A Genetic Algorithm Based Optimal Design Method for Solid Propellant Formula

Abstract

The invention discloses a solid propellant formulation energy optimization design method based on a genetic algorithm. The method comprises a first step of modeling, and building an energy characteristic calculation model of solid propellant according to a minimum free energy principle; a second step of setting and storing initial parameters, inputting component species used by the solid propellant, and a chemical formula and a quality proportion range of each component, and inputting species of combustion products produced by the solid propellant after being combusted, and chemical formulas and relative molecular mass of all the combustion products or selecting all the combustion products in a combustion product data base; and a third step of calling a genetic algorithm module by a data processor, and conducting optimization design to quality proportion of the designed solid propellant. The solid propellant formulation energy optimization design method based on the genetic algorithm is simple in steps, reasonable in design, convenient to achieve, good in using effect, capable of fast obtaining an optimum proportion of highest specific impulse of the solid propellant and effectively overcoming the defects, existing in an existing solid propellant compound design process, of being high in energy characteristic test cost, long in period, large in test dose, and the like.

Description

technical field [0001] The invention belongs to the technical field of solid propellant formulation optimization design, in particular to a genetic algorithm-based solid propellant formulation optimization design method. Background technique [0002] With the development of national defense (aerospace, weapons, etc.) technology, the requirements for propellants are becoming more and more stringent, requiring high energy and excellent performance. As we all know, under the condition of maintaining the basic properties of the propellant, the higher the energy of the propellant, the longer the range. For example, the specific impulse of the propellant used in ICBM intercontinental missiles (9260 kilometers) increases by 1%, and the range increases by 7.3% (676 kilometers); when the specific impulse of the propellant increases by 5%, the range increases by 45% (4167 kilometers) . The original intercontinental missile with a range of 9260 kilometers, as long as the specific imp...

AI Technical Summary

Problems solved by technology

[0003] The technical problem to be solved by the present invention is to provide a solid propellant formula optimization design method based on genetic algorithm, which has simple steps, reasonable design, convenient implementation, good use effect, and can quickly obtain The solid propellant has the best ratio of the highest specific impulse, which can effectively solve the defects of high energy characteristic test cost, long cycle, and large test volume in the existing solid propellant formula design process.

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