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  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (68)
  • 1975-1979  (68)
  • 1970-1974
  • 1935-1939
  • 1975  (68)
  • 1
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    Flight performance of a navigation, guidance, and control system concept for automatic approach and landing of space shuttle orbiter (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Unpowered automatic approaches and landings were conducted to study navigation, guidance, and control problems associated with terminal area approach and landing for the space shuttle vehicle. The flight tests were performed in a Convair 990 aircraft equipped with a digital flight control computer connected to the aircraft control system and displays. The tests were designed to evaluate the performance of a navigation and guidance concept that utilized blended radio/inertial navigation with VOR, DME, and ILS as the ground navigation aids. Results from 36 automatic approaches and landings from 11,300 m (37,000 ft) to touchdown are presented. Preliminary results indicate that this concept may provide sufficient accuracy to accomplish automatic landing of the shuttle orbiter without air-breathing engines.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TN-D-7899 , A-5321
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Space shuttle Solid Rocket Booster (SRB) separation (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The system is described which is used to separate the solid rocket boosters from the space shuttle after they have expended most of their propellant and their thrust is near burnout. The dynamics of the separation are simulated in a computer program so that the separation system can be analyzed. The assumptions and ground rules used in analyzing this system are explained and the method of analysis is delineated. The capability of the separation system is presented together with data which may be used to aid in the design of the external tank and solid rocket booster interface. The results of a parameter study to determine the sensitivity of the separation to the initial state of the space shuttle are also presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-64967
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Analysis and design of a capsule landing system and surface vehicle control system for Mars exploration (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Problems related to an unmanned exploration of the planet Mars by means of an autonomous roving planetary vehicle are investigated. These problems include: design, construction and evaluation of the vehicle itself and its control and operating systems. More specifically, vehicle configuration, dynamics, control, propulsion, hazard detection systems, terrain sensing and modelling, obstacle detection concepts, path selection, decision-making systems, and chemical analyses of samples are studied. Emphasis is placed on development of a vehicle capable of gathering specimens and data for an Augmented Viking Mission or to provide the basis for a Sample Return Mission.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-143374 , RPI-TR-MP-48
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Aerodynamic characteristics of MSFC model 454 of the 142 inch solid rocket booster tested in the LeRC 10 foot SWT at Mach numbers of 2.0 and 2.7 (SA6F) (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A 2.112 percent scale Space Shuttle Solid Rocket Booster (SRB) was tested in a ten foot, supersonic wind tunnel. The test Mach numbers were 2.0 and 2.7. Test angles of attack were from minus 5 degrees to plus 185 degrees. The Reynolds numbers ranged from 0.514 to 2.81 million per foot. Test roll angles were 0, 22.5, 45, 90, and 135 degrees. The following configurations were tested: (1) SRB without external protuberances, (2) SRB with an electrical tunnel and a thrust attachment structure, (3) SRB with two engine shroud strakes, (4) SRB with eight engine shroud strakes, and (5) SRB with an electrical tunnel, thrust attachment structure, eight engine shroud strakes, and separation motors.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-134422 , DMS-DR-2161
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Spacecraft charging at high altitudes - The SCATHA satellite program (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-08-13
    Description: Satellites at synchronous altitude exhibit unexplained behavior in the operation of electronic circuits and in the performance of thermal controls. A possible explanation for this behavior is the fact that satellites can be charged to large negative voltages by energetic electrons in the space environment. A space measurements program entitled SCATHA has been formulated to determine the characteristics of the charging process, to measure the response of the satellite when charging occurs, and to evaluate the utility of various corrective techniques which can minimize differential charging on the satellite. The instrumentation will measure charging levels and rates of twenty samples of satellite materials, some of which will be modified to prevent buildup of electrostatic charge. The electromagnetic interference background on the satellite will be measured for comparison with MIL STD 461, Electromagnetic Interference Characteristics Requirements for Equipment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 75-92 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA
    Format: text
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  • 6
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    Stabilization of large-scale systems - A spinning flexible spacecraft (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Stabilization of high-order constant systems by multilevel control is proposed in the framework of the decomposition-aggregation method for stability analysis of large-scale systems. An 11-order linear model of a spinning flexible spacecraft is stabilized by the method using both the passive and the active stabilization devices. The method can take advantage of the special structural features of the model to provide the best estimate of the stability region for an important parameter which couples the wobble and the spin motion of the spacecraft.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: International Federation of Automatic Control, Triennial World Congress; Aug 24, 1975 - Aug 30, 1975; oston; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    ATS-6 - Spacecraft Attitude Precision Pointing and Slewing Adaptive Control Experiment (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The primary objective of the Spacecraft Attitude Precision Pointing and Slewing Adaptive Control (SAPPSAC) experiment is to establish feasibility and evaluate capabilities of a ground-based spacecraft attitude control system, wherein RF command and telemetry links, together with a ground station on-line minicomputer, perform closed loop attitude control of the Applications Technology Satellite-6 (ATS-6). The ground processor is described, including operational characteristics and the controller software. Attitude maneuvers include precision pointing to fixed targets, slewing between targets, and generation of prescribed ground tracks. Test results show high performance and reliability for over 30 hours of on-line control with no serious anomalies. Attitude stabilization relative to a prescribed target has been achieved to better than 0.007 deg in pitch and roll and 0.02 deg in yaw for a period of 43 min. Ground tracks were generated which had maximum latitude/longitude deviations less than 0.15 deg from reference.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IEEE Transactions on Aerospace and Electronic Systems; AES-11; Nov. 197
    Format: text
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  • 8
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    Automatic computer controlled testing of spacecraft and experiments (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: Autotest is a flexible, fully automatic, programmable test system. It is externally controlled by a mnemonic test language. Once started, tests can run to completion without further manual intervention. Autotest can be operated manually as well as in automatic mode. Autotest can be adapted to a wide variety of test requirements. Though originally designed to test the Atmosphere Explorer (AE) spacecraft and experiments, autotest can easily be modified to test any electronic device suitable for automated computer testing.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Inst. of Environ. Sci. Proc. of 2d Aerospace Testing Seminar; 12 p
    Format: text
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  • 9
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    Heat transfer tests of an 0.006-scale thin-skin space shuttle thermocouple model (41-OTS) in the Langley Research Center unitary plan wind tunnel at M equals 3.7 (IH16) (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results are presented of supersonic heat transfer tests performed on the .006 scale space shuttle vehicle model (41-OTS) in the Langley Research Center Unitary Plan Wind Tunnel. These tests were conducted to parametrically investigate ascent heating of the integrated vehicle and its components. The tests were conducted at a nominal Mach number of 3.7 and Reynolds numbers per foot of 2 and 5 million. The model configurations investigated were the integrated vehicle and each component alone (i.e. orbiter, tank and SRB). All the configurations were run with and without transition strips and through an angle of attack range of 0 deg to minus 5 deg with the exception of the SRB which was tested through an angle of attack range of minus 5 deg to 90 deg. The heat transfer data were obtained from 223 iron constantan thermocouples attached to stainless steel thin-skin areas of the model.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141534 , DMS-DR-2166
    Format: application/pdf
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  • 10
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    Minimum thrust levels for spinning drag-free satellites (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A drag-free satellite, which contains an internal unsupported proof mass, is shielded from external forces such as solar pressure. Thrustors force the satellite to follow the proof mass and hence the satellite follows an almost purely gravitational orbit. The dominant internal disturbing force is the mass attraction of the satellite on the proof mass. Spinning the satellite reduces this force and it has been investigated what the size of the thrustors must be in this case. This size is much smaller than originally thought. Its impact on some other features is shown.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Automatica; 11; Nov. 197
    Format: text
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