KEYWORDS: Aerodynamics, Finite element methods, Domes, Refractive index, Chemical elements, Protactinium, Thermal optics, Weapons, 3D modeling, Solid state physics
In the field of conventional precision guided weapon design, the aircraft dome is generally designed as part of a hemispherical dome or hemispherical dome. Hemispherical domes are easy to produce, detect and correct aberration, but hypersonic vehicles equipped with hemispherical domes generate huge air resistance and a large number of aerodynamic thermal effects during atmospheric flight, seriously affecting the working conditions of precision guided weapons. Therefore, the paper breaks through the traditional spherical dome shape design, establishes the conformal dome model of freeform surfaces such as von Karman curve, quadratic curve and sine curve, and analyzes and compares the aerodynamic thermal performance of the above-mentioned various surface domes with finite element method. The conclusion is drawn that the optimization of the dome surface based on different free curves can effectively improve the aerodynamic thermal performance of supersonic precision guided weapons and reduce the influence of aerodynamic heating on its working state.
When the aircraft is flying at high speed in the atmosphere, the incoming flow is blocked in the front section of the dome, which causing the shape of the optical dome and the refractive index to change due to aerodynamic heating effect.These changes cause the beam from the target to generate additional phase after passing through the dome, causing the target image to shift, jitter, and blur. The aero-optical transmission effect affects the imaging quality of the target,meanwhile the high-temperature dome generates thermal radiation, thus generates radiation noise, and reduces the signal-to-noise ratio of the detector.In order to study the comprehensive impact of aero-optical effects (including the aero-optical transmission effect and the aerodynamic thermal radiation effect) on the imaging quality of high-speed aircraft,the temperature field distribution and deformation field distribution of the dome are obtained by the thermal analysis of the dome.The fourth-order Runge-Kutta method is used to trace beam from the target and the dome's own radiation beam.The point spread function, MTF curve of the target image formed on the detector and the irradiance distribution on the detector were obtained through simulation calculation, and the target distorted image was obtained under affecting by the aero-optical transmission effect and the aerodynamic thermal radiation effect .Research indicates that when the aircraft is flying at high speed, the imaging quality of the high-speed aircraft optical system is seriously degraded under the influence of the aero-optical transmission effect and the aerodynamic thermal radiation effect, hence the aero-optical effect cannot be ignored.
Access to the requested content is limited to institutions that have purchased or subscribe to SPIE eBooks.
You are receiving this notice because your organization may not have SPIE eBooks access.*
*Shibboleth/Open Athens users─please
sign in
to access your institution's subscriptions.
To obtain this item, you may purchase the complete book in print or electronic format on
SPIE.org.
INSTITUTIONAL Select your institution to access the SPIE Digital Library.
PERSONAL Sign in with your SPIE account to access your personal subscriptions or to use specific features such as save to my library, sign up for alerts, save searches, etc.