A rocket engine parameter calibration method and rocket

Abstract

The invention provides a rocket engine parameter calibration method. An engine parameter is used for an iterative guidance algorithm of a rocket, wherein the method comprises the following steps of obtaining the cumulative consumption quantity of an engine propellant in a preset time; obtaining a calibration coefficient of the engine parameter according to the cumulative consumption quantity of the engine propellant in the preset time; and obtaining the calibrated engine parameter according to the calibration coefficient of the engine parameter. The invention also discloses the rocket. The calibration coefficient of the engine parameter is obtained by calculating the cumulative consumption quantity of the rocket engine propellant in the preset time, the calibrated engine parameter is further obtained, and the calibrated engine parameter is applied to the calculation of the iterative guidance algorithm, so that the guidance precision of the iterative guidance algorithm after the calibration is improved, and the flight precision of the rocket is improved.

Description

technical field [0001] The invention relates to the technical field of rocket control, in particular to a rocket engine parameter calibration method and a rocket. Background technique [0002] Traditional rocket engines mostly use iterative guidance algorithms for precise guidance, and the remaining apparent velocity total impulse and remaining apparent position total impulse are important parameters in the iterative guidance algorithm. Generally speaking, the iterative guidance algorithm of a rocket engine uses the total apparent velocity impulse minus the generated apparent velocity impulse to calculate the remaining apparent position impulse, and uses the total apparent position impulse minus the generated apparent position impulse to calculate the remaining apparent position impulse. Total position rush. [0003] When calculating the remaining apparent speed total impulse and remaining apparent position total impulse, the above calculation method usually does not consid...

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Problems solved by technology

[0004] Therefore, the technical problem to be solved in the present invention is to overcome the defect that the consumption of rocket engine propellant has an impact on the remaining apparent velocity total impulse and the remaining apparent position total impulse, resulting in an increase in the error of the iterative guidance algorithm, thereby providing a rocket engine parameter calibration method , the engine parameters are used for the iterative guidance algorithm of the rocket, comprising the steps of:

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