Tether retracting and switching control system for space object towing, and method thereof

Abstract

Embodiments of the present application provide a tether retracting and switching control system for space object towing. The system comprises: a control module, wherein the control module comprises adigital signal processing DSP unit, a field programmable gate array FPGA unit, a 1553B communication circuit and an RS422 communication circuit, the DSP unit is configured to adopt a control strategycorresponding to an instruction signal according to the instruction signal received by an interface module, and output a control signal to a driving module, and the DSP unit is further configured to perform data communication with the communication circuits; the interface module, wherein the interface module is configured to receive the instruction signal, and perform collection and processing onsensor signals according to the instruction information; a rotary transformer signal collection module, wherein the rotary transformer signal collection module is configured to perform signal collection and processing on a rotary transformer at the motor end and on a buffer mechanism rotary transformer; the driving module, wherein the driving module is configured to perform driving on at least thefollowing motors: a tether winding motor, a tether pinch motor, a motor brake, a tether clamping cutting motor, and a tether connection motor; and a power source, wherein the power source is configured to connect the various modules, and provide secondary power to the circuits of the various modules.

Description

technical field [0001] The present application relates to the technical field of a space vehicle towing a target, in particular to a tether retraction and switching control system and a method thereof for space target towing. Background technique [0002] In order to meet the needs of non-cooperative target towing tasks such as malfunctioning spacecraft and space debris, it is necessary to use flexible structures such as nets or cloth to cover and wrap the target, and form a combination of reliable connections with the mission spacecraft through flexible tethers, and capture The target is dragged to the predetermined track. During the target towing process, the retractable control of the tether has an important impact on the attitude stability of the aircraft, and is a key technology for the aircraft tow in orbit. After the target towing task is completed, it is necessary to switch the tether and reconnect another rope net to prepare for the next towing task. [0003] The ...

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Problems solved by technology

[0004] (1) Tethers used in space towing tasks have the characteristics of light weight, small damping, high tensile strength, high (low) temperature resistance, light weight, and good flexibility, but they also have creep, nonlinear stiffness, and damping , plastic deformation, hysteresis effect and other phenomena, it is difficult for traditional control algorithms to adapt to time-varying and nonlinear systems;

[0005] (2) During the tether tension and speed control process, the change of coil diameter and acceleration and deceleration of the retractable mechanism, the no-load torque, torque ripple, and speed ripple of the motor, the friction torque and gap of the mechanism, and external interference , will affect the control accuracy of tension and speed, and cannot meet the control requirements of small tension and low speed of the tether;

[0006] (3) During the towing process of the space target, when failures such as mechanism failure, tether sticking or entanglement occur, the failure judgment cannot be made on the ground, and effective solutions cannot be taken for the failure mode, resulting in mission failure

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