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  • General Chemistry  (1,057)
  • SPACE VEHICLES  (597)
  • PROPULSION SYSTEMS  (349)
  • Cell & Developmental Biology
  • 1970-1974  (2,154)
  • 1945-1949  (111)
  • 1972  (2,154)
  • 1945  (111)
Collection
Keywords
Publisher
Years
  • 1970-1974  (2,154)
  • 1945-1949  (111)
Year
  • 1
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    Composite systems utilization for space shuttle structures (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Research and development of composite material systems to show applicability of these materials to shuttle structures and to demonstrate availability through a hardware development program is reported. The various configurations studied and potential areas of composite structures use are described and an outline of ongoing composite programs, complementing the indicated feasible applications, including a typical cost study, is shown. The following composite systems are investigated: Boron filaments with epoxy, polyimide, or aluminum matrix, and graphite filaments with epoxy or polyimide matrix.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 605-644
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  • 2
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    Flight loads and control (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The prediction of flight loads and their potential reduction, using various control logics for the space shuttle vehicles, is very complex. Some factors, not found on previous launch vehicles, that increase the complexity are large lifting surfaces, unsymmetrical structure, unsymmetrical aerodynamics, trajectory control system coupling, and large aeroelastic effects. Discussed are these load producing factors and load reducing techniques. Identification of potential technology areas is included.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 175-203
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  • 3
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    New considerations for pogo prevention on space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Recommendations for improving the methodology of pogo suppression for the space shuttle include: Consideration of inter-pump location for accumulator or active device, inclusion of tank outflow effects in dynamic structural analysis, the use of simplified transfer functions in systems studies, three phase dynamic testing program for turbopump with development of dynamic flowmeters, and the use of a linearized mathematical model for engine physics studies.
    Keywords: SPACE VEHICLES
    Type: NASA, Washington NASA Space Shuttle Technol. Conf.; p 97-116
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  • 4
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    Development of methods for fracture control of space shuttle structures (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The technology with respect to fracture control requirements of the shuttle is considered. The current state-of-the-art does permit an approach based on linear elastic fracture mechanics concepts. Development and implementation of a fracture control plan should recognize deficiencies and provide adequate resources for the extensive empirical test data which are required. With respect to the cost impact of such tests, recent experiences involving advanced aircraft systems have seen unit cost increases of from 200 to 500 percent.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 727-770
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  • 5
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    Docking devices for Soyuz-type spacecraft (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Two docking device designs for Soyuz-type spacecraft are compared. The first was flight tested successfully; the second achieves rigid and exact joining of two spacecraft, while incorporating changes to allow for the intravehicular transfer of crew members. The main functions of the docking device are considered, with the means by which they are accomplished, and measures for increasing its reliability and flexibility in service are noted.
    Keywords: SPACE VEHICLES
    Type: 6th Aerospace Mech. Symp.; p 143-150
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  • 6
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    Aerospace transporter and lifting body activities in Europe and potential participation in the development of the space shuttle orbiter (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The course of European aerospace research regarding reentry problems is briefly reviewed for the period from 1966 up to the present. The considerable experience gained by Europe, and particularly Germany, is shown to have led to their involvement and participation in the U.S. space shuttle program. The areas of investigation and expected contributions by European cooperation in the shuttle program are outlined.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 969-995
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  • 7
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    Pulse performance analysis for small hypergolic propellant rocket engines (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Small rocket engine tests were conducted for the purpose of obtaining pulse performance data to aid in preliminary design and evaluation of attitude control systems. Both monopropellant and hypergolic bipropellant engines of thrust levels from 5 to 445 N (1 to 100 lb) were tested. The performance data for the hypergolic propellant rockets are compared with theoretical performance calculated from idealized chamber filling and evacuation characteristics. Electromechanical delays in valve response and heat transfer characteristics were found to cause substantial deviation between theoretical performance and test performance. The theoretical analysis is modified to obtain a semiempirical model for hypergolic propellant rockets.
    Keywords: PROPULSION SYSTEMS
    Type: Res. Achievements Rev., Vol. 4, No. 6; p 61-74
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  • 8
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    Extendible rocket nozzle development (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: An evaluation is presented of J-2 engine modifications that will simplify operation and improve reliability of the advanced Saturn 1C launch vehicle. Methods of increasing thrust without extensively modifying the S-2 or S-4B stages are also evaluated. A thrust increase was achieved by raising engine combustion through a redesign of the engine thrust chamber and propellant feed system.
    Keywords: PROPULSION SYSTEMS
    Type: Res. Achievements Rev., Vol. 4, No. 6; p 105-115
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  • 9
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    Status of reusable surface insulation thermal protection system technology programs (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The development of three low-density rigidized insulation materials for the shuttle TPS application is reported. These materials consist of one high purity silica system and two systems based on mullite, an aluminum silicate. Both systems consist of fibers joined together with appropriate binders to obtain a rigidized insulation composite. Both material systems require the application of a glassy coating to provide a wear resistant, high emittance surface and to prevent the absorption of water by the fiber matrix. The technology program has addressed the development of water impervious coatings, methods of assembling the materials in design concepts while minimizing the thermal stress in the insulation, achieving compatibility between the RSI material and the structural system, and test evaluations to demonstrate the feasibility of the surface insulation concept.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 435-474
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  • 10
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    Overview of technology relative to the pogo instability on space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The prediction of pogo contains a major source of uncertainty in the difficulty of defining the dynamic characteristics of certain components. An overview of the space shuttle technology with respect to each the following pogo problem areas is presented: structure, tank-liquid interaction, feedline, engine (pump), pogo-loop/control-loop interaction, and stability analysis.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 117-138
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  • 11
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    Assessment of potential buffet problems on the space shuttle vehicle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Buffet of the space shuttle launch and reentry configuration is an area requiring continued evaluation to produce a safe reliable vehicle of minimum weight. Buffet forces result from flow separation and therefore can not be predicted accurately. Buffet loads are highly sensitive to configuration, angle of attack, and Mach number and can be reliably determined only by wind tunnel tests of elastically scaled models.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 25-43
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  • 12
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    Dynamic analysis for shuttle design verification (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Two approaches that are used for determining the modes and frequencies of space shuttle structures are discussed. The first method, direct numerical analysis, involves finite element mathematical modeling of the space shuttle structure in order to use computer programs for dynamic structural analysis. The second method utilizes modal-coupling techniques of experimental verification made by vibrating only spacecraft components and by deducing modes and frequencies of the complete vehicle from results obtained in the component tests.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 205-230
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  • 13
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    Surface studies on Surveyor 3 tubing sections (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Sections C and E of the unpainted, polished aluminum tubing from the strut of the radar altimeter and Doppler velocity sensor were examined in a transmission electron microscope for micrometeorite damage and ion bombardment. Both sections were contaminated and eroded on one side; it is suggested that these conditions were caused by sandblasting by lunar dust and retrorocket plume contamination during Surveyor 3 landing. Microcraters of different configurations were found on the bright sides of the tubes. Several degrees of violence were involved in the formation of the craters, and the particle size could be responsible for some differences. All micropits found were on the bright areas and data indicate 0.2 hypervelocity impact/sq cm and 2/sq cm for other types of craters. The greatest degree of damage resulted from particle impact and was limited to a maximum depth of 2 microns.
    Keywords: SPACE VEHICLES
    Type: NASA, Washington Analysis of Surveyor 3 Mater. and Phot. Returned by Apollo 12; p 154-158
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  • 14
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    Velocity diagrams (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The selection and design of velocity diagrams for axial flow turbines are considered. Application is treated in two parts which includes: (1) mean-section diagrams, and (2) radial variation of diagrams. In the first part, the velocity diagrams occurring at the mean section are assumed to represent the average conditions encountered by the turbine. The different types of diagrams, their relation to stage efficiency, and their selection when staging is required are discussed. In the second part, it is shown that in certain cases the mean-section diagrams may or may not represent the average flow conditions for the entire blade span. In the case of relatively low hub- to tip-radius ratios, substantial variations in the velocity diagrams are encountered. The radial variations in flow conditions and their effect on the velocity diagrams are considered.
    Keywords: PROPULSION SYSTEMS
    Type: Turbine Design and Appl., Vol. 1; p 69-99
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  • 15
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    Aerodynamic studies of delta-wing shuttle orbiters. Part 2: Hypersonics (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: An early version of an external hydrogen-oxygen tank orbiter was used as a baseline vehicle to experimentally evaluate: (1) nose shape and canopy effects on longitudinal, lateral, and directional stability and trim, and (2) yaw due to aerodynamic roll control at hypersonic speeds. Nose alterations were examined since that part of the vehicle may be subject to modifications because of internal packaging requirements, alleviation of potential high heating areas, and/or possible improvements in aerodynamic stability and control. There was also some concern about the effect of the rather high profile canopy on the aerodynamics; therefore its removal was examined. In addition, roll-yaw coupling was investigated because of its impact on the RCS fuel requirements for entry maneuvers.
    Keywords: SPACE VEHICLES
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 803-830
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  • 16
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    Impact of subsonic aerodynamic considerations on a space shuttle booster configuration (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Considerations of cruise-back efficiency and subsonic flying qualities are shown to have resulted in a configuration with an aft high wing of moderate aspect ratio and with vertical tails located at the wing tips. The need to protect the air breathing engines during ascent and reentry and the desire for a low trim penalty longitudinal control surface led to consideration of a jet-flap canard. The advantages of this application of STOL technology to a space system are examined and the results of both wind tunnel tests and flight simulations are discussed. Since the use of the jet-flap canard concept offers the potential for a minimum weight vehicle, a proposed technology development program is outlined in order that the full benefit of this concept may be realized.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol.3; p 737-784
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  • 17
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    On the possibility of Earth reentry simulation of shallow angle Jupiter entry (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Possible Earth reentry simulation of shallow-angle (3 to 30 deg) Jupiter entry was investigated in terms of four parameters of the bow shock layer ahead of a blunt vehicle: peak (equilibrium) temperature, peak pressure, peak inward radiative flux, and time-integrated radiative flux. It is shown that simulation ranging from fair to good can be achieved. Reentry is easiest (lowest Earth reentry speed) at steep Earth reentry, in the Earth entry speed range of 15 to 22 km/sec, for both the Jupiter nominal and cool atmospheres. Increased Earth speed is required, generally, for increasing Jupiter entry angle, and for increasing temperature, radiative flux, time-integrated flux and pressure, in that order.
    Keywords: SPACE VEHICLES
    Type: JPL Quart. Tech. Rev., Vol. 1, No. 4; p 19-29
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  • 18
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    Application of composite materials to space shuttle tanks (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Tanks are broken down into two categories: pressure vessels that carry primarily pressure loads, and structural tanks that carry structural loads such as thrust or bending in addition to pressure. A significant portion of the shuttle orbiter structure are tanks and in order to minimize both weight and cost growth on these shuttle tank structures, composite material tanks of both types are considered.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 573-603
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  • 19
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    Advanced design concepts for shuttle airframe structure (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The development of weight-saving advanced design concepts for shuttle airframe structure is presented. Design concepts under investigation employ selective composite reinforcement and/or efficient geometric arrangements. An effort to develop metallic panel designs which exploit the relaxation of smooth external-surface requirements for skin structure is reviewed. Available highlights from research and development studies which investigate the application of composite reinforcement to the design of two types of fuselage panels, a shear web, a large fuselage frame, and a landing-gear-door assembly are presented. Preliminary results from these studies suggest weight savings of 25 percent can be obtained.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 537-572
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  • 20
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    Flutter technology for space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The development of analytical and experimental techniques needed to predict space shuttle flutter boundaries and insure adequate flutter margins and anticipated problems associated with aeroelastic-model and full-scale testing to validate flutter clearance are considered. Results illustrating the best available tools for subsonic and supersonic flutter prediction are presented. Programs currently underway which will help overcome the difficult problems envisioned for the transonic wind-tunnel and flight flutter test program are also discussed.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 1-24
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  • 21
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    Gas-powered reentry body erection mechanism (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The design, analysis, testing, and flight of the supersonic planetary entry decelerator 2 spacecraft are described. The vehicle was launched in a folded condition and deployed to its required configuration following exit from the atmosphere. This concept was selected primarily because it allows utilization of existing launch vehicle systems in the most economical manner possible.
    Keywords: SPACE VEHICLES
    Type: 6th Aerospace Mech. Symp.; p 101-107
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  • 22
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    Satellite temperature correlation of predicted, test, and flight data (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: This study compares satellite temperature predictions with thermal vacuum test results and shows the improvement from testing. Orbital data were compared with prediction/test results to determine quantitatively an expected error criteria.
    Keywords: SPACE VEHICLES
    Type: NASA. Goddard Space Flight Center Space Simulation; p 425-443
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  • 23
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    Experiments on the dynamic stability of the space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Some dynamic stability experiments on the space shuttle using a half-model oscillatory technique are discussed. Resulting information from the experiments is presented and includes: (1) dynamic pitching characteristics of both the orbiter and the booster alone as well as of the two models mated into a single launch configuration; (2) the static and dynamic interference effects during an abort separation maneuver; and (3) the dynamic plume interference effect.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 933-968
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  • 24
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    Basic turbine concepts (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Turbine geometric, flow, energy transfer, efficiency, and performance characteristics are considered by the use of definitions, diagrams, and dimensionless parameters. Emphasis is placed on the determination of the fluid velocity as it passes from one blade row to the next. The general methods for constructing velocity diagrams and relating them to the work and flow capacity of the turbine are discussed.
    Keywords: PROPULSION SYSTEMS
    Type: Turbine Design and Appl., Vol. 1; p 21-67
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  • 25
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    Dynamic testing for shuttle design verification (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Space shuttle design verification requires dynamic data from full scale structural component and assembly tests. Wind tunnel and other scaled model tests are also required early in the development program to support the analytical models used in design verification. Presented is a design philosophy based on mathematical modeling of the structural system strongly supported by a comprehensive test program; some of the types of required tests are outlined.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 231-265
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  • 26
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    Neuter docking mechanism study (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Neuter (or androgynous) docking systems that allow space vehicles with similar or identical docking hardware to dock are discussed. Basic requirements applicable to docking mechanism design, four neuter concepts that were studied, and the concept selected by the NASA Manned Spacecraft Center for detailed investigation are presented.
    Keywords: SPACE VEHICLES
    Type: 6th Aerospace Mech. Symp.; p 43-49
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  • 27
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    Aerodynamic studies of delta-wing shuttle orbiters. Part 1: Low speed (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Numerous wind tunnel tests conducted on the evolving delta-wing orbiters have generated a fairly large aerodynamic data base over the entire entry operation range of these vehicles. A limited assessment is made of some of the aerodynamics of the current HO type orbiters, and several specific problem areas selected from the broad data base are discussed. These include, from a subsonic viewpoint, discussions of trim drag effect; effects of the installation of main rocket engine nozzles, OMS and RCS packages, Reynolds number effects, lateral-directional stability characteristics, and landing characteristics.
    Keywords: SPACE VEHICLES
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 785-802
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  • 28
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    Wing optimization for space shuttle orbiter vehicles (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The results were presented of a parametric study performed to determine the optimum wing geometry for a proposed space shuttle orbiter. The results of the study establish the minimum weight wing for a series of wing-fuselage combinations subject to constraints on aerodynamic heating, wing trailing edge sweep, and wing over-hang. The study consists of a generalized design evaluation which has the flexibility of arbitrarily varying those wing parameters which influence the vehicle system design and its performance. The study is structured to allow inputs of aerodynamic, weight, aerothermal, structural and material data in a general form so that the influence of these parameters on the design optimization process can be isolated and identified. This procedure displays the sensitivity of the system design of variations in wing geometry. The parameters of interest are varied in a prescribed fashion on a selected fuselage and the effect on the total vehicle weight is determined. The primary variables investigated are: wing loading, aspect ratio, leading edge sweep, thickness ratio, and taper ratio.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 831-860
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  • 29
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    Status of Langley studies of aerodynamics and interference effects of tandem launch vehicles (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Some of the aerodynamic and interference effects measured from wind-tunnel tests of three fully reusable space shuttle configurations at transonic and low-supersonic speeds are presented, and the status is given of an assessment of the analytical approach to date. The three configurations tested were a low-fineness-ratio booster combined in tandem with a delta-wing orbiter, designated the "low-fineness-ratio configuration,' and a phase B shuttle configuration consisting of the delta-wing orbiter and high-fineness-ratio booster, designated the "stage-arrangement configuration,' arranged in tandem and in parallel. The force measurements obtained at a Mach number of 1.5 for the low-fineness-ratio configuration were representative of the transonic and low-supersonic speed ranges where the interference effects are predominant and were used for comparison with values calculated at the same Mach number. This comparison is the basis for a preliminary assessment of the initial application of the analytical approach.
    Keywords: SPACE VEHICLES
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 707-736
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  • 30
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    Some contamination problems in the European TD satellite (1972)
    In:  CASI
    Details
    Publication Date: 2009-11-16
    Description: Materials were selected for the European TD satellite with a view to avoiding contamination of its stellar ultraviolet telescopes. Materiels were selected using the micro-VCM technique, and some typical cases of materials evaluation are described. The cleanliness of the satellite was monitored during integration and test phases, and in particular during long duration thermal vacuum tests.
    Keywords: SPACE VEHICLES
    Type: NASA. Goddard Space Flight Center Space Simulation; p 613-627
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  • 31
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    Minimum impulse tests of 0.45-N liquid hydrazine catalytic thrusters (1972)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: An exploratory test series was conducted on three types of 0.45-N (0.1 lbf) liquid hydrazine thrusters to ascertain the minimum impulse bit capability for this class of engine. The test series is described and the results are presented. The testing was performed at 21 and 145 C (70 and 300 F) while maintaining nominal 0.45 N (0.1 lbf) upstream conditions. Valve on-times as low as 0.008 sec were applied. Impulse bits were observed for thruster temperatures of 21 and 145 C (70 and 300 F), respectively.
    Keywords: PROPULSION SYSTEMS
    Type: JPL Quarterly Tech. Rev., Vol. 2, No. 1; p 107-112
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  • 32
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    Mariner 9 propulsion subsystem performance during interplanetary cruise and Mars orbit insertion (1972)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: On 14 November 1971 the Mariner 9 1334-N-(300-lbf)-thrust rocket engine was fired for just over 15 min to place the first man-made satellite into orbit about Mars. Propulsion subsystem data gathered during the 5-month interplanetary cruise and orbit insertion are of significance to future missions of this type. Specific results related to performance predictability, zero g heat transfer, and nitrogen permeation, diffusion, and solubility values are presented.
    Keywords: PROPULSION SYSTEMS
    Type: JPL Quarterly Tech. Rev., Vol. 2, No. 1; p 113-122
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  • 33
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    Solar-electric propulsion breadboard thrust subsystem (1972)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: A solar-electric propulsion breadboard thrust subsystem has been designed, built, and tested. A 1500-h test was performed to demonstrate the functional capabilities of the subsystem. Described are the subsystem functions and testing process. The results show that the ground work has been established for development of an engineering model of the thrust subsystem.
    Keywords: PROPULSION SYSTEMS
    Type: JPL Quart. Tech. Rev., Vol. 2, No. 2; p 100-112
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  • 34
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    STOL propulsion systems (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The selection and the characteristics of quiet, clean propulsion systems for STOL aircraft are discussed. Engines are evaluated for augmentor wing and externally blown flap STOL aircraft with the engines located both under and over the wings. Some supporting test data are presented. Optimum engines are selected based on achieving the performance, economic, acoustic, and pollution goals presently being considered for future STOL aircraft. The data and results presented were obtained from a number of contracted studies and some supporting NASA inhouse programs, most of which began in early 1972. The contracts include: (1) two aircraft and mission studies, (2) two propulsion system studies, (3) the experimental and analytic work on the augmentor wing, and (4) the experimental programs on Q-Fan. Engines are selected and discussed based on aircraft economics using the direct operating cost as the primary criterion. This cost includes the cost of the crew, fuel, aircraft, and engine maintenance and depreciation.
    Keywords: PROPULSION SYSTEMS
    Type: STOL Technol.; p 475-509
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    Engine noise technology (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The characteristics of aircraft engine noise are discussed. Data are provided to show the noise produced by the following aircraft components: (1) fan noise, (2) noise suppressing structures, (3) sonic inlets, (4) jet mixing noise due to nozzle flow, and (5) thrust reversers. Charts are developed to show the sound pressure level and the frequencies for each type of noise source. The use of laminates and composite materials to dissipate acoustic power is examined.
    Keywords: PROPULSION SYSTEMS
    Type: STOL Technol.; p 371-412
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  • 36
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    Quiet STOL propulsion session introductory remarks (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Research activities, preliminary design activities, and system optimization studies in support of the development of advanced, quiet, STOL propulsion systems are discussed. Noise alleviation by means of controlling the source and by means of acoustical treatment receive considerable emphasis. A STOL airplane designed for a given payload has essentially double the installed thrust of a comparable CTOL airplane. Unless compensated for during the design process, this alone will tend to increase the source noise by 3 db. The propulsive lift introduces flap impingement noise or duct and flap scrubbing noise, noise sources not present in CTOL airplanes to any significant degree. These additional noise sources are illustrated. Depending on the specific configuration, this will tend to increase the noise by several db or more. Although the propulsive lift characteristics of STOL airplanes will tend to increase source noise significantly, the proximity of STOL airfields to populated areas leads to STOL noise objectives considerably lower than those currently applicable to CTOL airplanes.
    Keywords: PROPULSION SYSTEMS
    Type: STOL Technol.; p 367-370
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  • 37
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    Statistical distribution of spacecraft maximum structural response. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Under nonstationary random excitations resulting from booster engine shutdown, a direct statistical analysis of spacecraft maximum response is performed, and the spacecraft structural reliability is obtained. It is found that the Gumbel (1958) Type I asymptotic distribution of maximum values provides a reasonably good statistical model for spacecraft maximum responses. This approach makes it possible to perform the reliability-based optimum design of spacecraft structures.
    Keywords: SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets; 9; Jan. 197
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  • 38
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    Thermal design verification testing for the ATS-F and -G spacecraft. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: There is a wide fluctuation in the internal power dissipation from the components within the earth viewing module (EVM). The electronic component functional reliability required for a two-to-five year mission is the most significant factor for the thermal design criteria. A mathematical thermal model of the EVM and the orbital environment is used to predict the performance of the thermal control system. Comparisons of the results obtained in chamber thermal balance tests with the data computed on the basis of the theoretical model provide the means for validating the thermal design.
    Keywords: SPACE VEHICLES
    Type: Journal of Environmental Sciences; 15; Mar
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  • 39
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    The space shuttle and its uses. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The development of reusable space-shuttle vehicles has been made practical by the availability of improved staged-combustion engines and durable thermal protection systems. A two-state launch configuration with fully reusable booster and orbiter elements is considered to be the best design solution, and size specifications for such a vehicle are examined as a function of launch costs. Significant vehicle characteristics are explained in terms of cargo bay dimensions, cross-range maneuvering capability, mission duration requirements, engine characteristics, and acceleration constraints. Shuttle flight activities include satellite deployment and repair, sortie missions for short-duration research purposes, and space station support operations. Phases of the development program are outlined, and structural details of several candidate space shuttle concepts are illustrated.
    Keywords: SPACE VEHICLES
    Type: Aeronautical Journal; 76; Jan. 197
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  • 40
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    Shuttle ascent guidance and control. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The requirements of a unified optimal guidance scheme are discussed, giving attention to a general formulation, aspects of self-targeting, problems of optimum guidance within the atmosphere, and a unified concept for all flight phases. Since no previous guidance scheme meets these requirements, the shuttle demands a fundamentally new approach. A new unified optimal guidance scheme, called Mascot, was developed. The capabilities of Mascot include the real-time solution of general trajectory-optimization problems and the unification of guidance for all flight phases.
    Keywords: SPACE VEHICLES
    Type: Astronautics and Aeronautics; 10; Feb. 197
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  • 41
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    Flying automated laboratories to the planets. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Review of results obtained by instrumented spacecraft in investigation of the planets, mainly Mars. It appears that Mars is a world of varying topographical structure, some of which must have been created by the same processes that sculptured the moon and by others thus far unique in the solar system. The atmosphere is too thin to shield the surface, and there are no traces of liquid water. The very large recent dust storm is discussed. Mariner 9 has revealed definite indication of probable volcanic activity on Mars in recent geologic times.-
    Keywords: SPACE VEHICLES
    Type: Teledyne Ryan Aeronautical Reporter; 33; Spring 1
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  • 42
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    Preliminary results of large supersonic burning combustor testing. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A hydrogen fueled supersonic-burning combustor 18 in. in diameter, which is equivalent to that of an engine about 6 ft in diameter, was tested as a direct-connected duct at inlet conditions which simulated Mach 8 flight at 115,000 ft alt. A synthetic air consisting of oxygen with 39% nitrogen and 38% water vapor at a total temperature of 4500 deg R and a total pressure of 300 psia was supplied to the combustor inlet by a hydrazine-nitrogen tetroxide hot gas generator which maintained a uniform inlet flow Mach number of 2.8. The large combustor size required a new approach to fuel injector design. Some hydrogen was injected through flush-wall injectors, but most was injected from two rows of swept and tapered struts immersed in the flow stream. Supersonic combustion was obtained at hydrogen equivalence ratios of 0.94 without encountering thermal cho king. Wall static pressures, and the radial distribution of hydrogen, Pitot pressure, and Mach number were determined at the combustor exit.
    Keywords: PROPULSION SYSTEMS
    Type: Journal of Aircraft; 9; Jan. 197
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  • 43
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    Skylab status report. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The laboratory will be launched on Apr. 30, 1973, aboard a Saturn V vehicle. Approximately twenty-three and a half hours later the first crew will be launched in a command and service module aboard a Saturn IB launch vehicle. The laboratory will consist of modules. The orbital workshop (OWS) is made from the liquid oxygen and liquid hydrogen tanks of a Saturn S-IVB third stage. The OWS contains the living quarters and two experiments areas. The airlock sits on top of the OWS and contains the controls and hatch for the extra-vehicular activity.
    Keywords: SPACE VEHICLES
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  • 44
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    Small-scale wind shear definition for aerospace vehicle design. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Rawinsonde wind profile data provide adequate wind shear information for vertical height intervals greater than 1 km. To specify wind shears for intervals below 1 km for space vehicle design, detailed wind-profile information like that provided by the FPS-16 Radar/Jimsphere system or an extrapolation procedure is required. This paper is concerned with the latter alternative. It is assumed that any realization from an ensemble of wind profiles can be represented in terms of a Fourier integral. This permits the calculation of the ensemble standard deviation and mean of the corresponding shear ensemble for any altitude and shear interval in terms of the power spectrum of the ensemble of wind profiles. The results of these calculations show that the mean and standard deviation of the wind shear ensemble, as well as the wind shear for any percentile, asymptotically behave like the vertical interval to the 0.7 power. This result is in excellent agreement with shear data from Cape Kennedy, Fla.
    Keywords: SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets; 9; Feb. 197
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  • 45
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    Shuttle status report. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The Space Shuttle Program is still in Phase B, a phase consisting predominantly of paper analyses and trade studies leading to the selection of a single design. A brief history of the program up to Phase B is discussed together with the results of the original year-long Phase B effort, and the objectives of the Phase B extension currently in work. A Lockheed study is discussed together with a Grumman/Boeing study, Phase B contractor results, displays and controls, simulations, and the flight test.
    Keywords: SPACE VEHICLES
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  • 46
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    Matrix transformations for spacecraft attitude determination. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: SPACE VEHICLES
    Type: Planetary and Space Science; 20; Oct. 197
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  • 47
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    Orbital propellant depot system. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Review of some of the problems involved in the design of a long-term propellant storage depot in earth orbit to act as a resupply station for cargo/personnel shuttles between earth orbit and lunar orbit, between low earth orbit and synchronous orbit, and possibly for use with interplanetary probes. The problems discussed pertain essentially to the long-term storage and propellant transfer capabilities.
    Keywords: SPACE VEHICLES
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  • 48
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    Effect on supersonic jet noise of nozzle plenum pressure fluctuations. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Demonstration that pressure fluctuations in the plenum chamber to a supersonic nozzle can strongly increase the noise radiated from the jet plume. The correlation shows that jet noise acoustic efficiency increases from 0.3% to 0.8% (or 4 dB) when the chamber roughness intensity increases from essentially no plenum chamber roughness to 2%. A roughness level of 2% has been observed in some turbojet engines. It is concluded that the reduction or elimination of plenum chamber pressure fluctuations may be an important method of reducing the total noise from jet engines.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA Journal; 10; July 197
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  • 49
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    A halo-orbit lunar station. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A relay satellite following a halo trajectory will always maintain line-of-sight contact with the earth and the moon's far side. The Integrated Program Plan for lunar exploration in the 1980s and beyond calls for a fully reusable earth-moon transportation system. The principal elements of the system are a Translunar Shuttle, a Lunar-Orbit Space Station or Halo-Orbit Space Station, and a Lunar Space Tug. It is shown that a halo-orbit space station could offer important operational and performance advantages compared to a lunar-orbit station in a second-generation lunar program.
    Keywords: SPACE VEHICLES
    Type: Astronautics and Aeronautics; 10; June 197
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  • 50
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    Self-contamination and environment of an orbiting satellite. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The flux of molecules emitted by the satellite and subsequently returning to its surface is investigated. The reflection occurs upon collision of these with ambient molecules. The evaluation of this flux is carried out from a knowledge of the outgassing rate of the satellite, its dimensions, and the orbit parameters. Condensation rates and adsorption layers on critical surfaces are calculated from the knowledge of this flux, and from the natures and temperatures of the gas and the surface. The calculation of these parameters, based on estimated and in some cases measured emission rates, has been carried out for a number of satellites. These developed relationships and graphs allow the estimation of several important parameters for an orbiting satellite. This report presents the pressures and densities at various distances from the satellite as produced by the surrounding ambient molecules and by the outgassing of the satellite.
    Keywords: SPACE VEHICLES
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  • 51
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    Electrodynamic sailing - Beating into the solar wind. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The recent suggestion by Alfven (1972) of a novel means of spacecraft propulsion based upon energy extraction from the electromagnetic field of the solar wind is critically reviewed. In response to this review, the original suggestion is somewhat amplified and clarified by its author.
    Keywords: PROPULSION SYSTEMS
    Type: Science; 178; Dec. 8
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  • 52
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    Swirling base injection for supersonic combustion ramjets. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Experimental evaluation of the swirling base injection proposed by Swithenbank and Chigier (1969) for application in supersonic combustion ramjets or scramjets. This concept of accelerated mixing in supersonic streams through swirl was tested, but the results indicate that swirl does not produce any enhancement of mixing.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA Journal; 10; Sept
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  • 53
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    Fusion power for space propulsion. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Principles of operation, interplanetary orbit-to-orbit mission capabilities, technical problems, and environmental safeguards are examined for thermonuclear fusion propulsion systems. Two systems examined include (1) a fusion-electric concept in which kinetic energy of charged particles from the plasma is converted into electric power (for accelerating the propellant in an electrostatic thrustor) by the van de Graaf generator principle and (2) the direct fusion rocket in which energetic plasma lost from the reactor has a suitable amount of added propellant to obtain the optimum exhaust velocity. The deuterium-tritium and the deuterium/helium-3 reactions are considered as suitable candidates, and attention is given to problems of cryogenic refrigeration systems, magnet shielding, and high-energy particle extraction and guidance.
    Keywords: PROPULSION SYSTEMS
    Type: New Scientist; 54; Apr. 20
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  • 54
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    Parameters influencing dynamic stability characteristics of Viking-type entry configurations at Mach 1.76. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Free-oscillation tests of three Viking-type blunt conical configurations were conducted in a wind tunnel to determine the important variables influencing their dynamic stability characteristics at Mach 1.76. The effects of sting geometry are shown to be significant at low angles of attack, while the effects of cross plane motions and tunnel vibration characteristics appear to be negligible. Variation of the reduced-frequency parameter and model base geometry caused significant effects in the data. An approximate technique was developed for converting effective data from either forced-oscillation or free-oscillation tests to values based on the instantaneous angle of attack.
    Keywords: SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets; 9; July 197
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  • 55
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    Ion-thruster propellant utilization. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Maximum propellant utilization in a mercury electron-bombardment thrustor is evaluated. The primary-electron region in the ion chamber of a bombardment thrustor is analyzed at maximum utilization. Both the analysis and experimental data from a range of ion-chamber configurations show a nearly constant loss rate for un-ionized propellant at maximum utilization over a wide range of total propellant flow rate. The discharge loss level of 1000 eV/ion was used to define maximum utilization. The exact level of this definition has no effect on the qualitative results and little effect on the quantitative results. The results obtained are particularly significant whenever efficient throttled operation is required.
    Keywords: PROPULSION SYSTEMS
    Type: Journal of Spacecraft and Rockets; 9; July 197
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  • 56
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    Space-Shuttle applications. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Discussion of the performance potential of the Space Shuttle and the high-energy transportation system to be derived from it. It is shown that, in addition to its cost effectiveness in earth-orbital missions, the Shuttle promises to be of major significance for future solar-system exploration. Eventually, the Shuttle will make possible the use of large interplanetary payloads launched at high velocities to the far reaches of the solar system.
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  • 57
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    Comparison of advanced propulsion concepts for deep space exploration. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Equations and charts are presented which permit rapid estimation of propulsion system performance requirements for some typical deep space missions. The simplicity results from use of gravity-free equations of motion, which are shown to yield good approximations to trip times obtained with solar gravity and planetary motion included. The agreement is satisfactory for missions that do not enter or depart from low orbits about the major planets. A number of advanced propulsion concepts for which performance estimates are available are compared with respect to their capability for fly-by, rendezvous, and round-trip planetary missions. Based on these estimates, the gas-core nuclear fission rocket and the pulsed fusion rocket yield the fastest trip times to the near planets. For round trips to Jupiter and beyond, the controlled fusion rocket shows progressively superior capabilities. Several propulsion concepts based on use of impinging laser beams are found to be noncompetitive with the other advanced concepts for deep space missions.
    Keywords: PROPULSION SYSTEMS
    Type: Journal of Spacecraft and Rockets; 9; Dec. 197
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  • 58
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    The Skylab orbital laboratory. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The Skylab orbital laboratory is described in terms of spacecraft design features, the experiment programs, and the schedule of planned missions. Attention is given to flight and crew operations, rescue measures, the Multiple Docking Adapter, the Airlock Module, the Workshop, the Apollo Telescope Mount, Saturn V booster, Command and Service Modules, the life support system, thermal and environmental control, electrical power, attitude and pointing control, instrumentation and communications, crew equipment, provisions, and stowage.
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  • 59
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    Advanced propulsion - Cleaner and quieter. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Studies were conducted to determine the factors which are significant in advancing propulsion technology. The studies surveyed a wide distribution of variables including aircraft configuration, payload, range, and speed. System studies placed major emphasis on reducing noise and exhaust emissions while attaining good economies and performance. An engine for an advanced transport will probably superficially resemble the presently emerging generation of modern high-bypass and high-temperature turbofan engines, but would incorporate the advances in component and system technology identified by the propulsion system studies. These advances could be used to improve aircraft economics significantly with no increase in noise, or to significantly reduce noise and pollution with few or no economic penalties.
    Keywords: PROPULSION SYSTEMS
    Type: Astronautics and Aeronautics; 10; Aug. 197
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  • 60
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    Satellite Aerodynamics and Density Determination from Satellite Dynamic Response (1972)
    In:  CASI
    Details
    Publication Date: 2014-09-09
    Description: The aerodynamic drag and lift properties of a satellite are first expressed as a function of two parameters associated with gas-surface interaction at the satellite surface. The dynamic response of the satellite as it passes through the atmosphere is then expressed as a function of the two gas-surface interaction parameters, the atmospheric density, the satellite velocity, and the satellite orientation to the high speed flow. By proper correlation of the observed dynamic response with the changing angle of attack of the satellite, it is found that the two unknown gas-surface interaction parameters can be determined. Once the gas-surface interaction parameters are known, the aerodynamic properties of the satellite at all angles of attack are also determined.
    Keywords: SPACE VEHICLES
    Type: Auburn Univ. The NASA-ASEE Summer Fac. Fellowship Program; p 345-364
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  • 61
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    The Large Space Telescope program. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The 1980's should see the establishment of the first major observatory in space. This observatory will contain a long-lifetime reflecting telescope of about 120 inches clear aperture. Advantages of an orbiting telescope include the elimination of astronomical seeing effects and improvements in resolving power. The small images and darker sky will permit low-dispersion spectrographs to avoid more of the contaminating background. The crispness of the images also has potential for very efficient high-dispersion spectroscopy. A further advantage lies in the accessibility of all the sky and nearly around-the-clock observing.
    Keywords: SPACE VEHICLES
    Type: Sky and Telescope; 44; Dec. 197
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  • 62
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    Unmanned planetary spacecraft chemical rocket propulsion. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Review of some chemical propulsion technology advances suitable for future unmanned spacecraft applications. Discussed system varieties include liquid space-storable propulsion systems, advanced liquid monopropellant systems, liquid systems for rendezvous and landing applications, and low-thrust high-performance solid-propellant systems, as well as hybrid space-storable systems. To optimize the performance and operational characteristics of an unmanned interplanetary spacecraft for a particular mission, and to achieve high cost effectiveness of the entire system, it is shown to be essential that the type of spacecraft propulsion system to be used matches, as closely as possible the various requirements and constraints. The systems discussed are deemed to be the most promising candidates for some of the anticipated interplanetary missions.
    Keywords: PROPULSION SYSTEMS
    Type: Journal of Spacecraft and Rockets; 9; Oct. 197
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  • 63
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    Automated techniques for spacecraft monitoring (1972)
    In:  CASI
    Details
    Publication Date: 2012-05-23
    Description: The feasibility of implementing automated spacecraft monitoring depends on four factors: sufficient computer resources, suitable monitoring function definitions, adequate spacecraft data, and effective and economical test systems. The advantages of automated monitoring lie in the decision-making speed of the computer and the continuous monitoring coverage provided by an automated monitoring program. Use of these advantages introduces a new concept of spacecraft monitoring in which system specialists, ground based or onboard, freed from routine and tedious monitoring, could devote their expertise to unprogrammed or contingency situations.
    Keywords: SPACE VEHICLES
    Type: AGARD Automation in Manned Aerospace Systems; 12 p
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  • 64
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    Mechanism problems (1972)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: It is pointed out that too frequently during the design and development of mechanisms, problems occur that could have been avoided if the right question had been asked before, rather than after, the fact. Several typical problems, drawn from actual experience, are discussed and analyzed. The lessons learned are used to generate various suggestions for minimizing mistakes in mechanism design.
    Keywords: SPACE VEHICLES
    Type: NASA. Lyndon B. Johnson Space Center The 7th Aerospace Mech. Symp.; p 3-13
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  • 65
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    Apollo Lunar Module Landing Gear (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Apollo lunar module landing-gear flight-performance results and three principal gear development problems are discussed. In evaluating the lunar module touchdown performance, strut stroking and toppling stability are the prime factors and are governed primarily by touchdown velocity and surface slope at the touchdown point. Flight results are shown to be well within design values, and the landing-gear has performed successfully in all landings.
    Keywords: SPACE VEHICLES
    Type: The 7th Aerospace Mech. Symp.; p 123-133
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  • 66
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    Dynamic analysis of Apollo-Salyut/Soyuz docking (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The use of a docking-system computer program in analyzing the dynamic environment produced by two impacting spacecraft and the attitude control systems is discussed. Performance studies were conducted to determine the mechanism load and capture sensitivity to parametric changes in the initial impact conditions. As indicated by the studies, capture latching is most sensitive to vehicle angular-alinement errors and is least sensitive to lateral-miss error. As proved by load-sensitivity studies, peak loads acting on the Apollo spacecraft are considerably lower than the Apollo design-limit loads.
    Keywords: SPACE VEHICLES
    Type: The 7th Aerospace Mech. Symp.; p 47-57
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  • 67
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    The Apollo 15 deployable boom anomaly (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: During the Apollo 15 mission, a boom with an attached mass spectrometer was required to retract periodically so that the instrument would not be in the field of view of other experiments. The boom did not fully retract on five of 12 occasions. Data analysis indicated that the boom probably retracted to within approximately 2.54 centimeters (1 inch) of full retraction. The pertinent boom-design details, the events in the mission related to the anomaly, a discussion of the inflight and postflight investigation of the problem, a discussion of the design changes to the boom mechanism as a result of the investigation, and subsequent flight performance are presented.
    Keywords: SPACE VEHICLES
    Type: the 7th Aerospace Mech. Symp.; p 15-26
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    Skylab (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Skylab program is presented to show the construction of the space vehicle and the facilities provided. The projects to be conducted during Skylab missions are described. The cost of the program is discussed and plans for future Skylab vehicles and missions are analyzed. Photographs of the interior of Skylab simulators are included to clarify the report.
    Keywords: SPACE VEHICLES
    Type: NASA. Marshall Space Flight Center Space for Mankind's Benefit; p 41-56
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    Unmanned spacecraft for research (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The applications of unmanned spacecraft for research purposes are discussed. Specific applications of the Communication and Navigation satellites and the Earth Observations satellites are described. Diagrams of communications on world-wide basis using synchronous satellites are developed. Photographs of earth resources and geology obtained from space vehicles are included.
    Keywords: SPACE VEHICLES
    Type: NASA. Marshall Space Flight Center Space for Mankind's Benefit; p 23-39
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    The potential impact of the space shuttle on space benefits to mankind (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The potential impact of the space shuttle on space benefits to mankind is discussed. The space shuttle mission profile is presented and the capabilities of the spacecraft to perform various maneuvers and operations are described. The cost effectiveness of the space shuttle operation is analyzed. The effects upon technological superiority and national economics are examined. Line drawings and artist concepts of space shuttle configurations are included to clarify the discussion.
    Keywords: SPACE VEHICLES
    Type: NASA. Marshall Space Flight Center Space for Mankind's Benefit; p 57-76
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  • 71
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    In-orbit flexible spacecraft dynamics program (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A continuous flexible body nonlinear dynamics computer program is used for simulating the spinning mode performance of a spacecraft under applied control torques. The program takes into account the continuous flexible nature of the antennas by representing deflections in terms of shape functions and integrated the spatial dependence in the formulation of the equations of motion. Comparison of RAE flight data on roll, pitch, and yaw with predictions of the computer program in the gravity gradient mode show fair to good agreement in roll and pitch and excellent agreement in the yaw angle.
    Keywords: SPACE VEHICLES
    Type: Significant Accomplishments in Technol., GSFC, 1970; p 30-35
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  • 72
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    Dynamical in-orbit behavior of the Radio Astronomy Explorer satellite (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Onboard sensors and associated ground based processing systems are used to maintain a well stabilized attitude for the RAE 1 in its near circular earth orbit despite the satellite's four extremely long and flexible antenna booms. Boom tip deflection pictures and central hub orientation measurements show that large boom vibrations and major attitude stability problems anticipated prior to launch have not materialized.
    Keywords: SPACE VEHICLES
    Type: Significant Accomplishments in Technol., GSFC, 1970; p 18-22
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  • 73
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    Comparison of satellite theories (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The accuracy of five mathematical models in computing a nominal orbit for the Vanguard 2 satellite by using a position velocity vector is considered. Either numerical integration or analytical theories are used in all models as well as the same force model that corresponds to a potential with the zonal harmonics to order four. The amounts of spread in the values of the total energy and the z-component of the angular momentum for a set of times are considered as measures of accuracy.
    Keywords: SPACE VEHICLES
    Type: Significant Accomplishments in Technol., GSFC, 1970; p 10-13
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  • 74
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    An analysis of the expected eccentricity perturbations for the second Radio Astronomy Explorer (RAE B) (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Analytical prediction of expected eccentricity perturbations for the RAE 2 lunar orbit shows that the eccentricity will grow linearly in time. Parametric inclination studies and analysis of perturbation equations establish a critical retrograde inclination of 116.565 at which the positive perturbation slope vanishes for a circular orbit about 1100 m above the lunar surface with an eccentricity constraint of less than 0.005 during a period of about one year.
    Keywords: SPACE VEHICLES
    Type: Significant Accomplishments in Technol., GSFC, 1970; p 14-17
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  • 75
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    Space shuttle orbiter handling quality criteria applicable to terminal area, approach, and landing (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An analytical pilot-vehicle study was made to determine the performance criteria for the space shuttle vehicle. Specifications for the flying qualities of piloted aircraft were used for appropriate portions of the space shuttle mission. The handling qualities during the terminal phases of the space shuttle flight were simulated to develop the necessary criteria. Additional criteria required for conditions during the unpowered approach and landing trajectory portion of the flight are explained.
    Keywords: SPACE VEHICLES
    Type: Space Shuttle Aerothermodyn. Tech. Conf., vol. 4; p 1239-1263
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  • 76
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    Effect of commercial and military performance requirements for transport category aircraft on space shuttle booster design and operation (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The effect of two sets of performance requirements, commercial and military, on the design and operation of the space shuttle booster is evaluated. Critical thrust levels are established according to both sets of operating rules for the takeoff, cruise, and go-around flight modes, and the effect on engine requirements determined. Both flyback and ferry operations are considered. The impact of landing rules on potential shuttle flyback and ferry bases is evaluated. Factors affecting reserves are discussed, including winds, temperature, and nonstandard flight operations. Finally, a recommended set of operating rules is proposed for both flyback and ferry operations that allows adequate performance capability and safety margins without compromising design requirements for either flight phase.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Tech. Conf., vol. 4; p 1191-1237
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  • 77
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    Space Shuttle Atmospheric ascent flight dynamics (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The atmospheric ascent flight phase of the mated composite booster and orbiter is discussed. The composite recoverable space shuttle booster and orbiter exhibits unique flight control characteristics. This uniqueness results from large lifting surfaces and aerodynamic and structural assymetrics. An effective load relief technique reduces aerodynamic loads on both the booster and the orbiter. Reducing aerodynamic loads permits decreasing the structural weight of the lifting and stabilizing surfaces. An orbiter payload penalty is caused by trajectory deviations resulting from load relief. However, the net effect of an effective load relief technique is an increase in payload capability. Atmospheric launch dynamics investigations have been carried out for different configuration types, which include expendable, straight wing, delta wing, and ballistic recoverable boosters.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Tech. Conf., vol. 4; p 1041-1062
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    Vehicle performance impact on space shuttle design and concept evaluation (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The continuing examination of widely varied space shuttle concepts makes an understanding of concept interaction with vehicle performance imperative. The estimation of vehicle performance is highly appurtenant to all aspects of shuttle design and hence performance has classically been a key indicator of overall concept desirability and potential. Vehicle performance assumes the added role of defining interactions between specific design characteristics, the sum total of which define a specific concept. Special attention is given to external tank effects.
    Keywords: SPACE VEHICLES
    Type: Space Shuttle Aerothermodyn. Tech. Conf., vol. 4; p 999-1039
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  • 79
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    Radiation problems associated with Skylab (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Radiation tests were conducted on the various types of Skylab film to establish the total radiation dosages compatible with an acceptable level of film fogging, and on the S190 borosilicate window to establish radiation limits for an acceptable darkening level. The results verified that most of the films would be unusable when returned to earth, and that the borosilicate window would be darkened beyond allowable limit, unless additional protection was provided. The operational solutions to these problems involve protecting the film with five film vaults and protecting the window with a radiation shield. The largest vault is made of aluminum and weighs over 2000 lb (its thickest compartment wall is 3.4 in.). The window radiation shield is a light honeycomb structure which is swung away for limited astronaut viewing or when the S190 experiment is in operation. Although the shield is light weight, it is heavy enough to stop the large number of low energy electrons making up a major part of the external environment and which are potentially damaging to the window. A brief description is given of the Skylab mission and some of the associated experiments. The radiation environment the spacecraft will encounter is discussed.
    Keywords: SPACE VEHICLES
    Type: NASA, Washington Proc. of the Natl. Symp. on Nat. and Manmade Radiation in Space; p 748-755
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    Radiation analysis of various vehicle and payload configurations for the reusable nuclear shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Radiation analyses were performed and shielding weight requirements were estimated for various candidate vehicle and payload configurations for use with the reusable nuclear shuttle. The analyses included both point kernel and Monte Carlo approaches. The effects on reduced shield weight were determined for propellant ranks with pointed conical tank bottoms and for one case of a cluster of small tanks. This later case, however, had an arrangement which had no center tank in the upper tier of tanks. This effect negated most of the gain of going to the smaller tanks. A range of shield weights is presented for various light and heavy manned payload configurations when used in conjunction with a single liquid hydrogen propellant tank, 33 ft in diameter with a 15 deg conical tank bottom.
    Keywords: SPACE VEHICLES
    Type: NASA, Washington Proc. of the Natl. Symp. on Nat. and Manmade Radiation in Space; p 58-64
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  • 81
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    Adhesives and the ATS satellite (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Adhesives in the ATS satellite allow the designers to save weight, simplify design and fabrication and provide thermal and electrical conductivity or resistivity as required. The selections of adhesives are restricted to those few which can pass rigorous outgassing tests in order to avoid contaminating lenses and thermal control surfaces in space. An epoxy adhesive is used to construct the honeycomb panels which constitute most of the satellite's structure. General purpose epoxy adhesives hold doublers and standoffs in place and bond the truss to its fittings. Specialized adhesives include a high temperature resistant polyamide, a flexible polyurethane and filled epoxies which conduct heat or electricity.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center Proc. of the Symp. on Welding, Bonding, and Fastening; 8 p
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  • 82
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    Apollo couch energy absorbers (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Load attenuators for the Apollo spacecraft crew couch and its potential applications are described. Energy absorption is achieved through friction and cyclic deformation of material. In one concept, energy absorption is accomplished by rolling a compressed ring of metal between two surfaces. In another concept, energy is absorbed by forcing a plastically deformed washer along a rod. Among the design problems that had to be solved were material selection, fatigue life, ring slippage, lubrication, and friction loading.
    Keywords: SPACE VEHICLES
    Type: The 7th Aerospace Mech. Symp.; p 157-167
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  • 83
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    Mechanically prestressed windows (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A method was developed for mechanically prestressing glass used in spacecraft windows so that surface imperfections of the glass will not propagate under stress. A metal ring, in tension, is placed around the periphery of the glass where the interference fit between the ring and glass fixes the glass in a state of uniform compression. When the glass is subjected to a pressure loading, the compressive prestress prevents tension loading of the outer surface and, therefore, eliminates the tendency for propagation of surface imperfections.
    Keywords: SPACE VEHICLES
    Type: The 7th Aerospace Mech. Symp.; p 149-156
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  • 84
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    Dynamic testing of docking system hardware (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Extensive dynamic testing was conducted to verify the flight readiness of the Apollo docking hardware. Testing was performed on a unique six degree-of-freedom motion simulator controlled by a computer that calculated the associated spacecraft motions. The test system and the results obtained by subjecting flight-type docking hardware to actual impact loads and resultant spacecraft dynamics are described.
    Keywords: SPACE VEHICLES
    Type: The 7th Aerospace Mech. Symp.; p 203-211
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  • 85
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    Cable Connected Spinning Spacecraft, 1. the Canonical Equations, 2. Urban Mass Transportation, 3 (1972)
    In:  CASI
    Details
    Publication Date: 2014-09-09
    Description: Work on the dynamics of cable-connected spinning spacecraft was completed by formulating the equations of motion by both the canonical equations and Lagrange's equations and programming them for numerical solution on a digital computer. These energy-based formulations will permit future addition of the effect of cable mass. Comparative runs indicate that the canonical formulation requires less computer time. Available literature on urban mass transportation was surveyed. Areas of the private rapid transit concept of urban transportation are also studied.
    Keywords: SPACE VEHICLES
    Type: Auburn Univ. The NASA-ASEE Summer Fac. Fellowship Program; p 563-570
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  • 86
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    Ply-tear webbing energy absorber (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Ply-tear webbing is essentially two plain webbings that are bound together by a portion of the warps and that can be torn apart and do work by breaking the binders. Nylon webbing were woven to range in tear force from 1 to 10 kilonewtons. This force is substantially independent of speed, which was as high as 100 m/sec in some cases. A specific energy absorption of 90 J/g was achieved in the dry state. However, lower rated webbings that absorb approximately 40 J/g are recommended for use in practice where it is acceptable.
    Keywords: SPACE VEHICLES
    Type: NASA. Lyndon B. Johnson Space Center The 7th Aerospace Mech. Symp.; p 215-232
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  • 87
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    Lunar roving vehicle deployment mechanism (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The space support equipment that supports the lunar roving vehicle during the flight to the moon and permits the vehicle to be deployed from the lunar module onto the lunar surface with a minimum amount of astronaut participation is discussed. The design and evolution of the equipment are reviewed. The success of the overall lunar roving vehicle design, including the space support equipment, was demonstrated on the Apollo 15 and 16 missions.
    Keywords: SPACE VEHICLES
    Type: NASA. Lyndon B. Johnson Space Center The 7th Aerospace Mech. Symp.; p 101-110
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  • 88
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    Docking system of androgynous and peripheral type (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Soviet and American space engineers have proceeded with creating compatible means for closing and docking spacecraft. It was decided to make a new advanced docking system of a peripheral and androgynous type. Because of a more complex design of the new-type docking mechanism, a number of technical problems arose. To a great extent, the solution of these problems depends on a chosen concept of the docking mechanism. The report deals with the docking system concept accepted by the Soviet engineers as the basis for further development. The description and structural arrangement of the docking system as a whole, its basic assemblies, and a kinematic scheme of the docking mechanism using a system of differentials are given. It should be noted that the experience that was gained from the development of previous docking systems was used to create a new type of docking system. The main problems to be solved in the course of designing and developing the advanced system are noted.
    Keywords: SPACE VEHICLES
    Type: NASA. Lyndon B. Johnson Space Center The 7th Aerospace Mech. Symp.; p 27-35
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    Space tug point design study. Volume 1: Summary (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design and characteristics of a space tug are discussed. The primary objective of the study is to verify the performance capability of a baseline design to deliver and retrieve payloads between 100 nautical miles, 28.5 degrees inclination, and geosynchronous. The space tug is ground based, reusable for 20 mission cycles, and is shuttled to and from low earth orbit by an earth orbital shuttle (EOS) with a 65,000 pound payload capability. It is shown that the baseline concept can meet the target performance goals. The design analysis encompassed: (1) definition of the vehicle primary structure, (2) thermal control, (3) meteoroid protection, (4) propulsion and mechanical subsystems, and (5) avionics including power generation and distribution.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-120109 , SD72-SA-0032-VOL-1
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  • 90
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    HEUS-RS applications study, volume 1 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Studies are given for sizing and integrating a high energy upper stage restartable solid motor into a flight stage with various payloads for use with Titan 3 and Thor launch vehicles. Motor and stage configurations are given along with performance evaluation of the HEUS-RS with the space shuttle.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-130274 , D2-116262-1-VOL-1
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  • 91
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    Apollo 15 mission report. Supplement 3: Ascent propulsion system final flight evaluation (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results from the postflight analysis of the ascent propulsion system (APS) performance during the Apollo 15 mission are presented. The duty cycle for the LM-10 APS consisted of two firings, and ascent stage liftoff from the lunar surface and the terminal phase ignition (TPI) burn. An evaluation was made of APS performance for the first firing and found to be satisfactory. No propulsion data was received from the second APS burn; however, all indications were that the burn was nominal. All performance parameters were well within their LM-10 3-sigma limits. Calculated throat erosion at engine cutoff for the LM-10 APS was approximately 3 percent greater than predicted.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-68932 , TRW-20029-H062-R0-00 , MSC-05161-SUPPL-3
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  • 92
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    A quasi-inertial attitude mode for orbiting spacecraft. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A method is presented for achieving quasi-inertial orientation of an orbiting spacecraft with minimal control effort. Spacecraft motion is a small-amplitude oscillation about the orbit normal with one principal axis held in the orbital plane. The nominal orientation of this axis is arbitrary, so that any spacecraft axis normal to it may be pointed arbitrarily on the celestial sphere and remain within a small neighborhood of the nominal orientation. Oscillation amplitude can be chosen to minimize control requirements for maintaining the mode and may range up to 18.8 deg depending on spacecraft inertia. The quasi-inertial mode would be an efficient means for maintaining a nominal solar orientation for NASA's Skylab configuration if the control-moment-gyros fail in the primary attitude control system. This approach, which utilizes the backup reaction thrust system, affords a substantial reduction in propellant requirements compared to that for a true solar inertial attitude hold.
    Keywords: SPACE VEHICLES
    Type: Journal of Spacecraft and Rockets; 9; Dec. 197
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  • 93
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    Study of solid rocket motor for space shuttle booster, Volume 3: Program acquisition planning (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The program planning acquisition functions for the development of the solid propellant rocket engine for the space shuttle booster is presented. The subjects discussed are: (1) program management, (2) contracts administration, (3) systems engineering, (4) configuration management, and (5) maintenance engineering. The plans for manufacturing, testing, and operations support are included.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-124238 , TWR-5672-VOL-3 , PUBL-0372-36176 , A10738
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    Apollo 14 mission report. Supplement 5: Descent propulsion system final flight evaluation (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The performance of the LM-8 descent propulsion system during the Apollo 14 mission was evaluated and found to be satisfactory. The average engine effective specific impulse was 0.1 second higher than predicted, but well within the predicted l sigma uncertainty. The engine performance corrected to standard inlet conditions for the FTP portion of the burn at 43 seconds after ignition was as follows: thrust, 9802, lbf; specific impulse, 304.1 sec; and propellant mixture ratio, 1603. These values are + or - 0.8, -0.06, and + or - 0.3 percent different respectively, from the values reported from engine acceptance tests and were within specification limits.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-69491 , MSC-04112-SUPPL-5 , TRW-17618-H219-R0-00-SUPPL-5
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  • 95
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    Study of solid rocket motors for a space shuttle booster. Volume 1: Executive summary (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analysis of the solid propellant rocket engines for use with the space shuttle booster was conducted. A definition of the specific solid propellant rocket engine stage designs, development program requirements, production requirements, launch requirements, and cost data for each program phase were developed.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-124236 , TWR-5672-VOL-1 , PUBL-0372-36174 , A09995
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    Liquid propellant gas generators (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design of gas generators intended to provide hot gases for turbine drive is discussed. Emphasis is placed on the design and operation of bipropellant gas generators because of their wider use. Problems and limitations involved in turbine operation due to temperature effects are analyzed. Methods of temperature control of gas turbines and combustion products are examined. Drawings of critical sections of gas turbines to show their operation and areas of stress are included.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-SP-8081
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    Water/glycol temperature control circuit failed in the automatic mode: Apollo 16 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An anomaly report concerning failure of the water/glycol temperature control circuit during the Apollo 16 flight is presented. The anomaly is described and diagrams of the system are presented. The malfunction was caused by cracked semiconductor chips in the output silicon-controlled rectifier. Surface contamination in the crack allowed the device to self-gate on and remain on, resulting in a secondary failure of the feedback capacitor.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-69234 , MSC-07598
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  • 98
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    Uneven drive rates of the scanning telescope: Apollo 16 mission (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was made into the cause or causes of uneven drive rates during operation of the Apollo 16 scanning telescope. It was suggested that such erratic behavior was caused by either changes in the characteristics noise level of the optics counter on the panels or the repositioning process by the computer or zero optics mode. Test results show the anomaly was not caused by either of the above suggestions, instead they were caused by a broken socket spring in the telescope harness. New harnesses will be manufactured for future flights.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-69233 , MSC-07573
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  • 99
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    Inertial subsystem warnings and coupling data unit failure indicators: Apollo 16 mission (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The indicated failures of the inertial coupling unit were investigated. The coupling data unit assembly failure detection circuits and the diagnostic tests are described. It is concluded that conductive contamination in a zener diode in the failure-detect circuit of the coupling data unit assembly most likely caused the problem.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-69199 , MSC-07571
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    Apollo 16 Mission: Oxidizer Deservicing Tank Failure (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An explosive failure of a ground support equipment decontamination unit tank occurred during the postflight deactivation of the oxidizer (nitrogen tetroxide) portion of the Apollo 16 command module reaction control system. A discussion of the significant aspects of the incident and conclusions are included.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-69323 , MSC-07032-REV-A
    Format: application/pdf
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