[author_cn_name].[cn_title][J].空军工程大学学报:自然科学版,[year_id],[volume]([issue]):[start_page]-[end_page] 基于线性二次型高斯(LQG)理论的最优制导规律-An Optimal Guidance Law Based on Linear Quadratic Gaussian (LQG) Theory
文章摘要
雷虎民,梁颖亮,杨强国.基于线性二次型高斯(LQG)理论的最优制导规律[J].空军工程大学学报:自然科学版,2002,(2):27-30
基于线性二次型高斯(LQG)理论的最优制导规律
An Optimal Guidance Law Based on Linear Quadratic Gaussian (LQG) Theory
  
DOI:
中文关键词: 线性二次型高斯  最优制导规律  比例导引规律  战术导弹
英文关键词: linear quadratic Gaussian (LQG)  optimal guidance law  proportional navigation (PN)  tactical missile
基金项目:
作者单位
雷虎民,梁颖亮,杨强国 1.西安交通大学电信学院陕西西安710049 2.空军工程大学导弹学院陕西三原713800 3.陕西新华书店陕西西安710003 
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中文摘要:
      以线性二次型高斯(LQG)理论为基础,研究一种最小化末端脱靶量和拦截周期内控制能量消耗的具有可变有效导航比的LQG最优制导规律。分析了这种制导规律的有效导航比及其在战术导弹上的应用。应用伴随方法对这种制导规律进行制导性能仿真计算。结果表明:这种制导规律的控制精度高、机动过载要求小。
英文摘要:
      Based on linear quadratic Gaussian (LQG) theory, this paper shows a study of a LQG optimal guidance law that minimizes the terminal miss distance and control energy consumption within the intercepting period. This paper also gives an analysis of the law's effective navigation ratio and these ratio's applications to the tactical missiles. The results obtained by using adjoint methods show that the optimal LQG guidance law has an advantage over the traditional one in control accuracy and maneuver overload.
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