基于二体理论的远程拦截中制导修正

doi:10.3969/j.issn.1001-506X.2020.08.21

系统工程与电子技术 ›› 2020, Vol. 42 ›› Issue (8): 1804-1811.doi: 10.3969/j.issn.1001-506X.2020.08.21

基于二体理论的远程拦截中制导修正

陈文钰(), 邵雷(), 雷虎民(), 骆长鑫(), 张涛()

空军工程大学防空反导学院, 陕西西安 710051

收稿日期:2019-11-20 出版日期:2020-07-25 发布日期:2020-07-27
作者简介:陈文钰 (1996-),男,硕士研究生,主要研究方向为武器系统总体技术。E-mail:lorilouto_cwy@163.com|邵雷 (1982-),男,副教授,博士,主要研究方向为武器系统总体技术、空天拦截器导航、制导与控制。E-mail:shaolei_zj@163.com|雷虎民 (1960-),男,教授,博士,主要研究方向为飞行器制导与控制技术。E-mail:hmleinet@21cn.com|骆长鑫 (1994-),男,博士研究生,主要研究方向为空天拦截器导航、制导与控制。E-mail:1710794652@qq.com|张涛(1992-),男,博士研究生,主要研究方向为空天防御系统与工程、临近空间飞行器制导控制技术。E-mail:ZhangTaoV2016@163.com
基金资助:
国家自然科学基金(61703421);国家自然科学基金(61773398);国家自然科学基金(61873278)

Mid-course guidance modification of super-range interception based on two body theory

Wenyu CHEN(), Lei SHAO(), Humin LEI(), Changxin LUO(), Tao ZHANG()

Air and Missile Defence College, Air Force Engineering University, Xi'an 710051, China

Received:2019-11-20 Online:2020-07-25 Published:2020-07-27
Supported by:
国家自然科学基金(61703421);国家自然科学基金(61773398);国家自然科学基金(61873278)

摘要/Abstract

摘要：

针对临近空间高超声速目标拦截弹交接班区域较高时的作战情景,参考轨道拦截理论,以高抛再入型拦截弹道为基准,将拦截弹运动视作二体运动,设计了远程拦截制导算法。首先,将复杂的运动模型进行简化,再根据受力分析将模型转换为二体轨道模型。然后,利用航迹角迭代法求解了Lambert问题,得到变轨需用速度,在轨道模型中提出通过调整速度至变轨需用速度完成拦截任务。最后,分析了拦截弹机动时推力有限带来的过渡段机动问题,提出采用速度增益制导法解决此问题。仿真结果表明,在高空域气动力微弱条件下,将拦截弹运动模型视作二体轨道模型是可行的,速度增益制导算法不仅能有效解决过渡段机动问题,而且针对预测拦截点变化的情况也具有良好的收敛性,能够完成临近空间的中制导拦截任务。

关键词: 临近空间, 中制导, 速度增益制导, 弹道修正, 二体理论

Abstract:

Aiming at the combat situation when the handover area of hypersonic target interceptor is high in the near space, referencing to the theory of orbit interception, based on the high throw and reentry interceptor trajectory and take interceptor as two body model, a long-range interceptor guidance algorithm is designed. Firstly, the complex motion model is simplified, and according to the force analysis, the model is transformed into a two body orbit model. Then, by using the track angle iteration method, the Lambert problem is solved, and the orbit change required speed is obtained. It is proposed to adjust the speed to the required speed of the orbit change to complete the intercepting task in the orbit model. Finally, because of the limited thrust, the maneuverability of the interceptor in transition period is analyzed, and the method of velocity gain guidance is proposed to solve the problem. The simulation results show that it is feasible to use the two body orbit model to represent the motion model of the interceptor under the condition of weak aerodynamic force in the high altitude domain. The speed gain guidance algorithm can not only solve the transition period maneuver problem effectively, but also has good convergence in predicting the change of interceptor points, so as to complete the medium guidance interception task in the near space.

Key words: near space, midcourse guidance, velocity gain guidance, trajectory correction, two body theory

中图分类号:

V448

陈文钰, 邵雷, 雷虎民, 骆长鑫, 张涛. 基于二体理论的远程拦截中制导修正[J]. 系统工程与电子技术, 2020, 42(8): 1804-1811.

Wenyu CHEN, Lei SHAO, Humin LEI, Changxin LUO, Tao ZHANG. Mid-course guidance modification of super-range interception based on two body theory[J]. Systems Engineering and Electronics, 2020, 42(8): 1804-1811.

图/表 11

图1

图2

图3

图4

图5

表1

图6

图7

表2

图8

图9

参考文献 24

1	王鹏飞, 王光明, 蒋坤, 等. 临近空间高超声速飞行器发展及关键技术研究[J]. 飞航导弹, 2019, (8): 22- 28, 34.
	WANG P F , WANG G M , JIANG K , et al. Research on the development and key technologies of hypersonic vehicle in near space[J]. Aerodynamic Missile Journal, 2019, (8): 22- 28, 34.
2	LIANG Z X, YI K, LI Q D, et al. Interceptor trajectory and guidance for hypersonic gliding targets[C]//Proc.of the Chinese Control Conference, 2016: 5666-5670.
3	GRANT B . Rapid indirect trajectory optimization for conceptual design of hypersonic missions[J]. Journal of Spacecraft and Rockets, 2015, 52 (1): 177- 182.
4	BARRON R . Costate approximation and comparisons between improved and classical indirect trajectory optimization[J]. Journal of Guidance, Control and Dynamics, 2011, 34 (2): 629- 634.
5	BARRON B , CHICK C M . Trim-reference functions for indirect method of trajectory optimization[J]. Journal of Guidance, Control and Dynamics, 2007, 30 (4): 1189- 1193.
6	BARRON B , CHICK C M . Improved indirect method for air-vehicle trajectory optimization[J]. Journal of Guidance, Control and Dynamics, 2006, 29 (3): 643- 652.
7	LIU H , BENSON H T . Indirect spacecraft trajectory optimization using modified equin octial elements[J]. Journal of Guidance, Control and Dynamics, 2010, 33 (2): 619- 622.
8	GATH P F, WELL K H. Trajectory optimization using a combination of direct multiple shooting and collocation[C]//Proc.of the AIAA Guidance, Navigation and Control Conference and Exhibit, 2001: AIAA-2001-4047.
9	MAO Y F , ZHANG D L , WANG L . Reentry trajectory optimiza-tion for hypersonic vehicle based on improved Gauss pseudospectral method[J]. Soft Computing, 2017, 21 (16): 4583- 4592.
10	ZHANG Y L , LIU L H , TANG G J , et al. Trajectory generation of heat load test based on Gauss pseudospectral method[J]. Science China Technological Sciences, 2018, 61 (2): 273- 284.
11	LIU C, ZHANG C, WANG J. Multi-stage trajectory optimization for time-on-target of tactical rockets using Gauss pseudospectral method[C]//Proc.of the 37th Chinese Control Conference, 2018: 2119-2124.
12	RIZVI S , HE L , XU D . Optimal trajectory and heat load analy- sis of different shape lifting reentry vehicles for medium range application[J]. Defence Technology, 2015, 11 (4): 350- 361.
13	PONTANI M , CECCHETTI G , TEOFILATTO P . Variable-time-domain neighboring optimal guidance applied to space traje- ctories[J]. Acta Astronautica, 2015, 115, 102- 120.
14	DWIVEDI P , BHATTACHARYA A , PADHI R . Suboptimal midcourse guidance of interceptors for high-speed targets with alignment angle constraint[J]. Journal of Guidance, Control and Dynamics, 2011, 34 (3): 860- 877.
15	HALBE O , RAJA R , PADHI R . Robust reentry guidance of a reusable launch vehicle using model predictive static programming[J]. Journal of Guidance, Control and Dynamics, 2014, 37 (1): 134- 148.
16	INDIG N, BEN A, FARBER N. Near-optimal spatial mid-course guidance law with angular constraint[C] //Proc.of the AIAA Guida-nce, Navigation, and Control Conference, 2012.
17	INDIG N , BEN A , FARBER N . Near optimal spatial midcourse guidance law with angular constraint[J]. Journal of Guidance, Control and Dynamics, 2014, 37 (1): 214- 223.
18	INDIG N, BEN A, SIGAL E. Near-optimal minimum time guida-nce under a spatial angular constraint in atmospheric flight[C]//Proc.of the AIAA Guidance, Navigation, and Control Conference, 2015: AIAA 2015-0089.
19	HUI Y, FAHROO F, ROSS I. Real-time computation of neighboring optimal control laws[C]//Proc.of the AIAA Guidance, Navigation, and Control Conference and Exhibit, 2002: AIAA-2002-4657.
20	TIAN B , ZONG Q . Optimal guidance law for reentry vehicles based on indirect Legendre pseudospectral method[J]. Acta Astronautica, 2011, 68, 1176- 1184.
21	LI N , LEI H , ZHOU J , et al. Variable-time-domain online neighboring optimal trajectory modification for hypersonic interceptors[J]. International Journal of Aerospace Engineering, 2017, 9456179.
22	刘光明, 文援兰, 尹大伟, 等. 基于微分改正的Lambert拦截摄动修正方法研究[J]. 弹箭与制导学报, 2009, 29 (5): 87- 90.
	LIU G M , WEN Y L , YIN D W , et al. The study on perturbation correction for lambert interception based on differential corrector[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2009, 29 (5): 87- 90.
23	雷虎民, 李炯, 胡小江, 等. 导弹制导与控制原理[M]. 北京: 国防工业出版社, 2018.
	LEI H M , LI J , HU X J , et al. Theory of guidance and control for missile[M]. Beijing: National Defense Industry Press, 2018.
24	张洪波. 航天器轨道力学理论与方法[M]. 北京: 国防工业出版社, 2015.
	ZHANG H B . Theories and methods of spacecraft orbital mechanics[M]. Beijing: National Defense Industry Press, 2015.

初始速度v₀/(m/s)	终端偏差A/km	全过程偏差B/km
2 000	0.797	0.147
2 200	0.849	0.170
2 400	0.901	0.195
2 600	0.957	0.222
2 800	1.015	0.252
3 000	1.077	0.284
3 200	1.141	0.319
3 400	1.210	0.357

初始倾角?₀/(°)	制导误差/km	开机时长/s
0	0.001 36	50.8
3	0.003 29	46.1
5	0.003 28	43.6
10	0.004 72	39.8
15	0.004 14	40.7
20	0.003 57	45.9
25	0.008 94	53.9

[1]	张君彪, 熊家军, 兰旭辉, 李凡, 刘文俭, 席秋实. 基于自适应滤波的高超声速滑翔目标三维跟踪算法[J]. 系统工程与电子技术, 2022, 44(2): 628-636.
[2]	张博伦, 周荻, 吴世凯. 临近空间高超声速飞行器机动模型及弹道预测[J]. 系统工程与电子技术, 2019, 41(9): 2072-2079.
[3]	潘媚媚, 曹运合, 王宇, 吴文华. 基于机动判别的变结构交互多模型跟踪算法[J]. 系统工程与电子技术, 2019, 41(4): 730-736.
[4]	毛柏源, 李君龙, 张锐. 考虑自动驾驶仪动态特性的多约束中制导律[J]. 系统工程与电子技术, 2019, 41(2): 382-388.
[5]	吕寿坤, 周荻, 孟克子, 王子才. 视线角约束自适应滑模中制导律[J]. 系统工程与电子技术, 2018, 40(4): 855-859.
[6]	郭建国, 张添保, 周军, 王国庆. 临近空间高超声速飞行器匹配化滑模姿态控制[J]. 系统工程与电子技术, 2017, 39(9): 2081-2086.
[7]	秦雷, 周荻, 李君龙. 临近空间非弹道式目标跟踪修正变结构滤波[J]. 系统工程与电子技术, 2017, 39(7): 1582-1589.
[8]	聂晓华, 张夫鸣, 徐一鸣. NSHV机动目标跟踪的自适应模型算法[J]. 系统工程与电子技术, 2016, 38(3): 506-511.
[9]	雷虎民1, 周觐1, 翟岱亮1, 张大元2, 王华吉1, 李宁波1. 基于二阶变分的中制导最优弹道修正[J]. 系统工程与电子技术, 2016, 38(12): 2807-2813.
[10]	孟克子, 周荻. 多约束条件下的最优中制导律设计[J]. 系统工程与电子技术, 2016, 38(1): 116-122.
[11]	秦雷1, 李君龙1, 周荻2. 基于AGIMM的临近空间机动目标跟踪滤波算法[J]. 系统工程与电子技术, 2015, 37(5): 1009-1014.
[12]	秦雷1，李君龙1，周荻2. 基于交互式多模型算法跟踪临近空间目标[J]. 系统工程与电子技术, 2014, 36(7): 1243-1249.
[13]	杨一，高社生，阎海峰. 临近空间伪卫星几何布局方案设计[J]. 系统工程与电子技术, 2014, 36(3): 532-538.
[14]	郭超, 梁晓庚, 王俊伟. 基于非线性干扰观测器的拦截弹动态逆控制[J]. 系统工程与电子技术, 2014, 36(11): 2259-2265.
[15]	潘彦鹏，周　军，呼卫军. 临近空间飞行器再入段复合控制律设计[J]. 系统工程与电子技术, 2013, 35(11): 2364-2369.

基于二体理论的远程拦截中制导修正

Mid-course guidance modification of super-range interception based on two body theory

RichHTML

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

图/表 11

参考文献 24

相关文章 15

编辑推荐

Metrics

本文评价