RBCC单级入轨运载器总体方案设计

System Design for Single-Stage-to-Orbit Launch Vehicle Utilizing RBCC Propulsion

火箭基组合循环发动机在进入纯火箭模态前,具有更大的马赫数工作区间,有利于减少燃料消耗,提高有效载荷。基于此,构建了RBCC单级入轨飞行器的数学模型,并使用hp-Radau伪谱法优化了上升段轨迹,分析了状态量的变化规律,给出了一组包括起飞规模与入轨质量,发动机组合形式与临界点选择在内的大型RBCC单级入轨运载器的初步设计方案。研究结果表明,冲压发动机性能优异,在技术上可以作为单级入轨运载器的推进方案,但严苛的工作条件间接导致飞行器结构质量偏大,制约RBCC运载器的发展。

The rocket-based combined cycle engine is the wider operating range of Mach number before switching to the rocket model.This advantage leads to fewer fuel consumption and higher effective loads.Firstly,the mathematic model of a single-stage-to-orbit launch vehicle utilizing RBCC propulsion is built.Then,the optimal ascent trajectory is solved by using hp-Radau pseudospectral method.Next,the curves of states are analyzed,and a set of preliminary design scheme of large RBCC SSTO launch vehicle,including the take-off mass,the payload,and the combination of engines,is proposed.The result demonstrates the efficiency of the ramjet,and that the RBCC engine is able to be utilized on a SSTO vehicle.However,the tough working condition indirectly increases inert weights,which is one of the major factors that restricts the development of RBCC vehicles.