一种小型火工机构的输出计算及其验证  

Calculation and Verification of the Outputs of a Small Pyrotechnic Mechanism

作　　者：杜永刚[1] 王雪松[1] 刘轶鑫 康昌玺 雷小光[1] 张文台[1] 孙永壮 DU Yonggang;WANG Xuesong;LIU Yixin;KANG Changxi;LEI Xiaoguang;ZHANG Wentai;SUN Yongzhuang(Lanzhou Institute of Physics,China Academy of Space Technology,Lanzhou 730000,China)

机构地区：[1]中国空间技术研究院兰州空间技术物理研究所,兰州730000

出　　处：《宇航学报》2024年第2期231-239,共9页Journal of Astronautics

基　　金：装备研究(2020)。

摘　　要：针对某折叠翼展开机构的小型化难题,研究了一种小型火工机构。利用内弹道理论建立了该火工机构的输出理论模型,通过理论模型计算和优化了机构参数,并用有限元法校验了计算结果。测试结果表明:该原型机具备了小型特点,其输出角度达到了128.5°。在逆风和顺风负载下,该火工机构的工作时间均小于200 ms,其最大角速度不大于3 000 (°)/s,试验数据证实该火工机构具备缓冲作用,理论计算结果和试验数据基本一致。研究成果可作为薄型折叠翼的一种设计方法,为薄型折叠翼的工程应用奠定技术基础。Aiming to miniaturize the deployment mechanism of a folding wing,a small pyrotechnic mechanism is investigated.The output theory of the pyrotechnic mechanism is developed based on the internal ballistic theory.The parameters of the mechanism are calculated and optimized using the theoretical model,and the results are verified by the finite element analysis.The test results indicate that the prototype meets the requirement of a small volume,and its output angle is 128.5°.Under wind or following wind,the mechanism takes less than 200 ms,and its maximum angular velocity is not greater than 3000(°)/s.Experimental data confirm that the pyrotechnic mechanism can reduce the impact,and the data are consistent with the calculated results.The research results of the paper can be used for the design theory of the thin folding wings,and they provide a technical foundation for the engineering application of this mechanism.

关 键 词：火工机构 折叠翼 小型化 理论模型 验证 

分 类 号：V219[航空宇航科学与技术—航空宇航推进理论与工程]