Rigid-Flexible Coupling Dynamic Modeling and Vibration Control for a Three-Axis Stabilized Spacecraft

Abstract

An approach is proposed to obtain the global analytical modes (GAMs) and establish discrete dynamic model with low degree-of-freedom for a three-axis attitude stabilized spacecraft installed with a pair of solar arrays. The flexible spacecraft is simplified as a hub–plate system which is a typical rigid-flexible coupling system. The governing equations of motion and the corresponding boundary conditions are derived by using the Hamiltonian principle. Describing the rigid motion and elastic vibration of all the system components with a uniform set of generalized coordinates, the system GAMs are solved from those dynamic equations and boundary conditions, which are used to discretize the equations of motion. For comparison, another discrete model is also derived using assumed mode method (AMM). Using ansys software, a finite element model is established to verify the GAM and AMM models. Subsequently, the system global modes are investigated using the GAM approach. Further, the performance of GAM model in dynamic analysis and cooperative control for attitude motion and solar panel vibration is assessed by comparing with AMM model. The discrete dynamic model based on GAMs has the capability to carry out spacecraft dynamic analysis in the same accuracy as a high-dimensional AMM model. The controller based on GAM model can suppress the oscillation of solar panels and make the control torque stable in much shorter time.

Observer-based multi-objective parametric design for spacecraft with super flexible netted antennas

“…(1) Different from many existing control methods that is proposed for a single objective (e.g., [2][3][4][5][6][7][8], [11][12][13][14][15][16][17][18][19][20][21]), this paper considers multi-objective design issues, and it aims to make the closed-loop system have simultaneously lower eigenvalue sensitivity, and also it aims a smaller control gain and a stronger tolerance for high-order unmodeled dynamics and disturbances.…”

“…Theorem 3. Suppose that A c and A o are given by (13), where A depends on perturbations ∆a 1 and ∆a 2 , as described in (8) and (9). Let the relation (42) hold, and Constraints C1 and C2 be met.…”

“…For example, in 1958 the satellite named "Explorer-1" caused the energy dissipation in the system owing to the flexible vibration of the four whip antennas that eventually led to the attitude roll [1]. Therefore, vibration suppression and attitude control of spacecraft with large flexible attachments is a critical problem and it has received lots of attention [2][3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19][20][21]. Sliding mode control (SMC) and backstepping control are commonly used control methods in order to solve this problem.…”

“…The problems of robust H ∞ controller design with input constraints are considered in [11,12]. In addition to SMC, backstepping, and robust H ∞ control, many other control methods are also applied to the vibration suppression and attitude control of flexible satellites, such as disturbance observer-based control [13][14][15], adaptive control [16][17][18][19][20], and finite-time control [16,18,21]. Many of the current control methods are proposed for a single control target (e.g., [2][3][4][5][6][7][8][11][12][13][14][15][16][17][18][19][20][21]) to provide flexible spacecraft control.…”

Nonlinear dynamic modeling and decoupling for rigid–flexible coupled system of spacecraft with rapid maneuver

“…The GMM overcomes the shortcomings of poor precision in the improper selection of the assumed modal functions, and has a lower dimension than FEM. 23 In fact, for dynamics of rigid–flexible coupled systems, both GMM and FEM can describe the dynamic behavior accurately while GMM is more convenient for the control design.…”