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  • 1
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    A stochastic model for particle impingements on orbiting spacecraft (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A general methodology for simulating particle impingements on orbiting spacecraft is developed. Major steps in the modeling process are presented as (1) modeling objective, (2) construction of the spacecraft geometrical model, (3) simulation of the particles in the space environment, (4) particle impact and subsequent events of interest, and (5) results of the simulation. A simulation of the expected meteoroid impingements on the Hubble Space Telescope and the resulting angular momentum transfers which can cause telescope pointing disturbances is given to illustrate these methods.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of the Astronautical Sciences (ISSN 0021-9142); 34; 375-401
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Pin puller impact shock attenuation (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Design of a pin arresting mechanism for a pyrotechnically actuated pin puller is reviewed. The investigative approach is discussed and the impact shock test results for various candidate designs are presented. The selected pin arresting design reduced the peak value of the shock response spectrum by five to one.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL 10th Aerospace Mech. Symp.; p 71-79
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    On the inclusion principle and spillover effect in the identification of distributed structures (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Distributed structures are Distributed-Parameter Systems (DPS) and must be modeled by large-dimensional systems. Practical limitations require that only a subset of the modes be actively controlled. Control of the residual (uncontrolled) modes is known as control spillover, and it can degrade the system performance. The contamination of the sensor signals by the residual modes is known as observation spillover and it can destabilize the system. An analogous effect exists in the identification problem. Distributed structures must be represented by discretized (finite-dimensional) models or lumped-parameter systems. The contamination of the measurements by the residual (unmodeled) modes is referred to as identification spillover, and it is the object of this study. To study the effects of identification spillover, we use a variational formulation to obtain the natural frequencies and mode shapes. This formulation has direct application to DPS. The identification technique consists of finding the stationary values of a pseudo-Rayleigh quotient.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL, Model Determination for Large Space Systems Workshop, Volume 1; p 72-80
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Analysis of internal ablation for the thermal control of aerospace vehicles (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A new method of thermal protection for transatmospheric vehicles is introduced. The method involves the combination of radiation, ablation and transpiration cooling. By placing an ablating material behind a fixed-shape, porous outer shield, the effectiveness of transpiration cooling is made possible while retaining the simplicity of a passive mechanism. A simplified one-dimensional approach is used to derive the governing equations. Reduction of these equations to non-dimensional form yields two parameters which characterize the thermal protection effectiveness of the shield and ablator combination for a given trajectory. The non-dimensional equations are solved numerically for a sample trajectory corresponding to glide re-entry. Four typical ablators are tested and compared with results obtained by using the thermal properties of water. For the present level of analysis, the numerical computations adequately support the analytical model.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-185919 , NAS 1.26:185919 , JIAA-TR-94
    Format: application/pdf
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  • 5
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    Design of a Mars entry 'aeroshell' (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The external shell of the Project Viking capsule, which will provide atmospheric deceleration for the 1976 landing of an unmanned spacecraft on the surface of Mars, is a wide-angle, stiffened cone subject to buckling under entry aerodynamic pressure. Complex, highly optimized structural prototype and flight designs were evolved through the application of relatively advanced buckling analysis methodology. Both designs were evaluated through tests and analysis with improved shell-of-revolution computer programs. Deviations between the analyses and experiments were resolved only by modeling the thin-walled rings as shell branches. The results illustrate the great complexity of shell behavior and the designer's need for reliable analysis tools capable of representing detailed structural behavior with greater accuracy than is current practice.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Buckling of structures; Jun 17, 1974 - Jun 21, 1974; Cambridge, MA
    Format: text
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