一种半径可控的参数化三维前缘钝化设计方法研究

Study on a Parametric Design Method for Blunting 3D Leading Edge with Specified Radius

高超声速飞行器面临的严峻气动热环境,使其在工程应用中必须对前缘进行钝化处理。对于脊形乘波体等复杂气动构型,其在不同纵截面内上、下表面轮廓线形状可能存在较大变化,所带来的三维效应使前缘钝化面临一定困难。目前,虽然已有相应三维钝化方法可使钝化前缘与飞行器表面光滑连接,但这些方法尚不能指定各前缘点处的钝化半径。本文提出了一种半径可控的参数化三维前缘钝化方法,给出了其在脊形乘波体上的应用实例,并对钝化外形进行了CFD计算仿真。结果表明,该方法不仅实现了钝化前缘与上下表面光滑连接,且形状沿横向连续变化,还可根据热防护需求指定钝化半径,实现热防护与气动外形的多学科耦合设计。该方法适用范围广,在高超声速气动外形设计中具有重要应用价值。

The severe aerothermal environment for hypersonic vehicles requires that the sharp leading edge have to be blunted in engineering application.For hypersonic vehicles with complex configurations like chined waveriders,the profiles of upper/lower surfaces may vary greatly in different longitudinal sections,which brings it with3-dimensional effect that makes it difficult to blunt the leading edge.So far,there are relevant 3 D blunting methods that connect leading edge with vehicles' surfaces smoothly,but the blunting radius at each leading edge point still cannot be specified.A parametric method for blunting3 D leading edge with specified radius is presented in this paper,an application example in chined waveriders is given,and the CFD simulation is carried out.Results show that this method can not only guarantee smooth connection between blunt leading edge and upper/lower surfaces,but also the shape changes continuously along the horizontal direction.It can also specify the blunting radius according to the requirement of thermal protection,so that the multidisciplinary coupling design of thermal protection and aerodynamic shape is realized.The method with wide adaptability has important practical value in the design of hypersonic aerodynamic configurations.