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  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE
  • 1985-1989  (165)
  • 1975-1979  (130)
  • 11
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    Control effectiveness characterization for state estimation and control on a highly flexible grid (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Control effectiveness tests of reaction wheel actuators on a highly flexible grid are reported herein. Analytic determination of actuator control effectiveness is accomplished with finite element modelling. Experimental determination is done with two algorithms. The first is an equation error parameter identification scheme which estimates the control coefficients of the second order difference equation model of each vibration mode. The second is a least square error algorithm using the same model. For both methods there is a lack of agreement with analytic prediction.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 86-2142
    Format: text
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    NASA TECHNICAL REPORTS
  • 12
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    Alternate space station freedom configuration considerations to accommodate solar dynamic power (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of a technical audit of the Space Station Freedom Program conducted by the Program Director was announced in early 1989 and included a proposal to use solar dynamic power generation systems to provide primary electrical energy for orbital flight operations rather than photovoltaic solar array systems. To generate the current program baseline power of 75 kW, two or more solar concentrators approximately 50 feet in diameter would be required to replace four pairs of solar arrays whose rectangular blanket size is approximately 200 feet by 30 feet. The photovoltaic power system concept uses solar arrays to generate electricity that is stored in nickel-hydrogen batteries. The proposed concept uses the solar concentrator dishes to reflect and focus the Sun's energy to heat helium-xenon gas to drive electricity generating turbines. The purpose here is to consider the station configuration issues for incorporation of solar dynamic power system components. Key flight dynamic configuration geometry issues are addressed and an assembly sequence scenario is developed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-101603 , NAS 1.15:101603
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    A small solar electric ion propulsion spacecraft for lunar science (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A lightweight spacecraft design concept has been developed which employs solar-electric ion propulsion to conduct a lunar science mission. The design relies on off-the-shelf technology to achieve high reliability and near-term launch readiness status. Overall project costs are kept to a minimum through the concentration of mission objectives, as well as through the minimization of payload launch costs by resort to the Space Shuttle's Get-Away Special canister. Attention is given to the spacecraft's instrumentation configuration.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 88-2836
    Format: text
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    NASA TECHNICAL REPORTS
  • 14
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    Space Station RT and E Utilization Study (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Descriptive information on a set of 241 mission concepts was reviewed to establish preliminary Space Station outfitting needs for technology development missions. The missions studied covered the full range of in-space technology development activities envisioned for early Space Station operations and included both pressurized volume and attached payload requirements. Equipment needs were compared with outfitting plans for the life sciences and microgravity user communities, and a number of potential outfitting additions were identified. Outfitting implementation was addressed by selecting a strawman mission complement for each of seven technical themes, by organizing the missions into flight scenarios, and by assessing the associated outfitting buildup for planning impacts.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-181707 , NAS 1.26:181707
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 15
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    Vehicle charging on STS-3 Mission (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the Vehicle Charging and Potential experiment on the STS-3 mission, a pulsed electron gun was used to eject known charges and currents from the Shuttle Orbiter, and the resulting perturbations of the surface charge and current densities were studied with appropriate instruments. An ejected current of 100 mA, if maintained for a time sufficiently long for equilibrium to be established, could change the vehicle potential by 50 V or more when the ambient plasma density was low. In general, the observed perturbations could be ordered qualitatively in terms of the plasma density and of the attitude of the shuttle relative to its orbital velocity vector.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Environ. Interactions. Technol., 1983; p 19-32
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 16
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    Lunar Get Away Special (GAS) spacecraft (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A new approach to the resumption of Lunar missions is discussed which relies upon Shuttle Get-Away-Special Canisters for launch and solar electric ion propulsion for slow orbit transfer to low Lunar orbit. The technique of orbit transfer is outlined along with a summary of a mission profile for a first mission which could carry a Gamma Ray Spectrometer. System design constraints are discussed followed by a description of the low mass spacecraft concept which has been developed. Particular emphasis is placed upon describing the small solar electric, xenon ion propulsion system.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 87-1051
    Format: text
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  • 17
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    The dynamics and control of large flexible space structures. Part B: Development of continuum model and computer simulation (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The equations of motion of an arbitrary flexible body in orbit were derived. The model includes the effects of gravity with all its higher harmonics. As a specific example, the motion of a long, slender, uniform beam in circular orbit was modelled. The example considers both the inplane and three dimensional motion of the beam in orbit. In the case of planar motion with only flexible vibrations, the pitch motion is not influenced by the elastic motion of the beam. For large values of the square of the ratio of the structural modal frequency to the orbital angular rate the elastic motion was decoupled from the pitch motion. However, for small values of the ratio and small amplitude pitch motion, the elastic motion was governed by a Hill's 3 term equation. Numerical simulation of the equation indicates the possibilities of instability for very low values of the square of the ratio of the modal frequency to the orbit angular rate. Also numerical simulations of the first order nonlinear equations of motion for a long flexible beam in orbit were performed. The effect of varying the initial conditions and the number of modes was demonstrated.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-156976
    Format: application/pdf
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  • 18
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    Simulation verification techniques study: Simulation performance validation techniques document (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Techniques and support software for the efficient performance of simulation validation are discussed. Overall validation software structure, the performance of validation at various levels of simulation integration, guidelines for check case formulation, methods for real time acquisition and formatting of data from an all up operational simulator, and methods and criteria for comparison and evaluation of simulation data are included. Vehicle subsystems modules, module integration, special test requirements, and reference data formats are also described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-150933 , MDC-E1136
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 19
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    Dynamics of spinning spacecraft during the deployment of flexible boom (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The effect of flexibility on the dynamics of a spinning symmetrical spacecraft during the extension (or retraction) of boom-type appendages is treated by modeling the appendages as compound spherical pendula with varying lengths. Both boom stiffness and structural damping are included. For constant boom length the resulting linearized equations of motion contain periodic coefficients involving the spin frequency. A bounded transformation converts this system into a kinematically equivalent one (with only constant coefficients), whose stability is analyzed using the Kelvin-Tait-Chetaev theorem. The dynamics during extension is predicted by numerical simulation of the nonlinear equations.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-489 , Structures, Structural Dynamics and Materials Conference; Apr 03, 1978 - Apr 05, 1978; Bethesda, MD
    Format: text
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    NASA TECHNICAL REPORTS
  • 20
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    Development and test of two flexible cryogenic heat pipes (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Results are presented for a comprehensive test program directed toward determining the physical and thermal performance of two flexible cryogenic heat pipes that can provide a highly efficient thermal link between a detector and a space radiator or other cooling system in spacecraft applications. A 100-200 K high-power heat pipe is tested with methane at 100-140 K while a 15-100 K low-temperature pipe is designed for operation with nitrogen and oxygen and is optimized for oxygen in the range 75-90 K. Parametric performance and design tradeoff studies are carried out to determine the optimum geometry and materials for the container and wicking systems. A spiral multiwrap wick in conjunction with braided bellows appears to be a workable solution to the problem of developing highly flexible heat transport devices for cryogenic applications.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 76-478 , Thermophysics Conference; Jul 14, 1976 - Jul 16, 1976; San Diego, CA
    Format: text
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