火箭推进

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.

引言
1 高超声速飞行器飞行过程模型
2 转级马赫数对巡航时间的影响
3 最佳转级马赫数的影响因素
4 结论

图1 火箭冲压组合方案系统的性能<br/>Fig.1 Performance of rocket-ramjet combined engines

图1 火箭冲压组合方案系统的性能
Fig.1 Performance of rocket-ramjet combined engines

图2 飞行器阻力系数随飞行马赫数的变化<br/>Fig.2 Variation of drag coefficient with flight Mach number

图2 飞行器阻力系数随飞行马赫数的变化
Fig.2 Variation of drag coefficient with flight Mach number

图3 火箭冲压组合方案飞行过程仿真<br/>Fig.3 Simulation of RWRR propulsion system hypersonic vehicle flight process

图3 火箭冲压组合方案飞行过程仿真
Fig.3 Simulation of RWRR propulsion system hypersonic vehicle flight process

图4 火箭冲压组合方案飞行时燃油余量变化<br/>Fig.4 Remaining fuel during hypersonic vehicle flight process

图4 火箭冲压组合方案飞行时燃油余量变化
Fig.4 Remaining fuel during hypersonic vehicle flight process

图5 火箭冲压组合方案飞行时加速度变化<br/>Fig.5 Acceleration of the vehicle at different Mach number

图5 火箭冲压组合方案飞行时加速度变化
Fig.5 Acceleration of the vehicle at different Mach number

图6 火箭冲压组合方案飞行时火箭消耗燃油量<br/>Fig.6 Fuel consumption of RWRR scheme during hypersonic vehicle flight process

图6 火箭冲压组合方案飞行时火箭消耗燃油量
Fig.6 Fuel consumption of RWRR scheme during hypersonic vehicle flight process

图7 飞行器加速过程中燃料消耗情况<br/>Fig.7 Fuel consumption during the acceleration process under different transition Mach numbers

图7 飞行器加速过程中燃料消耗情况
Fig.7 Fuel consumption during the acceleration process under different transition Mach numbers

图8 燃油装载量、燃油量和剩余燃油情况<br/>Fig.8 Weight of fuel initially loaded,consumption in accelerating process and remaining after acceleration

图8 燃油装载量、燃油量和剩余燃油情况
Fig.8 Weight of fuel initially loaded,consumption in accelerating process and remaining after acceleration

图9 最长巡航时间随转级马赫数的变化<br/>Fig.9 Variation of the maximum cruise time with transition Mach number

图9 最长巡航时间随转级马赫数的变化
Fig.9 Variation of the maximum cruise time with transition Mach number

图10 转级后的加速时间随转级马赫数的变化<br/>Fig.10 Aacceleration time after mode transition

图10 转级后的加速时间随转级马赫数的变化
Fig.10 Aacceleration time after mode transition

图11 最佳转级马赫数随着火箭发动机推力和比冲变化规律<br/>Fig.11 Optimal transition Mach number changes with rocket engine thrust and specific impulse

图11 最佳转级马赫数随着火箭发动机推力和比冲变化规律
Fig.11 Optimal transition Mach number changes with rocket engine thrust and specific impulse

图12 转级后的加速时间随转级马赫数的变化<br/>Fig.12 Maximum cruise time under the optimal transition Mach number changes with rocket engine thrust and specific impulse

图12 转级后的加速时间随转级马赫数的变化
Fig.12 Maximum cruise time under the optimal transition Mach number changes with rocket engine thrust and specific impulse

图13 不同起飞马赫数下最佳转级马赫数的变化规律<br/>Fig.13 Optimal transition Mach number changes with rocket engine specific impulse and the vehicle takeoff Mach number

图13 不同起飞马赫数下最佳转级马赫数的变化规律
Fig.13 Optimal transition Mach number changes with rocket engine specific impulse and the vehicle takeoff Mach number

图14 不同起飞马赫数下最长巡航时间的变化规律<br/>Fig.14 Maximum cruise time under the optimal transition Mach number changes with rocket engine thrust and specific impulse

图14 不同起飞马赫数下最长巡航时间的变化规律
Fig.14 Maximum cruise time under the optimal transition Mach number changes with rocket engine thrust and specific impulse

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备注

引言

1 高超声速飞行器飞行过程模型

2 转级马赫数对巡航时间的影响

3 最佳转级马赫数的影响因素

4 结论

期刊信息