火箭橇运动计算算法优化与试验验证

夏有财; 孙其会; 肖军; 耿强; 徐进欣; 马骏

doi:10.13224/j.cnki.jasp.20200462

火箭橇运动计算算法优化与试验验证

doi: 10.13224/j.cnki.jasp.20200462

中国华阴兵器试验中心, 陕西华阴 714200

详细信息

作者简介:
夏有财(1994-),男,助理工程师,硕士,主要从事火箭橇试验技术研究。

中图分类号: V411.3
计量
- 文章访问数: 583
- HTML浏览量: 230
- PDF量: 138
- 被引次数: 0
出版历程
- 收稿日期: 2020-12-01
- 刊出日期: 2021-07-28

Optimization and test verification of rocket sled motion calculation algorithm

China Huayin Ordnance Test Center, Huayin Shaanxi 714200, China

摘要

摘要: 对火箭橇试验系统进行了动力学分析，研究了火箭橇运动计算方法，在常规算法基础上对各参量计算方法进行改进，并引入了新的参量能量耗散阻力，进而得到优化算法。取四次不同速度的双轨橇车试验结果分别与常规算法和优化算法计算结果进行比较，得到：常规算法计算结果误差最小为7.67%，误差最大为37.91%，优化后算法计算结果误差最小为0.48%，误差最大为5.0%；取四次不同速度的单轨橇车试验结果分别与常规算法和优化算法计算结果进行比较，得到：常规算法计算结果误差最小为11.78%，误差最大为43.64%，而优化算法计算结果误差最小为0.11%，误差最大为5.31%。结果表明火箭橇运动计算优化算法相比常规算法能有效提高计算结果精度，计算结果对火箭橇试验设计具有一定工程指导意义。
- 火箭橇 /
- 运动计算 /
- 算法优化 /
- 试验验证 /
- 能量耗散阻力
Abstract: The dynamic analysis of rocket sled test system was carried out, and the calculation method of rocket sled motion was studied. Based on the conventional algorithm, the calculation method of some parameter was improved, and a new parameter energy dissipation resistance was introduced to obtain the optimization algorithm. Comparing the results of four double-track sled tests with different speeds with the calculation results of the conventional algorithm and the optimized algorithm, it was found that: the minimum error of the conventional algorithm calculation result was 7.67%, the maximum error was 37.91%, and the minimum error of the optimized algorithm calculation result was 0.48%, and the maximum error was 5.0%; comparing the results of four different speed monorail sled tests with the calculation results of the conventional algorithm and the optimized algorithm, it was found that: the minimum error of the conventional algorithm calculation result was 11.78%, and the maximum error was 43.64%, and the calculation result of the optimized algorithm had a minimum error of 0.11% and a maximum error of 5.31%. The results showed that the optimization algorithm of rocket sled calculation can effectively improve the accuracy of calculation results compared with conventional algorithms, and the calculation results have certain engineering guiding significance for rocket sled test design.
- rocket sled /
- motion calculation /
- algorithm optimization /
- test verification /
- energy dissipation resistance

HTML

参考文献(19)

[1]	杨兴邦.XB高精度火箭橇试验滑轨[J].中国工程科学,2000,2(10):98-104. YANG Xingbang.XB high precision rocket sled test track[J].Chinese Journal of Engineering Sciences,2000,2(10):98-104.(in Chinese)
[2]	邹伟红.火箭滑橇空气动力的数值模拟[D].南京:南京理工大学,2008. ZOU Weihong.Numerical simulation of rocket sled aerodynamics[D].Nanjing:Nanjing University of Science and Technology,2008.(in Chinese)
[3]	INGOLD N L.Reverse velocity rocket sled test bed for inertial guidance systems[J].Navigation,1983,30(1):90-99.
[4]	HUANG H,TONG Z,CHAI S,et al.Experimental and numerical study of chaff cloud kinetic performance under impact of high speed airflow[J].Chinese Journal of Aeronautics,2018,31(11):27-39.
[5]	ZHANG J H,JIANG S S.Rigid-flexible coupling model and dynamic analysis of rocket sled[J].Advanced Materials Research,2012,346:447-454.
[6]	王云.火箭橇试验滑轨的发展与展望[J].航空科学技术,2010(1):30-32. WANG Yun.Development and prospect of rocket sled test track[J].Aviation Science and Technology,2010(1):30-32.(in Chinese)
[7]	HEGEDUS M,MENDENHALL M,PERKINS S,et al.Engineering analysis for rocket sled aerodynamics[R].AIAA-2006-664,2006.
[8]	ROSENBERG B.Maglev rocket sled[J].Popular Mechanics,1996,173(3):26-27.
[9]	WANG L X,JUN-HUI X U,LIU J Y.Test data processing scheme of inertial system based on rocket sled[J].Journal of Chinese Inertial Technology,2008.
[10]	周学文,景建斌,田建明.惯导装置精度试验火箭橇弹道设计[J].导航与控制,2015,14(6):14-20. ZHOU Xuewen,JING Jianbin,TIAN Jianming.Ballistic design of the rocket sled on INS accuracy testing[J].Navigation and Control,2015,14(6):14-20.(in Chinese)
[11]	MEACHAM M B,KENNETT A,TOWNSEND D J,et al.Rocket sled propelled testing of a supersonic inflatable aerodynamic decelerator[R].AIAA 2013-1351,2013.
[12]	COATTA D,JUREWICZ D A,TUTT B A,et al.Development and testing of an 8m isotensoid supersonic inflatable aerodynamic decelerator (SIAD)[R].AIAA 2013-1328,2013.
[13]	房明,孙建红,王从磊,等.低亚声速火箭橇尾流场特性分析[J].空气动力学学报,2017,35(6):897-901. FANG Ming,SUN Jianhong,WANG Conglei,et al.Analysis of flow field characteristics of low subsonic rocket sled[J].Acta aerodynamics,2017,35(6):897-901.(in Chinese)
[14]	王明清.基于固体火箭发动机的火箭橇动力系统研究[D].南京理工大学,2017. WANG Mingqing.Research on rocket sled power system based on solid rocket engine[D].Nanjing:Nanjing University of Technology,2017.(in Chinese)
[15]	李金河,庞勇,赵继波.火箭橇试验加载技术研究[J].弹箭与制导学报,2010,30(5):137-139. LI Jinhe,PANG Yong,ZHAO Jibo.Research on loading technology of rocket sled test[J].Journal of Projectile and Guidance,2010,30(5):137-139.(in Chinese)
[16]	王健.高速火箭橇-轨道系统耦合动力学研究[D].南京:南京理工大学,2011. WANG Jian.The research for coupled dynamics of high speed rocket sled-track systems[D].Nanjing:Nanjing University of Science and Technology,2011.(in Chinese)
[17]	房明,孙建红,余元元,等.火箭橇系统的摩擦力分析与计算[J].航空动力学报,2017,32(11):216-223. FANG Ming,SUN Jianhong,YU Yuanyuan,et al.Friction analysis of the rocket sled system[J].Journal of Aeronautical Dynamics,2017,32(11):216-223.(in Chinese)
[18]	刘军,李磊子.火箭橇气动阻力系数取值方法技术研究[C]//中国空气动力学会测控专业委员会六届四次空气动力测控技术交流会论文集.湖北襄阳:中国空气动力学会,2013:1-6.
[19]	夏有财,徐进新,耿强.火箭橇试验系统研究现状与趋势[C]//中国航天第三专业信息网第四十届技术交流会暨第四届空天动力联合会议论文集.昆明:航天三网,2019:152-156.