飞行器随机控制系统参数辨识估计方法
发布时间：2018-11-16 12:23
【摘要】：为了使飞行器能够准确的进入预定轨道运行,在飞行器的方案设计阶段,迫切需要我们对飞行器随机控制系统应用系统参数辨识估计。飞行器飞行试验实测数据估算及飞行器轨道参数的轨迹参数辨识技术已越来越为人们所接受和重视,并已成为确定飞行器飞行轨道特性的一个重要手段。它不仅能为飞行器设计提供反映实际飞行特性和外部环境的轨道数学模型,且可以验证理论计算结果并修正地面试验数据结果。因此,对飞行器轨道参数辨识方法的探讨有着重大的理论意义和实际价值。本文主要研究两方面内容,其一,基于最小二乘法在航天器随机控制系统轨道运行过程中进行参数辨识,其二,基于卡尔曼滤波理论在多管火箭弹导航随机控制系统进行参数辨识,基本步骤如下:(1)基于最小二乘法精确先验参数估计方法研究(2)建立航天器随机控制系统质心模型;(3)最小二乘法在随机控制系统参数辨识的应用;(4)基于卡尔曼滤波连续线性、非线性扩展的滤波理论研究;(5)建立多管火箭弹随机控制系统模型;(6)基于拟线性卡尔曼滤波的多管火箭弹初始状态确定;(7)以MATLAB为操作平台,进行模拟仿真实验、分析。通过辨识方法在随机控制系统中的应用,并对其中的设计和关键程序进行分析,通过模拟仿真得到仿真曲线,结果表明两种参数辨识估计方法在飞行器随机控制系统中辨识精度较高、收敛性较好,具有较强的实用价值,可以向其它飞行器随机控制系统推广应用。
[Abstract]:In order to get the aircraft into the predetermined orbit accurately, it is urgent for us to identify and estimate the parameters of the vehicle stochastic control system in the project design stage. The estimation of flight test data and the identification of trajectory parameters of aircraft orbit parameters have been accepted and paid more and more attention, and have become an important means to determine the flight orbit characteristics of aircraft. It can not only provide an orbital mathematical model for aircraft design that reflects the actual flight characteristics and the external environment, but also verify the theoretical calculation results and revise the ground test data. Therefore, it is of great theoretical significance and practical value to study the identification method of aircraft orbital parameters. This paper mainly studies two aspects: first, based on the least square method in the spacecraft stochastic control system orbit operation process for parameter identification, second, Based on the Kalman filter theory, the parameters are identified in the multi-tube-rocket navigation stochastic control system. The basic steps are as follows: (1) based on the least square method accurate priori parameter estimation method is studied (2) the mass center model of spacecraft stochastic control system is established; (3) the application of least square method in the parameter identification of stochastic control system; (4) the study of filtering theory based on Kalman filter continuous linear and nonlinear expansion; (5) the establishment of stochastic control system model of multi-barrel rocket; (6) the initial state of multi-barrel rocket is determined based on quasilinear Kalman filter. (7) the simulation experiment is carried out with MATLAB as the operating platform and the analysis is carried out. Through the application of identification method in stochastic control system, the design and key program are analyzed, and the simulation curve is obtained by simulation. The results show that the two methods of parameter identification and estimation are of high accuracy and good convergence in the stochastic control system of aircraft. They are of great practical value and can be applied to other stochastic control systems of aircraft.
【学位授予单位】：沈阳理工大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V249.1
本文编号：2335510
[Abstract]:In order to get the aircraft into the predetermined orbit accurately, it is urgent for us to identify and estimate the parameters of the vehicle stochastic control system in the project design stage. The estimation of flight test data and the identification of trajectory parameters of aircraft orbit parameters have been accepted and paid more and more attention, and have become an important means to determine the flight orbit characteristics of aircraft. It can not only provide an orbital mathematical model for aircraft design that reflects the actual flight characteristics and the external environment, but also verify the theoretical calculation results and revise the ground test data. Therefore, it is of great theoretical significance and practical value to study the identification method of aircraft orbital parameters. This paper mainly studies two aspects: first, based on the least square method in the spacecraft stochastic control system orbit operation process for parameter identification, second, Based on the Kalman filter theory, the parameters are identified in the multi-tube-rocket navigation stochastic control system. The basic steps are as follows: (1) based on the least square method accurate priori parameter estimation method is studied (2) the mass center model of spacecraft stochastic control system is established; (3) the application of least square method in the parameter identification of stochastic control system; (4) the study of filtering theory based on Kalman filter continuous linear and nonlinear expansion; (5) the establishment of stochastic control system model of multi-barrel rocket; (6) the initial state of multi-barrel rocket is determined based on quasilinear Kalman filter. (7) the simulation experiment is carried out with MATLAB as the operating platform and the analysis is carried out. Through the application of identification method in stochastic control system, the design and key program are analyzed, and the simulation curve is obtained by simulation. The results show that the two methods of parameter identification and estimation are of high accuracy and good convergence in the stochastic control system of aircraft. They are of great practical value and can be applied to other stochastic control systems of aircraft.
【学位授予单位】：沈阳理工大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V249.1
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