Research Advance in Aero-Optical Effect of High-Speed Optical Dome
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摘要: 伴随着飞行器飞行速度的不断增加，高速光学头罩技术具有极大的应用潜力和前景.只是，高速光学头罩在大气层中飞行，受到气动光学效应的影响，成像目标会出现畸变、抖动、模糊和能量衰减，影响成像精度.通过对数十年来高速光学头罩流体力学和气动光学效应的总结和梳理，初步构建了高速光学头罩气动光学效应相似准则模型.归纳了气动光学效应抑制的主要技术路线以及目前已经开展的一些工作.最后总结和讨论了高速光学头罩气动光学效应关键技术难点及未来的发展趋势，可为今后的气动光学效应研究提供一些参考和帮助.Abstract: With the increase of the aircraft flight speed, high-speed optical dome has great application potential and prospect. However, due to the influence of aero-optical effect, distortion, jitter, blur and energy attenuation may appear in the imaging targets, which will affect the imaging accuracy. By summarizing the aerodynamics and aero-optics of optical dome in recent decades, a scaling law for aero-optics of high-speed optical dome was preliminarily constructed. The main technical route of aero-optical efffect control and some recent works were also summarized. Finally, the key technical difficulties and future development trend of high-speed optical dome were summarized and discussed, which can provide some reference and help for the research of aero-optical effect in the future.
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Key words:
- aero-optical effect /
- optical dome /
- high-speed /
- scaling law /
- flow control
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图 2 THAAD拦截弹实物图(图中蓝色椭圆部分为光学侧窗)
Figure 2. Physical picture of THAAD interceptor(the blue part in the picture is the optical side window)
图 3 美国/以色列开发的红外成像制导拦截弹发射场景
Figure 3. Infrared imaging guided interceptor missile launch scenes developed by USA/Israel
图 5 基于AEDC 9号风洞搭建的气动光学效应测试平台
Figure 5. Aero-optics test platform based on AEDC #9 wind tunnel
图 12 WISH获取的散射介质波前高空间分辨率测量结果
Figure 12. Looking through a diffuser without losing resolution by WISH
图 14 Invisible Vision公司出品的改进型SI超高速分幅相机(UBSI)
Figure 14. Improved SI ultra high speed framing camera(UBSI) produced by Invisible Vision
图 16 超声速(Ma=3.8)光学头罩流动显示结果(P0=0.1 MPa, T0=300 K, ρ∞= 0.039 kg/m3)
Figure 16. Flow visualization results of supersonic (Ma=3.8) optical dome(P0=0.1 MPa, T0=300 K, ρ∞= 0.039 kg/m3)
图 17 典型带切向喷流平面侧窗几何参数以及成像光束参数示意图
Figure 17. Schematic diagram of geometric parameters and imaging beam parameters of typical plate side window with tangential jet
图 23 不同波长对应的电磁波分布图
Figure 23. Electromagnetic wave distribution map corresponding to different wavelengths
表 1 部分高性能风洞性能参数汇总
Table 1. Performance parameters summary of some high performance wind tunnels
wind tunnel Ma T0/K P0/MPa H/km Re gases t/ms JF12a 5~9 1 500~3 500 2~6 25~40 none air ~100 LENSⅠb 8~18 <6 300(He)<7 780(H2) 3.5~150 7.6~91 1.0×104~3.28×108/m air 2~20 AEDC #9c 6~14 <1 871 186 none none N2 <15 000 HIESTd 6~10 ~10 000 50~150 none 2.5×105~1.0×107/m air ~2 
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表 2 不同Mach数下不同流场结构气动光学效应特征[122]
Table 2. Characteristics of aero-optics of different flow structures at different Mach numbers[122]
aero-optics Ma ≤ 0.3 0.3 < Ma≤8 Ma>8 boundary/shear layer (1) Incompressible flow;
(2) Due to the normal aero-optical effect, the strong op-tical aberration induced by the entrance of thermal energy could be ignored;
(3) Clasical fluid mechanics could be used to compute ch-aracteristics(1) Compressible flow;
(2) Ideal gas law is valid;
(3) Aero-optical linking equation is valid ${\rm{OPD}}_{rms}^2{\rm{ = }}\alpha K_{{\rm{GD}}}^2\int_0^L {\left\langle {\rho {'^2}} \right\rangle } {l_z}{\rm{d}}z$
(4) Weak optical aberration
OPDrme/λ < 1/π
SR∝exp-(2πOPDrme2/λ)
(5) Resolution loss θβ∝θD/S1/2
(6) Bandwidth requirements of normal aberration compensation >10 kHz;
(7) Thermal control of windows may not be necessary(1) Ideal gas law is invalid;
(2) Chemical reaction of gas appear;
(3) For the reflection, refraction, absor-ption and radiation effects of beams caused by ionization or plasma, the longer the wavelength is, the greater the loss is. The intensity of radiated sound inreases strongly with the velocity, which is likely to produce turbulent field;
(4) Thermal control of optical window is essential;
(5) The reradiation effect of the flow has a strong influence on the background noise of the detectornon-viscous flow/shock negligible impact (1) Boresight error and astigmatism;
(2) With the help of low-order adaptive optics, it can be adjusted unless the attack angle changes rapidly;
(3) Wavefront error increase according to ${\rm{OPD}} \propto {K_{{\rm{GD}}}}\int_0^L {\rho '{\rm{d}}z} $
(4) Shock intensity is a function of adiabatic index, Mach number and shock angle;
(5) Reradiation energy of flow would cause thermal noise of the detector(1) Non-viscous field, wavefront error increase accroding to OPD∝ρ′R(R is the radius of the flow field curvature);
(2) Wavefront decomposition induced by the ionization/plasma structure
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