红外与激光工程
紅外與激光工程
홍외여격광공정
INFRARED AND LASER ENGINEERING
2014年
1期
53-60
,共8页
任利锋%张靖周%单勇%刘喜岳
任利鋒%張靖週%單勇%劉喜嶽
임리봉%장정주%단용%류희악
旋翼%气动加热%红外辐射%直升机%数值计算
鏇翼%氣動加熱%紅外輻射%直升機%數值計算
선익%기동가열%홍외복사%직승궤%수치계산
rotor%aerodynamic heating%infrared radiation%helicopter%numerical calculation
文中采用数值模拟的方法较为系统地研究了旋翼表面温度分布及其对直升机红外辐射特征分布的影响。结果表明：(1)旋翼桨叶上自旋翼转轴到翼尖温度分布呈依次递增的趋势，最高温度值为316 K，高出环境温度29 K；遮挡罩表面最高温度值为317 K ，高出环境温度30 K；(2)探测角度一定时，旋翼红外辐射强度随时间上下波动，旋翼在3～5μm和8~14μm波段红外辐射强度随时间的变化趋势基本一致；(3)旋翼气动加热后3～5μm波段和8~14μm波段红外辐射强度值的增量占整机固体对应波段总的红外辐射强度的比重分别为15%～16%、5%～6%；（4）同一发射率下，气动加热的旋翼8~14μm波段红外辐射强度远大于3～5μm波段，约为3～5μm波段辐射强度的30倍，其8~14μm波段红外辐射强度约占整机固体8~14μm波段红外辐射强度的30%~40%，但降低旋翼表面发射率能有效降低旋翼8~14μm波段红外辐射强度，同时也能降低旋翼辐射占整机辐射的比重。
文中採用數值模擬的方法較為繫統地研究瞭鏇翼錶麵溫度分佈及其對直升機紅外輻射特徵分佈的影響。結果錶明：(1)鏇翼槳葉上自鏇翼轉軸到翼尖溫度分佈呈依次遞增的趨勢，最高溫度值為316 K，高齣環境溫度29 K；遮擋罩錶麵最高溫度值為317 K ，高齣環境溫度30 K；(2)探測角度一定時，鏇翼紅外輻射彊度隨時間上下波動，鏇翼在3～5μm和8~14μm波段紅外輻射彊度隨時間的變化趨勢基本一緻；(3)鏇翼氣動加熱後3～5μm波段和8~14μm波段紅外輻射彊度值的增量佔整機固體對應波段總的紅外輻射彊度的比重分彆為15%～16%、5%～6%；（4）同一髮射率下，氣動加熱的鏇翼8~14μm波段紅外輻射彊度遠大于3～5μm波段，約為3～5μm波段輻射彊度的30倍，其8~14μm波段紅外輻射彊度約佔整機固體8~14μm波段紅外輻射彊度的30%~40%，但降低鏇翼錶麵髮射率能有效降低鏇翼8~14μm波段紅外輻射彊度，同時也能降低鏇翼輻射佔整機輻射的比重。
문중채용수치모의적방법교위계통지연구료선익표면온도분포급기대직승궤홍외복사특정분포적영향。결과표명：(1)선익장협상자선익전축도익첨온도분포정의차체증적추세，최고온도치위316 K，고출배경온도29 K；차당조표면최고온도치위317 K ，고출배경온도30 K；(2)탐측각도일정시，선익홍외복사강도수시간상하파동，선익재3～5μm화8~14μm파단홍외복사강도수시간적변화추세기본일치；(3)선익기동가열후3～5μm파단화8~14μm파단홍외복사강도치적증량점정궤고체대응파단총적홍외복사강도적비중분별위15%～16%、5%～6%；（4）동일발사솔하，기동가열적선익8~14μm파단홍외복사강도원대우3～5μm파단，약위3～5μm파단복사강도적30배，기8~14μm파단홍외복사강도약점정궤고체8~14μm파단홍외복사강도적30%~40%，단강저선익표면발사솔능유효강저선익8~14μm파단홍외복사강도，동시야능강저선익복사점정궤복사적비중。
Based on CFD/IR numerical calculations, the temperature distribution of rotor skin and the effect on the infrared radiation characteristics of helicopter were studied systematically. The results show that: (1) The temperature distribution on the rotor blades shows an increasing tendency from the rotor shaft to wingtip, the maximum temperature is 316 K, 29 K higher than the ambient temperature; The maximum temperature of radiation shield is 317 K, 30 K higher than the ambient temperature; (2) At the same detection angle, rotor infrared radiation intensity fluctuates along of time, the change of infrared radiation intensity with time in 3-5μm and 8-14 μm bands is consistent; (3) The proportion of 3-5μm and 8-14μm band infrared radiation intensity increment of aerodynamic heating rotor in the same band infrared radiation intensity of overall solid are 15%-16%、5%-6%; (4) 8-14 μm band infrared radiation intensity of aerodynamic heating rotor is about thirty times as much as that of 3-5 μm band, the proportion of aerodynamic heating rotor 8-14 μm band infrared radiation intensity in the same band infrared radiation intensity of overall solid is about 30%-40%, but reduction of rotor surface emissivity is the effective method to reduce the 8-14μm band infrared radiation intensity and the proportion in the same band infrared radiation intensity of overall solid.
