CN-115984483-B - Rocket destaging data processing method and device

CN115984483BCN 115984483 BCN115984483 BCN 115984483BCN-115984483-B

Abstract

The application relates to the technical field of data processing, in particular to a rocket destaging data processing method, which comprises the steps of obtaining a three-dimensional relation model of a rocket and at least one rocket destaging posture deviation item, simulating an rocket body quality parameter change process of the three-dimensional relation model in a first preset process, simulating an rocket body stress change process of the three-dimensional relation model in a second preset process, and determining destaging posture parameters of the three-dimensional relation model according to the rocket body quality parameter change process, the rocket body stress change process and each rocket body destaging posture deviation item. The technical scheme provided by the application can accurately calculate the parameters of the destaging posture to a certain extent.

Inventors

ZHU PEIJIE
YANG YUE
KE ZHAO
LUO SHU

Assignees

航天科工火箭技术有限公司

Dates

Publication Date: 20260508
Application Date: 20230209

Claims (5)

1. A rocket destaging data processing method, the method comprising: Acquiring a three-dimensional relation model of a rocket and at least one rocket body off-platform attitude deviation item, wherein the rocket comprises an rocket body and supporting legs, and the rocket body off-platform attitude deviation item comprises a mass parameter deviation, a thrust related deviation, a ground friction coefficient deviation, a buffer performance parameter deviation, an rocket body axial deviation, a ground wind deviation and a ground inclination deviation; Taking a process of filling propellant into the rocket body to leave the rocket body as a first preset process, simulating an rocket body quality parameter change process of the three-dimensional relation model in the first preset process, taking a process of igniting an engine to the rocket body to leave the rocket body as a second preset process, and simulating an rocket body stress change process of the three-dimensional relation model in the second preset process; according to the arrow body destaging posture deviation items, calculating posture influence data of the arrow body destaging posture deviation items on the arrow body respectively; And adding all attitude influence data in the arrow body quality parameter change process and the arrow body stress change process, and determining the destaging attitude parameters of the three-dimensional relation model.
2. A method according to claim 1, wherein the obtaining a three-dimensional relationship model of the rocket comprises: and establishing a three-dimensional relationship model of the rocket, and constructing the connection relationship between the support legs and the rocket body through the coordinate conversion relationship.
3. The method of claim 1, wherein adding attitude impact data during the arrow body mass parameter change and the arrow body force change determines a destaging attitude parameter of the three-dimensional relationship model, comprising: Adding all attitude influence data in the arrow body quality parameter change process and the arrow body stress change process, and determining arrow body destaging time; And determining the destaging posture parameters of the three-dimensional relation model according to the destaging time of the arrow body.
4. The method of claim 3, wherein the determining the destaging pose parameters of the three-dimensional relationship model from the arrow destaging time comprises: And measuring the corresponding arrow body attitude angle and attitude angle rate according to the arrow body destaging time so as to determine destaging attitude parameters of the three-dimensional relation model.
5. A rocket-off-station data processing device, the device comprising: The rocket body off-platform attitude deviation item comprises a mass parameter deviation, a thrust related deviation, a ground friction coefficient deviation, a buffer performance parameter deviation, an rocket body axial deviation, a ground wind deviation and a ground inclination deviation; the simulation unit is used for simulating an arrow body parameter change process of the three-dimensional relation model in a first preset process by taking a process of filling the propellant into the arrow body for leaving the platform as a first preset process, and simulating an arrow body stress change process of the three-dimensional relation model in a second preset process by taking a process of igniting the engine until the arrow body leaves the platform as a second preset process; The determining unit is used for respectively calculating the attitude influence data of each arrow body off-platform attitude deviation item on the arrow body according to each arrow body off-platform attitude deviation item, and adding each attitude influence data in the arrow body quality parameter change process and the arrow body stress change process to determine the off-platform attitude parameters of the three-dimensional relation model.

Description

Rocket destaging data processing method and device Technical Field The application relates to the technical field of data processing, in particular to a rocket destaging data processing method and device. Background The lower end face of the tail section of the traditional carrier rocket is fixed with a launching pad, the gesture is comparatively stable when taking off and leaving the platform. The rocket can be demonstrated and verified by a reusable technology, and the rocket is directly supported on the ground by adopting fixed recovery supporting legs before taking off, and is influenced by factors such as uneven performance of four supporting legs, uneven ground, unstable taking-off thrust and the like, and a large initial inclination angle and angular velocity can exist when the rocket body leaves the platform. Meanwhile, at the moment, due to the reasons of unstable thrust and the like, the arrow body is not controlled, and the situations of falling of the arrow body, divergence of the posture after taking off and the like can occur during the process of leaving the platform. Therefore, the landing time of the rocket body support leg and the corresponding attitude information and other landing attitude parameters at the moment are required to be acquired and used as the starting control time and initial state input of flight control calculation so as to prevent accidents such as rocket body tilting or attitude divergence. Based on the above, a rocket destaging data processing method is urgently needed by those skilled in the art, so that destaging posture parameters can be accurately calculated. Disclosure of Invention The embodiment of the application provides a rocket destaging data processing method, which can accurately calculate destaging posture parameters at least to a certain extent. Other features and advantages of the application will be apparent from the following detailed description, or may be learned by the practice of the application. According to one aspect of the embodiment of the application, a rocket destaging data processing method is provided, and the method comprises the steps of obtaining a three-dimensional relation model of a rocket and at least one rocket destaging posture deviation item, simulating an rocket body quality parameter change process of the three-dimensional relation model in a first preset process, simulating an rocket body stress change process of the three-dimensional relation model in a second preset process, and determining destaging posture parameters of the three-dimensional relation model according to the rocket body quality parameter change process, the rocket body stress change process and each rocket body destaging posture deviation item. In some embodiments of the application, the method for obtaining the three-dimensional relationship model of the rocket comprises the steps of establishing the three-dimensional relationship model of the rocket and establishing the connection relationship between the support legs and the rocket body through coordinate transformation relationship. In some embodiments of the application, the acquiring at least one arrow body destaging attitude deviation term includes acquiring a mass parameter deviation, a thrust related deviation, a ground friction coefficient deviation, a damper performance parameter deviation, an arrow body axial deflection, a ground wind deviation, and a ground tilt deviation. In some embodiments of the application, the simulating the arrow quality parameter change process of the three-dimensional relation model in the first preset process comprises using a process of filling propellant into an arrow body to be separated from the platform as the first preset process and simulating the arrow quality parameter change process of the three-dimensional relation model in the first preset process. In some embodiments of the present application, the simulating the arrow body stress variation process of the three-dimensional relation model in the second preset process includes taking the process from the ignition of the engine to the separation of the arrow body as the second preset process, and the arrow body stress variation process of the three-dimensional relation model in the second preset process. In some embodiments of the present application, the determining the destaging posture parameters of the three-dimensional relationship model according to the arrow body quality parameter change process, the arrow body stress change process, and the arrow body destaging posture deviation items includes calculating posture influence data of each arrow body destaging posture deviation item on an arrow body according to each arrow body destaging posture deviation item, and adding each posture influence data in the arrow body quality parameter change process and the arrow body stress change process to determine the destaging posture parameters of the three-dimensional relationship model. In some embodiments of th