Multistage buffer device for separating firer components for spaceflight
A buffer device and component technology, applied in the field of aerospace separation, can solve the problems of high response peak value, affecting the safety of spacecraft operation, and long response decay time, and achieve the effects of high specific strength, good energy absorption capacity, and high specific stiffness.
Active Publication Date: 2022-04-12
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology
[0005]
In order to solve the problem that the impact response peak value of the implicated object is too high and the response decay time is too long during the separation of the existing aerospace pyrotechnic separation implicated device, which affects the safety of the spacecraft operation
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Embodiment 1
[0031] A kind of aerospace pyrotechnic component separation multistage buffer device, such as figure 1 As shown, a steel cable part and a piston-type combined buffer part are fixedly installed between the throwing piece 1 and the plug 12; The energy source drives the plug 12; the piston-type combined buffer component is fixedly connected to the plug 12, the plug 12 is a driven aerospace part, it can be understood as the start switch of related instruments, etc., and the peak value of the impulse response on the plug 12 needs to be as small as possible , the frequency needs to be as low as possible to prevent damage to the instrument;
[0032] figure 2It is the cable part of the device. In addition to throwing plate 1, it includes: steel ring 4 installed on throwing plate 1, U-shaped steel cable 5, rotating shaft 3, buffer rubber structure 2, piston rod 6; there is protruding steel ring 4 and reinforcement structure on throwing plate 1, steel The space left in the ring is e...
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The invention discloses a multi-stage buffer device for separation of firer parts for spaceflight, and belongs to the technical field of spaceflight separation. A steel cable part and a piston type combined buffering part are arranged between a throwing piece and a plug; the steel cable part is connected with the throwing piece and comprises a buffer rubber structure, a rotating shaft, a steel ring, a U-shaped steel cable and a piston rod; the steel ring is fixedly installed on the throwing piece and sleeved with the U-shaped steel cable, and enough space is reserved so that the U-shaped steel cable and the steel ring can move freely. The piston rod can radially rotate around the rotating shaft and the U-shaped steel rope; the piston type combined buffer component is connected with the plug and comprises a piston rod, a piston cylinder, a rubber buffer pad, a buffer component and an energy absorption component. The piston cylinder is fixedly mounted on the plug; the rubber buffering pad is tightly attached to the inner wall of the piston cylinder, and the buffering component and the energy-absorbing component are fixedly installed between the piston cylinder and the piston rod. According to the invention, the impact response peak value of the connected object during separation can be reduced, the response decay time is shortened, and the operation safety of the spacecraft is improved.
Description
technical field [0001] The invention relates to a multi-stage buffer device for separating pyrotechnic components used in aerospace, belonging to the technical field of aerospace separation. Background technique [0002] The pyrotechnic device refers to the pyrotechnic device that pushes the mechanism through the high-pressure gas generated by the explosion to achieve the required action. Usually, the pyrotechnic device is used on the separation surface with special requirements, and the types of mechanisms used are different, and the completed actions are also different. Compared with other actuating devices, the pyrotechnic actuating mechanism has the characteristics of lighter weight, smaller volume and higher reliability. [0003] For aerospace parts close to the explosion point before pyrotechnic separation, such as throwing discs, engineers often design and install implicated devices on them to connect with other aerospace parts. When separating, the throwing piece a...
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IPC IPC(8): B64G1/64F16F15/08F16F15/02
Inventor 杨恒杨一凡严璇赵文浩林三春方岱宁
Owner BEIJING INSTITUTE OF TECHNOLOGYGY