scholarly journals Consensus-Based Attitude Maneuver of Multi-spacecraft with Exclusion Constraints

Space Flight ◽  
2018 ◽  
Author(s):  
Innocent Okoloko
Keyword(s):  
Attitude Maneuver

Robust Control of Flexible Spacecraft During Large-Angle Attitude Maneuver

2014 ◽  
Vol 37 (3) ◽  
pp. 1027-1033 ◽  
Author(s):  
Ya’nan Yu ◽  
Xiuyun Meng ◽  
Keyong Li ◽  
Fenfen Xiong
Keyword(s):  
Robust Control ◽  
Large Angle ◽  
Flexible Spacecraft ◽  
Attitude Maneuver

scholarly journals Dynamic Sliding Mode Controller with Variable Structure for Fast Satellite Attitude Maneuver

2021 ◽  
Vol 2021 ◽  
pp. 1-11
Author(s):  
Gao Shan ◽  
Li You ◽  
Xue Huifeng ◽  
Yao ShuYue
Keyword(s):  
Convergence Rate ◽  
Attitude Control ◽  
Sliding Mode ◽  
Variable Structure ◽  
System Stability ◽  
System State ◽  
Satellite Attitude ◽  
Satellite Attitude Control ◽  
Attitude Maneuver ◽  
Mode Parameter

In order to deal with the low convergence rate of the standard sliding mode in satellite attitude control, a novel variable structure sliding mode is constructed in this paper by designing the update law of the sliding mode parameter. By implementing this method, the advantage such as simple structure and strong robustness of the standard sliding mode are maintained and the system convergence rate is largely improved. The fixed sliding mode parameter is modified, and the update law is designed. When the system state is away from the sliding mode surface, the parameter is fixed, and when the system state approaches the sliding mode surface, the parameter begins to update. The constraint on control torque and angular velocity is taken into consideration, and the constraint on control parameters is given to ensure that the system state do not exceed its upper bound. System stability is proved by the Lyapunov stability theorem, and the superiority of the proposed controller is demonstrated by numerical simulation.

scholarly journals Optimal Factorization of the State-Dependent Riccati Equation Technique in a Satellite Attitude and Orbit Control System

2021 ◽  
Vol 20 ◽  
pp. 98-107
Author(s):  
Alessandro Gerlinger Romero ◽  
Luiz Carlos Gadelha De Souza
Keyword(s):  
Control System ◽  
Riccati Equation ◽  
The State ◽  
Linear Control ◽  
Control Techniques ◽  
Orbit Control ◽  
Satellite Attitude ◽  
Modified Rodrigues Parameters ◽  
State Dependent ◽  
Attitude Maneuver

The satellite attitude and orbit control system (AOCS) can be designed with success by linear control theory if the satellite has slow angular motions and small attitude maneuver. However, for large and fast maneuvers, the linearized models are not able to represent all the perturbations due to the effects of the nonlinear terms present in the dynamics and in the actuators (e.g., saturation). Therefore, in such cases, it is expected that nonlinear control techniques yield better performance than the linear control techniques. One candidate technique for the design of AOCS control law under a large maneuver is the State-Dependent Riccati Equation (SDRE). SDRE entails factorization (that is, parameterization) of the nonlinear dynamics into the state vector and the product of a matrix-valued function that depends on the state itself. In doing so, SDRE brings the nonlinear system to a (nonunique) linear structure having state-dependent coefficient (SDC) matrices and then it minimizes a nonlinear performance index having a quadratic-like structure. The nonuniqueness of the SDC matrices creates extra degrees of freedom, which can be used to enhance controller performance, however, it poses challenges since not all SDC matrices fulfill the SDRE requirements. Moreover, regarding the satellite's kinematics, there is a plethora of options, e.g., Euler angles, Gibbs vector, modified Rodrigues parameters (MRPs), quaternions, etc. Once again, some kinematics formulation of the AOCS do not fulfill the SDRE requirements. In this paper, we evaluate the factorization options (SDC matrices) for the AOCS exploring the requirements of the SDRE technique. Considering a Brazilian National Institute for Space Research (INPE) typical mission, in which the AOCS must stabilize a satellite in three-axis, the application of the SDRE technique equipped with the optimal SDC matrices can yield gains in the missions. The initial results show that MRPs for kinematics provides an optimal SDC matrix.

Dynamic Modeling for a Flexible Spacecraft With Solar Arrays Composed of Honeycomb Panels and Its Proportional–Derivative Control With Input Shaper

2016 ◽  
Vol 138 (8) ◽  
Author(s):  
Lun Liu ◽  
Dengqing Cao
Keyword(s):  
Dynamic Model ◽  
Vibration Suppression ◽  
Hybrid Control ◽  
Flexible Spacecraft ◽  
Solar Array ◽  
Pd Controller ◽  
Pd Control ◽  
Solar Arrays ◽  
Attitude Maneuver ◽  
The One

A high-precision dynamic model of a flexible spacecraft installed with solar arrays, which are composed of honeycomb panels, is established based on the nonconstrained modes of flexible appendages (solar arrays), and an effective cooperative controller is designed for attitude maneuver and vibration suppression by integrating the proportional–derivative (PD) control and input shaping (IS) technique. The governing motion equations of the system and the corresponding boundary conditions are derived by using Hamiltonian Principle. Solving the linearized form of those equations with associated boundaries, the nonconstrained modes of solar arrays are obtained for deriving the discretized dynamic model. Applying this discretized model and combining the IS technique with the PD controller, a hybrid control scheme is designed to achieve the attitude maneuver of the spacecraft and vibration suppression of its flexible solar arrays. The numerical results reveal that the nonconstrained modes of the system are significantly influenced by the spacecraft flexibility and honeycomb panel parameters. Meanwhile, the differences between the nonconstrained modes and the constrained ones are growing as the spacecraft flexibility increases. Compared with the pure PD controller, the one integrating the PD control and IS technique performs much better, because it is more effective for suppressing the oscillation of attitude angular velocity and the vibration of solar array during the attitude maneuver, and reducing the residual vibration after the maneuver process.

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