基于简化模型的天线罩寄生回路稳定性分析

doi:10.12305/j.issn.1001-506X.2023.06.22

摘要/Abstract

摘要：

针对由天线罩误差引起的寄生回路影响制导系统稳定性的问题，提出了基于状态空间简化模型的天线罩寄生回路稳定性分析方法。为了准确分析天线罩误差特性对制导系统稳定性的影响，首先建立包含天线罩误差特性的导引头部件级模型，并采用低阶等效系统拟配方法建立导引头简化模型。该简化模型能够准确表征导引头的工作特性, 并有效降低了制导回路状态空间简化模型的阶数；在此基础上，采用小扰动线性化方法建立制导/控制/弹体多回路线性时不变(linear time invariant, LTI)简化模型，并与导引头低阶等效模型结合，建立了包含天线罩误差斜率参数的制导回路, 以简化模型状态空间描述形式。基于以上引入天线罩误差特性的制导回路状态空间模型，采用根轨迹方法分析确定了天线罩误差斜率的稳定域，分析了不同的天线罩误差斜率对制导系统稳定性的影响规律。最后，基于制导回路非线性模型进行仿真验证，仿真结果验证了基于简化模型的天线罩寄生回路稳定性分析方法的正确性。

关键词: 天线罩误差, 寄生回路, 制导回路, 简化模型, 稳定性分析

Abstract:

Aiming at the problem that the parasitic loop caused by radome error affects the stability of guidance system, a method of stability analysis of radome parasitic loop based on state space simplified model is proposed. In order to accurately analyze the influence of radome error characteristics on the stability of the guidance system, firstly a seeker-component-level model containing radome error is established and low-order equivalent system watching method is adopted to establish the simplified seeker model. The simplified model can accurately express the working character of seeker and effectively reduce the order of state space simplified model of guidance loop. On this basis, establishing the guidance/control/missile multi-loop linear time invariant (LTI) simplified model by using the small disturbance linearization method and combining with the low-order equivalent model of the seeker, the state space description of the guidance loop simplified model with radome error slope parameter is established. Based on the state space model of guidance loop with radome error characteristics introduced above, the stable region of radome error slope is analyzed and shaped by using root locus method, and the influence rule of different radome error slope on the stability of guidance system is analyzed. Finally, the simulation results verify the correctness of the stability analysis method of radome parasitic loop based on the simplified model.

Key words: radome error, parasitic loop, guidance loop, simplified model, stability analysis

中图分类号:

V249.12

陈旭, 肖瑶, 杨凌宇, 张晶. 基于简化模型的天线罩寄生回路稳定性分析[J]. 系统工程与电子技术, 2023, 45(6): 1784-1796.

Xu CHEN, Yao XIAO, Lingyu YANG, Jing ZHANG. Stability analysis of radome parasitic loop based on simplified model[J]. Systems Engineering and Electronics, 2023, 45(6): 1784-1796.

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参考文献 32

1	PALUMBON F , BLAUWKAMP R A , LIOYD J M . Basic principles of homing guidance[J]. Johns Hopkins APL Technical Digest, 2010, 29 (1): 25- 41.
2	LIN C L . Stability analysis of radome error and calibration using neural networks[J]. IEEE Trans.on Aerospace and Electronic Systems, 2001, 37 (4): 1442- 1450. doi: 10.1109/7.976979
3	LIN J M, LIN C H. Intelligent fuzzy terminal guidance law for high altitude air defense by taking turning rate and radome error slope into consideration[C]//Proc. of the 6th IEEE Conference on Industrial Electronics and Applications, 2011: 723-727.
4	MIHAITA A, GHEORGHE G. The influence of radome on radar antennas system[C]//Proc. of the 9th International Confe-rence on Communications, 2012: 151-154.
5	NESLINE F W , ZARCHAN P . Missile guidance design tradeoffs for high-altitude air defense[J]. Journal of Guidance, Control, and Dynamics, 1983, 6 (3): 39- 47.
6	NESLINEF W, ZARCHAN P. Radome induced miss-distance inaero dynamically controlled homing missiles[C]//Proc. of the AIAA Guidance & Control Conference, 1984.
7	NESLINE F W , ZARCHAN P . Line-of-sight reconstruction for faster homing guidance[J]. Journal of Guidance, Control, and Dynamics, 1985, 8 (1): 3- 8. doi: 10.2514/3.19927
8	SUSUMU M . Radome effect on the missdistance of a radar homing missile[J]. Electronics and Communications in Japan, 1998, 83 (7): 14- 22.
9	宗睿, 林德福, 兰玲, 等. 考虑天线罩误差的雷达导引头隔离度影响与UKF在线补偿[J]. 北京理工大学学报, 2016, 36 (12): 1269- 1278. doi: 10.15918/j.tbit1001-0645.2016.12.012
	ZONG R , LIN D F , LAN L , et al. Influence of radar seeker disturbance rejection rate with radome error and on-line compensation with UKF[J]. Transactions of Beijing Institute of Technology, 2016, 36 (12): 1269- 1278. doi: 10.15918/j.tbit1001-0645.2016.12.012
10	宋建梅, 蔡高华. 半捷联寻的导引头寄生回路稳定性分析与制导精度分析[J]. 宇航学报, 2014, 35 (5): 554- 563.
	SONG J M , CAI G H . Stability region analysis of the parasitical loop and guidance accuracy analysis of the semi-strapdown homing seeker[J]. Journal of Astronautics, 2014, 35 (5): 554- 563.
11	廖志忠, 王琪. 雷达导引头指向误差对导弹制导的影响与对策[J]. 系统工程与电子技术, 2021, 43 (2): 519- 525.
	LIAO Z Z , WANG Q . Influence and countermeasures of radar seeker pointing error on missile guidance[J]. Systems Engineering and Electronics, 2021, 43 (2): 519- 525.
12	WANG Q, LIAO Z Z, YAN F. Phased array radar seeker pointing error compensation using multiple-model extended Kalman filters[C]//Proc. of the 40th Chinese Control Conference, 2021.
13	CHEN K W , XIA Q L , DU X , et al. Influence of seeker disturbance rejection and radome error on the Lyapunov stability of guidance systems[J]. Mathematical Problems in Engineering, 2018, 2018, 1890426.
14	TIAN S , LIN D F , WANG J , et al. Dynamic stability of rolling missiles with angle-of-attack feedback three-loop autopilot considering parasitic effect[J]. Aerospace Science and Technology, 2017, 71, 592- 602. doi: 10.1016/j.ast.2017.10.023
15	EKSTRAND B . Equation of motion for a two-axes gimbal system[J]. IEEE Trans.on aerospace and electronic systems, 2001, 37 (3): 1083- 1091. doi: 10.1109/7.953259
16	JANG S A, RYOO C K, CHOI K Y, et al. Guidance algorithms for tactical missiles with strapdown seeker[C]//Proc. of the Society of Instrument and Control Engineers Annual Conference, 2008: 2616-2619.
17	ABDO M M , VALI A R , TOLOEI A R , et al. Stabilization loop of a two axes gimbal system using self-tuning PID type fuzzy controller[J]. ISA Transactions, 2014, 53 (2): 591- 602. doi: 10.1016/j.isatra.2013.12.008
18	雷虎民. 导弹制导与控制原理[J]. 战术导弹控制技术, 2007, 15 (1): 162- 164. doi: 10.3969/j.issn.1009-1300-B.2007.01.042
	LEI H M . Theory of guidance and control for missile[J]. Control Technology of Tactical Missile, 2007, 15 (1): 162- 164. doi: 10.3969/j.issn.1009-1300-B.2007.01.042
19	MURRAY T. Correlation of linear and nonlinear radome error induced miss distance predictions[C]//Proc. of American Control Conference, 1984.
20	KLEIN I , RUSNAK I . Loop-shaping approach to mitigate radome effects in homing missiles[J]. Journal of Guidance, Control and Dynamics, 2017, 40 (7): 1787- 1793.
21	KESHMIRI S, COLGREN R, MIRMIRANI M. Six DoF nonlinear equations of motion for a generic hypersonic vehicle[C]//Proc. of the AIAA Atmospheric Flight Mechanics Conference and Exhibit, 2007.
22	ZHANG L X , NIE L , CAI B , et al. Switched linear parameter-varying modeling and tracking control for flexible hypersonic vehicle[J]. Aerospace Science and Technology, 2019, 95, 105445. doi: 10.1016/j.ast.2019.105445
23	SRIDHARAN S, ECHOLS J A, RODRIGUEZ A A, et al. Integrated design and control of hypersonic vehicles[C]//Proc. of the American Control Conference, 2014.
24	陈禹六. 大系统理论及应用[M]. 北京: 清华大学出版社, 1992.
	CHEN Y L . Largescale systems theory and application[M]. Beijing: Tsinghua University Press, 1992.
25	BAKER J G , GRAVES P R . Pade approximants, part I: basic theory[M]. America: Addsion-Wesley Publishing Company, 1981.
26	MARY F S . Low-order equivalent models of highly augmented aircraft determined from flight data[J]. Journal of Guidance, Control, and Dynamics, 1982, 5 (5): 504- 511.
27	HODGKINSON J . History of low-order equivalent systems for aircraft flying qualities[J]. Journal of Guidance, Control, and Dynamics, 2005, 28 (4): 577- 583.
28	HODGKINSON J, PALOS V. History of low order equivalent systems for aircraft handing qualities analysis and design[C]//Proc. of the AIAA Atmospheric Flight Mechanics Conference and Exhibit, 2003.
29	EUDENE A . Low-order equivalent system identification for the Tu-144LL supersonic transport aircraft[J]. Journal of Guidance, Control, and Dynamics, 2003, 26 (2): 354- 362.
30	丛斌, 王立新. 飞翼布局飞机低阶等效拟配方法[J]. 北京航空航天大学学报, 2018, 44 (2): 286- 294.
	CONG B , WANG L X . Low-order equivalent matching methods for aircraft with flying wings[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44 (2): 286- 294.
31	杜运理, 夏群力, 蔡春涛. 雷达导引头天线罩误差对制导精度影响研究[J]. 弹箭与制导学报, 2010, 30 (5): 79- 82.
	DU Y L , XIA Q L , CAI C T . The study on miss distance of radar seeker guided missile due to radome slope error[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2010, 30 (5): 79- 82.
32	高建军, 白云. 雷达导引头伺服系统的建模与仿真研究[J]. 战术导弹技术, 2009, (2): 67- 70.
	GAO J J , BAI Y . Modeling and simulation research on servo system of radar seeker[J]. Tactical Missile Technology, 2009, (2): 67- 70.

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