Solid propellant formula optimization method based on genetic algorithm and energy feature graph

Abstract

The invention discloses a solid propellant formula optimization method based on a genetic algorithm and an energy feature graph. The solid propellant formula optimization method based on the genetic algorithm and the energy feature graph includes a first step of modeling, namely, establishing four energy feature calculation models according to a minimum free energy principle; a second step of setting and storing initial parameters; a third step of utilizing the genetic algorithm to implement formula optimization design; a fourth step of setting a value range used for graphic plotting and calculating mass contents of various kinds of raw material; and a fifth step of drawing the energy feature graph. The drawing process includes the steps of energy feature parameter inputting, energy feature curvilinear equation fitting, energy feature graph drawing, and synchronous energy feature graph displaying. The method is simple in step, reasonable in design, convenient to achieve and good in use effect, combines the genetic algorithm and the energy feature graph to carry out the solid propellant formula optimization design, and overcomes the defects that the energy feature experimental cost is high, the period is long and the experimental quantity is large and the like in an existing solid propellant formula optimization design process.

Description

technical field [0001] The invention belongs to the technical field of solid propellant formula optimization design, in particular to a solid propellant formula optimization method based on genetic algorithm and energy characteristic graph. 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...

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Problems solved by technology

[0003] The technical problem to be solved by the present invention is to provide a solid propellant formula optimization method based on genetic algorithm and energy characteristic graph in view of the deficiencies in the above-mentioned prior art. The method has simple steps, reasonable design, convenient implementation and good use effect. It can effectively solve the defects in the existing solid propellant formula design process, such as high cost, long cycle and large test volume of energy characteristics test

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