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  • Other Sources  (429)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (429)
  • 1975-1979  (429)
  • 1935-1939
  • 1977  (89)
  • 1975  (340)
  • 1936
  • 1
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    Space shuttle (1975)
    In:  CASI
    Details
    Publication Date: 2006-04-10
    Description: The transportation cost associated with space materials processing were studied to determine the feasibility of space manufacturing. The assumptions use to determining the cost estimates for a 12 year planning period are listed, and the orbitor is described in terms of payloads. Shuttle operational costs, ground operational costs, and nonrecurring investment and development costs were analyzed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Econ. Analysis of Materials Processing in Space; p 8-39
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  • 2
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    Evolution of spacecraft attitude control concepts before 1952 (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: The control of rotational motion of a spacecraft during its free flight regime is traced from pioneer space flight to the year 1952. Essentials of attitude control systems are reviewed and spin stabilization is examined. Other topics include passive stabilization and active closed loop control.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Washington Essays on the History of Rocketry and Astronautics, Vol. 1; p 156-169
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  • 3
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    F. Gomez Arias' rocket vehicle project (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Research done by Spanish pioneer rocket scientists in the 19th century was investigated with major emphasis placed on F. Gomez Arias' rocket vehicle project. Arias, considered the world's first designer of rocket propelled, manned aircraft, was interested in solving the problem of space navigation. Major concerns included ascent and direction of heavier-than-airmachines, as well as ascent and direction of balloons.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Washington Essays on the History of Rocketry and Astronautics, Vol. 1; p 176-185
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  • 4
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    Spacecraft-produced neutron fluxes on Skylab (1977)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Estimates of neutron fluxes in different energy ranges are reported for the Skylab spacecraft. Detectors composed of uranium, thorium, and bismuth foils with mica as a fission track recorder, as well as boron foils with cellulose acetate as an alpha-particle recorder, were deployed at different positions in the Orbital Workshop. It was found that the Skylab neutron flux was dominated by high energy (greater than 1 MeV) contributions and that there was no significant time variation in the fluxes. Firm upper limits of 7-15 neutrons/sq cm-sec, depending on the detector location in the spacecraft, were established for fluxes above 1 MeV. Below 1 MeV, the neutron fluxes were about an order of magnitude lower. The neutrons are interpreted as originating from the interactions of leakage protons from the radiation belt with the spacecraft.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Space Science Instrumentation; 3; Nov. 197
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  • 5
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    NASCAP, a three-dimensional Charging Analyzer Program for complex spacecraft (1977)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: A computer code, NASCAP (NASA Charging Analyzer Program), has been developed by Systems, Science and Software under contract to NASA-LeRC to simulate the charging of a complex spacecraft in geosynchronous orbit. The capabilities of the NASCAP code include a fully three-dimensional solution of Poisson's equation about an object having considerable geometrical and material complexity, particle tracking, shadowing in sunlight, calculation of secondary emission, backscatter and photoemission, and graphical output. A model calculation shows how the NASCAP code may be used to improve our understanding of the spacecraft-plasma interaction.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 6
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    Prediction and measurement results of radiation damage to CMOS devices on board spacecraft (1977)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Final results from the CMOS Radiation Effects Measurement (CREM) experiment flown on Explorer 55 are presented and discussed, based on about 15 months of observations and measurements. Conclusions are given relating to long-range annealing, effects of operating temperature on semiconductor performance in space, biased and unbiased P-MOS device degradation, unbiased n-channel device performance, changes in device transconductance, and the difference in ionization efficiency between Co-60 gamma rays and 1-Mev Van de Graaff electrons. The performance of devices in a heavily shielded electronic subsystem box within the spacecraft is evaluated and compared. Environment models and computational methods and their impact on device-degradation estimates are being reviewed to determine whether they permit cost-effective design of spacecraft.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 7
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    An analytical and experimental study for surface heat flux determination (1977)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: A numerical method by which data from a single embedded thermocouple can be used to predict the transient thermal environment for both high- and low-conductivity materials is described. The results of an investigation performed to verify the method clearly demonstrate that accurate transient surface heating conditions can be obtained from a thermocouple 1.016 cm from the surface in a low-conductivity material. Space Shuttle Orbiter thermal protection system materials having temperature- and pressure-dependent properties and typical Orbiter entry heating conditions were used to verify the accuracy of the analytical procedure. Analytically generated, as well as experimental, data were used to compare predicted and measured surface temperatures.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets; 14; Oct. 197
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  • 8
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    Magnetic attitude control system for dual-spin satellites (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A closed-loop control law is developed for a dual-spin satellite control system which utilizes the interaction of the geomagnetic field with the satellite dipole parallel to the spin axis. The control law consists of the linear combination of the pitch axis component of the rate of change of the geomagnetic field and the product of the roll angle and roll axis component of the geomagnetic field. Application of the method of multiple time scales yields approximate solutions for the feedback gains in terms of the system parameters. Approximate solutions are also obtained for the response of the system to disturbance torques. A comparison of the approximate solutions and numerical solutions obtained by numerical integration of the exact equations of motion is then given.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA Journal; 13; June 197
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  • 9
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    Pioneer 10 and Pioneer 11 (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: On December 3, 1974, Pioneer 11 passed the planet Jupiter at a distance of 42,000 km. The spacecraft is now headed for an encounter with the planet Saturn in September 1979. The prime scientific objectives of the Pioneer 10 and Pioneer 11 missions are discussed along with the spacecraft payload, aspects of spacecraft design, the spacecraft power supply, and details regarding the spacecraft trajectory during the approach to Jupiter.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Science; 188; May 2
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  • 10
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    Energetic solar proton vs terrestrially trapped proton fluxes (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The relative importance of solar and trapped proton fluxes in the consideration of shielding requirements for geocentric space missions is analyzed. Using models of these particles, their fluences encountered by spacecraft in circular orbits are computed as functions of orbital altitude and inclination, mission duration, threshold energy (10 to 100 MeV), and risk factor (for solar protons only), and ratios of solar-to-trapped fluences are derived. It is shown that solar protons predominate for low-altitude polar and very high-altitude missions, while trapped protons predominate for missions at low and medium altitudes and low inclinations. It is recommended that if the ratio of solar-to-trapped protons falls between 0.1 and 10, both fluences should be considered in planning shielding systems.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets; 12; Feb. 197
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  • 11
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    Large Space Telescope oscillations induced by CMG friction (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Conditions are predicted under which limit cycles may be caused by the friction torque of the control moment gyroscope (CMG) output gimbal used in the Large Space Telescope (LST). The parameter plane analysis technique is described, and three separate models of the CMG output friction nonlinearity are used in three separate analyses. The results suggest that the Dahl model (included in model 3) is the best available friction model for use in dynamic analysis. The analysis and analog simulation indicate the absence of limit cycle behavior due to the CMG output gimbal friction nonlinearity for presently estimated LST numerical parameters and the occurrence of one stable and one unstable limit cycle if substantially larger numerical values are allowed for the CMG gimbal pivot friction parameter and/or the running friction torque.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets; 12; Feb. 197
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  • 12
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    Spacecraft technology (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Developments in spacecraft technology are discussed with emphasis on the Explorer satellite program. The subjects considered include the following: (1) nutational behavior of the Explorer-45 satellite, (2) panoramic sensor development, (3) onboard camera signal processor for Explorer satellites, and (4) microcircuit development. Information on the zero gravity testing of heat pipes is included. Procedures for cleaning heat treated aluminum heat pipes are explained. The development of a five-year magnetic tape, an accurate incremental angular encoder, and a blood freezing apparatus for leukemia research are also discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Significant Accomplishments in Sci. and Technol.; p 139-178
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  • 13
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    The SAS-3 attitude control system (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: SAS-3 uses a reaction wheel to provide torque to control the spin rate. If the wheel speed becomes too great or too small, it must be restored to its nominal rate by momentum dumping which is done by magnetic torquing against the earth's magnetic field by the satellite's magnetic coils. A small rate-integrating gyro is used to sense the spin rate so that closed loop control of the spin rate can be achieved. These various systems are described in detail including the reaction wheel system, the gyro system, along with control modes (spin rate control and the star lock mode).
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: APL Technical Digest; 14; July-Sep
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  • 14
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    The SAS-3 power and thermal systems (1975)
    In:  Other Sources
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    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
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  • 15
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    In-orbit servicing (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A concept called the low-cost modular spacecraft, in which the subsystems would be contained in replaceable modules and which would be capable of various applications, is under engineering development. Studies have shown that servicing of such a spacecraft on orbit by the Space Shuttle over an extended lifetime is more economical than three other alternatives: launching replacement satellites on conventional boosters as existing satellites fail, launching replacements by Shuttle, or launching replacement satellites and retrieving malfunctioning satellites by Shuttle. For on-orbit servicing, the Shuttle would use its Remote Manipulator system (RMS) to bring the malfunctioning satellite into its cargo bay. The Flight Support System (FSS) on the Orbiter used for servicing the satellite would include an appendage storage frame, a retention cradle, a positioning platform, a Module Exchange Mechanism (MEM), and a storage magazine. Ground simulations are under way with the Orbiter mockup.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 13; Feb. 197
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  • 16
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    New directions in space electronics (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Five new directions in space electronics are defined to yield improvements over present means: automated operations aimed at a tenfold reduction in mission support costs, precision pointing and control, efficient data acquisition to permit the tenfold increase in information collection needed for global coverage, real-time data management, and low-cost data distribution to allow a thousand-fold increase in information availability and space-systems effectiveness. Technological developments and resources for each of the new directions are derived from space-technology and space-theme workshops. One to two order of magnitude improvements in instrument pointing stability will be necessary for Shuttle and planetary payloads of the 1980s. Low-cost user terminals will involve technological addressing both near-term and long-term applications. NASA has reoriented its research and technology-base programs to support the goals represented by the new directions in space electronics. Numerous charts and schematic diagrams supplement the text.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 15; Feb. 197
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  • 17
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    Space Shuttle's orbital environment (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Variations with the solar cycle of chemical composition, density and temperature of the orbital environment of the Space Shuttle are reviewed; micrometeoroid fluxes, ionizing radiation, photon fluxes and cosmic ray bombardment to which the Shuttle will be subjected are also mentioned. In addition, gases arising from offgassing and outgassing of contaminants (at about 300 K) from the Shuttle are considered, and particulates ejected during rocket firings or from the leakage of pressurized vessels (i.e., the cabin) are taken into account.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 18
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    Methods of shield analysis for protection against electrons in space (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: It is anticipated that many future manned space operations will be radiation limited and that laminated wall structures and the use of new materials will be required to reduce radiation exposure. Methods for electron shield analysis are reviewed in light of anticipated needs in the space program. The most general method is still the Monte Carlo method, which is of limited usefulness for shield analysis due to excessive computer requirements. Methods based on energy deposition coefficients or energy transmission and reflection factors are quite accurate, but are currently limited to aluminum shield material. Analytical methods based on Mar's approximation for the electron transmission factor are relatively general and computer efficient but seriously underestimate shield requirements. A correction to methods using Mar's approximate transmission factor is derived herein and results in a slightly conservative estimate of shield requirements. Techniques for laminated shield design are still lacking.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Nuclear Technology; 35; Aug. 197
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  • 19
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    Weight optimization methods in space radiation shield design (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An empirical relation between proton range and material density is used to examine relations between shield weight, geometry, and material composition for shielding against a space proton environment. The optimum material resulting in minimum shield weight usually lies at the extremes of either the lightest or heaviest materials. Aluminum, which has special prominence in the space program, appears universally suboptimal as a radiation shielding material. Assuming square-box geometry (rectangular prisms with two square faces), the optimum shape for the shielded objects is found to be a cube, although moderate deviations from a cube result in only a small weight penalty.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets; 12; Dec. 197
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  • 20
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    ATS-6 - Flight performance of the Advanced Thermal Control Flight Experiment (1975)
    In:  Other Sources
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    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
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  • 21
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    ATS-6 - Spacecraft Attitude Precision Pointing and Slewing Adaptive Control Experiment (1975)
    In:  Other Sources
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    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
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  • 22
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    ATS-6 - Description and performance (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The Applications Technology Satellite-6 embodies a geosynchronous technology that is sensitive enough to receive signals from simple inexpensive earth-based terminals and is powerful enough to relay color television and other high-quality signals to these terminals. This was accomplished by deploying a 9.1-m parabolic reflector antenna in space, by performing precision attitude maneuvers on commands from the earth to point the reflector to selected spots on the earth's surface, and by providing communications links and necessary power to receive and rebroadcast signals transmitted from the ground. All major objectives of the ATS program have been satisfied, with specifications being met or exceeded.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IEEE Transactions on Aerospace and Electronic Systems; AES-11; Nov. 197
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  • 23
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    Proceedings of the Spacecraft Charging Technology Conference: Executive Summary (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Aerospace environments are reviewed in reference to spacecraft charging. Modelling, a theoretical scheme which can be used to describe the structure of the sheath around the spacecraft and to calculate the charging currents within, is discussed. Materials characterization is considered for experimental determination of the behavior of typical spacecraft materials when exposed to simulated geomagnetic substorm conditions. Materials development is also examined for controlling and minimizing spacecraft charging or at least for distributing the charge in an equipotential manner, using electrical conductive surfaces for materials exposed to space environment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Res. Center Proc. of the Spacecraft Charging Technol. Conf.; p 9-20
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  • 24
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    Testing of typical spacecraft materials in a simulated substorm environment (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The test specimens were spacecraft paints, silvered Teflon, thermal blankets, and solar array segments. The samples, ranging in size from 300 to 1000 sq cm were exposed to monoenergetic electron energies from 2 to 20 keV at a current density of 1 NA/sq cm. The samples generally behaved as capacitors with strong voltage gradient at their edges. The charging characteristics of the silvered Teflon, Kapton, and solar cell covers were controlled by the secondary emission characteristics. Insulators that did not discharge were the spacecraft paints and the quartz fiber cloth thermal blanket sample. All other samples did experience discharges when the surface voltage reached -8 to -16kV. The discharges were photographed. The breakdown voltage for each sample was determined and the average energy lost in the discharge was computed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Proc. of the Spacecraft Charging Technol. Conf.; p 431-457
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  • 25
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    The Skylab Parasol (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An alternate thermal protection system for the Skylab space station cluster was deemed necessary shortly after launch when severe damage occured to the orbital workshop as it passed through the period of maximum dynamic pressure. Data indicated that the combination micrometeoroid and thermal shield on the sun facing side of the vehicle had been destroyed. The simultaneous design, fabrication, and test of the Skylab Parasol System which was completed in 6 days of around-the-clock effort is described. The Skylab Parasol design was selected as the primary sunshade device based on simplicity of design, ability to fabricate quickly, and early demonstration of a working prototype which featured semiautomatic deployment from within the workshop under shirt sleeve environment conditions.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: 9th Aerospace Mech. Symp.; p 99-113
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  • 26
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    An active nutation damper for spacecraft (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An active nutation damping device, consisting of an angular accelerometer, a dc-motor-driven flywheel, and associated electronics, developed for spacecraft use is described. This damping system was used on the LAGEOS spacecraft to control nutation buildup during the long coast period (approximately 75 minutes) after the third stage separation. The damper package was evaluated and proven on a three-axis gas-bearing simulator that duplicated the LAGEOS spacecraft critical flight dynamics. In addition, a failure analysis of the damper assembly was performed. Performance of the damper during the LAGEOS flight has confirmed the preflight evaluation and analysis.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: The 11th Aerospace Mech. Symp.; p 133-145
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  • 27
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    Comparative analysis of the designs and implementation of vehicles based on reactive propulsion proposed during the nineteenth and beginning of the twentieth centuries (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Examination of the presently known historical scientific literature related to the problem of reactive flight indicates that considerable attention had already been given to the idea of reactive propulsion in the nineteenth century; about thirty designs for reaction flying vehicles were proposed during this period. However, the authors of a majority of the designs limited themselves only to a presentation of a diagram of the engine or an account of the principle of its operation, giving neither plans for its structural development nor precise calculations of the amount of energy required for accomplishing reaction flight. None of these authors considered the reaction flying vehicle as an object of variable mass, their choice of energy sources was extremely random, and the theory of the flight of reaction flying vehicles remained completely undeveloped. Early rocket designs of Nezhdanovsky, Ganswindt, Goddard, Tsiolkovsky, and others are examined and the evolution of liquid-propellant rocket engines, solid-propellant rocket engines, and jet aircraft engines is reviewed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Washington Essays on the History of Rocketry and Astronautics Vol. 2; p 3-24
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  • 28
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    Automatic computer controlled testing of spacecraft and experiments (1975)
    In:  Other Sources
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    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
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  • 29
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    Evaluation philosophy for shuttle launched payloads (1975)
    In:  Other Sources
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    Publication Date: 2019-01-25
    Description: Potential benefits of factory-to-pad testing constitute major cost savings and increase test effectiveness. Overall flight performance will be improved. The factory-to-pad approach is compatible with space shuttle processing and the large space telescope program.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Inst. of Environ. Sci. Proc. of 2d Aerospace Testing Seminar; 8 p
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  • 30
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    Test and space experience with protoflight spacecraft (1975)
    In:  Other Sources
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    Publication Date: 2019-01-25
    Description: Based on system level test results, there appears to be some additional risk of space failures when a protoflight spacecraft is launched in lieu of a flight spacecraft. The space performance of all protoflight spacecraft to date has been satisfactory with failure rates slightly less than conventional flight spacecraft. The continued use of the protoflight concept is supported by this study.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Inst. of Environ. Sci. Proc. of 2d Aerospace Testing Seminar; 11 p
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  • 31
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    Space Station Systems Analysis Study. Volume 2: Program options, book 1, parts 1 and 2 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Program options are defined and requirements are determined for integrating crew, mass, volume, and electrical power for a space construction base which incorporates the space shuttle external tanks. Orbits, stabilization, flight control hardware, as well as modules and aids for orbital assembly and servicing are considered. The effectiveness of various program options for life science and radio astronomy missions, for the solar terrestrial observatory, and for public service platforms is assessed. Technology development items are identified and costs are estimated.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-161927 , NAS 1.26:161927 , NSS-SS-RP014-VOL-2-BK-1-PT-1/2
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  • 32
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    Space Station Systems Analysis Study. Volume 1: Executive summary, part 1 and 2 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The elements of space station programs required to support an operational base theme, a space laboratory theme, and advanced missions relatable to public needs/national interests are defined. Missions satisfying the foregoing requirements are identified, program scenarios/options are established. System options are evaluated for a selected number of program options. Subsystem analysis and programmatic comparisons are performed for selected primary concepts.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-161590 , NAS 1.26:161590 , NSS-SS-RP014-VOL-1-PT-1/2
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  • 33
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    Space Station Systems Analysis Study. Volume 2: Program review report (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Major growth options for tended and manned space stations in LEO and GEO are examined including increased orbiter augmentation and habitation requirements. Approaches for providing power supplies, construction aids needed to assemble support platforms, transportation system constraints, and the hardware required for various missions categories are defined. Subsystem requirements are analyzed for structure; flight control; power generation and storage; avionic; life support systems; personnel provisions; and environmental control. Tradeoffs are considered.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-161231 , NAS 1.26:161231 , NSS-SS-RP016-VOL-2
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  • 34
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    IUE/IRA system description (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The IUE/IRA rate sensor system designed to meet the requirements of the International Ultraviolet Explorer spacecraft mission is described. The system consists of the sensor unit containing six rate sensor modules and the electronic control unit containing the rate sensor support electronics and the command/control circuitry. The inertial reference assembly formed by the combined units will provide spacecraft rate information for use in the stabilization and control system. The system is described in terms of functional description, operation redundancy performance, mechanical interface, and electrical interface. Test data obtained from the flight unit are summarized.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-166652
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  • 35
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    Post Viking planetary protection requirements study (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Past planetary quarantine requirements were reviewed in the light of present Viking data to determine the steps necessary to prevent contamination of the Martian surface on future missions. The currently used term planetary protection reflects a broader scope of understanding of the problems involved. Various methods of preventing contamination are discussed in relation to proposed projects, specifically the 1984 Rover Mission.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-155585
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  • 36
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    Instrument pointing system applicability and orbiter stabilization for EVAL missions. Application studies (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Related aspect of the Earth Viewing Applications Laboratory (EVAL) shuttle missions were investigated. The applicability of the gimballed Instrument Pointing System (IPS) to EVAL missions by comparing the IPS capabilities with the EVAL requirements was evaluated, and a means of stabilizing the shuttle orbiter attitude in earth viewing orientations for prolonged periods without use of the orbiter gas reaction control system was assessed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-156662 , TRW-14897-6011-RU-00
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  • 37
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    Dual-spin attitude control for outer planet missions (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The applicability of dual-spin technology to a Jupiter orbiter with probe mission was investigated. Basic mission and system level attitude control requirements were established and preliminary mechanization and control concepts developed. A comprehensive 18-degree-of-freedom digital simulation was utilized extensively to establish control laws, study dynamic interactions, and determined key sensitivities. Fundamental system/subsystem constraints were identified, and the applicability of dual-spin technology to a Jupiter orbiter with probe mission was validated.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-155425 , JPL-PUB-77-74
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  • 38
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    Voyager electronic parts radiation program, volume 1 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Voyager spacecraft is subject to radiation from external natural space, from radioisotope thermoelectric generators and heater units, and from the internal environment where penetrating electrons generate surface ionization effects in semiconductor devices. Methods for radiation hardening and tests for radiation sensitivity are described. Results of characterization testing and sample screening of over 200 semiconductor devices in a radiation environment are summarized.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-155534 , JPL-PUB-77-41-VOL-1
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  • 39
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    Entry dynamics of space shuttle orbiter with lateral-directional stability and control uncertainties at supersonic and hypersonic speeds (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A six-degree-of-freedom simulation analysis was conducted to examine the effects of the lateral-directional static aerodynamic stability and control uncertainties on the performance of the automatic (no manual inputs) entry-guidance and control systems of the space shuttle orbiter. To establish the acceptable boundaries of the uncertainties, the static aerodynamic characteristics were varied either by applying a multiplier to the aerodynamic parameter or by adding an increment. Control-system modifications were identified that decrease the sensitivity to off-nominal aerodynamics. With these modifications, the acceptable aerodynamic boundaries were determined.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1011 , L-11112
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  • 40
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    Development of the engineering design integration (EDIN) system: A computer aided design development (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The EDIN (Engineering Design Integration) System which provides a collection of hardware and software, enabling the engineer to perform man-in-the-loop interactive evaluation of aerospace vehicle concepts, was considered. Study efforts were concentrated in the following areas: (1) integration of hardware with the Univac Exec 8 System; (2) development of interactive software for the EDIN System; (3) upgrading of the EDIN technology module library to an interactive status; (4) verification of the soundness of the developing EDIN System; (5) support of NASA in design analysis studies using the EDIN System; (6) provide training and documentation in the use of the EDIN System; and (7) provide an implementation plan for the next phase of development and recommendations for meeting long range objectives.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-151568 , TN-1977-810
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  • 41
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    Wind tunnel test 0A113 of the 0.010-scale space shuttle orbiter model 51-0 in the calspan hypersonic shock tunnel (48-inch leg) (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results are presented of wind tunnel test conducted Hypersonic Shock Tunnel using a 0.010-scale 140A/B configuration orbiter model designated 51-0. The test objectives were: (1) to obtain force and moment data at various Mach numbers and Reynolds numbers from which viscous interaction effects on stability and control may be determined. (1) To provide flow visualization data from which the effects of control surface separation may be evaluated. and (3) To obtain pressure data in conjunction with force and moment data to assist in analyzing viscous interaction and flow separation effects. Data were obtained at angles-of-attack of 20 deg, 30 deg, 40 deg, and 50 deg. The Mach number range covered was from 10 to 16 and the viscous interaction parameter range was from 0.01 to 0.06.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141547 , DMS-DR-2234
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  • 42
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    Thermoelastic flutter models for elements of flexible satellites (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Models of thermally induced flutter of the flexible elements of a satellite, such as beams, circular plates, and cylindrical shells, have been obtained. These models form the necessary blocks for analyzing the motion of satellites. The heat input is considered to be caused by solar radiation. The partial differential equations for all the elements of the satellite are linear in the space-dependent variables and nonlinear in the time-dependent variables. These equations are coupled through the motion of the center of mass of the satellite. Galerkin's method has been used to remove the space-dependence of these equations.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Acta Astronautica; 2; Sept
    Format: text
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  • 43
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    Heat transfer phase change paint tests of 0.0175-scale models (nos. 21-0 and 46-0) of the Rockwell International space shuttle orbiter in the AEDC tunnel B hypersonic wind tunnel (test OH25A) (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were conducted in a hypersonic wind tunnel using various truncated space shuttle orbiter configurations in an attempt to establish the optimum model size for other tests examining body shock-wing leading edge interference effects. The tests were conducted at Mach number 8 using the phase change paint technique. A test description, tabulated data, and tracings of isotherms made from photographs taken during the test are presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141546 , DMS-DR-2252
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  • 44
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    Payload/orbiter contamination control requirement study (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a contamination impact analysis upon the spacelab carrier and the spacelab carrier upon some of its potential payloads are presented. These results are based upon contamination computer modeling techniques developed to predict the induced environment for spacelab and to provide the basis for evaluation of the predicted environment against the current on orbit contamination control criteria as specified for payloads. Those spacelab carrier contamination sources evaluated against the stated contamination control criteria were outgassing/offgassing of the major nonmetallic thermal control coating of the spacelab carriers, spacelab core and experiment module and tunnel cabin atmosphere leakage, avionics bay vent, spacelab condensate vent, random particulate sloughing, and the return flux of the molecular content of these sources from the gas-gas interactions with the ambient orbital environment. It is indicated that the spacelab carrier can meet the intent of the contamination control criteria through incorporating known contamination control practices.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-143883 , MCR-75-202
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  • 45
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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
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  • 46
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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
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  • 47
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    Preliminary vibration, acoustic, and shock design and test criteria for components on the HEAO-A spacecraft (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: These vibration, acoustic, and shock specifications provide the qualification test criteria for spacecraft components and subassemblies and for the High Energy Astronomy Observatory (HEAO-A) experiments. The HEAO-A was divided into zones and subzones to obtain simple component groupings. Zones are designated primarily to assist in determining the applicable specification. A Subzone is available for use when the location of the component is known but component design and weight are not well defined. When the location, weight, and mounting configuration of the component are known, the appropriate Subzone weight ranges are available. Experiment and specific component specifications are available.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-64919
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  • 48
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    Verification of a landing dynamics computer program using Viking Lander data (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted to verify the accuracy of the Landing Dynamics Computer Program (LDCP) used to simulate the landing event of the Viking Lander (VL) on to the Martian surface. This verification was achieved by comparing the analytical data with results from a test program involving a dynamically scaled model of a VL configuration. A secondary objective of this study was to evaluate the sensitivity of the VL to initial rates and orientations, configuration modifications, and footpad friction.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-72653
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  • 49
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    Feasibility study of the Boeing Small Research Module (BSRM) concept (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N75-20453.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-137662 , D180-18450-2
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  • 50
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    Feasibility study of the Boeing Small Research Module (BSRM) concept (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N75-20453.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-137663 , D180-18450-3
    Format: application/pdf
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  • 51
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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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  • 52
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    Wind tunnel tests of an 0.019-scale space shuttle integrated vehicle -2A configuration (model 14-OTS) in the NASA Ames 8 X 7 foot unitary wind tunnel, volume 3 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were conducted to determine the effects of cold jet gas plumes on (1) the integrated vehicle longitudinal and lateral-directional force data, (2) exposed wing hinge moment, (3) wing pressure distributions, (4) orbiter MPS external pressure distributions, and (5) model base pressures. An investigation was undertaken to determine the similarity between solid and gaseous plumes; fluorescent oil flow visualization studies were also conducted. Tabulated data listings are included.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141520 , DMS-DR-2065-VOL-3
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  • 53
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    Wind tunnel tests of an 0.019-scale space shuttle integrated vehicle -2A configuration (model 14-OTS) in the NASA Ames 8 by 7 foot unitary wind tunnel (IA12C), volume 1 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The purpose of the test was to determine the effects of cold jet gas plumes on (1) the integrated vehicle longitudinal and lateral-directional force data, (2) exposed wing hinge moment, (3) wing pressure distributions, (4) orbiter MPS external pressure distributions, and (5) model base pressure. The similarity between solid and gaseous plumes was investigated, and fluorescent oil flow visualization studies were conducted.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141518 , DMS-DR-2065-VOL-1
    Format: application/pdf
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  • 54
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    Wind tunnel tests of an 0.019-scale space shuttle integrated vehicle -2A configuration (model 14-OTS) in the NASA Ames 8 X 7 foot unitary wind tunnel, volume 2 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The purpose of the test was to determine the effects of cold jet gas plumes on (1) the integrated vehicle longitudinal and lateral-directional force data, (2) exposed wing hinge moment, (3) wing pressure distributions, (4) orbiter MPS external pressure distributions, and (5) model base pressures. An investigation was undertaken to determine the similarity between solid and gaseous plumes; fluorescent oil flow visualization studies were also conducted. Plotted wing pressure data is tabulated.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141519 , DMS-DR-2065-VOL-2
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  • 55
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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
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  • 56
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    Effect of damping on excitability of high-order normal modes (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of localized structural damping on the excitability of higher-order large space telescope spacecraft modes is investigated. A preprocessor computer program is developed to incorporate Voigt structural joint damping models in a finite-element dynamic model. A postprocessor computer program is developed to select critical modes for low-frequency attitude control problems and for higher-frequency fine-stabilization problems. The selection is accomplished by ranking the flexible modes based on coefficients for rate gyro, position gyro, and optical sensor, and on image-plane motions due to sinusoidal or random PSD force and torque inputs.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-143884 , D180-18835-1
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  • 57
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    Flight performance of Skylab attitude and pointing control system (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Skylab attitude and pointing control system (APCS) requirements are briefly reviewed and the way in which they became altered during the prelaunch phase of development is noted. The actual flight mission (including mission alterations during flight) is described. The serious hardware failures that occurred, beginning during ascent through the atmosphere, also are described. The APCS's ability to overcome these failures and meet mission changes are presented. The large around-the-clock support effort on the ground is discussed. Salient design points and software flexibility that should afford pertinent experience for future spacecraft attitude and pointing control system designs are included.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TN-D-8003 , M-136
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  • 58
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    Results of heat transfer tests of an 0.0175-scale space shuttle vehicle model 22 OTS in the NASA-Ames 3.5-foot hypersonic wind tunnel (IH3), volume 3 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Heat-transfer data for the 0.0175-scale space shuttle vehicle 3 are presented, and interference heating effects were investigated by a model build-up technique of the orbiter. The test program was conducted at Mach 5.3 for nominal free-stream Reynolds number per foot values of 1,500,000 and 5,000,000.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141516 , DMS-DR-2136-VOL-3
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  • 59
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    Results of heat transfer tests of an 0.0175-scale space shuttle vehicle model 22 OTS in the NASA-Ames 3.5-foot hypersonic wind tunnel (IH3), Volume 2 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N75-24818.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141515 , DMS-DR-2136-VOL-2
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  • 60
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    Results of heat transfer tests of an 0.0175-scale space shuttle vehicle model 22 OTS in the NASA-Ames 3.5 foot hypersonic wind tunnel (IH3), volume 1 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Heat transfer data for the 0.0175-scale space shuttle vehicle 3 are presented. Interference heating effects were investigated by a model build-up technique of orbiter alone, tank alone, second, and first stage configurations. The test program was conducted in the NASA-Ames 3.5-foot hypersonic wind tunnel at Mach 5.3 for nominal free stream Reynolds number per foot values of 1.5, and 5.0 million.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141514 , DMS-DR-2136-VOL-1
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  • 61
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    Results of dynamic stability tests conducted on a .012 scale model modified 089 B shuttle orbiter in the AEDC-VKF tunnel B at a Mach number of 8.0 (LA42) (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental aerodynamic investigations were conducted on a .012 scale model of a NASA/Langley modified version of the Rockwell 089B Space Shuttle Orbiter. Using the forced oscillation test technique, dynamic stability derivatives were measured in the pitch, yaw and roll planes at a Mach number of 8 over an angle of attack range from -4 deg to 28 deg. Plotted and tabulated results are presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141535 , DMS-DR-2132
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  • 62
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    Hypersonic aeroheating test of space shuttle vehicle: Configuration 3 (model 22 OTS) in the NASA-Ames 3.5-foot hypersonic wind tunnel (IH20), volume 2 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The model tested was an 0.0175-scale version of the vehicle 3 space shuttle configuration. Temperature measurements were made on the launch configuration, orbiter plus tank, orbiter alone, tank alone, and solid rocket booster (SRB) alone to provide heat transfer data. The test was conducted at free stream Mach numbers of 5.3 and 7.3 and at free stream Reynolds numbers of 1.5, 3.7, 5.0, and 7.0 million per foot. The model was tested at angles of attack from -5 deg to 20 deg and side slip angles of -5 deg and 0 deg.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-134441 , DMS-DR-2148-VOL-2
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  • 63
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    Results of investigations of an 0.010-scale 140A/B configuration (model 72-OTS) of the Rockwell International space shuttle orbiter in the NASA/Langley Research Center unitary plan wind tunnel (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental aerodynamic investigations were conducted in the NASA/Langley unitary plan wind tunnel on a sting mounted 0.010-scale outer mold line model of the 140A/B configuration of the Rockwell International Space Shuttle Vehicle. The primary test objectives were to obtain: (1) six component force and moment data for the mated vehicle at subsonic and transonic conditions, (2) effects of configuration build-up, (3) effects of protuberances, ET/orbiter fairings and attach structures, and (4) elevon deflection effects on wing bending moment. Six component aerodynamic force and moment data and base and balance cavity pressures were recorded over Mach numbers of 1.6, 2.0, 2.5, 2.86, 3.9, and 4.63 at a nominal Reynolds number of 20 to the 6th power per foot. Selected configurations were tested at angles of attack and sideslip from -10 deg to +10 deg. For all configurations involving the orbiter, wing bending, and torsion coefficients were measured on the right wing.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141528 , DMS-DR-2206
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  • 64
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    Results of tests on a Rockwell International space shuttle orbiter (-139 configuration) 0.0175-scale model (no. 29-0) in AEDC tunnel B to determine boundary layer characteristics (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of wind tunnel tests were conducted to determine boundary layer characteristics on the lower surface of a space shuttle orbiter. Total pressure and temperature profile data at various model stations were obtained using a movable, four-degree-of-freedom probe mechanism and static pressure taps on the model surface. During a typical run, the probe was located over a preselected model location, then driven down through the bondary layer until contact was made with the model surface.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141540 , DMS-DR-2251
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  • 65
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    Hypersonic aeroheating test of space shuttle vehicle configuration 3 (model 22-OTS) in the NASA-Ames 3.5-foot hypersonic wind tunnel (IH20), volume 1 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of hypersonic wind tunnel testing of an 0.0175 scale version of the vehicle 3 space shuttle configuration are presented. Temperature measurements were made on the launch configuration, orbiter plus tank, orbiter alone, tank alone, and solid rocket booster alone to provide heat transfer data. The test was conducted at free-stream Mach numbers of 5.3 and 7.3 and at free-stream Reynolds numbers of 1.5 million, 3.7 million, 5.0 million, and 7.0 million per foot. The model was tested at angles of attack from -5 deg to 20 deg and side slip angles of -5 deg and 0 deg.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-134440 , DMS-DR-2148-VOL-1
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  • 66
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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
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  • 67
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    Design criteria for payload workstation accommodations (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Anticipated shuttle sortie payload man-system design criteria needs are investigated. Man-system interactions for the scientific disciplines are listed and the extent is assessed to which documented Skylab experience is expected to provide system design guidance for each of the identified interactions. Where the analysis revealed that the reduced Skylab data does not answer the anticipated needs candidate criteria, based on unreduced Skylab data, available prior research, original analysis, or related requirements derived from previous space programs, are provided.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-120777 , MCR-75-195
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  • 68
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    Centaur Standard Shroud (CSS) static limit load structural tests (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The structural capabilities of the jettisonable metal shroud were tested and the interaction of the shroud with the Centaur stage was evaluated. A flight-configured shroud and the assemblies of the associated Centaur stage were tested for applied axial and shear loads to flight limit values. The tests included various thermal, pressure, and load conditions to verify localized strength capabilities, to evaluate subsystem performance, and to determine the aging effect on insulation system properties. The tests series verified the strength capabilities of the shroud and of all associated flight assembles. Shroud deflections were shown to remain within allowable limits so long as load sharing members were connected between the shroud and the Centaur stage.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-71727
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  • 69
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    Results of transonic wind tunnel tests on an 0.010-scale space shuttle mated vehicle model 72-OTS in the LaRC 8-foot TPT (IA43) (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental aerodynamic investigations were conducted in NASA/Langley 8-Foot transonic pressure tunnel on a sting mounted 0.010-scale outer mold line model of 104A/B configuration of the Rockwell International space shuttle vehicle. Component aerodynamic force and moment data and base and balance cavity pressures were recorded over an angle of attack range of -10 deg to +10 deg at Mach numbers of 0.6, 0.8, 0.9, 0.98, 1.13, and 1.2. Selected configurations were tested at sideslip angles from -10 deg to +10 deg. For all configurations involving the orbit, wing bending and torsion were measured on the right wing. Inboard elevon setting of 0 deg, +4 deg and +8 deg and outboard settings of 0 deg, +4 deg and +8 deg were tested.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141525 , DMS-DR-2204
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  • 70
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    Airloads investigation of an 0.030-scale model of the Space Shuttle Vehicle 140 A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for MACH range 0.6 to 1.4 (IA14A), volume 10 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Pressure data are presented in tabular form on the external tank base and SRM booster base of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141502 , DMS-DR-2084-VOL-10
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  • 71
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    Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 11 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Pressure data are presented in tabular form on the external tank attach points and the external tank base rake of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141503 , DMS-DR-2084-VOL-11
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  • 72
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    Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 9 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Pressure data are presented in tabular form on the external tank and the SRM nozzle of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141501 , DMS-DR-2084-VOL-9
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  • 73
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    Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the arc 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 8 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Pressure data are presented in tabular form on the SRM booster of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-134450 , DMS-DR-2084-VOL-8
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  • 74
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    Airloads investigation of an 0.030 scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 7 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Pressure data are presented in tabular form on the left and right vertical tail surface of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-134449 , DMS-DR-2084-VOL-7
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  • 75
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    Airloads investigation of an 0.30-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 5 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Pressure data are presented in tabular form on the lower wing surface of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-134447 , DMS-DR-2084-VOL-5
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  • 76
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    Airloads investigation of an 0.030-scale model of the space shuttle vehicle 140A/B launch configuration (model 47-OTS) in the ARC 11-foot Unitary Plan Wind Tunnel for Mach range 0.6 to 1.4 (IA14A), volume 6 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Pressure data are presented in tabular form on the upper wing surface of the space shuttle launch vehicle configuration model. For Vol. 3, see N75-23657.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-134448 , DMS-DR-2084-VOL-6
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  • 77
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    Roll maneuver evaluation (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The current roll maneuver to the flight azimuth following lift-off is achieved by commanding roll attitude using a linear profile with no roll rate command. The linearity of this command profile implies an infinite acceleration to a constant roll rate; the vehicle cannot instantaneously achieve this rate, so the actual roll attitude lags the command attitude throughout the maneuver. The roll attitude error which thus develops can be reduced by augmenting the attitude command with a rate command and utilizing finite slopes on the rate command to give the vehicle time to accelerate. Results obtained from commanding various roll attitude and rate combinations to perform the maneuver are presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-147807 , REPT-1.3-DN-C0203-006
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  • 78
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    Results of preliminary Microwave Multi-Applications Payload (MMAP) study (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A preliminary feasibility study of the microwave multi-applications payload (MMAP) system for the Spacelab has been carried out. The initial objectives of this study have been to determine the minimum equipment requirements of the MMAP and the feasibility of placing the numerous large aperture antennas in the Spacelab. The study was begun by reviewing the experimental objectives and techniques and determining areas of commonality. Emphasis was given to the determination of common RF equipment requirements. These requirementers were considered after agreement among the experiments had been reached on limiting the number of frequencies to be used in the system. This was done so that the number of antennas, transmitters, and receivers could be minimized. The electronics system block diagram and the antenna configurations were considered in some details. It was concluded that the MMAP is feasible and can be an economical method of achieving a large number of experimental goals.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144762
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  • 79
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    Apu/hydraulic/actuator Subsystem Computer Simulation. Space Shuttle Engineering and Operation Support, Engineering Systems Analysis (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Major developments are examined which have taken place to date in the analysis of the power and energy demands on the APU/Hydraulic/Actuator Subsystem for space shuttle during the entry-to-touchdown (not including rollout) flight regime. These developments are given in the form of two subroutines which were written for use with the Space Shuttle Functional Simulator. The first subroutine calculates the power and energy demand on each of the three hydraulic systems due to control surface (inboard/outboard elevons, rudder, speedbrake, and body flap) activity. The second subroutine incorporates the R. I. priority rate limiting logic which limits control surface deflection rates as a function of the number of failed hydraulic. Typical results of this analysis are included, and listings of the subroutines are presented in appendicies.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-147768 , REPT-1.2-DN-B0105-03
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  • 80
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    Analysis of effect of internal and operating variables on performance of SVDS constraint model (ABIND) (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An examination of the factors which modify the simulation of a constraint in the motion of the aft attach points of the orbiter and external tank during separation has been made. The factors considered were both internal (spring and damper constants) and external (friction coefficient and dynamic pressure). The results show that an acceptable choice of spring/damper constant combinations exist over the expected range of the external factors and that the choice is consistent with a practical integration interval. The constraint model is shown to produce about a 10 percent increase in the relative body pitch angles over the unconstrained case whereas the MDC-STL constraint model is shown to produce about a 38 percent increase.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-147770
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  • 81
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    Computer program system for dynamic simulation and stability analysis of passive and actively controlled spacecraft. Volume 3: Demonstration problems (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N76-25319.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144760 , MCR-75-17-VOL-3
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  • 82
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    Computer program system for dynamic simulation and stability analysis of passive and actively controlled spacecraft. Volume 2: Program user's guide (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N76-25319.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144759 , MCR-75-17-VOL-2
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  • 83
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    Computer program system for dynamic simulation and stability analysis of passive and actively controlled spacecraft. Volume 1. Theory (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A theoretical development and associated digital computer program system is presented. The dynamic system (spacecraft) is modeled as an assembly of rigid and/or flexible bodies not necessarily in a topological tree configuration. The computer program system may be used to investigate total system dynamic characteristics including interaction effects between rigid and/or flexible bodies, control systems, and a wide range of environmental loadings. Additionally, the program system may be used for design of attitude control systems and for evaluation of total dynamic system performance including time domain response and frequency domain stability analyses. Volume 1 presents the theoretical developments including a description of the physical system, the equations of dynamic equilibrium, discussion of kinematics and system topology, a complete treatment of momentum wheel coupling, and a discussion of gravity gradient and environmental effects. Volume 2, is a program users' guide and includes a description of the overall digital program code, individual subroutines and a description of required program input and generated program output. Volume 3 presents the results of selected demonstration problems that illustrate all program system capabilities.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144758 , MCR-75-17-VOL-1
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  • 84
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    Space shuttle operations integration plan (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Operations Integration Plan is presented, which is to provide functional definition of the activities necessary to develop and integrate shuttle operating plans and facilities to support flight, flight control, and operations. It identifies the major tasks, the organizations responsible, their interrelationships, the sequence of activities and interfaces, and the resultant products related to operations integration.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-147670
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  • 85
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    Standardization and program effect analysis (Study 2.4). Volume 3: Design-to-cost analysis (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The program procedures that were incorporated into an on-going "design-to-cost" spacecraft program are examined. Program procedures are the activities that support the development and operations of the flight unit: contract management, documents, integration meetings, engineering, and testing. This report is limited to the program procedures that were implemented, with emphasis on areas that may depart from normal satellite development practices.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-147097 , ATR-76(7364)-1-VOL-3
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  • 86
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    Results of heat transfer tests of an 0.0175-scale space shuttle vehicle model 22 OTS in the NASA-Ames 3.5-foot hypersonic wind tunnel (IH3), volume 4 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Heat-transfer data for the 0.0175-scale Space Shuttle Vehicle 3 are presented. Interference heating effects were investigated by a model build-up technique of Orbiter alone, tank alone, second, and first stage configurations. The test program was conducted in the NASA-Ames 3.5-Foot Hypersonic Wind Tunnel at Mach 5.3 for nominal free-stream Reynolds number per foot values of 1.5 x 1,000,000 and 5.0 x 1,000,000.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141517 , DMS-DR-2136-VOL-4
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  • 87
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    Use of STS subsystems and components for MMSE, volume 2 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N76-18211.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-147477 , SD-75-SA-0181-VOL-2
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  • 88
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    Use of STS subsystems and components for MMSE, volume 1 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Multiuse mission support equipment (MMSE) is flight/ground equipment for the shuttle era which is used in conjunction with more than one mission payload. Initial verification of STS subsystem's applicability to MMSE is provided along with the cost savings potential and programmatic data needed for further program planning decisions. Some 70 MMSE requirements were found to be potentially satisfied by STS equipment, and and 6 items of particular interest were chosen for special emphasis. All were found to be feasible and beneficial. Program cost savings through their use are estimated to be substantial. Further study is recommended to identify additional MMSE requirements and hardware.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-147476 , SD-75-SA-0181-VOL-1
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  • 89
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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
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  • 90
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    Results of a Pressure Loads Investigation on a 0.030-scale Model (47-OTS) of the Integrated Space Shuttle Vehicle Configuration 5 in the NASA Ames Research Center 11 x 11 Foot Leg of the Unitary Plan Wind Tunnel (IA81A), Volume 6 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tabulated pressure data are presented on the right upper wing surface, right lower wing surface, and SRM booster of the integrated space shuttle vehicle configuration. For Vol. 1, see N76-15246.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141841 , DMS-DR-2169-VOL-6
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  • 91
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    Results of pressure distribution tests of a 0.010-scale space shuttle orbiter model (61-0) in the NASA/ARC 3.5-foot hypersonic wind tunnel (test OH38), volume 2 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N76-16152.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144584-VOL-2 , DMS-DR-2171-VOL-2
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  • 92
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    Results of pressure distribution tests of a 0.010-scale space shuttle orbiter model (61-0) in the NASA/ARC 3.5-foot hypersonic wind tunnel (test OH38), volume 1 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Test results are presented of hypersonic pressure distributions at simulated atmospheric entry conditions. Pressure data were obtained at Mach numbers of 7.4 and 10.4 and Reynolds numbers of 3.0 and 6.5 million per foot. Data are presented in both plotted and tabulated data form. Photographs of wind tunnel apparatus and test configurations are provided.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144584-VOL-1 , DMS-DR-2171-VOL-1
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  • 93
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    Results of tests using a 0.030-scale model (45-0) of space shuttle vehicle orbiter in the NASA/ARC 12-foot pressure wind tunnel (OA159) (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation (test OA159) was conducted in the NASA/ARC 12-foot Pressure Wind Tunnel from June 23 through July 8, 1975. The objective was to obtain detailed strut tare and interference effects of the support system used in the NASA/ARC 40 x 80-foot wind tunnel during 0.36-scale orbiter testing (OA100). Six-component force and moment data were obtained through an angle-of-attack range from -9 through +18 degrees with 0 deg angle of sideslip and a sideslip angle range from -9 through +18 degrees at 9 deg angle of attack results are presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141832 , DMS-DR-2265
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 94
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    Results of an aerodynamic investigation of a space shuttle orbiter/747 carrier vehicle configuration to establish a free-stream data base for ALT separation investigations, utilizing a 0.0125-scale model (48-0/AX1318I-1) in the ARC 14-foot wind tunnel (CA23A) (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Force and moment data are presented which were obtained for each vehicle separately at a Mach number of 0.6, and for the mated orbiter/747 configuration at Mach numbers of 0.3, 0.5, 0.6, and 0.7. Orbiter angles of attack from 0 degrees to +12 degrees and 747/Carrier angles of attack from -3 degrees to +7 degrees were investigated at angles of sideslip of 0 degrees and -5 degrees. Model variables include orbiter elevon and rudder deflections, orbiter tail cone-on and off, various orbiter/747 attach structure configurations, 747 stabilizer and rudder deflections, and 747 CAM modification components-on and off. Photographs of test configurations are included.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144583 , DMS-DR-2243
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 95
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    Pyrotechnic shock measurement and data analysis requirements (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: An investigation is described into the laboratory measurement and analysis of pyrotechnic shock which was prompted at JPL when two separate facilities generated discrepant pyrotechnic shock data while testing Mariner Jupiter/Saturn 1977 spacecraft hardware. Both of the testing facilities were surveyed. The only difference noted was in the FM tape recorders used to record the data. One facility used a tape recorder operating at 60 in./sec with a frequency response of 20 kHz; the other used a tape recorder operating at 120 in./sec with a frequency response of 80 kHz. The accelerometers, cables, charge amplifiers, and mechanical setups were identical.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Inst. of Environ. Sci. Proc. of 2d Aerospace Testing Seminar; 22 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 96
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    Transonic stability and control characteristics of a 0.015-scale (remotely controlled elevon) model 44-0 of the space shuttle orbiter tested in the NASA/LaRC 8 foot TPT (LA62) (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The objective of the test was to generate a detailed aerodynamic data base which can be used to substantiate the aerodynamic design data book for the current shuttle orbiter configuration. Special attention was directed to definition of nonlinear aerodynamic characteristics by taking data at small increments in Mach number, angle of attack, and elevon position. Six-component aerodynamic force and moment and elevon position data were recorded over an angle-of-attack range from -4 deg to 20 deg, at angles of sideslip of 0 deg and 2 deg. The test Mach numbers were from 0.35 to 1.20. The Reynolds number for most of the test was held at a constant 3.5 million per foot.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141843 , DMS-DR-2264
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 97
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    Unknown
    Results of a pressure loads investigation on a 0.030-scale model (47-OTS) of the integrated space shuttle vehicle configuration 5 in the NASA Ames Research Center 9 by 7 foot leg of the unitary plan wind tunnel (IA81B), volume 5 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N76-13185.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141821 , DMS-DR-2194-VOL-5
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 98
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    Unknown
    Results of a pressure loads investigation on a 0.030-scale model (47-OTS) of the integrated space shuttle vehicle configuration 5 in the NASA Ames Research Center 9 x 7 foot leg of the unitary plan wind tunnel (IA81B), volume 3 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N76-13185.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141819 , DMS-DR-2194-VOL-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 99
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    Unknown
    Wind tunnel test of the 0.019 scale space shuttle integrated vehicle (model 14-OTS) in the CALSPAN 8-foot transonic wind tunnel (IA36), volume 1 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N76-13183.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141814 , DMS-DR-2064-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 100
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    Unknown
    An investigation in MSFC 14-inch TWT to determine the static stability characteristics of 0.004-scale model (74-OTS) space shuttle vehicle 5 configuration (IA33), volume 1 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind tunnel tests were conducted to: (1) determine the static stability characteristics of the Shuttle Vehicle 5 configuration; (2) determine the effect on the Vehicle 5 aerodynamic characteristics of External Tank (ET) and Solid Rocket Booster (SRB) nose shape, SRB nozzle shroud flare angle, orbiter to tank fairing, and sting location; (3) provide flow visualization using thin film oil paint; and (4) determine rudder, body flap, and inboard and outboard elevon hinge moments. The mated vehicle model was mounted in three different ways: (1) the orbiter mounted on the balance with the SRB's attached to the tank and the tank in turn attached to the orbiter; (2) the tank mounted on the balance (with the sting protruding through the tank base) with the SRB's and orbiter attached to the tank, and (3) with the tank mounted on the balance and the balance in turn supported by a forked sting entering the nozzle of each SRB, extending forward into the SRB's then crossing over to the tank to provide a balance socket. Data were obtained for Mach numbers from 0.6 through 4.96 at angles-of-attack and -sideslip from -10 to 10 degrees.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-141811 , DMS-DR-2174-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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