火箭／冲压组合推进巡航飞行器有效载荷质量分析

摘要

针对火箭/冲压组合推进的临近空间巡航飞行器，采用“自上而下”的质量分析方法，对飞行器质量进行了合理分解，建立了飞行器有效载荷质量分析模型。以起飞质量3000 kg、航程1500 km作为总体设计要求，分别针对挤压式/泵压式供应方案、液氢/JP-10燃料、飞行器推重比以及航程等因素对有效载荷质量的影响作用进行了研究，并建立了有效载荷质量和推进系统质量对飞行器航程的响应面模型。研究结果表明，采用挤压式方案供应JP-10燃料时，飞行器可携带313 kg有效载荷；无论采用何种方案供应液氢燃料，飞行器的有效载荷均为0；以JP-10为燃料，不携带有效载荷的极限航程为2270 km；为了保证较低的推进剂质量消耗，飞行器爬升段推重比应当不低于1．2。%For rocket/dual-mode scramjet( RDMSJ) combined propulsion powered cruise vehicle operating in near space,vehi-cle mass was divided into several components utilizing the"from top to bottom"mass assessment method,and payload mass assess-ment model was established.Under the system requirements of takeoff mass of 3 000 kg,cruise range of 1 500 km,some factors af-fecting the payload mass were investigated,including gas pressure /turbo pump feeding system,liquid hydrogen /JP-10 fuel,thrust to weight ratio of vehicle,and cruise range.Response surface models were established for payload mass and propulsion system mass re-sponding to cruise range.The investigation results show that,for JP-10 fueled vehicle with gas pressure feeding system,the payload mass is 313 kg;if the vehicle is fueled by liquid hydrogen with neither feeding system,it can not carry any payload.The maximum cruise range of JP-10 fueled vehicle is 2 270 km without any payload on board.The thrust to weight ratio of RDMSJ powered vehicle should be greater than 1.2 to maintain a lower level of propellant consumption.