Connection and separation mechanism for satellite

Abstract

The invention provides a connection and separation mechanism for a satellite. The connection and separation mechanism comprises a connection bracket for connecting with a launch vehicle, a plurality of adapter rings evenly distributed on the connection bracket and used for connecting with the satellite, a plurality of firework devices arranged at the corners of the connection bracket and unlocked by an igniter, at least one non-electric detonation transmission device connected to the plurality of firework devices for multi-way transmission, at least one spring separation device arranged on the connection bracket and used for providing a separation speed for separation of the satellite, and at least one travel switch arranged on the connection bracket and used for providing a separate signal to a carrier when the satellite is separated. According to the connection and separation mechanism, the synchronization accuracy of unlocking can be effectively improved, the release speed and the posture stability are improved, in addition, the power supply current of the energy system can also be effectively reduced, and the size of the connection and separation device is decreased.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a connection and separation mechanism, which can be applied to spacecraft, especially spacecraft with release speed and release attitude requirements. Background technique [0002] The connection and separation mechanism of the satellite is used to realize the reliable connection between the satellite and the launch section of the launch vehicle and the safe release and separation of the orbit. Early spacecraft used explosive bolts to achieve attachment and separation. With the continuous development of spacecraft technology, a series of new connection and separation mechanisms have emerged, such as explosive bolt-type star-rocket connection and separation mechanisms, spring-loaded star-rocket connection and separation mechanisms, electrical-hydraulic circuit breakers and Space docking mechanism, etc. [0003] However, the existing spring-wrapped satellite-rocket connection ...

AI Technical Summary

Problems solved by technology

[0003] However, the existing spring-wrapped satellite-rocket connection and separation mechanism is not applicable in the case of strict space constraints due to its large envelope size, and most of the small satellites are carried and launched, and the small size can be predicted. The space left for connection and separation mechanism is also small

In addition, the detonation bolt-type separation mechanism needs to provide detonation current for each detonation bolt, and the detonation of each detonation bolt is asynchronous, which affects the stability of the attitude of satellite separation.

Also due to space constraints, these institutions often cannot be applied to small satellites with strict space requirements

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