组合动力高超声速飞机飞行任务剖面设计方法  

Flight mission profile design method for combined power based supersonic aircraft

作　　者：谭文倩[1] 孙立国 王衍洋[1] 魏金鹏[2] 党维高 TAN Wenqian;SUN Liguo;WANG Yanyang;WEI Jinpeng;DANG Weigao(School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China;AVIC Shenyang Aircraft Design and Research Institute,Shenyang 110035,China)

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]航空工业沈阳飞机设计研究所,辽宁沈阳110035

出　　处：《飞行力学》2022年第4期1-7,共7页Flight Dynamics

摘　　要：组合动力高超声速飞机具有飞行范围大及多动力模态的特点,其飞行任务剖面设计所考虑的要素不同于Ma<2的飞机。针对组合动力高超声速飞机的飞行特点,提炼飞行任务剖面的设计要素;建立多任务段的性能指标,结合多动力模态特点,设计基本任务剖面。在此基础上,建立满足飞行性能要求的参考气动/动力匹配模型,进而提出组合动力高超声速飞机的飞行任务剖面设计方法。结合SR-72气动数据构建飞机参考构型,并据此分析其气动/动力匹配关系。所提方法能够满足组合动力高超声速飞机总体设计的性能、气动和动力的递进设计需求。As the characteristic of large flight envelope and multi-dynamic modal of the supersonic aircraft equipped with turbine based combined cycle(TBCC) engine, the factors which should be considered in the flight mission profile design is different from that in the condition of Ma<2. Considering the flight characteristic of the TBCC engine based supersonic aircraft, the design elements of flight mission section were extracted. The performance indices of multi-mission section were established, and the basic mission section was designed based on the characteristics of multi-dynamic mode. On this basis, candidate aerodynamic/propulsion system models were developed to satisfy the requirements from the flight mission profile. Then, a flight mission profile design method for the TBCC engine supersonic aircraft was proposed. The aircraft reference configuration was constructed based on SR-72 aerodynamic data, and the aerodynamic/propulsion matching relationship was analyzed. Proposed method can meet the performance, aerodynamic and propulsion progressive design requirements of the overall design of the TBCC engine based supersonic aircraft.

关 键 词：高超声速飞机 涡轮基组合循环动力 飞行任务剖面 气/推耦合 闭环迭代设计 

分 类 号：V221[航空宇航科学与技术—飞行器设计]