Online identification method for mass property of carrier rocket and critical parameter of dynamics

A technology of launch vehicle, mass characteristics, applied in the field of control system design

Active Publication Date: 2017-01-25
BEIJING INST OF ASTRONAUTICAL SYST ENG +1
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AI Technical Summary

Problems solved by technology

Since there is no way for the rocket to directly measure these key parameters (including mass, moment of inertia, center of mass, and center

Method used

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  • Online identification method for mass property of carrier rocket and critical parameter of dynamics
  • Online identification method for mass property of carrier rocket and critical parameter of dynamics
  • Online identification method for mass property of carrier rocket and critical parameter of dynamics

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Embodiment 1

[0215] According to the formulas (23)-(39), the following initial values ​​can be used to realize the online identification of the mass characteristics and dynamic key parameters of the launch vehicle. For the specific identification results, see Figure 2-Figure 9 .

[0216] P λ (0|0)=100I 2×2 , P x (0|0)=100I 12×12 , V(0)=I 12×12 . where x 0 is the initial value of the flight state, λ 0 is the initial value of the estimated parameter.

[0217] Such as figure 2 is the position estimation result in the X direction in the embodiment of the present invention, image 3 is the position estimation result in the Y direction in the embodiment of the present invention; Figure 4 is the Z direction position estimation result in the embodiment of the present invention; Figure 5 is the estimation result of the pitch attitude angle in the embodiment of the present invention; Figure 6 is the yaw attitude angle estimation result in the embodiment of the present invention; ...

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Abstract

The invention relates to an online identification method for the mass property of carrier rocket and the critical parameter of dynamics. The method is based on the six degrees of freedom aviation dynamics equation and the unknown parameter dynamic equation. Through constructing the augmented state equation to realize a simultaneous estimate for state and parameter, the parameter vector and state vector to be identified is thus obtained. The greatest advantage of the present method is to estimate unknown parameters according to the output. When the system is changed, the mass property and the estimation result of the critical parameter of the dynamics can be accurately obtained, and can establish key technical foundation for online optimization and adjustment of the control parameters of carrier rocket. Meanwhile, the identification method can realize the simultaneous estimation of state and parameters online. The method has significances for reducing the conservativeness of rocket system deviations and for increasing the adaptability to malfunctions by rocket, and provides beneficial references for future rocket design.

Description

technical field [0001] The invention relates to an online identification method for mass characteristics and dynamic key parameters of a launch vehicle, and belongs to the technical field of control system design. Background technique [0002] At present, the design of my country's launch vehicle control system has the problems of poor adaptability to system deviation, low design level, and conservative design margin. It is impossible to accurately estimate the key dynamic parameters in the flight process, and realize the online adjustment of the control parameters to deal with various possible flight conditions. Therefore, there is an urgent need to carry out online identification technology research on key characteristic parameters of launch vehicles. On the one hand, it can be used by active rockets, which is beneficial to find out the system deviation, reduce the conservatism of system parameter design, and further tap the model potential. On the other hand, it can also b...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15
Inventor 陈宇李君程兴余光学杨云飞张普卓邓舞燕陈彬汤波李强宋敬群王海涛容易
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG
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