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Standard test model generation method and device and storage medium

A standard testing, model generation technique

Pending Publication Date: 2021-02-05
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention proposes a method for generating a standard test model, a generating device and a storage medium, aiming to solve the problem in the prior art that multiple different tests are required to perform coverage tests on aircraft components

Method used

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  • Standard test model generation method and device and storage medium
  • Standard test model generation method and device and storage medium
  • Standard test model generation method and device and storage medium

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0029] figure 1 A flow chart of steps of a method for generating a standard test model according to an embodiment of the present application is shown in FIG.

[0030] Such as figure 1 As shown, the standard test model generation method in this embodiment specifically includes the following steps:

[0031] S101, extracting model original solution input data according to the simulation model.

[0032] S102. Convert the acceleration of the input data of the original calculation of the model into the acceleration in the launching inertial coordinate system.

[0033] S103, generating an angular velocity based on the guidance instruction attitude angle of the input data from the original solution of the model.

[0034] S104. Generate the apparent acceleration in the rocket body coordinate system according to the guidance command attitude angle of the input data and the acceleration in the launching inertial coordinate system according to the original solution of the model.

[00...

Embodiment 2

[0062] image 3 A flow chart of steps of a method for generating a standard test model according to another embodiment of the present application is shown in FIG.

[0063] Such as image 3 As shown, the standard model generation method for configuring the test requirements based on the standard test model generation further includes the following steps:

[0064] S201. Obtain a test model according to a test requirement.

[0065] S202. Superimpose the guidance instructions of the test model and the standard test model to form a configuration guidance instruction.

[0066] S203. Convert the acceleration of the configured guidance command into the acceleration in the launching inertial coordinate system.

[0067] S204. Generate an angular velocity according to the attitude angle of the configuration guidance instruction.

[0068] S205. Generate the apparent acceleration in the rocket body coordinate system according to the attitude angle of the configuration guidance command ...

Embodiment 3

[0074] In Example 3, the air rudder polarity test is configured as an example for illustration. The configuration process is as follows:

[0075] First, according to the requirements of the polarity test of the controller, a polarity test model is formed. In this embodiment, the polarity test model is the air rudder polarity test;

[0076] Specifically, the air rudder polarity test usually introduces three-channel angle deviation curves, such as pitch angle deviation curves.

[0077] Figure 4 shows the pitch angle deviation curve of the standard test model configuration method according to another embodiment of the present application.

[0078] Such as Figure 4 As shown, the deviation curve usually uses a sine wave, taking a 15°, 0.02HZ sine curve as an example.

[0079] Next, configure the air rudder polarity test.

[0080] Specifically, the air rudder polarity test inputs the specified angular deviation command to the control system, and the control system generates a ...

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Abstract

The embodiment of the invention provides a standard test model generation method and device and a storage medium. The standard test model generation method comprises the following steps: extracting model original solution input data according to a simulation model; then converting the acceleration of the model original solution input data into the acceleration under a launch inertial coordinate system; generating an angular velocity according to a guidance instruction attitude angle of the model original solution input data; secondly, generating an apparent acceleration under a rocket body coordinate system according to a guidance instruction attitude angle of the model original solution input data and an acceleration under a launching inertial coordinate system; and finally, forming a standard test model according to the angular velocity and the apparent acceleration under the rocket body coordinate system. A plurality of test subjects can be covered in one test, the test frequency isreduced, and the problem that in the prior art, coverage tests need to be carried out on aircraft devices for multiple times and different tests is solved.

Description

technical field [0001] The application belongs to the field of aerospace technology, and in particular relates to a method for generating a standard test model, a generating device and a storage medium. Background technique [0002] The commercial solid launch vehicle is a complex system. In order to ensure the reliability of the flight, it mainly involves the joint debugging of the electrical system of the solid launch vehicle, the final assembly test, and the test effectiveness, adequacy and coverage of the range test. Among them, it is necessary to complete the coverage test of all devices on the ground as much as possible, including the function, performance, timing characteristics and other parameters of each device. Therefore, there are many test subjects, including unidirectional test, polarity test and comprehensive test. Etc. requires multiple tests of the device. In this way, more test subjects can meet the test coverage requirements, but it will increase the test...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/20
CPCG06F30/15G06F30/20Y02T90/00
Inventor 涂海峰严大卫陈喆宋志国梁卓葛云鹏吕瑞姜春旺杜肖谭清科胡骁李浩张亚琳潘彦鹏王凯旋李迎博陈旭东薛晨琛杨立杰谭黎立李烨张雪婷丁禹赵楠陈铁凝郝仁杰丘岳诗孟文霞张沁生
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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