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在超音速气动热能的加热下，当飞行器表面防/隔热材料的壁面温度超过其耐受极限时，表面区域将出现高温热化学烧蚀及机械剥蚀等退化损伤现象，产生的烧蚀扩散产物(烧蚀颗粒)引射到周围等离子体流场中悬浮在飞行器周围，形成伴有烧蚀扩散物的高超声速等离子体流场，烧蚀扩散物的存在可对原等离子体流场的物理特征及电磁特性产生重要影响。本文通过建立包覆钝头锥体的等离子体流场及机载天线的耦合电磁模型，采用射线追踪方法，定量分析了伴生烧蚀产物的尾迹区等离子体流场对喇叭天线辐射特性的影响。研究结果表明，包覆飞行器的等离子体流场可造成一定量的天线辐射能量损失，而流场中弥散的烧蚀颗粒将会使这一情况加重，且烧蚀产物的密度及几何尺寸都可对天线辐射能量的损失产生影响。该研究可为解决临近空间高超声速飞行器信息传输瓶颈背后的电磁波传播提供参考，为进一步深入研究高超声速飞行器的目标探测、识别、防/隔热材料及系统设计等技术提供理论参考。When the wall temperature of the thermal protection or insulation materials on the surface of an aircraft exceeds their tolerance limits under the heating of supersonic aerodynamic heat energy, degradation damage phenomena such as high-temperature thermochemical ablation and mechanical erosion will occur in the surface area. The ablation diffusion products (ablation particles) generated are ejected into the surrounding plasma flow field and suspended around the aircraft, forming a hypersonic plasma flow field with ablation diffusion substances. The presence of ablation diffusion substances can significantly affect the physical and electromagnetic characteristics of the original plasma flow field. To address this problem, this study establishes a coupled electromagnetic model of an ablative plasma flow field surrounding a blunt-nosed cone aircraft and analyzes the antenna radiation characteristics in the wake region of the ablative flow field. The research methodology consists of several key steps: Firstly, the plasma flow field around the blunt-nosed cone is simulated using ANSYS FLUENT, a computational fluid dynamics (CFD) software. This step provides the fundamental flow field parameters (e.g., electron density, temperature, and pressure distributions). Secondly, ablation particles, generated from thermal protection material degradation, are uniformly dispersed into the plasma flow. Then, the ablative plasma flow field is obtained. Thirdly, an X-band horn antenna is designed in ANSYS HFSS and loaded into the center of the wake region of the ablative plasma flow field. Based on above models, the ray-tracing method is employed to quantitatively evaluate the attenuation of antenna radiation as it propagates through the wake region. The numerical results demonstrate that the plasma flow field enveloping the aircraft induces significant attenuation of antenna radiation energy. More noteworthy is that the presence of ablation particles within the flow field substantially amplifies this energy dissipation effect. Both the ablation particle density and size distribution are identified as dominant factors controlling radiative energy loss, exhibiting proportional relationships with the incident field's attenuation. The study systematically proves the impact of ablation particle density and size on initial field energy attenuation. This research can provide a reference for addressing the electromagnetic wave propagation underlying the information transmission bottleneck of near-space hypersonic aircraft. It also offers a theoretical basis for further in-depth research on technologies such as target detection, identification, thermal protection/insulation materials, and system design of hypersonic aircraft.
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Keywords:
- supersonic /
- ablation /
- plasma flow /
- antenna radiation characteristics
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