Binary intelligent structure control device of satellite flexible vibration

Abstract

The invention relates to a binary intelligent structure control device and method of satellite flexible vibration. The control device comprises a plurality of piezoelectric sensors, a plurality of SMA (Shape Memory Alloy) wires and a controller, wherein the plurality of piezoelectric sensors transmit a voltage sensed through a cable to the controller which converts the voltage into a control current of the SMA wires, the control current is transmitted to the plurality of piezoelectric sensors through the cable, and the SMA wires are controlled to generate tension to control satellite flexiblevibration. By adopting PZT (Piezoceramics) as a stress measuring sensor and using the SMA as an actuating mechanism, the respective advantages of the two intelligent materials are exerted and the defects of the two intelligent materials, i.e. the PZT as a sensor has the characteristic of high sensitivity but has less driving force as a driver without being arranged in a gemel position, and the like (or else the extension of a sailboard is influenced) are avoided; and the SMA as the driver has the greater driving force than the PZT and can be folded without influencing the extension and the locking of the sailboard.

Description

technical field [0001] The invention relates to an intelligent control device and a control method for flexible vibration on a star, in particular to a binary intelligent structure control device and a control method, belonging to the technical field of high-precision and high-stability attitude control of spacecraft. Background technique [0002] Large and complex satellites, such as those represented by 0.1m very high-resolution earth observation and 1:10000 three-dimensional mapping, are multi-functional, high-performance large-scale systems. These complex satellites often present a typical large-scale multi-body flexible space structure, which is mainly manifested in the following aspects: multi-function and high performance require an increasing proportion of payloads, and public cabins such as central structures, antennas, and solar panels must be lightweight, so It must be used as a flexible multi-body structure satellite. On the other hand, these complex satellites ...

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Problems solved by technology

[0004] If conventional intelligent materials (such as piezoelectric sheets) are used for active vibration control, the following problems will also be encountered: First, this type of solar wing is composed of a base plate and a hinge, and the vibration deformation generated by the hinge is larger than that of the base plate; while the traditional Piezoelectric sheets can only be pasted on the substrate, so using piezoelectric sheets alone as actuators has poor control effects; second, when using piezoelectric sheets as actuators, it is often necessary to arrange more piezoelectric sheets on the solar wing Electrodes, corresponding signal lines and power lines are all distributed on the solar wing and transmit signals through the SADA slip ring. The cumbersome wiring may affect the deployment and normal operation of the solar wing; thirdly, for relatively large vibrations of the solar wing, The driving force of the piezoelectric actuator appears to be insufficient

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