固体火箭发动机有约束流场推力特性计算

推进技术 ›› 1995, Vol. 16 ›› Issue (1): 33-40.

固体火箭发动机有约束流场推力特性计算

方国尧,高山辉,孙哲禧,汤志东

北京航空航天大学宇航学院;北京航空航天大学宇航学院;北京航空航天大学宇航学院;北京航空航天大学宇航学院

发布日期:2021-08-15

THRUST CHARACTERISTICS OF SOLID ROCKET MOTOR WITH RESTRAINED FLOW FIELDS

School of Astronautics, Beijing Univ. of Aeronautics & Astronautics, Beijing, 100083;School of Astronautics, Beijing Univ. of Aeronautics & Astronautics, Beijing, 100083;School of Astronautics, Beijing Univ. of Aeronautics & Astronautics, Beijing, 100083;School of Astronautics, Beijing Univ. of Aeronautics & Astronautics, Beijing, 100083

Published:2021-08-15

摘要/Abstract

摘要： 为计算带约束流场的固体火箭发动机推力特性，建立了一维准定常变截面的内弹道计算和约束流场流动的数学模型。计算结果表明，约束流场使推力增加１４％，冲波进入喷管扩张段。与试验结果很接近，表明计算模型正确，可用于其它型号带约束流场的推力特性计算。

关键词: 固体推进剂火箭发动机;内弹道计算;气体－固体互作用;流动分布

Abstract: n order to compute the thrust characteristics of solid rocket motorwith the restrained flow, this paper establishes an internal ballistic mathematicalmodel by use of the steady one-dimensional flow equations in passage withchangable cross-sections in restrained flow fields. The results show that the thrustincreases by 14%, shock waves have entered the nozzle and the models developedare correct. The method is suitable for other solid rocket motors.

Key words: Solid propellant rocket engine;Interior ballistic calculation;Gassolid interaction;Flow distribution

方国尧,高山辉,孙哲禧,汤志东. 固体火箭发动机有约束流场推力特性计算[J]. 推进技术, 1995, 16(1): 33-40.