Grain Design, Performance Prediction and Optimization of Star Configuration for SRM
This paper presents a design methodology for efficient design of complex Solid Rocket Motors Grains involving computationally intensive analysis with number of design variables. A technique has been proposed to design and analyze the Star grain Geometry and thereafter extract optimal solution of the Solid Rocket Motor grain using very few trial designs. The optimization toolbox of Matlab Fmincon has been used in which maximum Thrust has been computed as the objective function with constraints of burning time and propellant mass while remaining within fixed length and diameter of grain. Upper and lower limits have been defined and an initial guess provided. The performance of proposed methodology is investigated in this paper for the designing, analysis, performance prediction and optimization of 2D grain design using Star configuration for Solid Rocket Motors that can be used for various missile systems and space launch vehicles. The results show that all desired functions have been achieved and an optimal design has been attained qualifying all ballistic parameters. By using this technique of design and optimization, the vital parameter of average thrust can be achieved to its maximum value in optimal burning time and propellant mass. Various iterations/permutations can be carried out by which required levels of design parameters can not only be achieved but also optimized. This method is useful in designing efficient Solid Rocket Motor that in turn will be used in designing overall missile system design.
Solid Rocket Motor Star Grain Geometry Internal Ballistics Optimization
Khurram Nisar Xu Peng Liang Guozhu
School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100083,China School of Astronautics,Beijing Univ.of Aeronautics and stronautics,Beijing 100083,China
国际会议
The 11th International Space Conference of Pacific-basin Societies(第11届环太平洋国际航天会议)
北京
英文
39-48
2007-05-16（万方平台首次上网日期，不代表论文的发表时间）