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  • 1
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    Dynamics and control of a Shuttle-attached antenna experiment (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 8; 344-353
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  • 2
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    Control of large antennas based on electromagnetic performance criteria (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The electromagnetic (EM) performance of large flexible antennas is traditionally achieved by imposing stringent geometric restrictions on the structural distortions from a nominal optimum configuration. An approach to alleviate the stringency of the geometrical criteria of satisfactory performance is presented. The approach consists of generating a linear optimal control problem with quadratic cost functional where the cost functional is obtained from the EM characteristics of the antenna and the dynamic system constraint is given by the structural model of the antenna. It is established that the EM based optimal controller is considerably more efficient than the traditional geometrical based controllers. The same EM performance can be achieved with a much reduced control effort.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Proc. of the Workshop on Identification and Control of Flexible Space Struct., Vol. 1; p 199-227
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  • 3
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    Space station dynamic modeling, disturbance accommodation, and adaptive control (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Dynamic models for two space station configurations were derived. Space shuttle docking disturbances and their effects on the station and solar panels are quantified. It is shown that hard shuttle docking can cause solar panel buckling. Soft docking and berthing can substantially reduce structural loads at the expense of large shuttle and station attitude excursions. It is found predocking shuttle momentum reduction is necessary to achieve safe and routine operations. A direct model reference adaptive control is synthesized and evaluated for the station model parameter errors and plant dynamics truncations. The rigid body and the flexible modes are treated. It is shown that convergence of the adaptive algorithm can be achieved in 100 seconds with reasonable performance even during shuttle hard docking operations in which station mass and inertia are instantaneously changed by more than 100%.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Proc. of the Workshop on Identification and Control of Flexible Space Struct., Vol. 1; p 103-139
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  • 4
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    Space Station dynamic modeling, control and simulation (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Dynamic disturbances of many orders of magnitude greater than those of conventional spacecraft will be routine for the Space Station. Accurate knowledge of inflight structural dynamics and disturbances will be lacking. System identification will reduce uncertainties. To deal with the remaining model errors and time-varying elements, adaptive control may be required. Dynamic models for two Space Station configurations are derived. A direct model reference adaptive control algorithm is synthesized and evaluated with respect to the station model parameter errors and plant dynamics truncations. Both the rigid body and the flexible modes are treated. Simulation results show that convergence of the adaptive algorithm can be achieved in 100 to about 300 seconds with reasonable performance even during Shuttle hard docking operations in which station mass and inertia are instantaneously changed by more than 100 percent.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 5
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    An improved output feedback control of flexible large space structures (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A special output feedback control design technique for flexible large space structures is proposed. It is shown that the technique will increase both the damping and frequency of selected modes for more effective control. It is also able to effect integrated control of elastic and rigid-body modes and, in particular, closed-loop system stability and robustness to modal truncation and parameter variation. The technique is seen as marking an improvement over previous work concerning large space structures output feedback control.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Conference on Decision and Control; Dec 10, 1980 - Dec 12, 1980; Albuquerque, NM
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  • 6
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    Dynamics and control of a Shuttle attached antenna experiment (1983)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Study results obtained to date identify the requirements for a large space system flight experiment. This paper considers the dynamics and control of an offset feed wrap-rib antenna attached to the Shuttle for such an experiment. Results reported in this paper are primarily based on the analysis and simulation of the combined Shuttle and antenna flexible dynamics model, and the Shuttle Vernier Reaction Control Subsystem. These results establish the technical feasibility of the Shuttle attached antenna flight experiment. Static and dynamic disturbances examined do not cause significant dynamic interactions to the experiment. Shuttle Vernier jets can be used for control purpose or as controlled excitation sources for experiment. Interface between the Shuttle and the antenna can be rigid or actively decoupled depending on the experiment objective. Key large space systems control technologies such as distributed sensing and actuation, system identification, figure estimation and control, and control for slew or reconfiguration can be validated with the experiment configuration described in this paper.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-2227 , Guidance and Control Conference; Aug 15, 1983 - Aug 17, 1983; Gatlinburg, TN
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  • 7
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    Dynamics and control simulation of large space structures (1984)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Attention is given to the dynamics and control simulation techniques applicable to large space structures, encompassing the model of the large structure as well as models of its dynamics, its onboard controller, its sensor/actuator systems, and various disturbances to which it may be subjected. Control performance parameters must be computed as functions of time, or of such other design parameters as control gain. A large space antenna is used as an example of the structures in question, illustrating the way in which an efficient dynamics and control simulation structure program can be developed, and how antenna parameters such as reflector surface distortions can be computed, without having to solve a large number of equations for each computation time interval.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Aerospace simulation; Feb 02, 1984 - Feb 04, 1984; San Diego, CA
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  • 8
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    NASA Office of Space Sciences and Applications study on Space Station attached payload pointing (1988)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A study has been conducted to determine the articulated-pointing requirements of a suite of instruments carried by the NASA Space Station, and define a pointing system architecture accomodating those requirements. It is found that these pointing requirements are sufficiently exacting, and the Space Station's disturbance environment sufficiently severe, to preclude the successful use of a conventional gimbal-pointing system; a gimbaled system incorporating an isolation stage is judged capable of furnishing the requisite levels of pointing performance.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 88-4105 , AIAA Guidance, Navigation and Control Conference; Aug 15, 1988 - Aug 17, 1988; Minneapolis, MN; United States
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  • 9
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    On-board estimation technology for space station - Current status and future developments. (1983)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Design considerations and projected solutions to on-board automated estimation techniques for advanced technology controls on a space station are described, with emphasis on the state estimator. The space station is modelled as a collection of rigid and flexible bodies connected at a finite number of hinges. The systems dynamics are characterized by angular velocities of the base body, gimbal angles, and deflections of the flexible appendages. The state estimator evolution is projected to occur in four generations, with the first being control logic in the Viking and Voyager spacecraft, the second in the Shuttle and Galileo probe, the third being large antennas and the prototype space station, the last, around the year 2000, for the actual space station. Considerations for attitude, ephemeris, shape determination, and position estimation through each generation are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS PAPER 83-067 , Guidance and control 1983; Feb 05, 1983 - Feb 09, 1983; Keystone, CO
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