塞式喷管设计和性能验证

提出了简化的塞式喷管型面设计和优化方法,并以气氢/气氧为推进剂,对圆转方内喷管一单元直排塞式喷管性能进行了热试实验验证.用圆弧和抛物线近似内喷管型面,用抛物线和三次曲线近似塞锥型面,以从海平面到设计高度的飞行总冲最大为目标函数,进行塞式喷管型面设计和优化.介绍了实验系统及实验发动机主要零部件的结构和设计参数,给出了实验参数测量结果、实验照片和数据分析.实验表明,塞式喷管具有良好的高度补偿能力和较高的效率.在三个不同高度下,实验喷管效率在93%～98%之间,预计设计点效率不低于98%.实验结果表明,所提出的塞式喷管型面设计和优化方法是合理可行的.

Studies on aerospike nozzle design and performance validation

A simple design and optimization method of aerospike nozzle contour and the results of hot-firing tests on a 1-cell GH2/GO2 linear aerospike nozzle engine with round-to-rectangle primary nozzle are presented.The cell contour is described by two circular arcs and a parabola;the plug contour is described by a parabola and a third-order curve.The maximum total impulse from sea level to design altitude is adopted as objective to optimize the aerospike nozzle contour.Test apparatus,structures and design parameters of the main parts of the experimental engine are described.Data measured in the tests,test photographs and data analyses are delivered.It is shown that good altitude compensation of thrust and high efficiencies were obtained in the tests.At three altitudes,efficiency of the tested aerospike nozzle varies within the range of 93% to 98%.The promising efficiency of more than 98% at design point can be expected.It is proved that proposed design and optimization method of aerospike nozzle contour is reasonable and feasible.