140 Hall Thruster for NASA Science Missions

    NASA Technical Reports Server (NTRS)

    Garner, Charles E.; Jorns, Benjamin A.; van Derventer, Steven; Hofer, Richard R.; Rickard, Ryan; Liang, Raymond; Delgado, Jorge

    2015-01-01

    Hall thruster systems based on commercial product lines can potentially lead to lower cost electric propulsion (EP) systems for deep space science missions. A 4.5-kW SPT-140 Hall thruster presently under qualification testing by SSL leverages the substantial heritage of the SPT-100 being flown on Russian and US commercial satellites. The Jet Propulsion Laboratory is exploring the use of commercial EP systems, including the SPT-140, for deep space science missions, and initiated a program to evaluate the SPT-140 in the areas of low power operation and thruster operating life. A qualification model SPT-140 designated QM002 was evaluated for operation and plasma properties along channel centerline, from 4.5 kW to 0.8 kW. Additional testing was performed on a development model SPT-140 designated DM4 to evaluate operation with a Moog proportional flow control valve (PFCV). The PFCV was commanded by an SSL engineering model PPU-140 Power Processing Unit (PPU). Performance measurements on QM002 at 0.8 kW discharge power were 50 mN of thrust at a total specific impulse of 1250 s, a total thruster efficiency of 0.38, and discharge current oscillations of under 3% of the mean current. Steady-state operation at 0.8 kW was demonstrated during a 27 h firing. The SPT-140 DM4 was operated in closed-loop control of the discharge current with the PFCV and PPU over discharge power levels of 0.8-4.5 kW. QM002 and DM4 test data indicate that the SPT-140 design is a viable candidate for NASA missions requiring power throttling down to low thruster input power.

  20. Design, construction, test and field support of a containerless payload package for rocket flight. [electromagnetic heating and confinement

    NASA Technical Reports Server (NTRS)

    1977-01-01

    The performance of a device for electromagnetically heating and positioning containerless melts during space processing was evaluated during a 360 second 0-g suborbital sounding rocket flight. Components of the electromagnetic containerless processing package (ECPP), its operation, and interface with the rocket are described along with flight and qualification tests results.

  1. Brushless dc motors. [applications in non-space technology

    NASA Technical Reports Server (NTRS)

    1975-01-01

    Brushless dc motors were intensively developed and tested over several years before qualification as the prime movers for Apollo Spacecraft life support blowers, and for circulating oxygen in the lunar portable life support system. Knowledge gained through prototype development and critical testing has significantly influenced the technology employed, broadened markets and applications, and reduced the cost of present day motors.

  2. An Overview of the NASA Aerospace Flight Battery Systems Program

    NASA Technical Reports Server (NTRS)

    Manzo, Michelle

    2003-01-01

    Develop an understanding of the safety issues relating to space use and qualification of new Li-Ion technology for manned applications. Enable use of new technology batteries into GFE equipment - laptop computers, camcorders. Establish a data base for an optimized set of cells (and batteries) exhibiting acceptable performance and abuse characteristics for utilization as building blocks for numerous applications.

  3. Alignment and qualification of the Gaia telescope using a Shack-Hartmann sensor

    NASA Astrophysics Data System (ADS)

    Dovillaire, G.; Pierot, D.

    2017-09-01

    Since almost 20 years, Imagine Optic develops, manufactures and offers to its worldwide customers reliable and accurate wavefront sensors and adaptive optics solutions. Long term collaboration between Imagine Optic and Airbus Defence and Space has been initiated on the Herschel program. More recently, a similar technology has been used to align and qualify the GAIA telescope.

  4. Enabling Roles to Reclaim Teacher Agency: Insights from the Advanced Certificate in Teaching (Foundation Phase)

    ERIC Educational Resources Information Center

    Ebrahim, H. B.; Verbeek, D. C.; Mashiya, J. N.

    2011-01-01

    In developing the Advanced Certificate in Teaching (ACT) as a professional qualification for continuing teacher education for early schooling at the University of KwaZulu-Natal we asked the following: "What are the enabling roles foundation phase teachers need to play in order to reclaim their space as agents who significantly influence their…

  5. Rosetta launch postponed

    NASA Astrophysics Data System (ADS)

    2003-01-01

    The Review Board called for Arianespace and all its partners to make sure, in the framework of a programme for the resumption of Ariane 5 flights, that all Ariane 5 system qualification and review processes have been checked. Arianespace and the European Space Agency, together with all interested parties, are now going to consult each other in order to determine arrangements for the soonest possible launch of Rosetta.

  6. SNAP 10A FS-3 reactor performance

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

    Hawley, J.P.; Johnson, R.A.

    1966-08-15

    SNAP 10FS-3 was the first flight-qualified SNAP reactor system to be operated in a simulated space environment. Prestart-up qualification testing, automatic start-up, endurance period performance, extended operation test and reactor shutdown are described as they affected, or were affected by, overall reactor performance. Performance of the reactor control system and the diagnostic instrumentation is critically evaluted.

  7. Information management system study results. Volume 2: IMS study results appendixes

    NASA Technical Reports Server (NTRS)

    1971-01-01

    Computer systems program specifications are presented for the modular space station information management system. These are the computer program contract end item, data bus system, data bus breadboard, and display interface adapter specifications. The performance, design, tests, and qualification requirements are established for the implementation of the information management system. For Vol. 1, see N72-19972.

  8. Remarks on Sentinel-1 Avionic SW Qualification

    NASA Astrophysics Data System (ADS)

    Candia, Sante; Pascucci, Dario

    2013-08-01

    The GMES Sentinel-1 Earth Radar Observatory, a projects co-funded by the European Union and the European Space Agency (ESA), is a constellation of C-band radar satellites. The satellites have been conceived to be a continuous and reliable source of C-band SAR imagery for operational application such as mapping of global landmasses, coastal zones and monitoring of shipping routes. ESA is responsible for the development of the Sentinel-1 satellites that are built by an industrial consortium headed by Thales Alenia Space Italy (TASI) as Prime Contractor. TAS-I is also directly responsible for the production of the Spacecraft Bus and the Avionic S/S including the Avionic SW (ASW), which is characterized by: · The high performances of its attitude and orbit determination and control function; · Scheduling of the imaging activity on position basis with high geo-location performances; · High on board autonomy both in routine and contingency situations. This paper is focused on the Sentinel-1 Avionic SW, which has currently been qualified by TAS-I for Flight. It covers both the SW architecture and development process areas: · Avionic SW context; · Avionic SW architecture; · Flexibility of PUS-based on-board autonomy and FDIR; · Validation and Qualification activities;

  9. Optical overview and qualification of the LLCD space terminal

    NASA Astrophysics Data System (ADS)

    DeVoe, C. E.; Pillsbury, A. D.; Khatri, F.; Burnside, J. M.; Raudenbush, A. C.; Petrilli, L. J.; Williams, T.

    2017-11-01

    In October 2013 the Lunar Laser Communications Demonstration (LLCD) made communications history by successfully demonstrating 622 megabits per second laser communication from the moon's orbit to earth. The LLCD consisted of the Lunar Laser Communication Space Terminal (LLST), developed by MIT Lincoln Laboratory, mounted on NASA's Lunar Atmosphere and Dust Environment Explorer (LADEE) spacecraft and a primary ground terminal located in New Mexico, the Lunar Laser Communications Ground Terminal (LLGT), and two alternate ground terminals. This paper presents the optical layout of the LLST, the approach for testing the optical subsystems, and the results of the optical qualification of the LLST. Also described is the optical test set used to qualify the LLST. The architecture philosophy for the optics was to keep a small, simple optical backend that provided excellent boresighting and high isolation between the optical paths, high quality wavefront on axis, with minimal throughput losses on all paths. The front end large optics consisted of a Cassegrain 107mm telescope with an f/0.7 parabolic primary mirror and a solar window to reduce the thermal load on the telescope and to minimize background light received at the sensors.

  10. The status of lightweight photovoltaic space array technology based on amorphous silicon solar cells

    NASA Technical Reports Server (NTRS)

    Hanak, Joseph J.; Kaschmitter, Jim

    1991-01-01

    Ultralight, flexible photovoltaic (PV) array of amorphous silicon (a-Si) was identified as a potential low cost power source for small satellites. A survey was conducted of the status of the a-Si PV array technology with respect to present and future performance, availability, cost, and risks. For existing, experimental array blankets made of commercial cell material, utilizing metal foil substrates, the Beginning of Life (BOL) performance at Air Mass Zero (AM0) and 35 C includes total power up to 200 W, power per area of 64 W/sq m and power per weight of 258 W/kg. Doubling of power per weight occurs when polyimide substrates are used. Estimated End of Life (EOL) power output after 10 years in a nominal low earth orbit would be 80 pct. of BOL, the degradation being due to largely light induced effects (-10 to -15 pct.) and in part (-5 pct.) to space radiation. Predictions for the year 1995 for flexible PV arrays, made on the basis of published results for rigid a-Si modules, indicate EOL power output per area and per weight of 105 W/sq m and 400 W/kg, respectively, while predictions for the late 1990s based on existing U.S. national PV program goals indicate EOL values of 157 W/sq m and 600 W/kg. Cost estimates by vendors for 200 W ultralight arrays in volume of over 1000 units range from $100/watt to $125/watt. Identified risks include the lack of flexible, space compatible encapsulant, the lack of space qualification effort, recent partial or full acquisitions of US manufacturers of a-Si cells by foreign firms, and the absence of a national commitment for a long range development program toward developing of this important power source for space.

  11. SCARLET I: Mechanization solutions for deployable concentrator optics integrated with rigid array technology

    NASA Technical Reports Server (NTRS)

    Wachholz, James J.; Murphy, David M.

    1996-01-01

    The SCARLET I (Solar Concentrator Army with Refractive Linear Element Technology) solar array wing was designed and built to demonstrate, in flight, the feasibility of integrating deployable concentrator optics within the design envelope of typical rigid array technology. Innovative mechanism designs were used throughout the array, and a full series of qualification tests were successfully performed in anticipation of a flight on the Multiple Experiment Transporter to Earth Orbit and Return (METEOR) spacecraft. Even though the Conestoga launch vehicle was unable to place the spacecraft in orbit, the program effort was successful in achieving the milestones of analytical and design development functional validation, and flight qualification, thus leading to a future flight evaluation for the SCARLET technology.

  12. SCARLET I: Mechanization solutions for deployable concentrator optics integrated with rigid array technology

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

    Wachholz, J.J.; Murphy, D.M.

    1996-05-01

    The SCARLET I (Solar Concentrator Army with Refractive Linear Element Technology) solar array wing was designed and built to demonstrate, in flight, the feasibility of integrating deployable concentrator optics within the design envelope of typical rigid array technology. Innovative mechanism designs were used throughout the array, and a full series of qualification tests were successfully performed in anticipation of a flight on the Multiple Experiment Transporter to Earth Orbit and Return (METEOR) spacecraft. Even though the Conestoga launch vehicle was unable to place the spacecraft in orbit, the program effort was successful in achieving the milestones of analytical and designmore » development functional validation, and flight qualification, thus leading to a future flight evaluation for the SCARLET technology.« less

  13. VEGA Launch Vehicle Vibro-Acoustic Approach for Multi Payload Configuration Qualification

    NASA Astrophysics Data System (ADS)

    Bartoccini, D.; Di Trapani, C.; Fotino, D.; Bonnet, M.

    2014-06-01

    Acoustic loads are one of the principal source of structural vibration and internal noise during a launch vehicle flight but do not generally present a critical design condition for the main load-carrying structure. However, acoustic loads may be critical to the proper functioning of vehicle components and their supporting structures, which are otherwise lightly loaded. Concerning the VEGA program, in order to demonstrate VEGA Launch Vehicle (LV) on-ground qualification, prior to flight, to the acoustic load, the following tests have been performed: small-scale acoustic test intended for the determination of the acoustic loading of the LV and its nature and full-scale acoustic chamber test to determine the vibro-acoustic response of the structures as well as of the acoustic cavities.

  14. The environmental heat flux routine, version 4 (EHFR-4) and Multiple Reflections Routine (MRR), volume 1

    NASA Technical Reports Server (NTRS)

    Dietz, J. B.

    1973-01-01

    The environmental heat flux routine version 4, (EHFR-4) is a generalized computer program which calculates the steady state and/or transient thermal environments experienced by a space system during lunar surface, deep space, or thermal vacuum chamber operation. The specific environments possible for EHFR analysis include: lunar plain, lunar crater, combined lunar plain and crater, lunar plain in the region of spacecraft surfaces, intervehicular, deep space in the region of spacecraft surfaces, and thermal vacuum chamber generation. The EHFR was used for Extra Vehicular Mobility Unit environment analysis of the Apollo 11-17 missions, EMU manned and unmanned thermal vacuum qualification testing, and EMU-LRV interface environmental analyses.

  15. Improving Student Naval Aviator Aircraft Carrier Landing Performance

    ERIC Educational Resources Information Center

    Sheppard, Thomas H.; Foster, T. Chris

    2008-01-01

    This article discusses the use of human performance technology (HPT) to improve qualification rates for learning to land onboard aircraft carriers. This project started as a request for a business case analysis and evolved into a full-fledged performance improvement project, from mission analysis through evaluation. The result was a significant…

  16. Measuring the Earnings Returns to Lifelong Learning in the UK

    ERIC Educational Resources Information Center

    Blanden, Jo; Buscha, Franz; Sturgis, Patrick; Urwin, Peter

    2012-01-01

    This paper examines the earnings returns to learning that takes place following the conventional "school-to-work" stage of the life-course. We operationalise such "lifelong learning" as the attainment of certified qualifications in adulthood, following the completion of the first period of continuous full-time education. Using…

  17. Qualification of quantum cascade lasers for space environments

    NASA Astrophysics Data System (ADS)

    Myers, Tanya L.; Cannon, Bret D.; Brauer, Carolyn S.; Crowther, Blake G.; Hansen, Stewart

    2014-06-01

    Laser-based instruments are enabling a new generation of scientific instruments for space environments such as those used in the exploration of Mars. The lasers must be robust and able to withstand the harsh environment of space, including radiation exposure. Quantum cascade lasers (QCLs), which are semiconductor lasers that emit in the infrared spectral region, offer the potential for the development of novel laser-based instruments for space applications. The performance of QCLs after radiation exposure, however, has not been reported. We report on work to quantify the performance of QCLs after exposure to two different radiation sources, 64 MeV protons and Cobalt-60 gamma rays, at radiation levels likely to be encountered during a typical space flight mission. No significant degradation in threshold current or slope efficiency is observed for any of the seven Fabry-Perot QCLs that are tested.

  18. Kiel sensors for the EPD instrument on-board Solar Orbiter - An overview of the qualification and acceptance test campaigns in phase D

    NASA Astrophysics Data System (ADS)

    Ravanbakhsh, A.; Kulkarni, S. R.; Panitzsch, L.; L Richards, M.; Munoz Hernandez, A.; Seimetz, L.; Elftmann, R.; Mahesh, Y.; Boden, S.; Boettcher, S. I.; Kulemzin, A.; Martin-Garcia, C.; Prieto, M.; Rodriguez-Pacheco, J.; Sanchez Prieto, S.; Schuster, B.; Steinhagen, J.; Tammen, J.; Wimmer-Schweingruber, R. F.

    2016-12-01

    Solar Orbiter is ESA's next solar and heliospheric mission which is planned to be launched in October 2018. The Energetic Particle Detector (EPD) on board on Solar Orbiter will provide key measurements for the Solar Orbiter science objectives. The EPD suite consists of four sensors; STEP, SIS, EPT and HET. The University of Kiel in Germany is responsible for the design, development, and building of STEP, and the two identical units EPT-HET 1 and EPT-HET 2. ESA's Solar Orbiter will explore the heliosphere at heliocentric distances between 0.28AU and 0.9AU and with inclination up to 38deg with respect to the Sun's equator. The spacecraft uses a heat shield to protect the bus and externally mounted instruments from the solar flux at the close distances to the sun. All three EPD-Kiel units are mounted externally but in different positions on the spacecraft outer deck. Although being protected by the spacecraft heat shield from high solar flux, EPT-HET1 and EPT-HET-2 as well as STEP experience a harsh environmental condition during the course of the mission. In addition due to the highly demanding science requirements, the qualification and acceptance test requirements of these externally mounted units are quite challenging. In this paper we present the development status of the EPT-HET 1, EPT-HET 2 and STEP sensors focusing on the activities performed in phase D and the qualification and acceptance test campaigns. The main objective of these test campaigns is to ensure and demonstrate the compatibility between the scientific requirements and the harsh environment expected during the mission. This paper includes the results summary of the environmental tests on the EPT-HET and STEP Proto-Qualification Models (PQMs) as well as Proto-Flight Models (PFMs). Only an adequate selection of environmental qualification and acceptance campaigns will guarantee the success of the scientific space missions.

  19. Sofradir latest developments for infrared space detectors

    NASA Astrophysics Data System (ADS)

    Chorier, Philippe; Delannoy, Anne

    2011-06-01

    Sofradir is one of the leading companies that develop and produce infrared detectors. Space applications have become a significant activity and Sofradir relies now on 20 years of experience in development and production of MCT infrared detectors of 2nd and 3rd generation for space applications. Thanks to its capabilities and experience, Sofradir is now able to offer high reliability infrared detectors for space applications. These detectors cover various kinds of applications like hyperspectral observation, earth observations for meteorological or scientific purpose and science experiments. In this paper, we present a review of latest Sofradir's development for infrared space applications. A presentation of Sofradir infrared detectors answering hyperspectral needs from visible up to VLWIR waveband will be made. In addition a particular emphasis will be placed on the different programs currently running, with a presentation of the associated results as they relate to performances and qualifications for space use.

  20. Integrated Testing Approaches for the NASA Ares I Crew Launch Vehicle

    NASA Technical Reports Server (NTRS)

    Taylor, James L.; Cockrell, Charles E.; Tuma, Margaret L.; Askins, Bruce R.; Bland, Jeff D.; Davis, Stephan R.; Patterson, Alan F.; Taylor, Terry L.; Robinson, Kimberly L.

    2008-01-01

    The Ares I crew launch vehicle is being developed by the U.S. National Aeronautics and Space Administration (NASA) to provide crew and cargo access to the International Space Station (ISS) and, together with the Ares V cargo launch vehicle, serves as a critical component of NASA's future human exploration of the Moon. During the preliminary design phase, NASA defined and began implementing plans for integrated ground and flight testing necessary to achieve the first human launch of Ares I. The individual Ares I flight hardware elements - including the first stage five segment booster (FSB), upper stage, and J-2X upper stage engine - will undergo extensive development, qualification, and certification testing prior to flight. Key integrated system tests include the upper stage Main Propulsion Test Article (MPTA), acceptance tests of the integrated upper stage and upper stage engine assembly, a full-scale integrated vehicle ground vibration test (IVGVT), aerodynamic testing to characterize vehicle performance, and integrated testing of the avionics and software components. The Ares I-X development flight test will provide flight data to validate engineering models for aerodynamic performance, stage separation, structural dynamic performance, and control system functionality. The Ares I-Y flight test will validate ascent performance of the first stage, stage separation functionality, validate the ability of the upper stage to manage cryogenic propellants to achieve upper stage engine start conditions, and a high-altitude demonstration of the launch abort system (LAS) following stage separation. The Orion 1 flight test will be conducted as a full, un-crewed, operational flight test through the entire ascent flight profile prior to the first crewed launch.

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