基于翼身融合布局载机的组合空射飞行器概念设计与气动优化

提出了一种使用翼身融合布局载机背载火箭助推空天飞行器的概念设计及其载机平台的气动优化设计, 本设计第1级是1个大型亚跨声速翼身融合布局载机, 第2级是两个推进剂外贮箱, 第3级是一种有翼火箭推进飞行器, 空基发射相对陆基或海基发射的优势是在同等入轨质量条件下, 可以大幅度减小初始发射质量, 大幅度节省推进剂, 显著降低发射成本, 提高空天发射的便捷性, 经过设计估算, 可以1×106 kg量级起飞达到陆基多级火箭2×106 kg量级发射航天飞机级质量的目的, 并可以重复使用。对于第3级飞行器, 利用空天飞行器因其具有的高度和速度而蓄积的引力势能和动能, 具有实现环球飞行量级的大航程高速无动力滑翔飞行的潜力, 探索空射型助推滑翔式系统如何将这些巨大能量缓慢释放用于实现无动力远距离高空高速滑翔飞行。考虑到高超声速飞行器部分的气动优化潜力有限, 利用多点多约束气动优化设计方法实现了载机平台高空发射状态升阻比的较大增加和起飞状态升力系数的显著增长, 用以增大载机平台的载重能力, 而载重能力的增加可用于提升空射系统的入轨质量或者滑翔航程, 从而优化系统整体。 

Conceptual Design and Aerodynamic Shape Optimization for the Assembled Air Lunched Vehicles Based on the BWB Carrier Aircraft

The conceptual design and the aerodynamic shape optimization of the carrier for the assembled air launched vehicles via the blended wing body(BWB) carrier aircraft and the aerospace plane with rocket engines were presented in this paper. The first stage of the vehicles is a large BWB carrier aircraft with the subsonic/transonic configuration. The second stage is two external tanks of the propellant for the rockets. The third stage is a winged rocket aircraft. The air launching method, compared with the land or sea launching methods, can be used to decrease the initial weight of the launching system with the same orbital weight. The propellant for the rocket engines can be decreased obviously, so the launching can be more convenient and the cost can be decreased significantly. The weight of a space shuttle can be launched into the orbit with the initial weight of about 1×106 kg, while the weight of the space shuttle system is over 2×106 kg tons before launching via rockets, and the system can be reusable. For the third stage vehicle, the gravitational potential energy and the kinetic energy of the aerospace plane due to the altitude and speed can be used to glide around the earth with a hypersonic speed, so the method to slowly release the energy for the air launched boost gliding system is researched. Considering the limited aerodynamic optimization potential of hypersonic vehicles, the carrier aircraft is redesigned to get an optimized ratio of lift to drag at the launching state and an obviously higher lift coefficient for the take-off state with the multi-point multi-constraint aerodynamic optimization method. The increase of load capacity can be used to increase the orbital weight or gliding range, so as to optimize the overall system.