圆转方塞式喷管型面设计和试验研究  

Contour Design and Test Studies of a Round to Square Aerospike Nozzle

作　　者：王一白[1] 覃粒子[1] 刘宇[1] 廖云飞[1] 王长辉[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《宇航学报》2006年第5期843-848,891,共7页Journal of Astronautics

基　　金：国家863-2高技术航天领域[2003AA722020]

摘　　要：提出了圆转方塞式喷管的内喷管和塞锥型面的设计方法，内喷管用圆弧和抛物线近似，塞锥型面用抛物线和三次曲线近似，设计了一单元圆转方塞式喷管试验发动机。并采用气氧作氧化剂，气氢作燃料，进行了点火热试研究。介绍了试验发动机的结构与设计参数，以及试验系统组成和点火方式，给出了试验发动机照片、试验结果照片、测量参数曲线和性能数据处理。试验结果表明，试验发动机具有较高的热试效率：在三个不同工作高度下，喷管推力系数效率在93％-98％之间，说明圆转方塞式喷管的型面设计和试验方法是可行的。Simple design methods of round to square inner nozzle contour and plug contour of the aerospike nozzle were presented. The inner nozzle contour was described by two circular arcs and a parabola; the plug contour was described by a parabola and a third-order curve. And the results of hot-firing tests on a 1-ceU linear aerospike nozzle engine with round to square inner nozzle were given, using oxygen as oxidant and hydrogen as fuel. Design parameters and structure photographs of the experimental engine, the test apparatus and ignition method were introduced. Curves measured in the tests, test photographs and data analyses were also provided. At three altitudes, thrust coefficient efficiencies vary within the range of 93% to 98%, which is shown that the test aerospike nozzle engine maintain high thrust efficiency. It is proved that the design and test methods of the aerospike nozzle are feasible.

关 键 词：塞式喷管 型面设计 点火试验 圆转方 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]