| 导引头隔离度对开关控制制导回路稳定性的影响 |
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| 引用本文： | 刘俊辉,贾庆忠,单家元. 导引头隔离度对开关控制制导回路稳定性的影响[J]. 宇航学报, 2016, 37(3): 298-306. DOI: 10.3873/j.issn.1000-1328.2016.03.008 |
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| 作者姓名： | 刘俊辉 贾庆忠 单家元 |
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| 作者单位： | 北京理工大学宇航学院飞行器动力学与控制教育部重点实验室, 北京100081 |
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| 基金项目： | 国家自然科学基金（61203064） |
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| 摘 要： | 为研究导引头隔离度寄生回路对开关控制制导回路稳定性的影响，首先应用回路等价变换原理统一了动力陀螺式和速率陀螺式导引头模型；然后，为分析开关系统稳定性，建立了含有隔离度寄生回路的开关控制制导回路等效Lure’模型；对比得出描述函数法在系统稳定保守性和稳定性趋势预测方面优于Popov稳定性理论和仿真方法，因此提出应用描述函数法对寄生回路稳定性进行分析。分析了在不同飞行器参数和调制器参数下导线和摩擦干扰力矩对寄生回路稳定域的影响。进一步，针对不稳定寄生回路提出了采用滞后校正网络来改善系统稳定性，改善后的制导回路仿真结果表明在外界干扰作用下，回路中不会再出现极限环，避免了脉冲喷管的“正反开”；飞行器机动跟踪目标时，保证制导精度基本不变的情况下，节省了燃料。
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| 关 键 词： | 导引头隔离度 寄生回路 极限环 Popov稳定性 描述函数 滞后校正 |
| 收稿时间： | 2015-04-12 |
Effect of Seeker Disturbance Rejection Rate on Stability of On Off Control Guidance Loop |
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| LIU Jun hui,JIA Qing zhong,SHAN Jia yuan. Effect of Seeker Disturbance Rejection Rate on Stability of On Off Control Guidance Loop[J]. Journal of Astronautics, 2016, 37(3): 298-306. DOI: 10.3873/j.issn.1000-1328.2016.03.008 |
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| Authors: | LIU Jun hui JIA Qing zhong SHAN Jia yuan |
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| Affiliation: | Key Laboratory of Dynamics and Control of Flight Vehicle of Ministry of Education, School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China |
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| Abstract: | The influence of seeker’s disturbance rejection rate on the stability of on-off guidance loop is analyzed. Firstly, a unified dynamics model for gyro-stabilized seeker and rate-gyro seeker is established by using equivalent transformation principle of loop. And then, equivalent Lure’ model of on-off guidance loop with the isolation parasitic loop is built to analyze the stability of the on-off control system. It is concluded from comparisons that the describing function method is superior to Popov theory and simulation method in the aspects of system conservation and stability trend predication. So, the describing function method is utilized to analyze the stability of the parasitic loop. Furthermore, the influence of cable torque and friction torque on the stable range of parasitic loop under parameters of different vehicles and modulators is obtained. Finally, the lag compensation method is put forward for unstable parasitic loop to improve system’s stability. Simulation results show that the limit cycle is not appeared again in the guidance loop under the vehicle’s attitude disturbance. It avoids pulsed thruster repeatly switching. And, when the vehicle maneuvers to a track target, it saves fuel and assures the guidance accuracy simultaneously. |
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