Computing The Rcs Of The Aircraft Wing Surface And Analyzed

To reduce the Radar Cross Section (RCS) of the object to the greatest extent is the purpose of stealth technique. The precision estimation of RCS is very important for aerocraft stealth design. Wings are one of the important scattering source on the aircraft. In order to reduce their RCS, the effective electromagnetic scattering analysis on wings are needed.It is the goal of this paper to present a method of designing a structural leading edge for which can offer obvious reduction of RCS within 2-18 GHz range, compared with the metal leading edge. The paper presents a scheme of using absorbing honeycomb with glass fiber sheet as the structural edge. The EM parameters and the shape of the metal-dielectric joint are the optimizing parameters. We adopt the surface integral equation method to establish models and adopt the moment of method which base on rigorous integral equations to calculate their RCS in this paper. The main results are as follows:1. Establish on numerical computing electromagnetic models of the two dimension scattering object (including whole dielectric object, dielectric coated object and metal-dielectric complex absorbing structure) in TM polarization wave. The emphasis is the precision calculation of RCS of a metal-dielectric complex front wedge wing including lossy material material covered by a fiber glass sheet.2. We use C++ language to programme on the two dimension electromagnetic scattering object model to get their RCS. In order to explain the validity of computer codes, we compare them to typical body's results which has analytical solution.3. According to an actual figure coordinate parameter and the modeled wing, we compute on the monostatic RCS and bistatic RCS of the metal wing, dielectric wing and metal-dielectric complex front wedge wing including lossy material covered by a fiber glass sheet, and have a theory explaining of numerical result.