基于二次点火的飞行器横向转移入轨弹道设计

鲜勇; 刘凯; 凌王辉; 张大巧

doi:10.13224/j.cnki.jasp.2018.02.009

基于二次点火的飞行器横向转移入轨弹道设计

doi: 10.13224/j.cnki.jasp.2018.02.009

火箭军工程大学空间工程系,西安 710025

计量
- 文章访问数: 750
- HTML浏览量: 5
- PDF量: 592
- 被引次数: 0
出版历程
- 收稿日期: 2016-07-13
- 刊出日期: 2018-02-28

Trajectory design of launchingplane transforming orbitinjection of spacecraft based on engine twice ignition

摘要

摘要: 为了解决航天器发射过程因发射场地的地理位置约束造成的入轨夹角问题,基于火箭上面级二次点火,对航天器横向转移零速度偏差入轨弹道进行了设计。对二次点火和变射面横向转移弹道进行了研究,根据横向转移弹道特点,为简化控制程序,分时序对火箭二级非连续点火纵横向飞行程序进行了设计；并分析横向转移入轨弹道各项约束条件,建立弹道优化模型。根据弹道设计模型,以某两级液体燃料运载火箭为研究对象,对二次点火横向转移入轨弹道进行优化仿真。结果表明：入轨时刻航天器位置偏差为0.391m,速度偏差为1.277m/s,速度偏差比二次点火固定射面入轨弹道减少了737.844m/s,满足零速度偏差入轨精度要求。
- 飞行器入轨 /
- 运载火箭 /
- 横向转移 /
- 二次点火 /
- 弹道设计
Abstract: In order to solve the velocity deviation of orbitinjection question in space launch by the geographical location of launching site, the trajectory of zero velocity deviation orbit injection based on engine twice ignition and Launchingplane transforming for the liquid launch vehicle was designed. According to the characteristics of the Launchingplane transforming trajectory, the twice ignition and Launchingplane transforming flight program model for the secondstage was established in different sequences to simplify the control program of the engine, and the constraints of the trajectory were analysed to establish the trajectory optimization model. Then, the trajectory was simulated according to the optimization model. Results indicated that the orbitinjection position deviation of the spacecraft was 0391m and the velocity deviation was 1277m/s, and the velocity deviation was 737844m/s less than the optimum result of the fixed launchingplane orbitinjection trajectory, meeting the requirement of the zero velocity deviation orbit injection.
- orbitinjection of spacecraft /
- launch vehicle /
- launchingplane transform /
- twice ignition /
- trajectory design

HTML

参考文献(19)

[1]	龙乐豪.总体设计［M］.北京:宇航出版社,1989.
[2]	鲜勇,许立军.遗传算法在导弹飞行程序设计中的应用研究［J］.系统仿真学报,2009,21(5):1502-1504.XIAN Yong,XU Lijun.Study of designing trajectory missiles flight process based on genetic algorithm［J］.Journal of System Simulation,2009,21(5):1502-1504.(in Chinese)
[3]	鲜勇,刘炳琪,李振华,等.一种横向机动弹道能量管理方法［J］.弹道学报,2014,26(2):43-47.XIAN Yong,LIU Bingqi,LI Zhenhua,et al.An energy management method of trajectory of transversely maneuvering missile［J］.Journal of Ballistics,2014,26(2):43-47.(in Chinese)
[4]	肖龙旭,王继平,魏诗卉,等.一种地地导弹变射面飞行程序设计方法［J］.弹道学报,2015,27(2):7-13.XIAO Longxu,WANG Jiping,WEI Shihui,et al.A design method of changeable launching plane flightprocess of groungtoground ballistic missiles［J］.Journal of Ballistics,2015,27(2):7-13.(in Chinese)
[5]	鲜勇,刘炳琪,王安民,等.变射面弹道横向转弯飞行程序的设计与优化［J］.弹道学报,2014,26(4):30-35.XIAN Yong,LIU Bingqi,WANG Anmin,et al.Design and optimization of lateral turning flight program on changeable launching plane trajectory［J］.Journal of Ballistics,2014,26(4):30-35.(in Chinese)
[6]	王继平,魏诗卉,肖龙旭,等.一种变射面飞行导弹的弹上迭代制导方法［J］.飞行力学,2015,33(3):243-247.WANG Jiping,WEI Shihui,XIAO Longxu,et al.Iterative guidance method of changeable launching plane flight missile［J］.Flight Dynamics,2015,33(3):243-247.(in Chinese)
[7]	张广明,高普云,冯志刚,等.基于脉冲点火弹头平面机动的被动段弹道设计［J］.弹道学报,2009,21(2):53-57.ZHANG Guangming,GAO Puyun,FENG Zhigang,et al.Design of trajectory of the maneuver of warhead in a plane based on impulse firing in the passive curve［J］.Journal of Ballistics,2009,21(2):53-57.(in Chinese)
[8]	李振华,鲜勇,雷刚,等.基于混合粒子群算法的上升段交会弹道快速优化设计［J］.航空动力学报,2015,30(12):2029-2034.LI Zhenhua,XIAN Yong,LEI Gang,et al.Rapid optimum design of ascent rendezvous trajectory for launch vehicles based on hybrid particle swarm algorithm［J］.Journal of Aerospace Power,2015,30(12):2029-2034.(in Chinese)
[9]	杨希祥,张为华.基于Gauss伪谱法的固体运载火箭上升段轨迹快速优化研究［J］.宇航学报,2011,32(1):15-20.YANG Xixiang,ZHANG Weihua.Rapid optimization of ascent trajectory for solid launch vehicles based on gauss pseudospectral method［J］.Journal of Astronautics,2011,32(1):15-20.
[10]	杨希祥,江振宇,张为华.基于粒子群算法的固体运载火箭上升段弹道优化设计研究［J］.宇航学报,2010,31(5):1304-1309.YANG Xixiang,JIANG Zhenyu,ZHANG Weihua.Aparticle swarm optimization algorithm based solid launch vehicle ascent trajectory optimum design［J］.Journal of Astronautics,2010,31(5):1304-1309.(in Chinese)
[11]	梁欣欣,李世鹏,陈阳,等.固体运载器大气飞行段内弹道优化设计研究［J］.弹道学报,2014,26(4):72-75.LIANG Xinxin,LI Shipeng,CHEN Yang,et al.Research on interior ballistics optimization design for solid launch vehicle in atmosphere flight phase［J］.Journal of Ballistics,2014,26(4):72-75.(in Chinese)
[12]	孙丕忠,夏智勋,郭振云.水平空中发射固体运载火箭轨道设计与优化［J］.固体火箭技术,2004,27(2):87-90.SUN Pizhong,XIA Zhixun,GUO Zhenyun.Trajectory calculation optimization of horizontally airlaunched vehicle with wings［J］.Journal of Solid Rocket Technology,2004,27(2):87-90.(in Chinese)
[13]	冉茂鹏,王青.一种基于EPSO的航天器交会轨迹优化方法［J］.宇航学报,2013,34(9):1195-1201.RAN Maopeng,WANG Qing.Spacecraft rendezvous trajectory optimization method based on EPSO［J］.Journal of Astronautics,2013,34(9):1195-1201.(in Chinese)
[14]	晁涛,王松艳,杨明,等.基于组合优化算法的临近空间飞行器轨迹优化［J］.宇航学报,2012,33(2):183-189.CHAO Tao,WANG Songyan,YANG Ming,et al.Near space vehicle trajectory optimization approach based on hybrid SVM and GA algorithm［J］.Journal of Astronautics,2012,33(2):183-189.(in Chinese)
[15]	CHEN H R,SPEYER L J,LIANOS D.Optimal intercept missile guidance strategies with autopilot lag［J］.Journal of Guidance,Control,and Dynamics,2010,33(4):1264-1272.
[16]	CRAIN T P,BISHOP R H,FOWLER W T.Interplanetary flyby mission optimization using a hybrid global/local search method［J］.Journal of Spacecraft and Rockets,2000,37(4):468-473.
[17]	ALGARNI A,KASSEM A H.On the optimization of aerospace plane ascent trajectory［J］.Transactions of the Japan Society for Aeronautical and Space Sciences,2007,50(168):113-120.
[18]	胡鹏翔.液体火箭的多体动力学建模与仿真研究［D］.北京：清华大学,2012.HU Pengxiang.Multibody dynamic modeling and simulation of liquidpropellant launch vehicles［D］.Beijing:Tsinghua University,2012.(in Chinese)
[19]	程仙垒,彭双春,郑伟,等.多约束条件下非连续助推弹道方案设计与优化［J］.系统工程与电子技术,2015,37(4):888-894.CHENG Xianlei,PENG Shuangchun,ZHENG Wei,et al.Discontinuous boosting trajectory project design and optimization［J］.Systems Engineering and Electronics,2015,37(4):888-894.(in Chinese)