Adaptive control applied to Space Station attitude control system

1992 ◽  
Author(s):  
QUANG LAM ◽  
RICHARD CHIPMAN ◽  
TSAY-HSIN HU ◽  
ERIC HOLMES ◽  
JOHN SUNKEL
Keyword(s):  
Adaptive Control ◽  
Control System ◽  
Attitude Control ◽  
Space Station ◽  
Attitude Control System

Adaptive control of free-flying space robot with position/attitude control system

1997 ◽  
Author(s):  
Kei Senda ◽  
Hideyuki Nagaoka ◽  
Yoshisada Murotsu ◽  
Kei Senda ◽  
Hideyuki Nagaoka ◽  
...  
Keyword(s):  
Adaptive Control ◽  
Control System ◽  
Attitude Control ◽  
Space Robot ◽  
Attitude Control System

Space Station RCS attitude control system

1991 ◽  
Author(s):  
STEVEN LEE ◽  
REINHOLD MATULENKO ◽  
J. CALDWELL
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Space Station ◽  
Attitude Control System

scholarly journals Design of Attitude Control System for UAV Based on Feedback Linearization and Adaptive Control

2014 ◽  
Vol 2014 ◽  
pp. 1-8 ◽  
Author(s):  
Wenya Zhou ◽  
Kuilong Yin ◽  
Rui Wang ◽  
Yue-E Wang
Keyword(s):  
Adaptive Control ◽  
Control System ◽  
Attitude Control ◽  
Feedback Linearization ◽  
Control Law ◽  
Attitude Control System ◽  
Model Uncertainties ◽  
Performance Indexes ◽  
Attitude Dynamic ◽  
Adaptive Control Law

Attitude dynamic model of unmanned aerial vehicles (UAVs) is multi-input multioutput (MIMO), strong coupling, and nonlinear. Model uncertainties and external gust disturbances should be considered during designing the attitude control system for UAVs. In this paper, feedback linearization and model reference adaptive control (MRAC) are integrated to design the attitude control system for a fixed wing UAV. First of all, the complicated attitude dynamic model is decoupled into three single-input single-output (SISO) channels by input-output feedback linearization. Secondly, the reference models are determined, respectively, according to the performance indexes of each channel. Subsequently, the adaptive control law is obtained using MRAC theory. In order to demonstrate the performance of attitude control system, the adaptive control law and the proportional-integral-derivative (PID) control law are, respectively, used in the coupling nonlinear simulation model. Simulation results indicate that the system performance indexes including maximum overshoot, settling time (2% error range), and rise time obtained by MRAC are better than those by PID. Moreover, MRAC system has stronger robustness with respect to the model uncertainties and gust disturbance.

Adaptive Control of Free-Flying Space Robot with Position/Attitude Control System

1999 ◽  
Vol 22 (3) ◽  
pp. 488-490 ◽  
Author(s):  
Kei Senda ◽  
Hideyuki Nagoaka ◽  
Yoshisada Murotsu
Keyword(s):  
Adaptive Control ◽  
Control System ◽  
Attitude Control ◽  
Space Robot ◽  
Attitude Control System

scholarly journals Waypoint following dynamics of a quaternion error feedback attitude control system

2021 ◽  
pp. 095441002110109
Author(s):  
Mark Karpenko ◽  
Julie K. Halverson ◽  
Rebecca Besser
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Angular Rate ◽  
Space Station ◽  
Reference Trajectory ◽  
Error Feedback ◽  
Attitude Control System ◽  
Attitude Tracking ◽  
Lunar Reconnaissance Orbiter ◽  
Z Domain

Closed-loop attitude steering is a concept for implementing an attitude trajectory by using a conventional quaternion error feedback controller to track the time-varying attitude reference, rather than to simply regulate to a desired orientation. This is done by sampling the reference input and executing the maneuver as a sequence of closely spaced regulating commands that are read out from the spacecraft’s command buffer. The idea has been employed in practice to perform zero-propellant maneuvers on the International Space Station and minimum-time maneuvers on NASA’s TRACE space telescope as well as NASA’s Lunar Reconnaissance Orbiter (LRO). A challenge for operational implementation of the idea is the limited capacity of a space vehicle’s command storage buffer, which is normally not designed with attitude tracking in mind. One approach to mitigate the problem is to downsample-and-hold the attitude commands so that the attitude control system (ACS) regulates to a series of waypoints. This article explores the waypoint following dynamics of a quaternion error feedback control law for such an approach. It is shown that downsample-and-hold induces a ripple between downsamples that causes the satellite angular rate to significantly overshoot the desired limit. Analysis in the z-domain is carried out in order to understand the phenomenon. An interpolating Chebyshev-type filter is proposed that allows the desired attitude trajectory to alternatively be encoded in terms of a small set of filter coefficients. Using the interpolating filter, the continuous-time reference trajectory can be reconstructed and issued at the ACS rate but with significantly reduced memory requirements. The ACS of the LRO is used as an example to illustrate the behavior of a practical ACS.

Attitude Stabilization and Control for a Manned Space Station

1984 ◽  
Vol 106 (4) ◽  
pp. 310-312
Author(s):  
A. R. Stubberud
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Space Station ◽  
Modular Construction ◽  
Attitude Control System ◽  
Flexible Control ◽  
Starting Point ◽  
Manned Space ◽  
The Individual ◽  
And Control

The present planning for the construction of a manned space station calls for modular construction in space over a period of several years with each module having different dynamic characteristics and attitude control requirements. Several of the modules will be best modeled as distributed (flexible) bodies. It is necessary that the attitude control system be capable of providing appropriate attitude control to a suitable accuracy for the individual modules at all times during the construction. This plus the extreme flexibility pose far more difficult problems to the attitude control designer than in previous spacecraft. In spite of this, the author believes that the design techniques for past spacecraft will be used as the starting point for the attitude control system of the space station. The new theories for flexible control systems will probably be used in computer simulations for preflight validation of the control system design. Substantial improvements in the attitude control will more than likely come from new mechanical designs for actuators, intersections between modules, and passive dampers.

scholarly journals Using of H-Infinity Control Method in Attitude Control System of Rigid-Flexible Satellite

2009 ◽  
Vol 2009 ◽  
pp. 1-9 ◽  
Author(s):  
Ximena Celia Méndez Cubillos ◽  
Luiz Carlos Gadelha de Souza
Keyword(s):  
Adaptive Control ◽  
Control System ◽  
Control Systems ◽  
Attitude Control ◽  
Control Method ◽  
Control Design ◽  
Attitude Control System ◽  
H Infinity ◽  
H Infinity Control ◽  
Linear And Nonlinear

The attitude control systems of satellites with rigid and flexible components are demanding more and more better performance resulting in the development of several methods control. For that reason, control design methods presently available, including parameters and states estimation, robust and adaptive control, as well as linear and nonlinear theory, need more investigation to know their capability and limitations. In this paper the investigated technique is H-Infinity method in the performance of the Attitude Control System of a Rigid-Flexible Satellite.

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