A semi-active control system and method

Abstract

The invention discloses a semi-active control system and method. The semi-active control system comprises a sensor array, a controller and a driver array, wherein the controller comprises a charge amplifier, a first signal conditioning module, a single chip microcomputer control module, a second signal conditioning module and a high-voltage amplification module; the charge amplifier is connected with the output end of the sensor array, the first signal conditioning module is connected with the output end of the charge amplifier, the single chip microcomputer control module is connected with the output end of the first signal conditioning module, the second signal conditioning module is connected with the output end of the single chip microcomputer control module, the high-voltage amplification module is connected with the output end of the second signal conditioning module, and the driver array is connected with the output end of the high-voltage amplification module. According to thesemi-active control method or method, multi-modal vibration control over a satellite unfolding arm structure can be achieved, the control capacity is improved, the control system is simplified, control time is shortened, the weight and the volume of the control system are reduced, and the requirement of an aerospace structure for vibration control can be better met.

Description

technical field [0001] The invention relates to the technical field of control, in particular to a semi-active control system and method. Background technique [0002] With the continuous development of the aerospace industry, the large-scale, low rigidity and flexibility of spacecraft is an important development trend at present. However, due to the spacecraft's own motion or the complex and changeable outer space environment, the spacecraft with a flexible structure is more likely to generate vibrations than the spacecraft with a rigid structure, and because the damping ratio of a spacecraft with a flexible structure is usually lower, once the vibration occurs , the decay time of the system oscillation is long, which makes the spacecraft unable to work normally for a long time. Therefore, the vibration control of spacecraft becomes more and more important. [0003] At present, the commonly used vibration control methods for spacecraft are passive control and active contr...

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Problems solved by technology

[0003] At present, the commonly used vibration control methods for spacecraft are passive control and active control based on piezoelectric materials. Passive control methods are used to control the vibration of large and flexible spacecraft, which requires external input energy, such as adding vibration isolators and vibration absorbers. Such control devices are not only complicated to control, but also require a long time, the control force is small, and the control effect is not good; while the active control based on piezoelectric materials uses piezoelectric materials as sensors and actuators of the system, by collecting displacement The control voltage generated by the signal is amplified by the power amplifier and loaded onto the piezoelectric material. This control method uses a power amplifier, resulting in a large volume and weight of the control equipment, which is contrary to the needs of the spacecraft.

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