Derived-Rate Increment Stabilization: Its Application to the Attitude Control Problem

1962 ◽  
Vol 84 (1) ◽  
pp. 54-60 ◽  
Author(s):  
J. C. Nicklas ◽  
H. C. Vivian
Keyword(s):  
Control System ◽  
Angular Velocity ◽  
Control Problem ◽  
Limit Cycle ◽  
Attitude Control ◽  
Dead Zone ◽  
The Other ◽  
Feedback Signal ◽  
Attitude Control System ◽  
Jet Actuators

A gyro-free nonlinear attitude control system for a spacecraft is analyzed. On-off jet actuators are used. Hysteresis and a dead zone are intentionally put into the system. Under certain conditions the feedback signal in the control system is proportional to an angular velocity increment of the system. This is called the derived-rate increment feedback signal. The analysis for a single axis of the attitude control system is given in two parts. One part is concerned with the performance of the system in a limit cycle. The other part discusses the convergence to a limit cycle after a disturbance has occurred. Experimental results verify the results of the analysis. Typical results show the performance of the system during convergence to and operation in a limit cycle. Although the technique is described for use in an attitude control system, it can be successfully employed in other applications.

scholarly journals Optimal Sliding Mode Controllers for Attitude Stabilization of Flexible Spacecraft

2011 ◽  
Vol 2011 ◽  
pp. 1-20 ◽  
Author(s):  
Chutiphon Pukdeboon
Keyword(s):  
Optimal Control ◽  
Control System ◽  
Sliding Mode Control ◽  
Control Problem ◽  
Attitude Control ◽  
Sliding Mode ◽  
Flexible Spacecraft ◽  
Attitude Control System ◽  
Control Laws ◽  
Mode Control

The robust optimal attitude control problem for a flexible spacecraft is considered. Two optimal sliding mode control laws that ensure the exponential convergence of the attitude control system are developed. Integral sliding mode control (ISMC) is applied to combine the first-order sliding mode with optimal control and is used to control quaternion-based spacecraft attitude manoeuvres with external disturbances and an uncertainty inertia matrix. For the optimal control part the state-dependent Riccati equation (SDRE) and optimal Lyapunov techniques are employed to solve the infinite-time nonlinear optimal control problem. The second method of Lyapunov is used to guarantee the stability of the attitude control system under the action of the proposed control laws. An example of multiaxial attitude manoeuvres is presented and simulation results are included to verify the usefulness of the developed controllers.

scholarly journals Asymptotic Stability of Quaternion-based Attitude Control System with Saturation Function

2017 ◽  
Vol 7 (4) ◽  
pp. 1994 ◽  
Author(s):  
Harry Septanto ◽  
Djoko Suprijanto
Keyword(s):  
Control System ◽  
Angular Velocity ◽  
Rigid Body ◽  
Attitude Control ◽  
Asymptotically Stable ◽  
Attitude Control System ◽  
Saturation Function ◽  
Continuous Scheme ◽  
Rotational Motions ◽  
The Stability

In the design of attitude control, rotational motion of the spacecraft is usually considered as a rotation of rigid body. Rotation matrix parameterization using quaternion can represent globally attitude of a rigid body rotational motions. However, the representation is not unique hence implies difficulties on the stability guarantee. This paper presents asymptotically stable analysis of a continuous scheme of quaternion-based control system that has saturation function. Simulations run show that the designed system applicable for a zero initial angular velocity case and a non-zero initial angular velocity case due to utilization of deadzone function as an element of the defined constraint in the stability analysis.

scholarly journals PICO-SATELLITE DETUMBLING SIMULATION USING MAGNETIC ATITUDE ACTUATOR (SIMULASI DETUMBLING PADA SATELIT PIKO MENGGUNAKAN AKTUATOR SIKAP MAGNETIK)

2017 ◽  
Vol 15 (1) ◽  
pp. 11 ◽  
Author(s):  
Ali Muksin ◽  
Ridanto Eko Poetro ◽  
Robertus Heru Triharjanto
Keyword(s):  
Magnetic Field ◽  
Control System ◽  
Attitude Control ◽  
The Other ◽  
Local Magnetic Field ◽  
Control Law ◽  
Attitude Control System ◽  
Transient Time ◽  
Matlab Simulink ◽  
The Moment

One of the methods to control Nano/pico-satellite’s attitude is using magneto-torquers as attitude actuators. ITB, at the moment is planning to develop a cubesat. Therefore, the objective of the research was to investigate the performance of such attitude control system for 3U class cubesat. The research used Matlab/simulink-based satellite simulator developed by LAPAN and ITB, and B-dot control law. The advantages of the method are that the actuators are small and lighter compared to the other type of actuators, such as momentum wheels or reaction wheels. However, the disadvantages is that the torques can be created only when the actuator oriented at non-zero angle with local magnetic field. The results showed that the attitude control system could performed the detumbling operation, with the best transient time at about two orbits period. Varying the gain parameter in the controller may result into variation of transient time and even unstability.   AbstrakSalah satu cara untuk mengendalikan sikap satelit nano/piko adalah dengan menggunakan magneto-torquer sebagai aktuator. Saat ini ITB tengah mewacanakan pengembangan cubesat, sehinggga tujuan dari penelitian ini adalah untuk mengevaluasi kinerja sistem kendali sikap berdasarkan medan magnet Bumi pada cubesat kelas 3U. Penelitian ini menggunakan simulator satelit berbasis MATLAB/simulink yang dikembangkan oleh LAPAN dan ITB, moda kendalinya berbasis hukum kendali b-dot. Keuntungan dari sistem kendali ini adalah ukuran dan beratnya yang kecil, dibandingkan dengan moda kendali lain, seperti momentum wheel atau reaction wheel. Sementara kerugiannya adalah hanya bisa menghasilkan torsi saat aktuator mempunyai sudut tidak nol dengan medan magnet Bumi. Hasil menunjukkan bahwa moda kendali tersebut dapat melakukan manuver de-tumbling, dengan waktu transient terbaik mendekati dua periode orbit. Juga ditunjukkan bahwa variasi waktu transient dan ketidakstabilan dapat diperoleh dengan memvariasikan parameter gain pada kontroler. 

Sign in / Sign up

Export Citation Format

Share Document