A Nonlinear Smooth Zeroing Method for Launch Vehicle Servo Mechanism

Abstract

A nonlinear smooth zero return method of a carrier rocket servo mechanism comprises the steps of determining the start nonlinear return-to-zero moment and nonlinear return-to-zero moment of each servomechanism, then obtaining nonlinear return-to-zero moment of each servo mechanism and corresponding time parameters, and finally calculating to obtain a corresponding return-to-zero coefficient according to the time parameters of each servo mechanism, so that the swinging angle of an engine of each servo mechanism after correction is obtained, and the nonlinear smooth return-to-zero of the servomechanism is completed.

Description

technical field [0001] The invention proposes a non-linear smooth zeroing method for a launch vehicle servomechanism, which involves the determination of the zeroing start and end time points and the calculation formula of the zeroing section servomechanism command. Background technique [0002] For rockets with traditional boosters, the booster engine cannot swing, but only provides thrust, does not participate in the attitude control of the rocket, and does not provide control force, so there is no need to reset the booster servo mechanism when the booster is separated. In the new generation of rockets, the booster engine can swing and participate in the attitude control of the rocket, providing thrust and control at the same time. In order to ensure the safe separation of the booster during the rocket flight, it is necessary to return the booster engine to the zero position before separation, that is, perform a zeroing process on the booster servo mechanism that drives th...

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Problems solved by technology

[0003] In addition, traditional rockets do not perform the engine zeroing process during the first-stage separation, second-stage separation, etc., or use a direct zeroing method, that is, directly send a zero command to the servo mechanism during stage transfer or stage transfer.

This method has two disadvantages. One is that the direct return to zero is a step signal, which will interfere with the attitude of the rocket. The other is that the servo mechanism of the engine drainage cannot swing because the engine flow is too small before separation, and the servo return cannot be completed. zero

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