飛行器隨機控制系統(tǒng)參數(shù)辨識估計方法
發(fā)布時間：2018-11-16 12:23
【摘要】：為了使飛行器能夠準確的進入預定軌道運行,在飛行器的方案設計階段,迫切需要我們對飛行器隨機控制系統(tǒng)應用系統(tǒng)參數(shù)辨識估計。飛行器飛行試驗實測數(shù)據(jù)估算及飛行器軌道參數(shù)的軌跡參數(shù)辨識技術已越來越為人們所接受和重視,并已成為確定飛行器飛行軌道特性的一個重要手段。它不僅能為飛行器設計提供反映實際飛行特性和外部環(huán)境的軌道數(shù)學模型,且可以驗證理論計算結果并修正地面試驗數(shù)據(jù)結果。因此,對飛行器軌道參數(shù)辨識方法的探討有著重大的理論意義和實際價值。本文主要研究兩方面內容,其一,基于最小二乘法在航天器隨機控制系統(tǒng)軌道運行過程中進行參數(shù)辨識,其二,基于卡爾曼濾波理論在多管火箭彈導航隨機控制系統(tǒng)進行參數(shù)辨識,基本步驟如下:(1)基于最小二乘法精確先驗參數(shù)估計方法研究(2)建立航天器隨機控制系統(tǒng)質心模型;(3)最小二乘法在隨機控制系統(tǒng)參數(shù)辨識的應用;(4)基于卡爾曼濾波連續(xù)線性、非線性擴展的濾波理論研究;(5)建立多管火箭彈隨機控制系統(tǒng)模型;(6)基于擬線性卡爾曼濾波的多管火箭彈初始狀態(tài)確定;(7)以MATLAB為操作平臺,進行模擬仿真實驗、分析。通過辨識方法在隨機控制系統(tǒng)中的應用,并對其中的設計和關鍵程序進行分析,通過模擬仿真得到仿真曲線,結果表明兩種參數(shù)辨識估計方法在飛行器隨機控制系統(tǒng)中辨識精度較高、收斂性較好,具有較強的實用價值,可以向其它飛行器隨機控制系統(tǒng)推廣應用。
[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.
【學位授予單位】：沈陽理工大學
【學位級別】：碩士
【學位授予年份】：2015
【分類號】：V249.1
本文編號：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.
【學位授予單位】：沈陽理工大學
【學位級別】：碩士
【學位授予年份】：2015
【分類號】：V249.1
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