塞式喷管热试实验研究  

Hot-firing tests on aerospike nozzles

作　　者：王长辉[1] 刘宇[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《火箭推进》2007年第4期1-7,共7页Journal of Rocket Propulsion

基　　金：国家博士后科学基金(20060400038)

摘　　要：全面介绍了多个塞式喷管的热流实验研究。实验获得了固体推进剂、气氧/酒精及气氧/气氢三种推进剂组合塞式喷管的热试车性能。实验塞式喷管包括了瓦状塞锥和平板塞锥等两种塞锥形式。实验结果表明,塞式喷管特别适合用于飞行高度范围跨度大的固体或液体火箭发动机。气氧/酒精瓦状直锥塞式喷管热试车的效率达到了95%,验证了瓦状塞式喷管的高度补偿特性。一单元塞式喷管和单侧三单元塞式喷管气氢/气氧发动机热试实验成功进行了爆震波多管点火。一单元塞式喷管发动机在CNPR=110附近,效率达到93%～95%;在CNPR=450附近,效率达到96%～98%;在CNPR=1000附近,效率达到93%～96%。单侧三单元塞式喷管发动机在CNPR=50附近,效率达到92%～93.5%;在CNPR=350附近,效率达到95%～96%,预计在设计点的效率不低于98%。Comprehensive studies on hot-firing tests of the aerospike nozzles are presented. Hot-firing performance of aerospike nozzles with solid propellant, gaseous O2/alcohol （GO2/alcohol） and gaseous H2/gaseous O2 （GH2/GO2） propellant combinations was obtained in the tests. Two types of plug ramps - the tile-shape and the flat shape were designed for aerospike nozzle experiments. It was shown that the aerospike nozzle was well suitable for large operation altitude range solid rocket motor or liquid rocket engines. The efficiency of experimental GO2/alcohol propellant aerospike nozzle with tile-shaped cylindrical plug ramp reached 95%, the altitude compensation capacity of the aerospike nozzle was also verified. GH2/GO2 propellant hot-firing tests were carried out on a 1-cell aerospike nozzle and a 3-cell aerospike nozzle. Multi-pipe detonation wave ignitor was successfully performed in the tests. For 1-cell aerospike nozzle, efficiency was 93% to 95% around CNPR=110, ef- ficiency was 96% to 98% around CNPR=450 and efficiency was 93% to 96% around CNPR=1000. For 3-cell aerospike nozzles, efficiency varied from 92% to 93.5% around CNPR=50 and efficiency varied from 95% to 96% around CNPR=350. At design point the promising efficiency of more than 98% can be expected.

关 键 词：航空 航天推进系统 火箭发动机 塞式喷管 

分 类 号：V433.9[航空宇航科学与技术—航空宇航推进理论与工程]