Electromagnetic locking and releasing mechanism for satellite-rocket separation and electromagnetic locking and releasing method

Abstract

The invention provides an electromagnetic locking and releasing mechanism for satellite-rocket separation and an electromagnetic locking and releasing method. The electromagnetic locking and releasingmechanism comprises a rack, an ejection unit, a satellite unit, a locking and releasing unit and a locking and releasing driving unit. The ejection unit comprises an ejection spring, an ejection ejector rod and a spring sleeve; the locking and releasing unit comprises a locking pin, a locking sliding block, an unlocking spring and a base. The locking and releasing driving unit comprises an electromagnet limiting nut, an electromagnet movable core and an electromagnet. The point type positioning locking and releasing mechanism has the advantages that the point type positioning locking and releasing mechanism can be repeatedly tested and is used for separating the microsatellite from the rocket, and reliable locking and reliable separation of the satellite and the rocket can be achieved ina complex mechanical environment; the separation test can be repeatedly carried out on the ground; separation is completely mechanism action, and no pollution is caused; the separation action is continuous mechanism action and has no impact on a satellite; and the satellite development cost is reduced.

Description

technical field [0001] The invention belongs to the field of aerospace technology, and in particular relates to an electromagnetic locking and releasing mechanism and an electromagnetic locking and releasing method for separating satellites and rockets. Background technique [0002] The satellite locking and releasing mechanism is mainly used in the satellite-rocket separation mechanism. Its main working principle is: before the rocket reaches the predetermined orbit, the reliable connection between the satellite and the rocket is realized; after the rocket enters the orbit, a separation command is given to release the satellite safely , ie: make the satellite separate from the rocket at the designed velocity. [0003] The key design elements of the satellite lock release mechanism are the mechanism form and the active device. In the prior art, the mechanism form mainly adopts a docking ring and a tape-wrapped separation mechanism. The main problem is that the docking ring ...

AI Technical Summary

Problems solved by technology

In the prior art, the mechanism form mainly adopts a docking ring and a tape-wrapped separation mechanism. The main problem is that the docking ring and the tape-wrapped separation mechanism require that the satellite must have a docking surface to be connected and installed with the separation mechanism, which cannot be applied to Irregular shaped satellites that require point positioning and locking

Active devices mainly use pyrotechnic products, hot knives, memory alloys, motors, etc. The main problems are: the cost of pyrotechnic products is expensive, the management requirements are complicated, and they are destructive separations, so repeated tests cannot be carried out on the ground; hot knives can The load it bears is very small, and it is difficult to fix the entire satellite, and the action time is uncertain, and the synchronization cannot be guaranteed; the action time of the memory alloy is uncertain, and the synchronization cannot be guaranteed; the motor needs continuous power supply, and the micro satellite is generally launched by a rocket. Rockets generally cannot provide continuous current, so it is difficult to apply to tiny satellites

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