Al/AP粉末火箭发动机推力调节性能试验

Experimental study on thrust regulation characteristics of aluminum/ammonium perchlorate powder rocket motor

基于气压驱动活塞、气体夹带颗粒输运的粉末供给方式,通过调节驱动气量和流化气量,改变粉末推进剂质量流率。采用40μm Al粉和100μm AP粉末分别作为燃料和氧化剂,对Al/AP粉末火箭发动机进行变推力点火试验。结果表明,随着粉末火箭发动机燃烧室压强的升高,Al/AP粉末的燃烧效率不断增加,燃烧效率最高可达到86.7%;在变推力调节阶段,AP粉末流量转调时间为1.1 s,Al粉末的流量转调时间为1.7 s;在喷管喉径为8 mm且氧燃比不变的情况下,推力调节比能达到1∶2.94,可实现粉末火箭发动机对推力调节的需求。

Based on the gas-driving piston and gas entrainment particles transport method, the mass flow rate of powdered pro- pellant is changed by adjusting the driving and fluidizing gas in quantity. The ignition experiments of Al/AP powder rocket motor have been carried out by using the 40μm A1 powder and 100μm AP powder as the fuel and oxidant, respectively.The results show that with the increase of combustion chamber pressure, the combustion efficiency of A1/AP powder increases, and the maximum com- bustion efficiency can reach 86.7%.In the stage of variable thrust adjustment,the transfer time of AP powder flow is 1.1 s,and the transfer time of the flow rate of A1 is 1.7 s. When the nozzle throat diameter is 8 mm and the oxygen/fuel ratio is constant, the thrust adjustment ratio is 1 ： 2.94, which can satisfy the needs of powder propellant rocket motor to realize the thrust adjustment.