| Based on the develop requirement for satellite-rocket separation system for small satellite, The separated system requires high separation velocity, small impact, low cost, small separated attitude perturbations, no pollution, excellent reliability.In this paper, A technical scheme of non-pyrotechnic devices for satellite-rocket separation is proposed, which taking compressed gas as power supply, and a analysis method of separation process is present.The main contents in this thesis are shown as follows:The advantages and disadvantages of conventional satellite-rocket separation are summarized, technical schemes for lock、unlock and pneumatic launched separation by compressed gas are proposed. Locking and unlocking devices by gas、separation device and gas supply device are analyzed, the structure design、main principle and the process of system parameters determined for those technical scheme are specific researched.The mathematic model of separation process for satellite-rocket separation system by pneumatic launched method are established based on pneumatic thermodynamic and Newtonian mechanics、associated with the process of gas flow and the loss coefficient obtained by testing data adjusting,the separation velocity affected by design parameters such as pressure of gas supply、pipe diameter of gas supply、structural mass、structural dimension are studied。The technical scheme and theoretical analysis method proposed in this paper are proved by ground test and flight test,The results show that the deviation between theoretical analysis and test data is less than 10%. On the other hand, the reliability assessment of performances of locking and unlocking by gas 、and satellite-rocket separation system by pneumatic launched method is carried out.The satellite-rocket separation system by pneumatic launch method can be promoted and applied in many areas such as fairing separation system、stage separation system、interference missile releasing、folding wing deployment。... |
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