吸气式重复使用运载器设计初步研究  

Preliminary Design for Air Breathing Reusable Launch Vehicle

作　　者：田喜明[1] 詹浩[2] 

机构地区：[1]海军驻西安地区航空军事代表室,陕西西安710021 [2]西北工业大学航空学院,陕西西安710072

出　　处：《航空计算技术》2009年第4期61-64,共4页Aeronautical Computing Technique

摘　　要：分析了国内外吸气式可重复使用天地往返运载器的研究现状,在此基础上提出了一个水平起飞和着陆的单级吸气式运载器方案。采用Euler方程数值解法Dahlem-Buck公式和切楔法对该方案气动布局的亚、跨、超、高超音速气动特性进行了计算分析,由结果可见建立的气动布局可以满足总体方案设想中飞行任务的要求。对该方案拟采用的火箭基组合循环发动机(RBCC)进行了详细分析和性能计算,并在此基础上对该方案的飞行弹道进行了计算分析,通过与采用纯火箭发动机动力的天地往返运载器的飞行弹道对比表明,该方案能明显减小运载器的燃料消耗。Based on summarizing the development of air breathing reusable launch vehicle, the conceptual design of air breathing reusable launch vehicle is put forward. The subsonic, transonic, supersonic, and hypersonic aerodynamic performance of this design is analyzed, the results show that the aerodynamic configuration of this design can satisfy the aerodynamic requirement. The RBCC （Rocked Based Combined Cycle） engine, which is plan to used in this design, is analyzed and its performance is calculated. Base on these calculated results of the aerodynamic performance of this design and the performance of RBCC engine, the flight trajectory of this design is calculated. The comparison of flight trajectory between this design and launch vehicle using pure rocket engine indicate that, this design have obvious advantage on fuel consumption.

关 键 词：吸气式可重复使用运载器 气动布局 火箭基组合循环发动机 飞行弹道 

分 类 号：V475[航空宇航科学与技术—飞行器设计]