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  • Spacecraft Design, Testing and Performance  (39)
  • 1960-1964  (39)
  • 1945-1949
  • 1961  (39)
  • 1
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    Method for Approximating the Vacuum Motions of Spinning Symmetrical Bodies with Nonconstant Spin Rates (1961)
    In:  CASI
    Details
    Publikationsdatum: 2019-05-11
    Beschreibung: A method for approximating the vacuum motions of spinning rigid symmetrical bodies with varying spin rates and inertias has been completed. The analysis includes the effects of time varying thrust misalignments, mass unbalance, and jet damping. Results are given in the form of equations for space referenced Euler angles, flight-path angles, body referenced attitude rates, and earth-referenced vehicle-trajectory coordinates. The method consists of dividing the problem into intervals during which the time-dependent variables are assumed constant at their mean interval value. In order to check this procedure, solutions for various interval sizes are compared with solutions obtained with numerical methods. Although the method is somewhat lengthy for accurate hand computation in most cases, it is readily programed for machine solutions. Probably more important, the general solutions give insight into the separate effects of the variables and, in many cases, can be quickly used to determine the approximate ranges of the variables required for the desired solution to a given problem. In this respect, equations for determining maximum wobble have been derived for certain input conditions. The method has been shown to compare closely with the numerical solutions of two sample problems. The sample problems also illustrated the relatively large effect of pitch and yaw jet damping on body motions.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: NASA-TR-R-115
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 2
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    Method for Approximating the Vacuum Motions of Spinning Symmetrical Bodies with Nonconstant Spin Rates (1961)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-20
    Beschreibung: The analysis includes non-constant spin rates and inertias and considers the effects of time-varying thrust misalignments, mass unbalance, and jet damping. The method was developed for bodies having small trans verse angular velocities. Results are presented in the form of equations for space-referenced Euler angles, flight-path angles, body-referenced attitude rates, and earth-referenced vehicle-trajectory coordinates. Also, equations for maximum wobble have been derived for certain input conditions. Comparisons with numerical solutions are included for two sample problems.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: NASA-TR-R-115
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 3
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    Landing of Manned Reentry Vehicles (1961)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Landing characteristics were investigated using dynamic models. The landing speeds for several let-down systems are simulated. Demonstrations include: (1) the vertical landing of parachute-supported capsules on water; (2) reduction of landing acceleration by shaping the impact surface for water entry; (3) problems created by horizontal velocity due to wind; (4) the use of energy absorbers (yielding metal legs or torus bags) for land or water landings; (5) problems associated with horizontal land landings; (6) the use of a paraglider to aid in vehicle direction control; (7) a curved undersurface to serve as a skid-rocker to convert sinking-speed energy into angular energy; (8) horizontal-type landing obtained with winged vehicles on a hard runway; (9) the dangers of high-speed water landings; and (10) the positive effects of parachute support for landing winged vehicles.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: L-600
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 4
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    An Exploratory Investigation of Jet Blast Effects on a Dust Covered Surface at Low Ambient Pressure (1961)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: A preliminary investigation has been conducted to determine the effects of jet blast, at low ambient pressures, on a surface covered with loose particles. Tests were conducted on configurations having from one to four nozzles at 0, 10, 20, and 30 degree cant angles and heights of 2 and 4 inches above the particle-covered surface.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: L-671
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 5
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    Investigation of the Static Longitudinal and Lateral Stability Characteristics of a 0.10-Scale Model of a Three-Stage Configuration of the Scout Research Vehicle at Mach Numbers of 2.29, 2.96, 3.96, and 4.65 (1961)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: An investigation w a s made i n the Langley Unitary Plan wind tunnel o determine the effects of fin area and the effects of antennas and w iring tunnels on the static longitudinal and lateral stability of a 0 .10- scale model of a three- stage configuration of the Scout vehicle. The tests were performed at Mach numbers of 2.29, 2.96, 3.96, and 4. 65 6 and at Reynolds numbers of about 3.5 X 10 per foot.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: NASA-TN-D-711 , L-1269
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 6
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    Effects of Mass-Loading Variations and Applied Moments on Motion and Control of a Manned Rotating Space Vehicle (1961)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: An analytical study has been made to determine the effects of mass-loading variations and onboard rotating machinery on a hypothetical earth-satellite space station, rotating to provide an artificial gravity equal to one-fourth of that at the earth's surface. Attempts were also made to damp out or minimize undesirable motions by using mass shifts, constant-rate inertia wheels, or jet-reaction moments. Results obtained indicate that the shifting of masses within the rotating space station could bring about large roll oscillations (plus or minus 100 degrees) or even continuous rolling motions if the craft is rotating about the axis of intermediate moment of inertia. The pitch angles obtained were generally small (less than plus or minus 1 degree). The amplitudes of the roll and pitch oscillations are dependent upon the angle of displacement of the greatest principal axis of inertia from the initial spin axis. In attempting to damp out or minimize undesirable motions, it was found that a constant-rate inertia wheel located on and rotating about the axis about which the craft is rotating (Z-axis) was beneficial in keeping the roll angles relatively small, provided it had a sufficient amount of angular momentum. It was also found that the use of jet-reaction moments was very satisfactory for damping undesirable motions in that the roll oscillations could be damped.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: NASA-TN-D-803 , L-1406
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 7
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    The Effect of Solar Radiation Pressure on the Motion of an Artificial Satellite (1961)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: The effects of solar radiation pressure on the motion of an artificial satellite are obtained, including the effects of the intermittent acceleration which results from the eclipsing of the satellite by the earth. Vectorial methods have been utilized to obtain the nonlinear equations describing the motion, and the method of Kryloff-Bogoliuboff has been applied in their solution.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: NASA-TN-D-1063
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 8
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    Study of a Satellite Attitude Control System Using Integrating Gyros as Torque Sources (1961)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: This report considers the use of single-degree-of-freedom integrating gyros as torque sources for precise control of satellite attitude. Some general design criteria are derived and applied to the specific example of the Orbiting Astronomical Observatory. The results of the analytical design are compared with the results of an analog computer study and also with experimental results from a low-friction platform. The steady-state and transient behavior of the system, as determined by the analysis, by the analog study, and by the experimental platform agreed quite well. The results of this study show that systems using integrating gyros for precise satellite attitude control can be designed to have a reasonably rapid and well-damped transient response, as well as very small steady-state errors. Furthermore, it is shown that the gyros act as rate sensors, as well as torque sources, so that no rate stabilization networks are required, and when no error sensor is available, the vehicle is still rate stabilized. Hence, it is shown that a major advantage of a gyro control system is that when the target is occulted, an alternate reference is not required.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: NASA-TN-D-1073 , A-443
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 9
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    Charts Depicting Kinematic and Heating Parameters for a Ballistic Reentry at Speeds of 26,000 to 45,000 Feet Per Second (1961)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: Reentry trajectories, including computations of convective and radiative stagnation-point heat transfer, have been calculated by using equations for a point-mass reentry vehicle entering the atmosphere of a rotating, oblate earth. Velocity was varied from 26,000 to 45,000 feet per second; reentry angle, from the skip limit to -20 deg; ballistic drag parameter, from 50 to 200. Initial altitude was 400,000 feet. Explicit results are presented in charts which were computed for an initial latitude of 38 deg N and an azimuth of 90 deg from north. A method is presented whereby these results may be made valid for a range of initial latitude and azimuth angles.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: NASA-TN-D-968 , L-1750
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
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  • 10
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    Effects of Ionizing Radiation on Solid Rocket Motor Components (1961)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-14
    Beschreibung: Problems which the solid propellant rocket engineer will encounter in designing for long-term storage in a radiation environment are discussed. A summary of present knowledge of the radiation environment is given. Mechanisms of radiation degradation and its effects on tensile properties of propellant binders are discussed qualitatively. Data from a program of irradiation of several propellants is presented. Properties of two of the propellants were changed significantly by doses of the order of 4 x 10(exp 6) rads.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: JPL-TR-32-234
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
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