Aircraft infrared (IR) signature studies are complex, due to their dependence on several parameters, e.g., line of sight ( LOS ) and viewing aspect ( LOS ^ ). There is no equivalent counterpart of the well-known radar cross section (RCS) that can be easily used for obtaining IR lock-on range, R LO , λ 1 λ 2 . This study introduces the concept of IR cross section ( IRCS ) λ 1 λ 2 of complete aircraft as seen by seeker in λ 1 λ 2 band in LOS ^ and of aircraft part in an orthogonal view. The IR solid angle ( ω IR , λ 1 λ 2 ) subtended by ( IRCS ) λ 1 λ 2 of complete aircraft and of an aircraft part is also introduced, which is the basis for redefined general criterion for lock-on by IR-guided missile. Equality based on ω IR , λ 1 λ 2 at aircraft part level and at complete aircraft level is the basis for obtaining R LO , λ 1 λ 2 of complete aircraft in terms of its ( IRCS ) λ 1 λ 2 . Dimensionless scalar factor, Π IRCS , λ 1 λ 2 , converting visual area to ( IRCS ) λ 1 λ 2 is studied, for temperatures ranging from close to ambient to maximum afterburning (reheat) mode of aeroengine. The Π IRCS , λ 1 λ 2 enables assessment of effectiveness of IR seekers with single or dual bands, for all-aspect engagement and for rear-view only.


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    Title :

    Aircraft Signature Studies Using Infrared Cross Section and Infrared Solid Angle


    Contributors:

    Published in:

    Journal of Aircraft ; 59 , 1 ; 126-136


    Publication date :

    2022-01-01




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English