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Complex system transfer function computing method based on high-precision polynomial arithmetic

A transfer function and complex system technology, applied in the field of complex system transfer function calculation, can solve the problems of easy distortion of frequency characteristics, poor calculation accuracy, dimension disaster, etc.

Inactive Publication Date: 2013-11-20
BEIJING INST OF ASTRONAUTICAL SYST ENG +1
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Problems solved by technology

[0004] The technical problem to be solved in the present invention is: the calculation method of dynamic model transfer function in the prior art has poor calculation accuracy when dealing with complex systems, which easily leads to "dimension disaster", and the frequency characteristics are prone to distortion

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  • Complex system transfer function computing method based on high-precision polynomial arithmetic
  • Complex system transfer function computing method based on high-precision polynomial arithmetic
  • Complex system transfer function computing method based on high-precision polynomial arithmetic

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Embodiment Construction

[0058] A complex system transfer function calculation method based on high-precision polynomial operations of the present invention will be described in detail below in conjunction with the drawings and embodiments.

[0059] A kind of complex system transfer function calculation method based on high-precision polynomial operation of the present invention, comprises the following steps:

[0060] Step 1 input data pre-processing;

[0061] Step 2 state space matrix calculation;

[0062] Step 3 adopts the traditional FADEEVA method to calculate the transfer function of the rocket body;

[0063] In step 4, by expanding the floating-point data information, changing the internal processing mechanism of the algorithm, redefining the polynomial operation algorithm, and realizing high-precision polynomial operation; using the above-mentioned high-precision method, the two transfer functions of the inertial navigation platform channel and the rate gyro channel Add up to get the transfe...

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Abstract

The invention belongs to the technical field of carrier rocket control, and particularly relates to a complex system transfer function computing method based on the high-precision polynomial arithmetic. The method comprises the first step of pre-processing input data, the second step of calculating a state space matrix, the third step of calculating the transfer function of a rocket body by adopting the FADEEVA method, the fourth step of expanding floating point data information to obtain the transfer function of the sum of the rocket body, a platform and a gyroscope and the transfer function of the sum of the rocket body, the platform, the gyroscope and a steering engine, and the fifth step of obtaining the transfer function of an attitude control system open loop. The limitation of the word length of a robot is broken through, effective figures are reserved, the computing round-off error is reduced, and the solving precision of the transfer function is improved in the process of processing a complex system.

Description

technical field [0001] The invention belongs to the technical field of launch vehicle control, and in particular relates to a calculation method of a complex system transfer function based on high-precision polynomial operation. Background technique [0002] To analyze the stability of the attitude control system of the launch vehicle, there are usually two methods: one is the root locus method, that is, to examine the distribution of the algebraic characteristic roots corresponding to the differential equation describing the attitude control system, if all the roots have negative real The second is the frequency method, that is, the stability of the entire system is judged by finding the open-loop amplitude-phase characteristics and amplitude-phase margin of the system. Since the nonlinear and hysteresis characteristics of the servo mechanism in the attitude control system cannot be described by a linear system, it brings some difficulties to design the attitude control sys...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F19/00F42B15/01
Inventor 陈宇杨云飞李君程兴邓舞燕陈彬贾大玲李聃何巍牟宇
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG
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