火箭冲压组合发动机的最佳转级马赫数  

Optimal stage-transition Mach number of the rocket-ramjet combined engine

作　　者：王友银 唐井峰[1] 常军涛[1] 高进 鲍文[1] WANG Youyin;TANG Jingfeng;CHANG Juntao;GAO Jin;BAO Wen(School of Energy Science and Engineering,Harbin Institute of Technology,Harbin 150001,China)

机构地区：[1]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《火箭推进》2021年第6期46-54,共9页Journal of Rocket Propulsion

基　　金：国家自然科学基金(51676053)。

摘　　要：随着组合发动机在可重复使用的高超声速飞行器中广泛应用,组合发动机转级马赫数的选择对于飞行系统的整体性能至关重要。使用飞行仿真模型计算采用火箭冲压组合动力系统的飞行器的飞行过程,研究了不同的加速方案对应的0~6 Ma加速过程特性以及影响巡航时间的因素。分析表明转级马赫数越低冲压发动机消耗的燃油量越高,但转级马赫数较高时,火箭发动机的耗油率增加,因此火箭组合发动机存在最佳的转级马赫数。通过对最佳转级马赫数的影响因素进行分析,发现最佳转级马赫数受火箭发动机的比冲影响较大,在宽速域推进系统中使用具有高比冲和推力的火箭将增加高超音速飞行器的巡航时间。As the combined engine is widely used on the reusable hypersonic vehicle,the selection of transition Mach number of combined engines is significant to the overall performance of the entire flight system.By calculating the flight process of rocket-ramjet combined propulsion system with the flight simulation model,the characteristics of 0~6 Ma acceleration process and the influence factors of the cruising duration corresponding to different acceleration schemes were analyzed.The analysis showed that lower transition Mach number leads to higher fuel consumption of ramjet engine,but higher transition Mach number leads to higher fuel consumption of rocket engine.So,there is an optimal transition Mach number.The analysis on the influences of transition Mach number showed that the optimal transition Mach number largely depends on the specific impulse of rocket engine,and the high specific impulse and thrust rocket engine of the wide range propulsion system can increase the cruise time of hypersonic vehicles.

关 键 词：火箭冲压组合发动机 超燃冲压发动机 转级马赫数 燃油消耗量 发动机性能 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]