A method for starting the engine of the soft landing stage of the launch vehicle
A technology for launch vehicles and engines, which is applied in complex mathematical operations, geometric CAD, instruments, etc., and can solve the problem of inaccurate soft landing positions, excessive fuel consumption by rockets, ignoring rocket fuel consumption, and deviation adaptability. Landing terminal state requirements, etc. question
Active Publication Date: 2021-07-23
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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[0005] The purpose of the present invention is to provide a method for starting the engine in the soft landing stage of the launch vehicle, aiming at solving the problem that the existing method for starting the engine in the soft landing stage of the rocket power does not consider the impact of the thrust adjustment range on the fuel consumption of the rocket, the deviation adaptability and the landing terminal state The impact of the requirements, causing the rocket to consume too much fuel during the landing process, the soft landing position is not accurate
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[0053] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.
[0054] Please also refer to figure 1 , 2 Now, a method for starting an engine in the soft landing stage of a launch vehicle powered by the present invention will be described. A method for starting an engine in a soft landing stage of a launch vehicle, comprising:
[0055] Step 1: Establish the rocket power soft landing segment motion equation and the rocket power soft landing segment state constraint equation according to the rocket soft landing motion process; the rocket power soft landing segment state constraint equation includes: the rocket power soft landin...
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The invention provides a method for starting an engine in a power soft landing section of a launch vehicle, which belongs to the technical field of launch vehicle control. The present invention comprehensively considers the influence of the thrust adjustment range on the rocket fuel consumption, the deviation adaptability and the landing terminal state requirements by establishing the motion equation of the rocket power soft landing section and the state constraint equation of the rocket power soft landing section according to the rocket soft landing motion process. Solve the trajectory planning problem of the ideal startup speed with the largest feasible region, and can calculate the maximum ideal startup speed and ideal landing time in the feasible region of the power soft landing section corresponding to the current position in real time. By estimating the deviation between the actual speed of the rocket and the ideal startup speed , when the deviation value is the smallest, the engine start-up command is issued, which improves the deviation adaptability of the rocket-powered soft landing segment and creates good initial access conditions for the landing process after the engine is turned on.
Description
technical field [0001] The invention belongs to the technical field of launch vehicle control, and more specifically relates to a method for starting an engine in a launch vehicle power soft landing section. Background technique [0002] The vertical recovery technology of reusable launch vehicles is one of the important development directions of new generation launch vehicles. As the landing process, the powered soft landing section is the last flight stage of the rocket, and it needs to adapt to the deviation caused by the environmental uncertainty of the aerodynamic deceleration section. Considering the fuel consumption, deviation adaptability, engine thrust adjustment range, and landing terminal state requirements in the powered soft landing phase, the engine start-up condition of the rocket in the powered soft landing phase is a key control quantity. Especially for a rocket with a large thrust-to-weight ratio, the rocket will always be in a continuous deceleration proc...
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IPC IPC(8): G06F30/15G06F30/20G06F17/11G06F111/04G06F119/14
CPCG06F17/11G06F30/15G06F30/20G06F2111/04G06F2119/14
Inventor 王聪宋征宇胡海峰巩庆海
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST