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  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (38)
  • 1980-1984
  • 1975-1979  (38)
  • 1975  (38)
  • 1
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    ATS-6 - Flight performance of the Advanced Thermal Control Flight Experiment (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The Advanced Thermal Control Flight Experiment on ATS-6 was designed to demonstrate the thermal control capability of a thermal diode (one-way) heat pipe, a phase-change material for thermal storage, and a feedback-controlled heat pipe. Flight data for the different operational modes are compared to ground test data, and the performance of the components is evaluated on an individual basis and as an integrated temperature-control system.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IEEE Transactions on Aerospace and Electronic Systems; AES-11; Nov. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Simulation verification techniques study: Simulation performance validation techniques document (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Techniques and support software for the efficient performance of simulation validation are discussed. Overall validation software structure, the performance of validation at various levels of simulation integration, guidelines for check case formulation, methods for real time acquisition and formatting of data from an all up operational simulator, and methods and criteria for comparison and evaluation of simulation data are included. Vehicle subsystems modules, module integration, special test requirements, and reference data formats are also described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-150933 , MDC-E1136
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Attitude control requirements for an earth-orbital solar electric propulsion stage (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Solar Electric Propulsion Stage (SEPS) application in earth orbit requires considerably more maneuvering for thrust vector steering and solar array pointing than planetary missions. Attitude maneuver requirements for geosynchronous and low earth-orbital missions are presented. Situations which result in optimum steering torque requirements exceeding the capability of current SEPS configurations are defined. Sub-optimal steering techniques are defined which reduce the geosynchronous mission torque requirements to acceptable levels with negligible performance penalties. Some low earth-orbital flight regimes with earth shadowing are found to result in much larger torque requirements and impose significant mechanization penalties if serious performance losses are to be avoided. Alternative attitude control mechanization techniques are defined for these cases.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 75-353 , American Institute of Aeronautics and Astronautics, Electric Propulsion Conference; Mar 19, 1975 - Mar 21, 1975; New Orleans, LA
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    The SAS-3 power and thermal systems (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Solar array configurations of the SAS-3 are described: a configuration with two sets of coplanar panels in the horizontal and two others in the vertical position, and two other configurations with either four horizontal or four vertical sets of panels. The nickel-cadmium battery of the power subsystem is described in detail, with emphasis on voltage limits and charge-discharge characteristics. The characteristic of 'solar-only' operation in the case of damage to the battery is discussed. The thermal subsystem of SAS-3 is considered, with discussions of thermal design criteria and the thermal environment. Temperature is controlled by using internal thermal louvers that regulate the rate at which the heat load from electronic equipment is transmitted to the outer surface for dumping to space.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: APL Technical Digest; 14; July-Sep
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Space shuttle orbiter trimmed center of gravity extension study. Volume 1: Effects of configuration modifications on the aerodynamic characteristics of the 140 A/B orbiter at Mach 10.3 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Longitudinal and lateral-directional characteristics were obtained on several modified versions of the Rockwell International 140 A/B orbiter (0.010 scale). These modifications, designed to extend trim capability to center-of-gravity locations forward of the 65 percent fuselage station, consisted of two forebodies, two canard trimmers, and two body-wing fillets. Tests were performed over an angle-of-attack range of 12 to 36 degrees at a Reynolds number of 1.03 million based on body reference length. Data were obtained with the elevons and body flap deflected at the full-up and full-down design values. This investigation was conducted in the NASA Langley continuous flow hypersonic tunnel.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-72661
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Results of investigation on an 0.004-scale 140c modified configuration space shuttle vehicle orbiter model (74-0) in the NASA/Langley Research Center hypersonic nitrogen tunnel (OA89) (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind tunnel test data for the modified space shuttle vehicle orbiter is documented. Tests were made at various elevon settings and additionally in wing off/bodyflap off configuration at angles of attack from -5 to 42.5 degrees at zero yaw. Data obtained on high hypersonic longitudinal and lateral directional stability and control characteristics of the updated SSV configuration in an initially diatomic medium are included.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141513 , DMS-DR-2214
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Results of investigations on a 0.004-scale 140C modified configuration space shuttle vehicle orbiter model (74-0) in the NASA/Langley Research Center hypersonic helium tunnel (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Data obtained during a wind tunnel test of a 0.004-scale 140C modified configuration SSV orbiter are documented. The test was conducted during August 1974 with 80 occupancy hours charged, and all runs were conducted at a nominal Mach number of 20 and at Reynolds numbers of 0.7, 1.0, 1.8, and 1,100,000 based on body length. The complete -140C modified model was tested with various elevon settings at angles of attack from 10 to 50 degrees at zero yaw and from angles of sideslip of -10 to +10 at 35 deg angle of attack. The purpose of this test was to obtain high hypersonic longitudinal and lateral-directional stability and control characteristics of the updated SSV configuration.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141532 , DMS-DR-2205
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    A computer-aided telescope pointing system utilizing a video star tracker (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Video Inertial Pointing (VIP) System developed to satisfy the acquisition and pointing requirements of astronomical telescopes is described. A unique feature of the system is the use of a single sensor to provide information for the generation of three axis pointing error signals and for a cathode ray tube (CRT) display of the star field. The pointing error signals are used to update the telescope's gyro stabilization and the CRT display is used by an operator to facilitate target acquisition and to aid in manual positioning of the telescope optical axis. A model of the system using a low light level vidicon built and flown on a balloon-borne infrared telescope is briefly described from a state of the art charge coupled device (CCD) sensor. The advanced system hardware is described and an analysis of the multi-star tracking and three axis error signal generation, along with an analysis and design of the gyro update filter, are presented. Results of a hybrid simulation are described in which the advanced VIP system hardware is driven by a digital simulation of the star field/CCD sensor and an analog simulation of the telescope and gyro stabilization dynamics.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-73079 , A-6365
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Modal analysis and dynamic stresses for acoustically excited shuttle insulation tiles (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Improvements and extensions to the RESIST computer program developed for determining the normalized modal stress response of shuttle insulation tiles are described. The new version of RESIST can accommodate primary structure panels with closed-cell stringers, in addition to the capability for treating open-cell stringers. In addition, the present version of RESIST numerically solves vibration problems several times faster than its predecessor. A new digital computer program, titled ARREST (Acoustic Response of Reusable Shuttle Tiles) is also described. Starting with modal information contained on output tapes from RESIST computer runs, ARREST determines RMS stresses, deflections and accelerations of shuttle panels with reusable surface insulation tiles. Both programs are applicable to stringer stiffened structural panels with or without reusable surface insulation titles.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144958
    Format: application/pdf
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  • 10
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    Results of an investigation of the 0.003-scale space shuttle external tank MSFC model 460 in NASA/MSFC 14 x 14-inch trisonic wind tunnel to determine static pressure distributions during reentry (TA2F), volume 4 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N76-16132.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141826 , DMS-DR-2165-VOL-4
    Format: application/pdf
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