Straight acting device for spacecraft based on SMA (Shape Memory Alloy) spring and use method thereof

Abstract

The invention discloses a straight acting device for a spacecraft based on an SMA (Shape Memory Alloy) spring and a use method thereof. The straight acting device for the spacecraft based on the SMA spring comprises a piston jacking rod, an upper end cover, a limiting spring, a sleeve, the SMA spring, a heater resistance wire, an electric heater, a soft outgoing line and an electric connector, wherein the sleeve is a piston cavity; a piston acting rod, the limiting spring, the SMA spring, the electric heater and the soft outgoing line are arranged in the sleeve from top to bottom; when the straight acting device does not work, the piston jacking rod is restrained in an initial position by the limiting spring, and the limiting spring and the SMA spring are balanced; when the straight acting device acts in orbit, any one of two heating wires in the heater is electrified through instruction, the SMA spring is heated, after the temperature reaches a phase-transition temperature, memory alloy is subjected to phase-transition, and the heat expanding type SMA spring stretches out and drives the piston jacking rod. The straight acting device for the spacecraft based on the SMA spring utilizes the advantage of easiness in controlling the action of the SMA spring and ensures the high reliability of a spacecraft mechanism.

Description

technical field [0001] The present invention relates to a linear actuation device and its usage method, in particular to a space vehicle linear actuation device based on SMA (shape memory alloy) spring and its usage method. Background technique [0002] At present, most of the actuating mechanisms used on spacecraft are spring push rod devices actuated by ordinary compression springs. The disadvantage of this device is that the initial compression force of the spring is large, and a large pre-tightening force is required to overcome the problem. The action of the spring is not convenient for actuation control. In the design of aerospace mechanisms based on SMA spring actuation, due to the limited space of the actuator, higher requirements are put forward for the heating of memory alloy springs: such as low power consumption, high efficiency, small size, and convenient connection. . Contents of the invention [0003] The technical problem to be solved by the present inven...

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Problems solved by technology

[0002] At present, most of the actuating mechanisms used on spacecraft are spring push rod devices actuated by ordinary compression springs. The disadvantage of this device is that the initial compression force of the spring is large, and a large pre-tightening force is required to overcome the problem. The action of the spring, and it is not convenient for actuation control

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