Abstract
In order to achieve the attitude maneuver performance of the noncontact close-proximity formation satellite architecture, this paper presents a compound control strategy with variable-parameter sliding mode control and disturbance observer-based feedforward compensation. Firstly, the variable-parameter sliding mode control is proposed to guarantee the attitude maneuver performance of the payload module. Secondly, the collision avoiding control with disturbance observer-based feedforward compensation is proposed to guarantee the synchronization of the two separated modules within the small air clearance constraint of the noncontact Lorentz actuator. Finally, a physical air-floating platform is established to verify the effectiveness of the proposed approach.
Highlights
With the development of the space camera technology, highresolution imaging under attitude maneuver has been focused on recently [1,2,3]
Where hs = Jsωs + hc represents the total angular momentum of the service module; Js represents the inertia tensor of the service module; ωs represents the angular velocity vector of the service module; hc represents the angular momentum of the control moment gyroscopes mounted on the service module; ωs represents the angular velocity vector; Cai and qai (i = 1, 2) represent the coupling matrix and modes of the solar panels, as shown in Equations (7) and (8); Tcs represents the control torque of the control moment gyroscopes; Tns represents the sum of the external disturbance torque to the service module; and Tps represents the reaction torque of the noncontact Lorentz actuators to the service module, as shown in Equation (9)
The variable-parameter sliding mode control algorithm is adopted to guarantee the active attitude maneuver control for payload module, while the disturbance observer-based feedforward compensation is adopted to guarantee the cooperative synchronization for service module within the small air clearance constraint
Summary
With the development of the space camera technology, highresolution imaging under attitude maneuver has been focused on recently [1,2,3]. In view of the application, the noncontact architecture design demonstrates the structure separating and inertia tensor separating, indicating that the attitude maneuver operation can be realized through two-echelon stratification It is more difficult than stability control due to its close-proximity formation characteristics. (1) Compared with the previous researches on the noncontact close-proximity formation satellite in [19,20,21,22,23,24], this paper extends its advantage into the attitude maneuver operation by using compound control strategy (2) Compared with the 1R-DOF ground test system established in [14], the physical air-floating platform with full 3R-DOF can effectively verify the overall performance of the noncontact close-proximity formation satellite with multidynamics.
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