Numerical simulation on infrared radiation characteristics of vertical take-off and landing nozzle
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摘要:
为提高飞机排气系统的红外隐身性以及机动性，发展和提出一种多轴级联旋转式垂直起降喷管，并运用Malkmus统计窄谱带模型和反向蒙特卡洛法(RMCM)对常规巡航、垂直起降和中间形态S隐身模式下喷管红外辐射特性进行参数化研究。结果表明：相比于常规巡航模式喷管，垂直起降模式喷管红外辐射强度最大降低23%，S隐身模式喷管最大降低47%；舱段相对转角变化规律对S隐身模式喷管红外辐射特性影响显著，此外靠近出口的舱段相对转角变化规律对垂直起降模式喷管红外辐射特性影响较小。
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关键词:
- 排气系统 /
- 垂直起降喷管 /
- Malkmus统计窄谱带模型 /
- 反向蒙特卡洛 /
- 红外辐射
Abstract:In order to improve the infrared stealth and maneuverability of aircraft exhaust system, a multi-axis cascade rotary vertical take-off and landing nozzle was developed and proposed, and the infrared radiation characteristics of nozzles in conventional cruise, vertical takeoff and landing and intermediate form S stealth modes were studied parameterized by using Malkmus statistical narrow band model and the reverse Monte Carlo method (RMCM). The results showed that compared to the conventional cruise mode nozzle, the infrared radiation intensity of the vertical takeoff and landing mode nozzle was reduced by a maximum of 23% and the S stealth mode nozzle by a maximum of 47%. And the relative angles of the cabins had a significant effect on the infrared radiation characteristics of the S stealth mode nozzle, and the relative angles of the cabins near the exit had little effect on the infrared radiation characteristics of the nozzle in vertical takeoff and landing mode.
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图 1 垂直起降喷管模型及其结构示意图
Figure 1. Vertical takeoff and landing nozzle model and its structure diagram
图 5 CO2在4.3 μm吸收带处透过率计算与实验对比
Figure 5. Comparison of spectral transmittance of CO2 at 4.3 μm simulated by malkmus to the experiment
图 6 RMCM数值计算值与圆形平面辐射强度理论值对比
Figure 6. Comparison of the calculated value of circular plane RMCM and its theoretical value of infrared radiation
图 7 不同探测角下喷管壁面可探测面积
Figure 7. Detectable area of nozzle wall at different detection angles
图 8 不同模式下喷管红外辐射强度分布
Figure 8. Infrared radiation intensity distribution of nozzle under different modes
图 9 不同模式下喷管对称面以及壁面温度分布
Figure 9. Temperature distribution of nozzle symmetry plane and wall under different modes
图 10 各S型喷管对称面燃气以及壁面温度分布
Figure 10. Symmetrical surface and wall temperature distribution of S-shaped nozzles
图 11 D和E喷管对称面的流线以及湍流动能分布
Figure 11. Distribution of streamlines and turbulent kinetic energy on the symmetry surface of nozzles D and E
图 12 各S隐身型喷管红外辐射强度分布
Figure 12. Infrared radiation intensity distribution of S-shaped nozzles
图 13 各垂直起降型喷管红外辐射强度分布
Figure 13. Infrared radiation intensity distribution of vertical takeoff and landing nozzles
图 14 各垂直起降型喷管温度分布
Figure 14. Temperature distribution of vertical takeoff and landing nozzles
表 1 喷管结构尺寸
Table 1. Nozzle structure size
mm 参数 数值 参数 数值 L1 240 R 600 L2 600 H 550 L3 600 W 1000 L4 360 ΔΥ 560 
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表 2 不同喷管相对转角组合
Table 2. Different nozzle relative angle combination
工况模式 相对转角/（°） θ1 θ2 θ3 常规巡航 0 0 0 S隐身型（前缓后急） −16 −25 41 垂直起降 30 35 30
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表 3 S喷管相对转角组合
Table 3. S-shaped nozzle relative angle combination
喷管工况编号 相对转角/（°） θ1 θ2 θ3 A（前缓后急） −16 −25 41 B（前缓后急） −22 −12 34 C（缓急相当） −28 0 28 D（前急后缓） −34 12 22 E（前急后缓） −40 23 17
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表 4 垂直起降型喷管相对转角组合
Table 4. Vertical takeoff and landing nozzle relative angle combination
喷管工况编号 相对转角/（°） θ1 θ2 θ3 A1 30 25 40 B1 30 35 30 C1 30 45 20
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