塞式喷管运载器外流干扰冷流试验研究  

Cold flow test of outflow influence on vehicle with aerospike nozzle

作　　者：张晓光[1] 程诚 刘宇[3] 

机构地区：[1]西安航天动力研究所,陕西西安710100 [2]中航商用航空发动机有限责任公司,上海201108 [3]北京航空航天大学,北京100191

出　　处：《火箭推进》2015年第3期46-51,共6页Journal of Rocket Propulsion

摘　　要：采用风洞冷流试验方法研究了使用塞式喷管的运载器在4个典型飞行马赫数下外流对运载器流场和性能的影响。试验模型由截短的线性塞武喷管和升力体构成,利用纹影显示技术得到了塞式喷管流场结构并测量了不同试验工况下模型的轴向力和升力。结果表明：外流使塞式喷管喷流的膨胀程度变大,横向侧流强度增强;外流干扰下塞式喷管的推力损失包括过膨胀损失和横向侧流损失,试验喷管总推力损失在4.7%~9.6%之间,其中过膨胀损失在3%以内。Cold flow tests on effects of outflow on flow field and performance of vehicle with aerospike nozzle during flight with four typical Mach numbers are presented in this paper. The model for cold flow test is composed of a truncated linear plug nozzle and a lift body. In the tests, the nozzle flow field structure was displayed with schlieren display technology, and the axial and lift forces of the model were measured under different conditions. The results show that the existence of outflow leads to an increase in nozzle jet expansion degree and lateral flow intensity, and the thrust loss （includes over expansion loss and lateral flow loss） of aerospike nozzle, caused by outflow, is between 4.7% and 9.6%, in which the over expansion loss is less than 3%.

关 键 词：塞式喷管 升力体 外流干扰 风洞 冷流试验 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]