火箭推进

针对ATR/冲压并联组合动力的高超声速飞行器,按照典型弹道对其总体性能参数进行计算和分析。结果表明:ATR工作段飞行器的加速性能良好,尤其是在Ma2.0～3.5范围内。总航程随着推重比增加而迅速增加,而飞行时间差别很小,其中ATR工作阶段所占比例显著降低。总航程和飞行时间随着升阻比增加而显著增加,且影响最大的是冲压发动机工作的Ma6.0附近区域。上述研究从飞行器系统角度出发,进一步深化了对ATR发动机的认识。

For the hypersonic aircraft with ATR/ramjet parallel combined power, its overall performance parameters are calculated and analyzed according to a typical trajectory. The results show that the acceleration of the aircraft is good during the operating phase of ATR engine, especially in the range of Mach 2.0～3.5. The total flight range increases rapidly as the thrust-weight ratio increases, while the difference of flight time is very small, in which the proportion of ATR operating phase is significantly decreased. The total flight range and flight time increase significantly with the increase of lift-drag ratio, and a sharp increment turns up when Mach number reaches up to about 6.0. The above research further deepens the understanding of ATR engine from the view of aircraft system.

引言
1 总体性能计算方法
2 总体性能分析
3 结论

图1 马赫数-高度曲线<br/>Fig.1 Height curve with Mach number

图1 马赫数-高度曲线
Fig.1 Height curve with Mach number

图2 马赫数-升阻比曲线<br/>Fig.2 Lift drag ratio curve with Mach number

图2 马赫数-升阻比曲线
Fig.2 Lift drag ratio curve with Mach number

图3 ATRR发动机沿弹道的比冲和推力变化<br/>Fig.3 Variation of specific impulse and thrust of ATRR engine along its trajectory

图3 ATRR发动机沿弹道的比冲和推力变化
Fig.3 Variation of specific impulse and thrust of ATRR engine along its trajectory

图4 不同推重比条件下航程随着马赫数的变化<br/>Fig.4 Variation of flight range with Mach number under different thrust-weight ratios

图4 不同推重比条件下航程随着马赫数的变化
Fig.4 Variation of flight range with Mach number under different thrust-weight ratios

图5 不同推重比条件下轴向过载随着马赫数的变化<br/>Fig.5 Variation of axial overload with Mach number under different thrust-weight ratios

图5 不同推重比条件下轴向过载随着马赫数的变化
Fig.5 Variation of axial overload with Mach number under different thrust-weight ratios

图6 不同推重比条件下飞行时间随着马赫数的变化<br/>Fig.6 Variation of flight time with Mach number under different thrust-weight ratios

图6 不同推重比条件下飞行时间随着马赫数的变化
Fig.6 Variation of flight time with Mach number under different thrust-weight ratios

表1 不同推重比条件下飞行器的航程和飞行时间<br/>Tab.1 Flight range and time of aircraft under different thrust-weight ratios

表1 不同推重比条件下飞行器的航程和飞行时间
Tab.1 Flight range and time of aircraft under different thrust-weight ratios

图7 不同升阻比条件下飞行时间随着马赫数的变化<br/>Fig.7 Variation of flight time with Mach number under different lift drag ratios

图7 不同升阻比条件下飞行时间随着马赫数的变化
Fig.7 Variation of flight time with Mach number under different lift drag ratios

图8 不同升阻比条件下航程随着马赫数的变化<br/>Fig.8 Variation of flight range with Mach number under different lift drag ratios

图8 不同升阻比条件下航程随着马赫数的变化
Fig.8 Variation of flight range with Mach number under different lift drag ratios

表2 不同升阻比条件下飞行器的航程和飞行时间<br/>Tab.2 Flight range and time of aircraft under different lift drag ratios

表2 不同升阻比条件下飞行器的航程和飞行时间
Tab.2 Flight range and time of aircraft under different lift drag ratios

[1] ZARLINGO F. Air-breathing propulsion concepts for high speed tactical missiles: AIAA 1988-3070 [R]. USA: AIAA, 1988.
[2] 南向谊,王拴虎,李平. 空气涡轮火箭发动机研究的进展及展望[J].火箭推进, 2008, 34(6):31-35.
[3] BRIGGS M M, ANDRUS S R. Synthesis and performance of an air-turbo ramjet-propelled supersonic target vehicle: AIAA 1984-0075 [R]. USA: AIAA, 1984.
[4] BOSSARD J A, CHRISTENSEN K L, POTH G E. ATR propulsion system design and vehicle integration: AIAA1988-3071 [R] USA: AIAA, 1988.
[5] LILLEY J S, HECHT S E, KIRKHAM B G, et al. Experimental evaluation of an air turbo ramjet: AIAA 1994-3386 [R]. USA: AIAA, 1994
[6] BOSSARD J A, CHRISTENSEN K L, FEDUN M H. Return of the solid fuel gas generator ATR: AIAA 1987-1997 [R]. USA: AIAA, 1987.
[7] OSTRANDER M J, THOMAS M E. Air turbo-rocket solid propellant development and testing: AIAA 1997-3258 [R]. USA: AIAA, 1997.
[8] SATO T, TANATSUGU N, HATTA H, et al. Development study of the ATREX engine for TSTO spaceplane: AIAA 2001-1839 [R]. USA: AIAA, 2001.
[9] EDEFUR H, HAGLIND F, OLSSON S. Design of an air-launched tactical missile for three different propulsion systems: ATR, rocket and turbojet: GT 2007-27844 [R]. USA: ASME, 2007.
[10] 屠秋野, 陈玉春, 苏三买, 等. 固体推进剂吸气式涡轮火箭发动机的建模及特征研究[J]. 固体火箭技术, 2006, 29(5): 317-345.
[11] PAN Hongliang, ZHOU Peng. Performance analysis of liquid air turbo rocket: AIAA 2008-0070 [R]. USA: AIAA, 2008.
[12] 李文龙,李平,李光熙,等. 局部进气条件下空气涡轮火箭发动机掺混燃烧研究[J].推进技术, 2013, 34(9):1222-1230.
[13] 张留欢,刘嬿,张蒙正. 基于碳氢燃料裂解工作的ATR发动机性能分析[J]. 火箭推进,2017,43(3):1-5.
[14] MA Yuan, ZHU Yan, NAN Xiangyi, et al. Investigation of the propellant preheating in air turbine rocket engine[C]// 66th International astronautical congress. [S.l.]: [s.n.], 2015, 10: 7859-7868.
[15] MATTINGLY J D, HEISER W H, PRATT D T. Aircraft engine design[M]. 2nd ed. Virginia. AIAA, 2002.
[16] 张彦军,芮长胜,付鹏哲. Ma3一级高速涡轮发动机结构方案研究[J]. 航空科学技术, 2015, 26(11):67-72.

备注

引言

1 总体性能计算方法

2 总体性能分析

3 结论

期刊信息