双组元离心式喷注器10 N发动机偏工况试验
赵 婷1,2,刘昌国1,2,吴凌峰1,2,倪维根1,2

(1.上海空间推进研究所,上海 201112; 2.上海空间发动机工程技术研究中心,上海 201112)

10 N发动机; 双组元离心式喷注器; 偏工况

Experimental investigations on non-rated condition performance of a 10 N thruster with bi-centrifugal swirl injector
ZHAO Ting1,2, LIU Changguo1,2, WU Lingfeng1,2, NI Weigen1,2

(1.Shanghai Institute of Space Propulsion, Shanghai 201112, China; 2.Shanghai Engineering Research Center of Space Engine, Shanghai 201112, China)

10 N thruster; bi-centrifugal swirl injector; non-rated condition

备注

根据国内外同类发动机研制经验,双组元10 N发动机在入口压力为0.8～2.2 MPa范围内,入口压力偏差会使发动机真空比冲、燃气温度等性能产生较大变化。为了获得双组元离心式喷注器10 N发动机在落压推进系统要求的入口压力范围内性能,通过采用小流量喷雾试验台和42 km 高模试验台,对偏工况条件下的冷态性能及热试性能进行试验研究。试验结果表明:该发动机额定入口压力1.58 MPa时真空比冲为2 881 N·s/kg; 当入口压力在0.6～2.5 MPa变化时,对应真空推力从4.7 N增加到14 N,落压比为3; 入口压力0.6 MPa时真空比冲为2 600 N·s/kg,入口压力2.5 MPa 时真空比冲为2 956 N·s/kg; 入口压力在0.6～2.5 MPa试验范围内,发动机燃烧室壁温均低于材料许用温度,表明发动机热设计优良,可满足双组元落压推进系统对姿控发动机的性能需求。

According to the development experience of 10 N bi-propellant thrusters at home and abroad, the range of inlet pressure is from 0.8 MPa to 2.2 MPa.The deviation of inlet pressure will cause great changes in thruster performance such as vacuum specific impulse and gas temperature.To investigate the performance of a 10 N bi-propellant thruster at different supply pressures from 0.8 MPa to 2.2 MPa,experiments were conducted on the discharge device with two-dimensional particle dynamic analyzer,as well as with the 42 km-high-altitude simulation test facility.It has successfully undergone all qualification tests recommended for bipropellant blowdown propulsion system.The results show that the 10 N bi-propellant thruster can fit the supply pressures from 0.6 MPa to 2.5 MPa,the nominal specific impulse of the thruster is greater than 2 881 N·s/kg when the inlet pressure is 1.58 MPa.When the inlet pressure changes from 0.6 MPa to 2.5 MPa, the corresponding vacuum thrust increases from 4.7N to 14 N and the pressure drop-down ratio is 3.As inlet pressure increases, the specific impulse also increases, when the inlet pressure is 0.6 MPa, the vacuum specific impulse is 2 600 N·s/kg; and when the inlet pressure is 2.5 MPa, the vacuum specific impulse is 2 956 N·s/kg.Within the range, the combustion chamber temperature of the thruster is lower than the allowable temperature of the material, reflecting the excellent design of the thruster, which can meet the performance demands of bipropellant blowdown propulsion system for attitude control.