Radar Cross-Section Measurements of a Full-Scale Aircraft Duct/Engine Structure

Wong, S.K.; Riseborough, E.; Duff, G.; Chan, K.K.

doi:10.1109/tap.2006.879223

Cited by 34 publications

(15 citation statements)

References 10 publications

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“…To reduce its backward Radar Cross Section (RCS), M-shaped and ∧-shaped inlets as shown in Figure 1 have been widely used. 17,20,33,34,36 However, due to its complex geometry, the inlet/fuselage integration has become a challenge task. We propose an effective method to integrate the non-conventional inlet into an arbitrary fuselage with the aerodynamic performance consideration.…”

Section: Serpentine Inlet Design and Fuselage Integration Methodsmentioning

confidence: 99%

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Serpentine Inlet Design and Analysis

Shi

Guo

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Fuselage integrated serpentine inlet has the potential to satisfy the low signature requirement for the next generation aerial vehicle. The design method and aerodynamic characteristics of serpentine inlet with sawtooth entrance are investigated in this paper using numerical and experimental approach. The steady and unsteady aerodynamic performance of the inlet at different inflow Mach numbers, angles of attack and yaw angles are obtained. The designed top-mounted serpentine inlet with triangular entrance can provide the acceptable pressure recovery and distortion without any flow control techniques. Furthermore, the structure and dynamics of the vortices inside the serpentine diffuser are analyzed under several critical conditions. Nomenclature AIP = the aerodynamic interface plane α = angle of attack β = yaw angle Ma 0 = free stream Mach number Ma 2 = Mach number at the AIP σ = total pressure recovery 0 σ ∆ = circumferential distortion index C p = pressure coefficient L1 = inner lip L2 = outer lip D = diameter of the AIPouter lip ε = turbulence intensity ϕ = mass flow ratio W = synthesis distortion index e P * = averaged total pressure at the AIP P * ∞ = total pressure at the free stream uv = local coordinate of the lip cross section α b= angle of the bottom corner of the throat cross section α t = angle of the top corner of the throat cross section R 0 = radius of the entrance corner of the transition section R top = radius of the top corner of the throat cross section R bottom = radius of the bottom corner of the throat cross section C1-C22 = static pressure taps #1-#22 on the centerline of the inlet near cowl side R1-R31 = static pressure taps #1-#31 on the centerline of the inlet near ramp side DP1-DP4 = dynamic pressure transducer #1-#4

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Section: Serpentine Inlet Design and Fuselage Integration Methodsmentioning

confidence: 99%

“…1, 8-10, 9, 16, 22, 24 The inlet fully integrated into the fuselage combined with the serpentine diffuser which can provide line-of-sight blockage of the engine blades has the potential to satisfy the requirement of low signature, light weight and low drag for the next generation propulsion system. 17,20,33,34,36 …”

Section: Introductionmentioning

confidence: 99%

Serpentine Inlet Design and Analysis

Shi

Guo

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…Suppose that both low speed and ultra-high speed targets, which presumably have the same Radar Cross-Section (RCS) [37], exist in each pulse during a short observation time. After demodulation and matched filtering which are introduced in Section III, these targets very likely hold very similar energy in the received data.…”

Section: A Identification Theorymentioning

confidence: 99%

Short-Time Velocity Identification and Coherent-Like Detection of Ultrahigh Speed Targets

Wang¹,

Zhou²,

Li³

et al. 2018

IEEE Trans. Signal Process.

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“…For example, a complex-shaped cavity such as a jet engine inlet of an aircraft typically produces a major RCS contribution at a head-on view which is a key target identification feature and also vital to the RCS calculation of the entire aircraft [1].A variety of analytical (exact, modal, etc.) and numerical techniques [geometric optics (GO) and geometric theory of diffraction (GTD); shooting and bouncing rays (SBR); physical optics (PO) and physical theory of diffraction (PTD); integral-equation methods; finite element methods; differential-equation methods; hybrid techniques, etc.]…”

mentioning

confidence: 99%

mentioning

confidence: 99%

A component model approach for the RCS validation of an electrically large open-ended cylindrical cavity

Dumanian

Burt

Kemp

2007

2007 IEEE Antennas and Propagation Society International Symposium

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The electromagnetic scattering of large open-ended cavity structures is an important problem in both military and civilian applications primarily for target characterization and radar cross section (RCS) reduction. For example, a complex-shaped cavity such as a jet engine inlet of an aircraft typically produces a major RCS contribution at a head-on view which is a key target identification feature and also vital to the RCS calculation of the entire aircraft [1].A variety of analytical (exact, modal, etc.) and numerical techniques [geometric optics (GO) and geometric theory of diffraction (GTD); shooting and bouncing rays (SBR); physical optics (PO) and physical theory of diffraction (PTD); integral-equation methods; finite element methods; differential-equation methods; hybrid techniques, etc.] have been developed and explored by researchers in an effort to generate accurate, efficient radar signatures for both simple and complex cavity geometries [2]. The particular technique chosen to solve a cavity scattering problem is dependent on many factors such as the size of cavity (electrically large versus small), the complexity of the cavity geometry (simple versus complex), the accuracy desired, the computer memory, time, and storage limitations, and the scattering phenomena that one wishes to ultimately capture in the radar signature. The RCS of a jet engine is difficult to compute due to the large and complex 3D structure, the multiple interactions between the cavity walls, and all the deficiencies of the various methods are encountered. The only alternative to these techniques is to collect measurements on a full size or scaled target which tends to be costly, time consuming, and typically will not include all radar viewing angles and frequencies.Currently no single prediction code can simultaneously meet all accuracy and computational time requirements required for the image generation (Nyquist sampling requirement) of electrically large complex targets (large asymmetric 3D targets with small features, cavities, dielectric materials, multiple interactions, etc.) with a time dependent motion. In this paper we present a novel RCS component prediction model approach to producing both fast and accurate scattering from an electrically large open-ended cylindrical cavity (circular cross section). The component model is a hybrid approach which easily permits individual scattering mechanisms to be coherently combined to produce a high fidelity signature. For this problem, the component model included scattering 2471 1-4244-0878-4/07/$20.00 ©2007 IEEE produced from the interior of the cavity calculated via the waveguide modal approach combined with the scattering produced from the cavity's finite thick rim opening (i.e., annulus) computed via the Method of Moments (MoM) and finally combined with the cavity's external base ring edge diffraction computed via PTD. Narrowband and wideband signature analysis for the circular cylindrical cavity configuration are presented to validate the component prediction model with static...

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Radar Cross-Section Measurements of a Full-Scale Aircraft Duct/Engine Structure

Cited by 34 publications

References 10 publications

Serpentine Inlet Design and Analysis

Serpentine Inlet Design and Analysis

Short-Time Velocity Identification and Coherent-Like Detection of Ultrahigh Speed Targets

A component model approach for the RCS validation of an electrically large open-ended cylindrical cavity

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