摘要：【中文】本发明涉及高超声速飞行器飞行测量领域，公开了一种高超飞行器表面压力测量装置及其引压管路连接方法，包括多个布置于飞行器壳体表面的测压孔，壳体上还设置有与测压孔同轴连通的安装孔；测压孔内设置有测压嘴，测压嘴的前端与测压孔连通，测压嘴的后端设置有金属引压管；金属引压管的外壁套接有PVC软管，PVC软管通过Teflon软管与电子压力扫描阀连通。本发明中引压管路连接牢固，连接处防热、密封性能良好；测压过程利用测压孔引入外界气流，气流流经测压嘴、金属引压管和PVC软管，Teflon软管连接PVC软管和电子压力扫描阀，实现不同引压孔口径的连接过渡；气流最后由Teflon软管引入电子压力扫描阀，实现飞行器表面测点沿弹道的压力测量。 【EN】The invention relates to the field of hypersonic aircraft flight measurement, and discloses a hypersonic aircraft surface pressure measurement device and a pressure leading pipeline connection method thereof, wherein the hypersonic aircraft surface pressure measurement device comprises a plurality of pressure measuring holes arranged on the surface of a shell of an aircraft, and the shell is also provided with mounting holes coaxially communicated with the pressure measuring holes; a pressure measuring nozzle is arranged in the pressure measuring hole, the front end of the pressure measuring nozzle is communicated with the pressure measuring hole, and a metal pressure guiding pipe is arranged at the rear end of the pressure measuring nozzle; the outer wall of the metal pressure leading pipe is sleeved with a PVC hose which is communicated with the electronic pressure scanning valve through a Teflon hose. The pressure-leading pipeline is firm in connection, and the connection part is heat-proof and good in sealing performance; in the pressure measuring process, external airflow is introduced by using a pressure measuring hole, the airflow flows through a pressure measuring nozzle, a metal pressure guiding pipe and a PVC hose, and the Teflon hose is connected with the PVC hose and an electronic pressure scanning valve to realize connection transition of different pressure guiding hole calibers; and finally, introducing the air flow into an electronic pressure scanning valve through a Teflon hose to realize the pressure measurement of a measuring point on the surface of the aircraft along the trajectory.

摘要：【中文】本发明涉及高超声速飞行器姿控动力技术领域，公开了一种高超声速飞行器反作用控制装置及其防护安装机构，反作用控制装置通过防护安装机构固定于飞行器尾部底板上，反作用控制装置包括通过管路依次连接的气瓶、金属膜片贮箱和推力发动机，气瓶出口端通过电爆阀与金属膜片贮箱进气端连接，推力发动机的推进剂进口端设置有电磁阀，金属膜片贮箱的出口与推力发动机推进剂进口端的电磁阀进口连通，且金属膜片贮箱的出口与电磁阀之间设置有破裂膜片。本发明的推进剂的管理及使用安全可靠，反作用控制装置的安装满足强度和刚度要求，推力发动机喷管增加防热保护罩，避免喷管承受严酷的气动加热，反作用控制装置可适应高超声速飞行器长时间的安全飞行。 【EN】The invention relates to the technical field of attitude control power of hypersonic aircraft, and discloses a hypersonic aircraft reaction control device and a protective mounting mechanism thereof. The propellant is safe and reliable to manage and use, the reaction control device is installed to meet the requirements of strength and rigidity, the heat-proof protective cover is added to the thrust engine spray pipe, the spray pipe is prevented from bearing severe pneumatic heating, and the reaction control device can adapt to long-time safe flight of the hypersonic aircraft.

摘要：【中文】本发明涉及高超声速飞行器热防护技术领域，公开了一种高超声速飞行器超高温端头热密封结构，包括固定于飞行器端头帽近端的热阻转接板一和固定于飞行器的铝合金壳体前端的热阻转接板二；热阻转接板一与热阻转接板二之间通过连接螺钉固定连接；端头帽边缘与铝合金壳体边缘对接部位通过迷宫槽搭接；铝合金壳体外壁由内至外依次设置有气凝胶隔热层和舱体外防热层。本发明的端头帽与舱体铝合金壳体采用转接板连接，铝合金壳体与端头帽连接面为搭接迷宫槽结构，外表面连接与内表面搭接面位置错开，减小舱体防热层受热膨胀的影响，从而减小舱体防热层热应变，并减少热气流向舱体内部传热，有效实现了热密封，保证了结构的安全可靠。 【EN】The invention relates to the technical field of thermal protection of hypersonic aircraft, and discloses a hypersonic aircraft ultrahigh-temperature end head thermal sealing structure which comprises a thermal resistance adapter plate I fixed at the near end of an aircraft end head cap and a thermal resistance adapter plate II fixed at the front end of an aluminum alloy shell of an aircraft; the first thermal resistance adapter plate is fixedly connected with the second thermal resistance adapter plate through a connecting screw; the end cap edge is lapped with the aluminum alloy shell edge butt joint part through a labyrinth groove; the outer wall of the aluminum alloy shell is sequentially provided with an aerogel heat-insulating layer and an outer cabin heat-proof layer from inside to outside. The end cap and the aluminum alloy shell of the cabin body are connected by the adapter plate, the connection surface of the aluminum alloy shell and the end cap is in a lap joint labyrinth groove structure, and the lap joint positions of the outer surface connection and the inner surface are staggered, so that the influence of thermal expansion of the heat-proof layer of the cabin body is reduced, the thermal strain of the heat-proof layer of the cabin body is reduced, the heat transfer of hot air flowing to the interior of the cabin body is reduced, the heat sealing is effectively realized, and the safety and the reliability of the structure are ensured.