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  • NAVIGATION  (55)
  • AERODYNAMICS  (30)
  • Spacecraft Design, Testing and Performance  (23)
  • SPACE RADIATION
  • SPACE SCIENCES
  • 1960-1964  (127)
  • 1960  (127)
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  • 1960-1964  (127)
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  • 1
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    Space Activities Summary (1960)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-28
    Beschreibung: No abstract available
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 2
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    Orbital Thermal Control of the Mercury Capsule (1960)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-27
    Beschreibung: The approach to orbital thermal control of the Project Mercury capsule environment is relatively unsophisticated compared with that for many unmanned satellites. This is made possible by the relatively short orbital flight of about 4 1/2 hours and by the presence of the astronaut who is able to monitor the capsule systems and compensate for undesirable thermal conditions. The general external features of the Mercury configuration as it appears in the orbital phase of flight are shown. The conical afterbody is a double-wall structure. The inner wall serves as a pressure vessel for the manned compartment, and the outer wall, of shingle type construction, acts as a radiating shield during reentry. Surface treatment of the shingles calls for a stably oxidized surface to minimize reentry temperatures. The shingles are supported by insulated stringers attached to the inner skin. Areas between stringers are insulated by blankets of Thermoflex insulation. This insulation is especially effective at high altitude due to the reduction of its thermal conductivity with decreasing pressure. As a result of the design of the afterbody for the severe reentry conditions, the heat balance on the manned compartment indicates the necessity for moderate internal cooling to compensate for the heat generation due to human and electrical sources. This cooling is achieved by the controlled vaporization of water in the cabin and astronaut-suit heat exchangers.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: NASA Conference on Thermal Radiation Problems in Space Technology: A Compilation of Summaries of the Papers Presented; 52-54
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 3
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    An Analysis of Ablation-Shield Requirements for Manned Reentry Vehicles (1960)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: The problem of sublimation of material and accumulation of heat in an ablation shield is analyzed and the results are applied to the reentry of manned vehicles into the earth's atmosphere. The parameters which control the amount of sublimation and the temperature distribution within the ablation shield are determined and presented in a manner useful for engineering calculation. It is shown that the total mass loss from the shield during reentry and the insulation requirements may be given very simply in terms of the maximum deceleration of the vehicle or the total reentry time.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: NASA-TR-R-62
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 4
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    Analytical Investigation of the Dynamic Behavior of a Nonlifting Manned Reentry Vehicle (1960)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: An analytic investigation was made of the dynamic behavior of a nonlifting manned reentry vehicle as it descended through the atmosphere. The investigation included the effects of variations in the aerodynamic stability derivatives, the spin rate, reentry angle, and velocity. The effect of geostrophic winds and of employing a drogue parachute for stability purposes were also investigated. It was found that for the portion of the flight above a Mach number of 1 a moderate amount of negative damping could be tolerated but below a Mach number of 1 good damping is necessary. The low-speed stability could be improved by employing a drogue parachute. The effectiveness of the drogue parachute was increased when attached around the periphery of the rear of the vehicle rather than at the center. Neither moderate amounts of spin or the geostrophic winds had appreciable effects on the stability of the vehicle. The geostrophic winds and the reentry angle or velocity all showed important effects on the range covered by the reentry flight path.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: NASA-TN-D-416 , L-867
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 5
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    Motion and Heating During Atmosphere Reentry of Space Vehicles (1960)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-16
    Beschreibung: The results of an analysis of the motion and heating during atmospheric reentry of manned space vehicles has shown the following: 1. Flight-corridor depths which allow reentry in a single pass decrease rapidly as the reentry speed increases if the maximum deceleration is limited to 10 g. 2. Use of aerodynamic lift can result in a three-to five fold increase in corridor depth over that available to a ballistic vehicle for the same deceleration limits. 3. Use of aerodynamic lift to widen these reentry corridors causes a heating penalty which becomes severe for values of the lift-drag ratio greater than unity for constant lift-drag entry. 4. In the region of most intense convective heating the inviscid flow is generally in chemical equilibrium but the boundary-layer flows are out of equilibrium. Heating rates for the nonequilibrium boundary layer are generally lower than for the corresponding equilibrium case. 5. Radiative heating from the hot gas trapped between the shock wave and the body stagnation region may be as severe as the convective heating and unfortunately occurs at approximately the same time in the flight.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: NASA-TN-D-334
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 6
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    Satellite Attitude Control Using a Combination of Inertia Wheels and a Bar Magnet (1960)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-16
    Beschreibung: The use of inertia wheels to control the attitude of a satellite has currently aroused much interest. The stability of such a system has been studied in this investigation. A single-degree-of-freedom analysis indicates that a response with suitable dynamic characteristics and precise control can be achieved by commanding the angular velocity of the inertia wheel with an error signal that is the sum of the attitude error, the attitude rate, and the integral of the attitude error. A digital computer was used to study the three-degree-of-freedom response to step displacements, and the results indicate that the cross-coupling effects of inertia coupling and precession coupling had no effect on system stability. A study was also made of the use of a bar magnet to supplement the inertia wheels by providing a means of removing any momentum introduced into the system by disturbances such as aerodynamic torques. A study of a case with large aerodynamic torques, with a typical orbit, indicated that the magnet was a suitable device for supplying the essential trimming force. Single-degree-of-freedom bench tests generally verified the dynamic response predicted by the analytical study. the test table to within plus or minus 9 arc-seconds of the reference direction, even though the hardware components that were used in these tests were not specifically designed for the control system.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: NASA-TN-D-626 , L-1160
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 7
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    A Flight Study of a Power-Off Landing Technique Applicable to Re-Entry Vehicles (1960)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-15
    Beschreibung: A power-off landing technique, applicable to aircraft of configurations presently being considered for manned re-entry vehicles, has been developed and flight tested at Ames Research Center. The flight tests used two configurations of an airplane for which the values of maximum lift-drag ratios were 4.0 and 2.8. Twenty-four idle-power approaches were made to an 8000-foot runway with touchdown point and airspeed accuracies of +/-600 feet and +/-10 knots, respectively. The landing pattern used was designed to provide an explicitly defined flight path for the pilot and, yet, to require no external guidance other than the pilot's view from the cockpit. The initial phase of the approach pattern is a constant high-speed descent from altitude aimed at a ground reference point short of the runway threshold. At a specified altitude and speed, a constant g pull-out is made to a shallow flight path along which the air-plane decelerates to the touchdown point. Repeatability and safety are inherent because of the reduced number of variables requiring pilot judgment, and because of the fact that a missed approach is evident at speeds and altitudes suitable for safe ejection. The accuracy and repeatability of the pattern are indicated by the measured results. The proposed pattern appears to be particularly suitable for configurations having unusual drag variations with speed in the lower speed regime, since the pilot is not required to control speed in the latter portions of the pattern.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: NASA-TN-D-323
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 8
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    Gyroscopic Motion of an Unsymmetrical Satellite Under No External Forces (1960)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-15
    Beschreibung: This report gives the results of an investigation on the transition from spin about the axis of minimum moment of inertia to spin about the axis of maximum moment of inertia by dissipation of internal mechanical energy. A mathematical discussion, together with charts and diagrams, shows that angular velocities and nutation angle are dependent on the energy and symmetry factors. The low stability of rotation about the axis of maximum moment of inertia, when this inertia is only slightly greater than the mean moment of inertia, is shown.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: NASA-TN-D-596
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 9
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    An Approximate Analytical Method for Studying Atmosphere Entry of Vehicles with Modulated Aerodynamic Forces (1960)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-15
    Beschreibung: The dimensionless, transformed, nonlinear differential equation developed in NASA TR R-11 for describing the approximate motion and heating during entry into planetary atmospheres for constant aerodynamic coefficients and vehicle shape has been modified to include entries during which the aerodynamic coefficients and the vehicle shape are varied. The generality of the application of the original equation to vehicles of arbitrary weight, size, and shape and to arbitrary atmospheres is retained. A closed-form solution for the motion, heating, and the variation of drag loading parameter m/C(D)A has been obtained for the case of constant maximum resultant deceleration during nonlifting entries. This solution requires certain simplifying assumptions which do not compromise the accuracy of the results. The closed-form solution has been used to determine the variation of m/C(D)A required to reduce peak decelerations and to broaden the corridor for nonlifting entry into the earth's atmosphere at escape velocity. The attendant heating penalty is also studied.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: NASA-TN-D-319
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 10
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    Landing Energy Dissipation for Manned Reentry Vehicles (1960)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-15
    Beschreibung: Analytical and experimental investigations have been made to determine the landing-energy-dissipation characteristics for several types of landing gear for manned reentry vehicles. The landing vehicles are considered in two categories: those having essentially vertical-descent paths, the parachute-supported vehicles, and those having essentially horizontal paths, the lifting vehicles. The energy-dissipation devices discussed are crushable materials such as foamed plastics and honeycomb for internal application in couch-support systems, yielding metal elements as part of the structure of capsules or as alternates for oleos in landing-gear struts, inflatable bags, braking rockets, and shaped surfaces for water impact. It appears feasible to readily evaluate landing-gear systems for internal or external application in hard-surface or water landings by using computational procedures and free-body landing techniques with dynamic models. The systems investigated have shown very interesting energy-dissipation characteristics over a considerable range of landing parameters. Acceptable gear can be developed along lines similar to those presented if stroke requirements and human-tolerance limits are considered.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: NASA-TN-D-453 , L-1082
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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