用于级间分离研究的TBCC动力TSTO气动布局概念设计

Conceptual design of TBCC based TSTO configurations for stage seperation investigation

基于涡轮/冲压组合动力的水平起降两级入轨飞行模式是重复使用飞行器降低发射成本、缩短发射周期的重要途径之一,气动布局设计需要在飞行器总体规模尺度约束下满足全速域全空域的气动特性、操稳特性及防热特性需求。为研究级间分离特性,讨论了任务使命、动力配置、飞行模式及总体规模限制下的两级入轨(TSTO)重复使用飞行器的气动布局设计,针对二级及一级面临的飞行任务需求和气动特性需求,分别提出了多种气动布局方案。对两种改进方案进行了初步的气动计算,并进行了上升段升重平衡下的飞行剖面重构。为提高级间分离的安全性并提高超声速/高超声速的升阻效率和航向稳定性,对双垂尾及可下折翼梢进行了适当修改,形成了TSTO系统新一轮研究方案,并在此基础上规划了后续研究工作。

Horizontal take-off and horizontal landing (HTHL) two stage to orbit (TSTO) reusable launch vehicle (RLV) system using turbine based combined cycle engines (TBCC) is one of the most possible approaches to decrease launch cost and shorten launch operation cycle. Aerodynamic configurations for TSTO vehicle system should satisfy overall requirements covering all fly speed range and airspace range under the strictly restriction of overall sizing and mass,including aerodynamic characteristics,stability and controllability,thermal safety,maintenance,and reliability. Design consideration of a TSTO vehicle system is proposed,and several vehicle configurations for the first and the second stages are sketched separately according to each vehicle mission,propulsion selection,fight mode,and overall constraints. Advantages and disadvantages of the possible vehicle configurations are analyzed. Operation envelops for two upgraded concepts are re-designed to meet the equilibrium condition of lift and weight. To ensure the safety of stage separation,and improve lift-drag efficiency and directional stability,V tails and foldaway wingtips are adjusted,through which a new TSTO system concept is primarily ideated. Further efforts are also proposed.