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  • 1985-1989  (6)
  • 1
    Electronic Resource
    Electronic Resource
    Automated derivation of optimal regulators for nonlinear systems by symbolic manipulation of Poisson series (1985)
    Springer
    Journal of optimization theory and applications 45 (1985), S. 443-476 
    Details
    ISSN: 1573-2878
    Keywords: Optimal control theory ; perturbation methods ; Lie series ; Poisson series
    Source: Springer Online Journal Archives 1860-2000
    Topics: Mathematics
    Notes: Abstract Concepts of programmability and compact programmability are defined relative to a class of modified Poisson series. Lie-series-based canonical perturbation methods from astrodynamics are applied to the Hamiltonian system boundary-value problem, and more usual methods are applied to the perturbed Hamilton-Jacobi-Bellman partial differential equation, in order to obtain a complete set of equations for the perturbed optimal feedback control law for both infinite-time and finite-time regulator problems. The relative advantages of each approach are evaluated. A major aim of the paper is to determine the largest class of perturbations, within the set of Poisson series, for which the equations can be derived on a computer by symbolic manipulation. The more general the class, the more accurate the perturbation solution can be, for a given order. The solutions developed are complete; all that remains is to program them in order to have computerized derivations of the optimal nonlinear feedback control laws.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00938446
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Automated derivation of optimal regulators for nonlinear systems by symbolic manipulation of Poisson series (1985)
    Springer
    Details
    Publication Date: 1985-03-01
    Print ISSN: 0022-3239
    Electronic ISSN: 1573-2878
    Topics: Mathematics
    Published by Springer
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    PAPER CURRENT
  • 3
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    Dynamics During Thrust Maneuvers of Flexible Spinning Satellites with Axial and Radial Booms (1986)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: The dynamic response to operational maneuvers of spinning symmetric spacecraft with radial and axial booms was analyzed as part of the prelaunch dynamic analysis of the ISEE-3 spacecraft placed in a halo orbit around an Earth-Sun libration point, and later renamed ICE when it was directed to fly-by comet Giacobini-Zinner. The results presented use simple spacecraft models, and frequently give predictions that are good and easily obtained when the results from using a general purpose multibody dynamics program were very time consuming to obtain. Deployment of radial booms, spin-up after partial deployment, stationkeeping, and trajectory changes are analyzed. The latter two can involve both axial thrusting and pulsed radial thrusting once per revolution.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ESA Proceedings of the Second International Symposium on Spacecraft Flight Dynamics; p 13-18
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Identifiability of conservative linear mechanical systems (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: With a sufficiently great number of sensors and actuators, any finite dimensional dynamic system is identifiable on the basis of input-output data. It is presently indicated that, for conservative nongyroscopic linear mechanical systems, the number of sensors and actuators required for identifiability is very large, where 'identifiability' is understood as a unique determination of the mass and stiffness matrices. The required number of sensors and actuators drops by a factor of two, given a relaxation of the identifiability criterion so that identification can fail only if the system parameters being identified lie in a set of measure zero. When the mass matrix is known a priori, this additional information does not significantly affect the requirements for guaranteed identifiability, though the number of parameters to be determined is reduced by a factor of two.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of the Astronautical Sciences (ISSN 0021-9142); 33; 95-118
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Actuator placement by degree of controllability including the effect of actuator mass (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Various concepts of the degree of controllability (DOC) have been previously developed for the purpose of choosing actuator locations in the control of large flexible spacecraft. A perturbation technique is presented to efficiently account for the actuator mass in the computation of the fuel-optimal, time-optimal, and energy-optimal DOC definitions. Methods are developed for computing each of the three DOCs, when the mass of the actuator is nonnegligible. The energy-optimal DOC is employed to find optimal actuator locations for a large spacecraft under study by the NASA Langley Research Center. The mass of the actuator is seen to have a significant effect on the optimal actuator locations and is shown to spread the actuator locations more evenly for large mass actuators. Results indicate that when the actuator mass is large when compared to the structural mass it should be included in selecting actuator locations.
    Keywords: CYBERNETICS
    Type: VPI&SU Symposium; May 08, 1989 - May 10, 1989; Blacksburg, VA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Learning control for slewing of a flexible panel (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper studies the applicability of a discrete-time learning control method to the slewing control of a large flexible panel. Among the issues discussed are feasibility of the desired trajectories and their specification schemes, learning control by linear feedback, limitation of the actuator device output, and robustness to parameter changes or modeling errors associated with the chosen learning control design. To demonstrate the effectiveness of learning control, the system is designed with a proportional controller of the base angle only. Then application of the learning control is shown to make the system learn quickly to achieve the desired slewing without residual vibration at the end of the maneuver. Simulation results are reported and discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: VPI&SU Symposium; May 08, 1989 - May 10, 1989; Blacksburg, VA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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