可重复使用宽域高速飞行器低速段动力方案分析与选型

Analysis and selection of engine schemes for reusable wide-range high-speed aircraft in the low-speed phase

为快速评估不同类型的发动机方案在可重复使用宽域高速飞行器上的适用性,对飞行器动力方案中至为关键的低速段动力方案进行了综述分析。系统研究了不同动力方案在解决宽域工作问题方面基本原理的差异,给出了各方案的工作过程及宽域工作性能,并概括分析了典型方案所适配的目标飞行器的基本情况,为飞行器总体动力方案的设计提供参考。研究结果表明:宽域高速飞行器任务需求差异对低速段动力方案的选择具有重要影响;宽域加速型任务与高速巡航型任务差异较大,但随着飞行器马赫数上限的增加,两种任务模式下低速段动力方案选择的差异开始变小;对于某一确定飞行任务的宽域高速飞行器,满足其加速需求的低速段动力方案也不唯一;基于涡扇的变循环发动机方案、燃料直接预冷发动机方案及火箭冲压RBCC与现货涡轮发动机组合的方案在加速型任务与高马赫数巡航型任务中均可适用;基于现货发动机改造及组合的低速段动力方案,在低成本、高敏捷的两级入轨飞行器第一级中应用前景较好。

In order to quickly evaluate the applicability of different types of engine schemes for reusable wide-range high-speed aircraft,those engine schemes in the low-speed phase which is the most critical part for the feasibility evaluation,are reviewed.The difference in basic principles between different propulsion schemes for solving the wide-range work problems is systematically studied.The working process and performance of each scheme are given,and the target aircraft adapted to the typical scheme is summarized and analyzed to support the engine scheme design.The research results show that different mission requirements of the widerange high-speed aircraft have important impacts on the selection of low-speed-phase engine schemes,especially between the wide-range acceleration mission and the high-speed cruise mission.However,as the upper limit of the aircraft’s Mach number increases,the difference in the selection of propulsion schemes in the low-speed phase between the two missions is narrowed.For a wide-range high-speed aircraft with a certain flight mission,the low-speed power scheme that can meet its requirement is not unique.The variable cycle engine scheme based on turbofans,the fuel precooling engine scheme,and the combined RBCC and turbofan scheme are all applicable to the acceleration mission as well as the high Mach number cruise mission.The low-speed engine schemes based on the modification and combination of existing engines have a good application prospect in the first stage of the two-stage-to-orbit(TSTO)vehicle with low cost and high agility.