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  • Spacecraft Design, Testing and Performance  (864)
  • 2005-2009  (1,980)
  • 1
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    In:  CASI
    Publication Date: 2019-09-07
    Description: The power point presentation includes an overview of the Hubble Space Telescope, pointing control hardware peculiarities, the two-gyro science (TGS) control system, TGS modifications to preserved hardware lifetime, chasing-down disturbance torques less than or equal to 0.002 Nm, inertia tensor optimization, and a summary with lessons learned.
    Keywords: Spacecraft Design, Testing and Performance
    Type: LMSS; Sep 11, 2007 - Sep 13, 2007; Sunnyvale, CA; United States
    Format: application/pdf
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  • 2
    Publication Date: 2019-08-28
    Description: This Interim Standard establishes requirements for evaluation, testing, and selection of materials that are intended for use in space vehicles, associated Ground Support Equipment (GSE), and facilities used during assembly, test, and flight operations. Included are requirements, criteria, and test methods for evaluating the flammability, offgassing, and compatibility of materials.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA-STD-(I)-6001B , JSC-CN-23865
    Format: application/pdf
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  • 3
    Publication Date: 2019-08-28
    Description: A method is provided for controlling operations in a video guidance sensor system wherein images of laser output signals transmitted by the system and returned from a target are captured and processed by the system to produce data used in tracking of the target. Six modes of operation are provided as follows: (i) a reset mode; (ii) a diagnostic mode; (iii) a standby mode; (iv) an acquisition mode; (v) a tracking mode; and (vi) a spot mode wherein captured images of returned laser signals are processed to produce data for all spots found in the image. The method provides for automatic transition to the standby mode from the reset mode after integrity checks are performed and from the diagnostic mode to the reset mode after diagnostic operations are carried out. Further, acceptance of reset and diagnostic commands is permitted only when the system is in the standby mode. The method also provides for automatic transition from the acquisition mode to the tracking mode when an acceptable target is found.
    Keywords: Spacecraft Design, Testing and Performance
    Format: application/pdf
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  • 4
    Publication Date: 2019-08-28
    Description: The International Space Station (ISS) Program has many lessons to offer for the future of space exploration. Among these lessons of the ISS Program, three stand out as instrumental for the next generation of explorers. These include: 1) resourcefulness and the value of a strong international partnership; 2) flexibility as illustrated by the evolution of the ISS Program and 3) designing with dissimilar redundancy and simplicity of sparing. These lessons graphically demonstrate that the ISS Program can serve as a test bed for future programs. As the ISS Program builds upon the strong foundation of previous space programs, it can provide insight into the prospects for continued growth and cooperation in space exploration. As the capacity for spacefaring increases worldwide and as more nations invest in space exploration and space sector development, the potential for advancement in space exploration is unlimited. By building on its engineering and research achievements and international cooperation, the ISS Program is inspiring tomorrow s explorers today.
    Keywords: Spacecraft Design, Testing and Performance
    Type: IAC-06-B4.1.01 , International Astronautical Congress - Valencia 2006; Oct 02, 2006 - Oct 06, 2006; Valencia,; Spain
    Format: application/pdf
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  • 5
    Publication Date: 2019-08-27
    Description: An androgynous mating system for mating two exoatmospheric space modules comprising a first mating assembly capable of mating with a second mating assembly; a second mating assembly structurally identical to said first mating assembly, said first mating assembly comprising; a load ring; a plurality of load cell subassemblies; a plurality of actuators; a base ring; a tunnel; a closed loop control system; one or more electromagnets; and one or more striker plates, wherein said one or more electomagnets on said second mating assembly are capable of mating with said one or more striker plates on said first mating assembly, and wherein said one or more striker plates is comprised of a plate of predetermined shape and a 5-DOF mechanism capable of maintaining predetermined contact requirements during said mating of said one or more electromagnets and said one or more striker plates.
    Keywords: Spacecraft Design, Testing and Performance
    Format: application/pdf
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