具有碰撞角约束的三维圆轨迹制导律

电子与自动控制

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

具有碰撞角约束的三维圆轨迹制导律

胡锡精, 黄雪梅

北京控制与电子技术研究所, 北京 100038

收稿日期:2011-06-13 修回日期:2011-08-19 出版日期:2012-03-25 发布日期:2012-03-24
通讯作者: 胡锡精 E-mail:hu_xijing@163.com

Three-dimensional Circular Guidance Law with Impact Angle Constraints

HU Xijing, HUANG Xuemei

Beijing Institute of Control and Electronic Technology, Beijing 100038, China

Received:2011-06-13 Revised:2011-08-19 Online:2012-03-25 Published:2012-03-24

摘要/Abstract

摘要： 针对再入飞行器带碰撞角约束的导引问题,设计了一种新型三维(3D)制导律。改进并扩展了圆轨迹导引算法,定义了2个圆轨迹跟踪误差变量。通过对导引任务的分析,提出闭环修正导引方法。在此基础上,对再入飞行器制导过程的动力学方程进行解析推导,设计出能适应再入飞行器速度大小变化的三维闭环圆轨迹制导律(3CCGL)。数学仿真结果表明:此制导律能导引再入飞行器沿终端约束方向精确命中目标;同已有算法相比,该制导算法优势明显,其导引的飞行路径短,终端碰撞速度大,并能实现大角度转向攻击,大幅提高再入飞行器的末段机动能力。

关键词: 再入, 制导律, 三维空间, 圆轨迹导引, 碰撞角约束, 闭环修正

Abstract: A novel three-dimensional (3D) guidance law is proposed for a reentry vehicle with impact angle constraints. To make the circular guidance more applicable, two deviation variables are defined. Then a closed-loop modification method is presented for the mission. Furthermore, a 3D closed-loop circular guidance law (3CCGL) for varying velocities is derived by solving the dynamical equations of the reentry vehicle. The simulation results demonstrate that the 3CCGL can assure the reentry vehicle to impact the target accurately from a specified direction. Compared with another law from the literature, the proposed guidance law is shown to perform favorably with shorter path length, larger terminal velocity and great improvement in the terminal maneuverability of the reentry vehicle in a large-angle turning engagement scenario.

Key words: reentry, guidance law, 3D space, circular navigation, impact angle constraints, closed-loop modification

中图分类号:

V448

胡锡精, 黄雪梅. 具有碰撞角约束的三维圆轨迹制导律[J]. 航空学报, 2012, (3): 508.

HU Xijing, HUANG Xuemei. Three-dimensional Circular Guidance Law with Impact Angle Constraints[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, (3): 508.

参考文献

[1] Hu Z D, Guo C F, Cai H. Integrated guidance law of reentry maneuvering warhead with terminal angular constraint. Journal of National University of Defense Technology, 2008, 30(3): 21-26. (in Chinese) 胡正东, 郭才发, 蔡洪. 带落角约束的再入机动弹头的复合导引律. 国防科技大学学报, 2008, 30(3): 21-26.

[2] Lu P, Doman D B, Schierman J D. Adaptive terminal guidance for hypervelocity impact in specified direction. Journal of Guidance, Control, and Dynamics, 2006, 29(2): 269-278.

[3] Ratnoo A, Ghose D. Impact angle constrained interception of stationary targets. Journal of Guidance, Control, and Dynamics, 2008, 31(6): 1817-1822.

[4] Ratnoo A, Ghose D. Impact angle constrained guidance against nonstationary nonmaneuvering targets. Journal of Guidance, Control, and Dynamics, 2010, 33(1): 269-275.

[5] Chen X L, Hua W H. Ground target interception proportional navigation law with terminal constraints. Journal of Ballistics, 2010, 22(2): 15-18. (in Chinese) 陈兴林, 花文华. 具有终端约束的地面目标拦截比例导引. 弹道学报, 2010, 22(2): 15-18.

[6] Lee Y I, Ryoo C K, Kim E. Optimal guidance with constraints on impact angle and terminal acceleration. AIAA-2003-5795, 2003.

[7] Ryoo C K, Cho H, Tahk M J. Optimal guidance laws with terminal impact angle constraint. Journal of Guidance, Control, and Dynamics, 2005, 28(4): 724-732.

[8] Ryoo C K, Cho H, Tahk M J. Time-to-go weighted optimal guidance with impact angle constraints. IEEE Transactions on Control Systems Technology, 2006, 14(3): 483-492.

[9] Shaferman V, Shima T. Linear quadratic differential games guidance law for imposing a terminal intercept angle. AIAA-2008-7302, 2008.

[10] Shaferman V, Shima T. Linear quadratic guidance laws for imposing a terminal intercept angle. Journal of Guidance, Control, and Dynamics, 2008, 31(5): 1400-1412.

[11] Ohlmeyer E J, Phillips C A. Generalized vector explicit guidance. Journal of Guidance, Control, and Dynamics, 2006, 29(2): 261-268.

[12] Han D P, Sun W M, Zheng Z Q, et al. A new 3D guidance law based on Lie-group method. Acta Aeronautica et Astronautica Sinica, 2009, 30(3): 468-475. (in Chinese) 韩大鹏, 孙未蒙, 郑志强, 等. 一种基于李群方法的新型三维制导律设计. 航空学报, 2009, 30(3): 468-475.

[13] Harl N, Balakrishnan S N. Impact time and angle guidance with sliding mode. AIAA-2009-5897, 2009.

[14] Ratnoo A, Ghose D. SDRE based guidance law for impact angle constrained trajectories. AIAA-2007-6539, 2007.

[15] Ratnoo A, Ghose D. State-dependent Riccati-equation-based guidance law for impact-angle-constrained trajectories. Journal of Guidance, Control, and Dynamics, 2009, 32(1): 320-325.

[16] Manchester I R, Savkin A V. Circular navigation missile guidance with incomplete information and uncertain autopilot model. AIAA-2003-5448, 2003.

[17] Manchester I R, Savkin A V. Circular navigation guidance law for precision missile/target engagements. Journal of Guidance, Control, and Dynamics, 2006, 29(2): 314-320.

[18] Lam V C. Circular guidance laws with and without terminal velocity direction constraints. AIAA-2008-7304, 2008.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

具有碰撞角约束的三维圆轨迹制导律

Three-dimensional Circular Guidance Law with Impact Angle Constraints

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	郑昊, 唐勇, 陈湘男, 李霁, 林志强, 石保禄. 液体火箭反推进再入过程底部热环境与流动特性[J]. 航空学报, 2026, 47(8): 132772-132772.
[2]	赵耀, 张曦, 周荻, 李玉堂, 李思远. 考虑主动远离禁飞区的飞行器再入轨迹快速规划[J]. 航空学报, 2026, 47(6): 332509-332509.
[3]	胡庆雷, 张姝新, 韩拓, 王青云. 相对距离剖面高阶重塑的多约束末制导律[J]. 航空学报, 2025, 46(6): 531405-531405.
[4]	闫循良, 王培臣, 郭杨. 再入滑翔机动突防轨迹规划与制导方法综述[J]. 航空学报, 2025, 46(17): 331810-331810.
[5]	贺杨超, 李炯, 邵雷, 卜祥伟, 张锦林, 姬博洋. 基于改进“当前”统计模型的再入目标跟踪算法[J]. 航空学报, 2024, 45(S1): 730800-730800.
[6]	万清橙, 余萌, 李玉报, 王寅. 逆轨拦截的目标命中点分支预测智能制导算法[J]. 航空学报, 2024, 45(S1): 730873-730873.
[7]	王培臣, 闫循良, 李新国, 王子安. 考虑时间约束的解析再入滑翔制导[J]. 航空学报, 2024, 45(23): 329844-329844.
[8]	白显宗, 黎克波, 李昊键, 董伟. 基于固定时间收敛误差动力学的微分几何制导律设计[J]. 航空学报, 2024, 45(16): 329712-329712.
[9]	刘哲, 张羲格, 韦常柱, 崔乃刚. 亚轨道飞行器再入轨迹高精度自适应凸规划[J]. 航空学报, 2023, 44(S2): 729430-729430.
[10]	吴紫怡, 何绍溟, 王亚东, 李虹言. 针对运动目标的可观性增强非线性最优制导律[J]. 航空学报, 2023, 44(S2): 729750-729750.
[11]	徐世昊, 关英姿, 浦甲伦, 韦常柱. VTHL运载器再入返回预设时间滑模控制[J]. 航空学报, 2023, 44(7): 326857-326857.
[12]	盛永智, 甘佳豪, 张成新. 弹道可调的落角约束分数阶滑模制导律设计[J]. 航空学报, 2023, 44(7): 327073-327073.
[13]	王因翰, 范世鹏, 吴广, 王江, 何绍溟. 基于GRU的敌方拦截弹制导律快速辨识方法[J]. 航空学报, 2022, 43(2): 325024-325024.
[14]	周印佳, 张志贤, 付新卫, 阿嵘. 再入飞行器烧蚀热防护一体化计算方法[J]. 航空学报, 2021, 42(7): 124520-124520.
[15]	刘哲, 陆浩然, 郑伟, 闻国光, 王奕迪, 周祥. 多滑翔飞行器时间协同轨迹快速规划[J]. 航空学报, 2021, 42(11): 524497-524497.