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弹道学报  2015 

一种地地导弹变射面飞行程序设计方法

Keywords: 弹道导弹,变射面,飞行程序,hp-RPM伪谱法

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Abstract:

传统地地弹道导弹一般只进行俯仰飞行程序设计,所采用的设计模型与方法不能适应变射面飞行程序的设计。针对此问题,在射面转移变换规划的基础上,提出了一种地地导弹变射面飞行程序设计方法,在假设地球为圆球的情况下,建立射面变换飞行程序优化模型,采用hp-RPM伪谱法进行优化设计;对优化出的离散俯仰/偏航飞行程序数据进行多项式拟合平滑,并建立地球扁率影响修正模型进行修正,最终确定了射面变换俯仰/偏航飞行程序。仿真计算结果表明,优化出的变射面飞行程序有效、可行,证明了设计方法的正确性。

References

[1]  WANG Ji-ping,WANG An-min,WEI Shi-hui,et al.Planning-method of the ballistic trajectory plane transfer of ballistic missile[J].Journal of Ballistics,2014,26(2):22-28.(in Chinese)
[2]  鲜勇,田海鹏,冯杰,等.基于改进遗传算法的最优精度飞行程序角设计方法[J].四川兵工学报,2013,34(1):1-4.
[3]  XIAN Yong,TIAN Hai-peng,FENG Jie,et al.Study of designing trajectory missile’s flight process of the optimal precision based on the improved genetic algorithm[J].Journal of Sichuan Ordnance,2013,34(1):1-4.(in Chinese)
[4]  王永圣.固体弹道导弹推进/气动/弹道优化设计研究[D].哈尔滨:哈尔滨工业大学,2013.
[5]  WANG Yong-sheng.Study on the propulsion aerodynamics trajectory integrated optimal design for solid ballistic missile[D].Harbin:Harbin Institute of Technology,2013.(in Chinese)
[6]  洪蓓,梁欣欣,辛万青.固体运载火箭多约束弹道优化[J].导弹与航天运载技术,2012(3):1-5.
[7]  HONG Bei,LIANG Xin-xin,XIN Wan-qing.Multi-constraint trajectory optimization for solid launch vehicle[J].Missiles and Space Vehicles,2012(3):1-5.(in Chinese)
[8]  张洪倩.基于高斯伪谱法的弹道优化设计与实现[D].南京:南京理工大学,2014.
[9]  ZHANG Hong-qian.Trajectory optimization designing and realization based on Gauss pseudospectral method[D].Nanjing:Nanjing University of Science and Technology,2014.(in Chinese)
[10]  洪蓓,辛万青.基于hp自适应伪谱法的固体运载火箭轨迹优化[J].航天控制,2012,30(4):18-22.
[11]  HONG Bei,XIN Wan-qing.Trajectory optimization of solid launch vehicle based on Hp-Adaptive pseudospectral method[J].Aerospace Control,2012,30(4):18-22.(in Chinese)
[12]  王继平,王安民,魏诗卉,等.弹道导弹弹道面转移变换规划方法[J].弹道学报,2014,26(2):22-28.
[13]  张鹏程,李新国.基于Gauss伪谱方法的高超声速滑翔飞行器滑翔段轨迹优化[J].电子设计工程,2013,21(15):105-107.
[14]  ZHANG Peng-cheng,LI Xin-guo.Trajectory optimization of glide phase for hypersonic glide vehicle based on GPM[J].Electronic Design Engineering,2013,21(15):105-107.(in Chinese)
[15]  国海峰,黄长强,丁达理,等.多约束条件下高超声速导弹再入轨迹优化[J].弹道学报,2013,25(1):10-15.
[16]  GUO Hai-feng,HUANG Chang-qiang,DING Da-li,et al.Re-entry trajectory optimization for supersonic missile considering multiple constraints[J].Journal of Ballistics,2013,25(1):10-15.(in Chinese)
[17]  王小虎,陈翰馥,刘锋.机动再入飞行器主动段再入点约束闭路制导研究[J].宇航学报,2002,23(4):37-40.
[18]  WANG Xiao-hu,CHEN Han-fu,LIU Feng.Study of the closed-loop guidance law for boost phase with reentry constraints of maneuvering reentry vehicles[J].Journal of Astronautics,2002,23(4):37-40.(in Chinese)

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