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  • 1
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    Impact of atmospheric density scale height on the performance of aeroassisted coplanar orbital transfer vehicles (1987)
    In:  CASI
    Details
    Publication Date: 2004-10-02
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Old Dominion Univ., Guidance and Control Strategies for Aerospace Vehicles; 14 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    On the method of matched asymptotic expansions (1987)
    In:  CASI
    Details
    Publication Date: 2004-10-02
    Keywords: NUMERICAL ANALYSIS
    Type: Old Dominion Univ., Guidance and Control Strategies for Aerospace Vehicles; 14 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    The Coherent Launchsite Wind Sounder (CLAWS) (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: This talk will provide a description of the Coherent Launchsite Wind Sounder (CLAWS) program for the development of a near real-time launchsite wind measurement system. The CLAWS program was motivated by the need to have wind measurements for spacecraft launch systems that are more timely than those from balloons. and that measure the winds along the booster's flight path. This program went from conceptual development to the testing of a breadboard system at KSC in concert with the launch of STS-48 in September of 1991. The system demonstrated the capability to measure the wind field, that a launch vehicle will traverse, from ground level to an altitude of 26 Km in approximately six minutes. The presentation will cover the concept, the hardware and the algorithms required, the test program and some results from the CLAWS system.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: (ISSN 0065-3438); sic Space Science; U
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    NASA TECHNICAL REPORTS
  • 4
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    An integrated controls-structures design methodology for a flexible spacecraft (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper proposes an approach for the design of flexible spacecraft, wherein the structural design and the control system design are performed simultaneously. The integrated design problem is posed as an optimization problem in which both the structural parameters and the control system parameters constitute the design variables, which are used to optimize a common objective function, thereby resulting in an optimal overall design. The approach is demonstrated by application to the integrated design of a geostationary platform, and to a ground-based flexible structure experiment. The numerical results obtained indicate that the integrated design approach generally yields spacecraft designs that are substantially superior compared to the conventional approach, wherein the structural design and control design are performed sequentially.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS PAPER 92-060 , In: Guidance and control 1992; Proceedings of the 15th Annual AAS Rocky Mountain Conference, Keystone, CO, Feb. 8-12, 1992 (A93-50576 21-18); p. 369-385.
    Format: text
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  • 5
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    Technology development program for twenty-first century aerospace vehicles (1987)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A program to meet the avionics technology needs for the design of future space transportation systems is presented. The program is designed to meet as many technology goals as possible by 1996 so decisions can be made as to which vehicles are feasible and which should be constructed.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: AGARD, The Design, Development and Testing of Complex Avionics Systems; 6 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Singular perturbations and time scales in the design of digital flight control systems (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results are presented of application of the methodology of Singular Perturbations and Time Scales (SPATS) to the control of digital flight systems. A block diagonalization method is described to decouple a full order, two time (slow and fast) scale, discrete control system into reduced order slow and fast subsystems. Basic properties and numerical aspects of the method are discussed. A composite, closed-loop, suboptimal control system is constructed as the sum of the slow and fast optimal feedback controls. The application of this technique to an aircraft model shows close agreement between the exact solutions and the decoupled (or composite) solutions. The main advantage of the method is the considerable reduction in the overall computational requirements for the evaluation of optimal guidance and control laws. The significance of the results is that it can be used for real time, onboard simulation. A brief survey is also presented of digital flight systems.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-2844 , L-16440 , NAS 1.60:2844
    Format: application/pdf
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  • 7
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    Adaptive guidance for an aero-assisted boost vehicle (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Keywords: SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 13; 586-595
    Format: text
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  • 8
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    Adaptive guidance for an aero-assisted boost vehicle (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An adaptive guidance system incorporating dynamic pressure constraint is studied for a single stage to low earth orbit (LEO) aero-assist booster with thrust gimbal angle as the control variable. To derive an adaptive guidance law, cubic spline functions are used to represent the ascent profile. The booster flight to LEO is divided into initial and terminal phases. In the initial phase, the ascent profile is continuously updated to maximize the performance of the boost vehicle enroute. A linear feedback control is used in the terminal phase to guide the aero-assisted booster onto the desired LEO. The computer simulation of the vehicle dynamics considers a rotating spherical earth, inverse square (Newtonian) gravity field and an exponential model for the earth's atmospheric density. This adaptive guidance algorithm is capable of handling large deviations in both atmospheric conditions and modeling uncertainties, while ensuring maximum booster performance.
    Keywords: SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING
    Type: AIAA PAPER 88-4173 , AIAA Guidance, Navigation and Control Conference; Aug 15, 1988 - Aug 17, 1988; Minneapolis, MN; United States
    Format: text
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