Large angle attitude control of spacecraft with actuator saturation

Bang, Hyochoong; Tahk, Min-Jea; Choi, Hyung-Don

doi:10.1016/s0967-0661(02)00216-2

Cited by 99 publications

(59 citation statements)

References 9 publications

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“…As discussed in [7,8] input saturation can severely degrade closed-loop system performance or even in some cases cause system instability if they are not carefully tackled in attitude control process. Because of this, many researchers have focused on input saturation in attitude controller design of spacecraft [9][10][11][12][13]. In [12], neural network was used to estimate the unknown input saturation and then the effect of input saturation was compensated by inserting the saturation compensator into the feed-forward loop of the system.…”

Section: Introductionmentioning

confidence: 99%

Fault-Tolerant Attitude Control for Flexible Spacecraft with Input Saturation

Long¹,

Zhao²

2017

IRATJ

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Fault-tolerant constrained attitude controllers are proposed for flexible spacecraft in the presence of input saturation and actuator fault, as well as model uncertainty and external disturbance. Two input saturations, that is amplitude saturation and, amplitude and rate saturation are considered and simple and effective compensators are designed to deal with the effect of input saturation. Two parameter update laws are designed to endure stuck fault, partial and complete loss of effectiveness fault. The stability of the resulting closed-loop systems by the proposed controllers is guaranteed by Lyapunov-based approach. The effectiveness of the proposed algorithms is assessed through numerical simulations.

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Section: Introductionmentioning

confidence: 99%

Fault-Tolerant Attitude Control for Flexible Spacecraft with Input Saturation

Long¹,

Zhao²

2017

IRATJ

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“…There are plenty of attitude control methods applied to the space robot. From PD, PID control [13,14], optimal control [15], adaptive control [16,17] to robust control [18], they all have received good control results. But the dynamic model of the space robot system is multivariable strong coupling and nonlinear.…”

Section: Introductionmentioning

confidence: 99%

Attitude control for astronaut assisted robot in the space station

Liu

Gao

Liu

et al. 2016

Int. J. Control Autom. Syst.

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Because of the limited working hours of astronauts in the space station, the in-cabin robot has high value in the technological validation and scientific research. Based on this requirement, we proposed and designed an Astronaut Assisted Robot(AAR) working in the space station. It can float in the space station cabin, fly autonomously, and hold a fixed position and/or posture. In addition, it also possesses environmental awareness capabilities and intelligence. Thus the AAR can assist astronauts to complete some special scientific experiments or technical tests. In this paper, the system architecture and experimental equipment of the AAR are designed firstly depending on the characteristics of space microgravity environment and the requirements of assisting astronauts missions. And then, the motion principles of the AAR are analyzed and the robot's dynamic model is established by using the Newton -Euler algorithm. Since the attitude control of the robot is the basis for its free movement, the PID Neural Network(PIDNN) algorithm, which is a kind of intelligent control algorithm, is used to design the attitude controller of the AAR. Finally, the reasonability of the robot's structural design and the availability of its attitude controllers are verified through the simulation experiments.

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“…An attitude control of satellite with considering fast maneuvers and saturation constraint has been presented in [3], but reaction wheels and their effects on control performance have not been considered in this reference. In [4], attitude control of a satellite with imagery mission by three-axis stabilization zero momentum method has been discussed.…”

Section: Introductionmentioning

confidence: 99%

Sliding Mode Active Vibration Control and Three Axis Attitude Control using Four Reaction Wheels

Saberi¹,

Khalajian²,

Mani³

2016

IJCA

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The most important problems in satellites are their energy supply and decreasing weight. One of the solutions is using flexible appendages. Flexibility can supply both energy and weight loss in satellites. Also other appendages like antennas and mechanical arms can be flexible. But flexibility can produce some vibrations. These vibrations cause complexity attitude control systems due to flexible appendages.In this paper, the attitude control of flexible satellite by using four reaction wheels in presence of gravity gradient and orbit frequency has been considered. The dynamic of flexible appendages have been derived from energy equations and Lagrange method. Also, momentum management and minimization of the momentum have been employed to avoid of reaction wheels saturation. Then, the control command law using the quaternion error vector for attitude control of rigid body and sliding mode control (SMC) for active suppuration of flexible appendages have been used. Finally the performance of control system between presence and absence of reaction wheels has been compared.

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Large angle attitude control of spacecraft with actuator saturation

Cited by 99 publications

References 9 publications

Fault-Tolerant Attitude Control for Flexible Spacecraft with Input Saturation

Fault-Tolerant Attitude Control for Flexible Spacecraft with Input Saturation

Attitude control for astronaut assisted robot in the space station

Sliding Mode Active Vibration Control and Three Axis Attitude Control using Four Reaction Wheels

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