Design and Applications of Preliminary Evaluation Platform of Aerodynamic Forces for Supersonic/Hypersonic Vehicles

超声速/高超声速飞行器气动力快速估算平台设计及应用

¹ School of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China
² Shaanxi Aerospace Vehicle Design Key Laboratory, Xi’an 710072, China

Received: 18 December 2017

Abstract

Rapid evaluation of aerodynamic forces is a key technology in conceptual and preliminary performance assessment and design optimization for supersonic/hypersonic vehicles, which is expected to achieve a balance between accuracy and time. In this paper, the preliminary evaluation platform of aerodynamic forces is built based on the physical theories and engineering methods. This platform computes the local velocity vector by using the streamline tracing technology, and extracts the pressure and friction coefficients by calling methods in method database. Furthermore, an example based on HL-20 is brought out. A good agreement is obtained by comparing the calculated results via CFD with the experimental. Also, a good angle of attack compatibility of streamline tracing technology is concluded. This platform has a computation time less than that via CFD and an flight range greater than that via wind tunnel. Finally, the simple flight dynamics simulation is taken out and the synergetic process is verified.

摘要

超声速/高超声速飞行器气动力快速估算是飞行器初步设计阶段性能评估及设计优化的关键技术之一，气动力快速估算要求达到计算精度和计算速度的平衡。基于机理性的理论和工程模型建立了超声速/高超声速飞行器气动力快速估算平台。使用流线追踪方法和面元法来计算飞行器表面任意点的流动速度矢量，并调用算法数据库计算飞行器所承受的压力和摩擦力。结果表明，快速估算平台和CFD以及实验数据有较好的吻合性，基于流线的计算方法有很好的迎角适应性，算法模型符合快速估算的要求。相比于CFD，快速估算平台有更快的计算速度；相比于实验，快速估算平台有更大的适用范围。通过简单的飞行动力学仿真，验证了快速估算平台和弹道计算平台的协同仿真能力。