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  • 1985-1989  (6)
  • 1980-1984  (5)
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  • 1
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    New approach to attitude/momentum control for the Space Station (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 12; 714-722
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Postflight evaluation of the Shuttle guidance, navigation, and control during powered-ascent flight phase (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 19, p. 2996, Accession no. A82-38960
    Keywords: SPACE TRANSPORTATION
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 6; 418-423
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Multivariable control of a soft coupled space station (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The paper discusses a multivariate controller design for a control configured space station concept. The space station concept is novel in that mechanical filters (soft couplers) are used to reduce structural interaction between adjacent modules. The primary objective of this study is to provide stability augmentation to the soft coupled configuration. The control objective is achieved by a state feedback compensator design. To obtain the desired feedback gains, a modified LQR technique is developed which provides prescribed close-loop frequencies and damping ratios.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL Proc. of the Workshop on Identification and Control of Flexible Space Struct., Vol. 1; p 37-50
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Digital redesign of an optimal momentum management controller for the Space Station (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A new digital redesign technique is developed for determining the digital version of an optimal momentum management controller previously designed by the authors for the Space Station Freedom. The technique matches all the states at all sampling instants to find a pseudo-continuous time quadratic regulator. It is shown that the redesigned digital states closely match the continuous time optimal states. It is also shown how the redesign technique can be applied to a state estimator.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 89-3474 , AIAA Guidance, Navigation and Control Conference; Aug 14, 1989 - Aug 16, 1989; Boston, MA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Multivariable control of a soft coupled space station (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The paper discusses a multivariable controller design for a control configured space station concept. The space station concept is novel in that mechanical filters (soft couplers) are used to reduce structural interaction between adjacent modules. The primary objective of this study is to provide stability augmentation to the soft coupled configuration. The control objective is achieved by a state feedback compensator design. To obtain the desired feedback gains, a modified LQR technique is developed which provides prescribed close-loop frequencies and damping ratios.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 84-1920
    Format: text
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  • 6
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    Evaluation of the Shuttle GN&C during powered ascent flight phase (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An overview of the ascent trajectory and GN&C (guidance, navigation, and control) system design is followed by a summary of flight test results for the ascent phase of STS-1. The most notable variance from nominal pre-flight predictions was the lofted trajectory observed in first stage due to an unanticipated shift in pitch aerodynamic characteristics from those predicted by wind tunnel tests. The GN&C systems performed as expected on STS-1 throughout powered flight. Following a discussion of the software constants changed for Flight 2 to provide adequate performance margin, a summary of test results from STS-2 and STS-3 is presented. Vehicle trajectory response and GN&C system behavior were very similar to STS-1. Ascent aerodynamic characteristics extracted from the first two test flights were included in the data base used to design the first stage steering and pitch trim profiles for STS-3.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 82-1554 , Guidance and Control Conference; Aug 09, 1982 - Aug 11, 1982; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Computationally efficient algorithm for the dynamics of multi-link mechanisms (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A computationally efficient algorithm for the dynamics of multi-rigid-link mechanisms is presented which is applicable to on-board processing for robotic manipulator control systems. A formulation of the equations of motion for such systems is presented which results in a solution algorithm of the order the number of system degrees of freedom. The formulation is presented for tree topology systems, where the chain topology of typical manipulators is a subset. Comparison of this algorithm is made with existing multibody simulation programs to illustrate the increased computational efficiency.
    Keywords: CYBERNETICS
    Type: AIAA PAPER 89-3527 , AIAA Guidance, Navigation and Control Conference; Aug 14, 1989 - Aug 16, 1989; Boston, MA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    A new momentum management controller for the Space Station (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A new approach to CMG (control moment gyro) momentum management and attitude control of the Space Station is developed. The control algorithm utilizes both the gravity-gradient and gyroscopic torques to seek torque equilibrium attitude in the presence of secular and cyclic disturbances. Depending upon mission requirements, either pitch attitude or pitch-axis CMG momentum can be held constant; yaw attitude and roll-axis CMG momentum can be held constant, while roll attitude and yaw-axis CMG momentum cannot be held constant. As a result, the overall attitude and CMG momentum oscillations caused by cyclic aero-dynamic disturbances are minimized. A state feedback controller with minimal computer storage requirement for gain scheduling is also developed. The overall closed-loop system is stable for + or - 30 percent inertia matrix variations and has more than + or - 10 dB and 45 deg stability margins in each loop.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 88-4132 , AIAA Guidance, Navigation and Control Conference; Aug 15, 1988 - Aug 17, 1988; Minneapolis, MN; United States
    Format: text
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  • 9
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    Attitude control and stability of a Space Station (1983)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Certain problems arise in connection with the design and construction of a Space Station. These problems are partly related to the impossibility to predict in advance the ultimate form and size which the Space Station will assume. Due to the abatement of volume and strength constraints it will be desirable (for maximum utility of mass) to permit very low structural resonance frequencies, and due to complexity of the configuration there will be an extremely high density of modal frequencies. The basic approaches available to an attitude control system designer for coping with the dynamics of a plant with the considered characteristics are examined. In order to overcome difficulties related to a use of currently widely considered approaches, a technique is proposed whereby the degrees of freedom requiring active control are isolated mechanically from other superfluous vibratory modes.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS PAPER 83-065 , Guidance and control 1983; Feb 05, 1983 - Feb 09, 1983; Keystone, CO
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    An optimal momentum management controller for the Space Station (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper presents a new sequential design procedure for determining an optimal CMG (control moment gyro) momentum management and attitude control system for the Space Station Freedom. First, the Space Station equations of motion are linearized and uncoupled, and the associated state space equations are defined. Next, a new sequential procedure is used for the development of a continuous quadratic regulator with eigenvalue placement in a specified region of the complex plane. The regional pole assignment method is utilized since it is best suited for tradeoffs between eigenvalue locations and robustness with respect to parameter variations, sensor failures, implementation accuracies and gain reductions. The matrix sign function is used for solving the Riccati equations which appear in the design procedure. Simulation results are given which show that the resultant design provides desired system performance.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 89-3473 , AIAA Guidance, Navigation and Control Conference; Aug 14, 1989 - Aug 16, 1989; Boston, MA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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