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Solid rocket engine performance progressive matching design method

A solid rocket and design method technology, applied in the field of aerospace, can solve the problems of increased calculation time consumption and low efficiency

Active Publication Date: 2020-12-29
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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  • Solid rocket engine performance progressive matching design method

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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 solid rocket engine performance progressive matching design method. The solid rocket engine performance progressive matching design method comprises the steps of acquiring task objectives of total indexes of a solid rocket engine; determining a time interval division number according to the working time of a preset thrust demand in the task target; obtaining an initial training sample set of the preset thrust demand matching degree based on an initial balance pressure method; according to the initial training sample set, operating the combustion surface and internal ballistic trajectory calculation model in the initial time interval to obtain N thrust curves, and constructing a thrust approximation model according to the N thrust curves; carrying out inaccurate sampling to obtain alternative solutions; substituting the alternative solution into a combustion surface calculation and internal trajectory calculation model, and calculating the performance of the internal trajectory within simulation time to obtain an alternative thrust curve; when the simulation time is not less than the working time, adding the alternative solution as a new sample point into asample set to obtain an updated sample set; and when a preset convergence condition is reached, outputting the alternative thrust curve as an 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 Applications(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靖博杨家伟王鹏宇
Owner NAT UNIV OF DEFENSE TECH
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