固体火箭飞行静载荷计算的偏差使用方法优化  

Using Method Optimization of Deviation for Static Flight Load Calculation of Solid Rocket

作　　者：张静 戴婷婷 闫奕含 刘帅帅 ZHANG Jing;DAI Tingting;YAN Yihan;LIU Shuaishuai(Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China)

机构地区：[1]北京宇航系统工程研究所,北京100076

出　　处：《宇航总体技术》2022年第6期9-14,共6页Astronautical Systems Engineering Technology

摘　　要：新型固体火箭对提升运载效率的需求日益强烈,由此发展出一些以提升载荷设计精度为目标的载荷优化方法,可有效实现结构的减载减质。现有优化方法仅考虑单项偏差,未考虑各项偏差间的匹配性和传递过程的合理性,很大程度上限制了载荷设计精度的进一步提升。梳理和分析了载荷计算过程涉及的多项参数偏差,提炼出原始偏差和过程偏差的概念,指出了传统方法在偏差使用及传递过程中的不合理。在此基础上,充分结合新型固体火箭的研制特点,改进了偏差的使用方法,降低了过程偏差对载荷计算精度的影响。结果表明该方法可有效提高载荷设计精度、准确性和效率。New solid rocket has an increasingly strong demand for improving delivery efficiency. Hence some load optimization methods have been developed to improve the load accuracy of load design, which can effectively reduce the load and weight of the structure. The existing optimization methods only consider a single deviation. They do not consider the matching between various deviations and the rationality of the transmission process, which significantly limits the further improvement of load design accuracy. This paper combs and analyzes several parameter deviations involved in the load calculation process, refines the concepts of original deviation and process deviation, and points out the irrationality of the traditional methods in the application and transmission of deviation. On this basis, combined with the development characteristics of the new solid rocket, the application method of deviation is improved, and the influence of process deviation on load calculation accuracy is reduced. The results show that this method can effectively improve load design’s precision, accuracy, and efficiency.

关 键 词：固体火箭 飞行载荷计算 过程偏差 使用方法优化 

分 类 号：V475.1[航空宇航科学与技术—飞行器设计]