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  • Other Sources  (45)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (45)
  • Chemistry
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  • 2020-2022
  • 2010-2014
  • 1995-1999
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  • 1988  (45)
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  • 2020-2022
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  • 1995-1999
  • 1985-1989  (45)
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  • 1
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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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  • 2
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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
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  • 3
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    Calculation of space station infrared irradiance from atmosphere-induced emissions (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The excitation mechanisms and radiance estimates over the 1 to 10 micron region for CO2(v), H2O(v), CO(v), OH(v), NO2(2B-2A) and N2(B3 pi - A3 sigma) are discussed. The infrared irradiance of the Space Station at an altitude of 460 km was estimated. The surface material was presumed to be non-carbonaceous and inert. The determined number densities of the various gases relevant to the Space Station from both ambient and outgassing sources are presented. A model for the production of and emission from the infrared active molecules was constructed that considers two classes of production processes: (1) gas phase excitation of molecules in the near Station environment by collision with ambient flux; and (2) surface processes that lead to molecular excitation. A composite spectrum of all major emitting species shows that the observed irradiance is non-uniform over the 1 to 8 micron region. The comparison of predicted irradiance with the zodiacal background indicates that the Space Station infrared background from atmosphere-induced emissions may be a problem of consequence.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Langley Research Center, A Study of Space Station Contamination Effects; p 61-69
    Format: application/pdf
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  • 4
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    An application of high authority/low authority control and positivity (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Control Dynamics Company (CDy), in conjunction with NASA Marshall Space Flight Center (MSFC), has supported the U.S. Air Force Wright Aeronautical Laboratory (AFWAL) in conducting an investigation of the implementation of several DOD controls techniques. These techniques are to provide vibration suppression and precise attitude control for flexible space structures. AFWAL issued a contract to Control Dynamics to perform this work under the Active Control Technique Evaluation for Spacecraft (ACES) Program. The High Authority Control/Low Authority Control (HAC/LAC) and Positivity controls techniques, which were cultivated under the DARPA Active Control of Space Structures (ACOSS) Program, were applied to a structural model of the NASA/MSFC Ground Test Facility ACES configuration. The control systems design were accomplished and linear post-analyses of the closed-loop systems are provided. The control system designs take into account effects of sampling and delay in the control computer. Nonlinear simulation runs were used to verify the control system designs and implementations in the facility control computers. Finally, test results are given to verify operations of the control systems in the test facility.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-100338 , NAS 1.15:100338
    Format: application/pdf
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  • 5
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    Simulation of launch and re-entry acceleration profiles for testing of Shuttle and unmanned microgravity research payloads (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: A procedure was developed for the simulation of the launch and reentry acceleration profiles of the Space Shuttle (3.3 and 1.7 g maximum, respectively) and of two versions of NASA's proposed materials research Reusable Reentry Satellite (RRS) (8 and 4 g maximum, respectively). With a 7-m centrifuge, the time dependence of five different acceleration episodes was simulated for payload masses up to 59 kg. Test results obtained for the Materials Dispersion Apparatus, a commercial low-cost payload device, are presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Advances in Space Research (ISSN 0273-1177); 8; 12 1; 141-146
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  • 6
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    Microprocessor controlled force actuator (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 11; 230-236
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  • 7
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    A new momentum management controller for the Space Station (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A new approach to CMG (control moment gyro) momentum management and attitude control of the Space Station is developed. The control algorithm utilizes both the gravity-gradient and gyroscopic torques to seek torque equilibrium attitude in the presence of secular and cyclic disturbances. Depending upon mission requirements, either pitch attitude or pitch-axis CMG momentum can be held constant; yaw attitude and roll-axis CMG momentum can be held constant, while roll attitude and yaw-axis CMG momentum cannot be held constant. As a result, the overall attitude and CMG momentum oscillations caused by cyclic aero-dynamic disturbances are minimized. A state feedback controller with minimal computer storage requirement for gain scheduling is also developed. The overall closed-loop system is stable for + or - 30 percent inertia matrix variations and has more than + or - 10 dB and 45 deg stability margins in each loop.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 88-4132 , AIAA Guidance, Navigation and Control Conference; Aug 15, 1988 - Aug 17, 1988; Minneapolis, MN; United States
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  • 8
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    An intelligent, free-flying robot (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The ground-based demonstration of 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: Space Station Automation IV; Nov 07, 1988 - Nov 09, 1988; Cambridge, MA; United States
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  • 9
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    Assessment and control of structural damage (1988)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: The objective of this paper is to summarize and review several investigations on the assessment and control of structural damage in civil engineering. Specifically, the definition of structural damage is discussed. A candidate method for the evaluation of damage is then reviewed and demonstrated. Various ways of implementing passive and active control of civil engineering structures are next summarized. Finally, the possibility of applying expert systems is discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL, Model Determination for Large Space Systems, Volume 3; 43 p
    Format: text
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  • 10
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    Identification of the zero-g shape of a space beam (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 25; 405-412
    Format: text
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