考虑扰动及控制饱和的多约束末制导方法
收稿日期: 2013-11-11
修回日期: 2014-01-23
网络出版日期: 2014-02-10
基金资助
国家自然科学基金委创新研究群体科学基金（61021002）；中央高校基本科研业务费专项资金（HIT.NSRIF.2014036）；重点实验室开放基金（HIT.KLOF.2013081）
Terminal Guidance Method with Multiple Constraints in the Presence of Disturbances and Control Saturation
Received date: 2013-11-11
Revised date: 2014-01-23
Online published: 2014-02-10
Supported by
Innovative Team Program of the National Natural Science Foundation of China (61021002); the Fundamental Research Funds for the Central Universities (HIT.NSRIF.2014036); the Opening Funding of the National Key Laboratory of Science and Technology (HIT.KLOF.2013081)
在末制导阶段，飞行器受到建模误差、风、目标运动等多种扰动的影响，且导引头视场、攻角及落角受到约束。为此，提出一种多约束及扰动下的末制导方法。将制导问题转化为存在扰动与控制饱和的系统的镇定问题。设计低增益状态反馈律镇定系统，利用线性扩张状态观测器观测系统中的扰动并在反馈律中对其进行补偿。以此为基础推导得到末制导律。基于Lambert W函数研究制导律参数对视线角收敛的影响，并提出制导律参数的自适应整定方法。通过在线调整制导律参数，保证全部约束得到满足。在多种扰动下，通过数值仿真验证提出的制导方法。仿真结果表明，制导律满足所有约束且获得的制导精度较高。
董晨 , 晁涛 , 王松艳 , 杨明 . 考虑扰动及控制饱和的多约束末制导方法[J]. 航空学报, 2014 , 35(8) : 2225 -2233 . DOI: 10.7527/S1000-6893.2013.0531
In the terminal guidance phase, a vehicle is subject to various disturbances, such as modeling error, wind, and target movement. Moreover, the seeker's field-of-view, attack angle, and impact angle are constrained. To guide the vehicle under these conditions, a guidance method under multiple constraints and disturbances is proposed. The guidance problem is transformed to a stabilization problem of a system with control saturation and disturbance. A low-gain state feedback law with disturbance compensation is designed to stabilize the system, and a linear extended state observer is used to estimate the disturbance. Then, a terminal guidance law is derived. Using Lambert W function, effects of the guidance law parameters on the convergence of the line-of-sight angle are investigated. Moreover, an adaptive parameter regulation method is presented to adjust the guidance law parameters online. The proposed guidance method is demonstrated by numerical simulation under various disturbances. All the constraints are observed and high guidance precision is achieved.
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