Spatial flying net synchronous launching device

Abstract

The invention discloses a spatial flying net synchronous launching device which comprises an igniter, an exploder, a main piston, a guide pin, a seal ring, four auxiliary piston sleeves, four auxiliary pistons, a shearing pin, a main piston guide sleeve and connecting rods. The four auxiliary pistons are pushed by the main piston, in the initial stage, the main piston pushes the auxiliary pistons to cut off the shearing pin through mechanical contact, the main piston continues to move to allow the seal ring to lose sealing effect, high-pressure fuel gas directly acts on the auxiliary pistons, each auxiliary piston pushes the corresponding connecting rod and the mass block fixedly connected with the connecting rod, so that launching of multiple mass blocks is achieved, launching synchronism of the mass blocks is achieved, launching speed is increased by utilizing the high-pressure fuel gas, and high safety is achieved.

Description

technical field [0001] The invention relates to a space flying net synchronous launching device, in particular to a space flying net launching synchronous launching device, which belongs to the field of aerospace technology. Background technique [0002] With the development of space technology, it is becoming more and more important to capture non-cooperative targets such as space debris and abandoned satellites on-orbit. Among them, the flying net capture technology is a space technology that is relatively popular in international research. It mainly uses the flying net deployment mechanism to launch a large net made of thin ropes in the direction of the captured target. After wrapping the target spacecraft, it will The target spacecraft is retracted or controlled. Taking advantage of the fact that the flying net has a large interception area, which is beneficial to cover the captured target, the flying net capture technology has become a capture system with a certain fau...

AI Technical Summary

Problems solved by technology

The direct launch deployment method has a simple mechanism, less energy consumption and faster deployment, and the size of the flying net is not limited, but it is difficult to maintain the shape of the flying net during the movement process, and complex and chaotic movements may occur. control

like figure 1 As shown, the ROGER project of the European Space Agency has proposed a coaxial configuration flying net launcher, its main disadvantage is: after the separation, the protective cover will fly forward, which will inevitably have a collision effect on the target body; through Launched with spring energy storage, the ability to increase the launch speed is limited

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