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  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (250)
  • 1985-1989  (250)
  • 1
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    NASA in-house Commercially Developed Space Facility (CDSF) study report. Volume 1: Concept configuration definition (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of a NASA in-house team effort to develop a concept definition for a Commercially Developed Space Facility (CDSF) are presented. Science mission utilization definition scenarios are documented, the conceptual configuration definition system performance parameters qualified, benchmark operational scenarios developed, space shuttle interface descriptions provided, and development schedule activity was assessed with respect to the establishment of a proposed launch date.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-101586-VOL-1 , NAS 1.15:101586-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    A steerable radiator for spacecraft application (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Future large space structures such as the Space Station will have high dissipation and long life requirements which dictate the requirements for steerable radiators. Several rotary coupling concepts were considered to accomplish heat transport across the steerable radiator system's rotating interface. Rotary fluid couplings were chosen over rotary contact couplings or flexible lines because of low temperature gradients and operational flexibility. A rotary fluid coupling has been designed for use on initial operating capability (IOC) and growth Space Station. Its internal seals have been demonstrated to a 10 year life with minimal (0.055 lbm NH3/year) leakage between internal passages. Materials compatibility tests have been conducted to demonstrate compatibility with ammonia. A seal leakage management system has been designed to: (1) monitor pressures between the internal seals, (2) remove leakage, and (3) store the leakage fluid in a reservoir.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 86-1298
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Nuclear-powered space debris sweeper (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Future spacecraft design will be affected by collisions with man-made debris orbiting the earth. Most of this orbital space debris comes from spent rocket stages. It is projected that the source of future debris will be the result of fragmentation of large objects through hypervelocity collisions. Orbiting spacecraft will have to be protected from hypervelocity debris in orbit. The options are to armor the spacecraft, resulting in increased mass, or actively removing the debris from orbit. An active space debris sweeper is described which will utilize momentum transfer to the debris through laser-induced ablation to alter its orbital parameters to reduce orbital lifetime with eventual entry into the earth's atmosphere where it will burn. The paper describes the concept, estimates the amount of velocity change (Delta V) that can be imparted to an object through laser-induced ablation, and investigates the use of a neutral particle beam for the momentum transfer. The space sweeper concept could also be extended to provide a collision avoidance system for the space station and satellites, or could be used for collision protection during interplanetary travel.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 5; 582-590
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    New approach to attitude/momentum control for the Space Station (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 12; 714-722
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Optimal experiment design for identification of large space structures (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The optimal experiment design for on-orbit identification of modal frequency and damping parameters in large flexible space structures is discussed. The main result is a separation principle for D-optimal design which states that under certain conditions the sensor placement problem is decoupled from the input design problem. This decoupling effect significantly simplifies the overall optimal experiment design determination for large MIMO structural systems with many unknown modal parameters. The error from using the uncoupled design is estimated in terms of the inherent damping of the structure. A numerical example is given, demonstrating the usefulness of the simplified criteria in determining optimal designs for on-orbit Space Station identification experiments.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Automatica (ISSN 0005-1098); 24; 357-364
    Format: text
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  • 6
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    Expanding role for autonomy in military space (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The Jet Propulsion Laboratory is currently transferring satellite on-board autonomy technology to the USAF for use in military spacecraft as a means of lowering the ground support requirements. The techniques were proven on the Viking and Voyager spacecraft and permitted on-board fault detection and correction. New military satellites will incorporate an autonomous redundancy and maintenance management subsystem in an on-board computer, while the system will still be subject to ground-based safing commands for situations demanding deeper analyses. A level 5 autonomy will need 256 kb memory, 10 Mb nonvolatile data storage and 50 W power and will weigh 20 kg. Systems will be periodically checked and compared with an ideal in the data base. Deviations detected will result in a rollback and redundant examination by two microprocessors, which can initiate correction commands until operational criteria are met. The development of the expert systems to the point that they satisfy military specifications is expected to take 10 yr.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Aerospace America (ISSN 0740-722X); 23; 74-77
    Format: text
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  • 7
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    An intelligent, free-flying robot (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The ground based demonstration of the extensive extravehicular activity (EVA) Retriever, a voice-supervised, intelligent, free flying robot, is designed to evaluate the capability to retrieve objects (astronauts, equipment, and tools) which have accidentally separated from the Space Station. The major objective of the EVA Retriever Project is to design, develop, and evaluate an integrated robotic hardware and on-board software system which autonomously: (1) performs system activation and check-out; (2) searches for and acquires the target; (3) plans and executes a rendezvous while continuously tracking the target; (4) avoids stationary and moving obstacles; (5) reaches for and grapples the target; (6) returns to transfer the object; and (7) returns to base.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL, California Inst. of Tech., Proceedings of the NASA Conference on Space Telerobotics, Volume 5; p 373-379
    Format: application/pdf
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  • 8
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    Navigation and pointing timeline development for an autonomous free-flying Shuttle payload (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 11; 110-118
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Maximum Entropy/Optimal Projection (MEOP) control design synthesis: Optimal quantification of the major design tradeoffs (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The underlying philosophy and motivation of the optimal projection/maximum entropy (OP/ME) stochastic modeling and reduced control design methodology for high order systems with parameter uncertainties are discussed. The OP/ME design equations for reduced-order dynamic compensation including the effect of parameter uncertainties are reviewed. The application of the methodology to several Large Space Structures (LSS) problems of representative complexity is illustrated.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Marshall Space Flight Center Structural Dynamics and Control Interaction of Flexible Structures; p 1033-1070
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Development of the Spartan 101 navigation and pointing timeline (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents the techniques and analyses that were used to construct the Spartan 101 mission pointing timeline for the Space Shuttle Orbiter-detached portion of its flight. This covers the design process that had to transform requirements and constraints originating from the experimenter, the Space Transportation System, and the payload hardware design into a workable set of pointing instructions sequenced to mission events. The paper will discuss the technical approach used for initial attitude acquisition, determining target visibility, observation scheduling, and calculation of vehicle maneuvers.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 86-2526
    Format: text
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