固液混合火箭发动机缩尺效应研究  

Investigation on scale effects of hybrid rocket engines

作　　者：余佳[1] 田辉[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《火箭推进》2015年第2期33-37,共5页Journal of Rocket Propulsion

摘　　要：全尺寸固液混合火箭发动机试验耗费大,通常采用缩比发动机进行试验。为确保缩比试验代替全尺寸试验的准确性和有效性,对固液混合火箭发动机进行了相似性理论研究。结果表明当缩尺发动机与全尺寸发动机几何相似、采用相同的氧化剂和燃料组合,且氧化剂流率与药柱内径比值相同时,理论上缩比试验一定程度上能够反映全尺寸发动机的特性。Since it is very expensive to execute the test of the full-scale hybrid rocket engine, the scale hybrid rocket engine is usually adopted for the test. In order to improve the cost-efficiency ratio of the test, the similarity analysis is carried out for the hybrid rocket engine to determine the conditions under which a laboratory scale hybrid rocket engine should be tested to simulate the firing of a full-scale system and to define the relevant scaling rules for hybrid propulsion system. Similarity requirements are given and analyzed in consideration of liquid oxidizer. The relative significance of the requirements is evaluated, and are established. The performance of hybrid rocket engine is predicted according to the scaling rules established for the full-scale hybrid engine.

关 键 词：固液混合火箭发动机 缩尺效应 相似性分析 

分 类 号：V436-34[航空宇航科学与技术—航空宇航推进理论与工程]