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Charging design method of solid rocket engine

A design method, solid rocket technology, applied in design optimization/simulation, calculation, special data processing applications, etc., can solve the problems of relying on experience, low efficiency of the solid rocket motor charge design process, etc. The effect of reducing the number of simulations

Active Publication Date: 2016-09-21
NAT UNIV OF DEFENSE TECH
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

[0013] The purpose of the present invention is to provide a solid rocket motor charge design method, which solves the technical problems of low efficiency in the prior art solid rocket motor charge design process and excessive reliance on experience

Method used

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  • Charging design method of solid rocket engine
  • Charging design method of solid rocket engine
  • Charging design method of solid rocket engine

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Embodiment Construction

[0048] The accompanying drawings constituting a part of this application are used to provide further understanding of the present invention, and the schematic embodiments and descriptions of the present invention are used to explain the present invention, and do not constitute an improper limitation of the present invention.

[0049] For ease of understanding, the brief description of the method provided by the present invention is as follows: the design method provided by the present invention first discretizes each thrust curve corresponding to the overall requirement into several points, constructs a proxy model through each discrete point, and depicts the thrust curve that varies with time. process. In the process of searching for the optimal solution, the approximation degree of each discrete point to the design index is considered, and the proxy model is updated by reducing the deviation between each discrete point and the design index. This reduces the number of iterati...

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Abstract

The invention provides a charging design method of a solid rocket engine. An agent model is used as a basis to directly carry out approximation on a thrust curve, and the thrust curve, instead of the agent model of a least square deviation between the thrust curve and a design index, is constructed to effectively describe a change rule of the thrust along with time so as to obviously reduce the simulation frequency of a high-precision burning surface and a trajectory. The agent model can better describe the change rule of the thrust curve, effectively guides subsequent search in a subsequent design, and can obviously improve the charging design efficiency of the solid rocket engine.

Description

technical field [0001] The invention relates to the technical field of aircraft engine design, in particular to a solid rocket motor charge design method. Background technique [0002] Solid rocket motor is one of the important power systems of space vehicles such as missiles and rockets. The charge design of a solid rocket motor generally requires the selection of the charge type and the determination of its geometric parameters under the ballistic performance of the engine and related constraints, and at the same time comprehensively consider the thermal insulation layer, lining layer and artificial debonding layer inside the combustion chamber shell. Design requirements. Charge design is the core technology of solid rocket motor design. The space shuttle solid booster rocket motor has the characteristics of large length-to-diameter ratio, high axial pressure drop, severe erosion and combustion, complex ignition process, uncertainty of hump effect in charge manufacturing...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 王东辉武泽平张为华胡凡江振宇
Owner NAT UNIV OF DEFENSE TECH
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