多变量调节固冲发动机性能分析

Performance Analysis of Multivariable-adjustable Ducted Rocket

针对多变量调节、喷管调节、进气道调节及定几何固冲发动机开展全飞行包线工作性能数值仿真,对比分析了不同类型固冲发动机不同工况下工作性能的分布情况和具体差异。结果表明,可调喷管可提高小喉径不可调喷管低空低速和大喉径不可调喷管高空高速时的推力性能;低速和高速状态下可调进气道和可调喷管分别对推力提升作用更大;在使用可调喷管的基础上使用可调进气道不仅能最大限度提高发动机推力和比冲,还可扩大发动机的正常工作包线;与中等喷管喉径定几何固冲发动机相比,多变量调节固冲发动机在高度为5 km,速度为Ma 2.5时推力提高24%,在高度为20 km,速度为Ma 4时比冲提高26%。

Directed against ducted rockets of multivariable-adjustable,adjustable-nozzle,adjustable-inlet and fixed-geometry,this paper carries out numerical simulation of working performance in full flight envelope curve.Then,compared and analyzed the conversion and specific difference of working performance of different types ducted rockets under different operating conditions.Results show that,adjustable-nozzle can improve the thrust performance of small throat diameter nonadjustable-nozzle at low altitude and low speed,as well as large throat diameter nonadjustable-nozzle at high altitude and high speed.Adjustable-inlet improves thrust great at low speed and adjustable-nozzle at high speed.On the basis of using adjustable-nozzle,using adjustable-inlet can not maximize the thrust and specific impulse,but also expand the normal working envelope.Compared with the nozzle of medium throat diameter fixed-geometry ducted rocket,the thrust of multivariable-adjustable at 5 km/Ma 2.5 is increased by 24%,and the specific impulse at 20 km/Ma 4 is increased by 26%.