一种可重复使用天地往返升力体飞行器概念及其气动布局优化设计研究

摘要

A new reusable launch vehicle (RLV) concept FL-T1 is proposed via biconic cross section design method and the parametric geometry representation method CST based on class function and shape function. On the basis of aerodynamic force analysis regarding this configuration and matching design for the control surfaces, the aerodynamic characteristics and the control efficiency are studied for the vehicle. By the concept of multi-objective optimization, the integrated aerodynamics and aerothermodynamics optimization is conducted. It has been indicated that the proposed RLV concept FL-T1 has a high hypersonic trimming lift to drag ratio, effective deceleration ability, and acceptable heating environment. It can be considered as potential concept for future RLV. The overall performance of optimized concepts is significantly improved, compared with the original one. These optimized concepts can be considered as potential choices for future design.%通过调研和梳理国内外可重复使用天地往返运输系统的方案、任务剖面、气动布局、气动特点以及飞行性能等发展情况,综合使用二次曲线方法与基于类型函数和形状函数的CST方法,提出一种具有较好的继承性和可持续自主创新发展的新型的可重复使用天地往返升力体飞行器概念(FL-T1).通过对其进行全速域的升阻特性、压心与质心布置、稳定性分析等,全面掌握了该升力体布局的气动特性.通过对该布局控制舵的匹配设计,研究了飞行器的操纵效率问题.通过多目标优化设计的思想,发展和完善了多目标优化计算方法和软件.针对本文提出的可重复使用天地往返升力体飞行器概念(FL-T1),开展了考虑气动力/气动热综合的多目标优化,获得了性能较优的优化布局.研究表明,该新型气动布局概念具有较大的高超声速配平升阻比、较好的减速特性、可接受的气动热环境、较好的高超声速稳定性和气动控制效率,可以作为未来可重复使用天地往返飞行器的潜在可行方案.在综合性能上,通过本文发展的多目标优化软件优化获得的一系列气动布局方案较初始气动布局,在所关注的方面均有显著的改进,可作为一系列备选方案供设计者选择.