带热流密度限制的推力可控导弹三维制导律

传统三维制导律设计通常将三维空间分成垂直面和水平面分别考虑, 容易导致耦合信息的缺失, 同时没有考虑导弹红外导引头对导弹头部热流密度的限制和终端速度约束。针对以上问题, 基于具有推力可控能力的导弹, 在视线旋转坐标系的视线瞬时旋转平面内进行制导律设计。该制导律包含根据运动伪装理论设计的一种新的满足运动伪装条件的视线法方向加速度指令, 以及通过变系数加权法综合考虑导引头热流密度限制及终端速度约束的视线方向加速度指令。数值仿真结果表明了存在导引头初始对准误差时, 该制导律在满足红外导引头对导弹头部的热流密度限制、终端速度约束以及轴向过载限制下对高速机动目标制导性能良好, 视线角速率可控制在3 ( °)/s以下, 具有一定的工程应用价值。

Abstract

The traditional three-dimensional guidance law generally divides three-dimensional space into vertical plane and horizontal plane respectively, which may lead to the lack of coupling information. It also doesn′t take heat flux of infrared seeker and constraint of terminal velocity into account. To solve this problem, a guidance law based on the missile of adjustable thrust was proposed in the instantaneous rotary line-of-sight plane of rotary line-of-sight frame. The acceleration instruction in the direction of perpendicular to line-of-sight was designed to satisfy the criterion of motion camouflage strategy. Meanwhile, an overload instruction in the direction of line-of-sight was built with variable weighted change rate of heat flux limit and ideal overload which can satisfy the constraint of terminal velocity. Simulation results demonstrate that the designed guidance law has a good performance with the heat flux limit of infrared seeker, constraint of terminal velocity and available axial overload limit when attacking the high maneuvering target and initial misalignments of infrared seeker exists. The rate of line-of-sight is under 3 ( °)/s, so it has certain engineering application value.

参考文献

[1] 陈阳, 储海荣, 郭立红. 捷联导引头积分比例导引制导精度[J]. 红外与激光工程, 2016, 45(6): 0631001.

Chen Yang, Chu Hairong, Guo Lihong. Precision of integral proportion navigation guidance with strapdown seeker [J]. Infrared and Laser Engineering, 2016, 45(6): 0631001. (in Chinese)

[2] 臧路尧, 侯淼, 王辉, 等. 一种适用于红外制导弹药的变增益比例导引律[J]. 红外与激光工程, 2017, 46(5): 0504004.

Zang Luyao, Hou Miao, Wang Hui, et al. A switched-gain proportional navigation applicable for infrared guidance munitions [J]. Infrared and Laser Engineering, 2017, 46(5): 0504004. (in Chinese)

[3] Wei X, Wang Y, Dong S, et al. A three-dimensional cooperative guidance law of multimissile system [J]. International Journal of Aerospace Engineering, 2015(4): 1-8.

[4] 叶继坤, 雷虎民, 赵岩, 等. 基于二阶滑模控制的微分几何制导律[J]. 系统工程与电子技术, 2017, 39(4): 837-845.

Ye Jikun, Lei Humin, Zhao Yan, et al. Differential geometric guidance law based on second-order sliding control [J]. Systems Engineering and Electronic, 2017, 39(4): 837-845. (in Chinese)

[5] Li K B, Chen L, Bai X Z. Differential geometric modeling of guidance problem for interceptors [J]. Sci China Tech, 2011, 54(9): 2283-2295.

[6] Hughes R. Wielding a Bigger Stick: Western advances in BVRAAM capabilities [J]. Jane′s International Defence Review, 2016, 49(7): 50-55.

[7] Halswijk W. Online dynamic flight optimisation applied to guidance of a variable-flow ducted rocket [C]// AIAA Guidance, Navigation, and Control Conference, 2009: 1-14.

[8] Kingery J E, Ames F E. Stagnation region heat transfer augmentation at very high turbulence levels [J]. Journal of Turbomachinery, 2016, 138(8): 1-12.

[9] 关英姿. 整流罩气动加热对红外成像系统像质的影响[J].红外与激光工程, 2013, 42(2): 290-293.

Guan Yingzi. Effort of pneumatic calefaction of the dome on IR imaging system quality [J]. Infrared and Laser Engineering, 2013, 42(2): 290-293. (in Chinese)

[10] 王锐. 激光红外主被动复合导引系统[J]. 中国光学, 2013, 6(4): 536-543.

Wang Rui. Compound guided system with active laser imaging and passive infrared imaging [J]. Chinese Optics, 2013, 6(4): 536-543. (in Chinese)

[11] 李佳峰, 姜欢, 陈万春. 基于拟勒让德谱变换的防空导弹弹道优化[J]. 弹道学报, 2009, 21(3): 69-73.

Li Jiafeng, Jiang Huan, Chen Wanchun. Midcourse trajectory optimization design for a surface-to-air missile based on legendre pseudospectral method [J]. Journal of Ballistics, 2009, 21(3): 69-73. (in Chinese)

[12] Ebrahimi B, Bahrami M, Roshanian J. Optimal sliding-mode guidance with terminal velocity constraint for fixed-interval propulsive maneuvers [J]. Acta Astronautica, 2008, 62(10):556-562.

[13] Justh E W, Krishnaprasad P S. Steering laws for motion camouflage [J]. Proceeding of the Royal Society A: Mathematical Physical and Engineering Science, 2005, 462(2076): 3629-3643.

[14] Reddy P V, Justh E W, Krishnaprasad P S. Motion camouflage in three dimensions [C]// IEEE Conference on Decision & Control, 2006: 13-15.

[15] 高长生, 李涧青, 荆武兴. 拦截机动目标的运动伪装制导律[J]. 宇航学报, 2016, 37(6): 737-743.

Gao Changsheng, Li Jianqing, Jing Wuxing. Motion camouflage strategy guidance law for intercepting maneuvering target [J]. Journal of Astronautics, 2016, 37(6): 737-743. (in Chinese)

[16] 郭宁, 吕俊伟, 邓江生. 光电跟踪系统纯角度滤波器的设计[J]. 光学精密工程, 2013, 21(7): 1818-1824.

Guo Ning, Lv Junwei, Deng Jiangsheng. Design of filter only by angle information in opto-electronic tracking system [J]. Optics and Precision Engineering, 2013, 21(7): 1818-1824. (in Chinese)

[17] 李涧青. 远程空空导弹复合制导与控制研究[D]. 哈尔滨: 哈尔滨工业大学, 2014: 56-61.

Li Jianqing. Study on compound guidance and control problems for long-range air to air missile [D]. Harbin: Harbin Institute of Technology, 2014: 56-61. (in Chinese)

王宏涛, 石德平, 刘恒军. 带热流密度限制的推力可控导弹三维制导律[J]. 红外与激光工程, 2018, 47(3): 0304004. Wang Hongtao, Shi Deping, Liu Hengjun. Three-dimensional guidance law for missile of adjustable thrust with heat flux limit[J]. Infrared and Laser Engineering, 2018, 47(3): 0304004.

带热流密度限制的推力可控导弹三维制导律

关于本站 Cookie 的使用提示

全站搜索

带热流密度限制的推力可控导弹三维制导律

相关论文

相关资讯

关于本站 Cookie 的使用提示

全站搜索