Aircraft engine's infrared lock-on range due to back pressure penalty from choked convergent nozzle

被引:20
作者
Baranwal, Nidhi [1 ]
Mahulikar, Shripad P. [1 ,2 ]
机构
[1] Indian Inst Technol, Mandi 175001, Himachal Provin, India
[2] Indian Inst Technol, Dept Aerosp Engn, Bombay 400076, Maharashtra, India
关键词
Back pressure penalty; IR suppression; IR lock-on range; Low observables; Stealth; Susceptibility; REAR FUSELAGE; TECHNOLOGY; SIGNATURE;
D O I
10.1016/j.ast.2014.09.020
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
The study of lock-on envelop of an aircraft is of fundamental interest for determining its susceptibility to infrared (IR) guided threats. The performance of IR signature suppression system for aircraft engine is affected by the penalties associated with its installation. This paper gives the qualitative and quantitative assessment on the IR lock-on range (R-LO) due to increase in the engine back-pressure penalty, for several operating conditions. As a case study, the effect of reducing the exit area of a choked convergent nozzle of a turbojet engine on its IR signature is analyzed. Reduction in exit area of choked convergent nozzle below the design point value results in optical blockage of hot parts and therefore, solid angle subtended by the hot parts reduces. But the effect of back-pressure penalty is to increase the IR signature from the rear aspect and in the net, the IR signature and R-LO for the same thrust level increases. Polar plots in 2-D of R-LO for different view angles with reduction in choked convergent nozzle exit area in horizontal and vertical planes are examined for 3-5 mu m band. (C) 2014 Elsevier Masson SAS. All rights reserved.
引用
收藏
页码:377 / 383
页数:7
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