高超声速可调进气道的记忆合金变形原理及其气动调节规律研究

Shape memory alloy is a promising material on the development of hypersonic variable inlet. Under the financial support of the preceding NSFC project, the current research team has achieved a remarkable progress on the aerodynamic principle of hypersonic variable inlet driven by shape memory alloy. Based on these results, the current project firstly plans to obtain the deformation law and the corresponding control method of shape memory alloy plate and shape memory alloy spring. Then, the variable structure scheme of hypersonic variable inlet based on shape memory alloy is proposed and the regulation law of hypersonic variable inlet performance is studied. Finally, typical morphing tests and hypersonic variable inlet wind tunnel test are arranged to check the feasibility of shape memory alloy driven inlet and demonstrate its high aerodynamic performance. By combination of hypersonic inlet aerodynamics and functional material, the current project is promising to obtain high inlet performance at a small cost of system weight and complexity, making the hypersonic variable inlets driven by shape memory alloy more realizable.

记忆合金在高超声速可调进气道上有着良好的应用前景。在上一个国家自然基金项目的支持下，课题组在基于记忆合金的高超声速可调进气道气动原理方面取得了较大进展。以此为基础，本项目拟针对前期提出的各种气动调节措施，结合记忆合金片、记忆合金弹簧开展形状记忆合金的变形规律与控制方法研究，并据此发展既便于记忆合金技术实现，又符合进气道气动调节原理的高超声速进气道变结构方法，分析掌握变结构进气道的性能调节规律和记忆合金变形/流场结构耦合作用规律，最终通过典型部位变形试验、进气道模型吹风试验展示记忆合金变形方法的可实现性，检验高超声速可调进气道的流场结构和气动性能。通过高超声速进气道空气动力学和功能材料学间的学科交叉，本项目有望进一步将记忆合金驱动的高超声速可调进气道技术推向实用，从而以较小的变结构代价获得变几何进气道的性能。

高超声速进气道往往具有宽马赫数工作的特点，其内外部的激波结构和激波/边界层干扰特性可能随马赫数的改变而发生显著变化，为了在较宽的马赫数范围内获得良好的综合性能，必须对其采取流动控制措施。以上一个国家自然基金项目为基础，本项目利用记忆合金技术实现了进气道前体激波系控制和进气道唇罩激波/边界层干扰控制的新方法。结合仿真和实验技术，获得了满足变形精度要求的记忆合金板的制备方法，掌握了进气道的性能调节规律和记忆合金变形/流场结构耦合作用规律，并进行了特定部位变形实验、进气道模型吹风实验展示了记忆合金变形方法的可实现性，并检验了采用该技术的可调进气道的气动性能。进一步将局部记忆合金驱动的高速可调进气道技术推向实用。.在该项目的资助下，已在AIAA Journal，Journal of Propulsion and Power等期刊上发表论文多篇，并获发明专利授权2项。