A progressive matching design method for solid rocket motor performance

A solid rocket and design method technology, applied in the aerospace field, can solve problems such as low efficiency and increased calculation time, and achieve the effects of saving calculations, improving design efficiency, and avoiding invalid calculations

Active Publication Date: 2021-07-09
NAT UNIV OF DEFENSE TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, the current commonly used engine matching design method has the disadvantage that the fitness evaluation must be performed after the simulation is completed in each iteration process, resulting in repeated calculations of poor solutions, resulting in increased calculation time and low efficiency.

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  • A progressive matching design method for solid rocket motor performance
  • A progressive matching design method for solid rocket motor performance
  • A progressive matching design method for solid rocket motor performance

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Embodiment Construction

[0071] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in various ways defined and covered by the claims.

[0072] The invention provides a progressive matching design method for solid rocket motor performance, comprising:

[0073] Obtain the mission objective of the solid rocket motor overall index;

[0074] Determine the number of divided time intervals and the length of the time interval according to the working time of the preset thrust requirement in the task target;

[0075] The initial training sample X of the preset thrust requirement matching degree is obtained based on the initial equilibrium pressure method i (i=1,2,...,N);

[0076] According to the initial training sample, run the burning surface and the internal ballistic calculation model in the initial time interval to obtain corresponding N thrust curves in the initial time interval, and constr...

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Abstract

The invention provides a progressive matching design method for the performance of solid rocket motors, which includes: obtaining the mission target of the overall index of the solid rocket motor; According to the initial training sample set, run the combustion surface and internal ballistic calculation model in the initial time interval to obtain N thrust curves, and build a thrust approximate model according to the N thrust curves ; Perform inaccurate sampling to obtain an alternative solution; substitute the alternative solution into the combustion surface calculation and internal ballistic calculation model, calculate the internal ballistic performance within the simulation time, and obtain an alternative thrust curve; when the simulation time is not less than the described work time, the alternative solution is added to the sample set as a new sample point to obtain an updated sample set; when the preset convergence condition is reached, the alternative thrust curve is output as the optimal solution.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a design method for progressive matching of solid rocket motor performance. Background technique [0002] Solid rocket motor is one of the important power systems of space vehicles such as missiles and rockets. In the design of solid rocket motors, the thrust-time curve is the most direct performance output of the motor, and it is also the most concerned motor performance of the missile as a whole. With the continuous improvement of the refined design level of missiles, the demand for engines with specific thrust curves is more urgent. Therefore, the performance matching design for solid rocket motors can better meet the overall refined design requirements of missiles and improve the overall performance of missile weapons. Different from the existing design requirements for performance indicators, engine performance matching design is to find a set of design schemes in the d...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/20G06F111/04
CPCG06F30/15G06F30/20G06F2111/04
Inventor 武泽平王东辉王文杰张为华孙婧博杨家伟王鹏宇
Owner NAT UNIV OF DEFENSE TECH
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