飞行加速度对固体火箭发动机前封头绝热层烧蚀特性影响研究

推进技术 ›› 1998, Vol. 19 ›› Issue (2): 28-30.

飞行加速度对固体火箭发动机前封头绝热层烧蚀特性影响研究

田维平,余贞勇,任全彬,孟庆富

陕西动力机械研究所;陕西动力机械研究所;陕西动力机械研究所;陕西化学动力实验所

发布日期:2021-08-15

EFFECTS OF FLIGHT ACCELERATION ON EROSION CHARACTERISTICS OF FORWARD DOME INSULATION OF SOLID ROCKET MOTORS

Shaanxi Test Inst.of Chemical Power,Xi′an,710000;Shaanxi Test Inst.of Chemical Power,Xi′an,710000;Shaanxi Test Inst.of Chemical Power,Xi′an,710000;Shaanxi Test Inst.of Chemical Power,Xi′an,710000

Published:2021-08-15

摘要/Abstract

摘要： 对固体火箭发动机前封头绝热层在加速度环境中的炭化烧蚀特性进行了实验研究，研制了烧蚀试验发动机及相应的离心试验台，用ＮＢＲ，ＥＰＤＭ绝热层模拟实际烧蚀环境进行了不同轴向加速度条件下的烧蚀试验，得到了飞行加速度对绝热层炭化烧蚀率影响规律和经验关系式。

关键词: 固体推进剂火箭发动机;隔热材料;烧蚀试验;加速度试验

Abstract: The charring ablation characteristics of solid rocket motors forward dome insulation in the acceleration environment were investigated by experiments.The ablation test motor and corresponding centrifugal ignition test device were researched and developed.By simulating actual ablation environment,the ablation tests of NBR and EPDM insulation were performed in different axial acceleration conditions.The influential regularities and empirical formulas were obtained

Key words: Solid propellant rocket engine;Thermal insulating material;Ablation test;Acceleration test

田维平,余贞勇,任全彬,孟庆富. 飞行加速度对固体火箭发动机前封头绝热层烧蚀特性影响研究[J]. 推进技术, 1998, 19(2): 28-30.