Study On The Electric Ducted Power Of UAV (Unmanned Aerial Vehicle) Launcher

In recent years with the development of science and technology,people realize the importance of unmanned aerial vehicle(UAV)in many fields,many enterprises in China and abroad to participate in the development of UAV,small UAVs get unprecedented development.Small UAV has been widely used in military and civilian USES: can be used for artillery correction,the military battlefield reconnaissance,assessment and used as a target,etc.,can be used for topographic mapping,on the civil disaster relief,meteorological observation and exploration,and the like.The current way of small UAV take off with smooth run take-off,throwing off,air delivery,rocket booster,rubber band ejection,etc.The runway for take-off runway area demand is higher,throwing off the failure rate is higher,rocket booster with a rubber band catapult takeoff initial overload is larger.In this paper,we study the electric bypass power take-off launch way,has low requirements for take-off venue,launch a high success rate and the characteristics of the small launch overload.The overall research work includes four parts: the first part of the launch of the UAV to launch the analysis to estimate the parameters Then design the structure of the launch pad assembly drawing in CATIA;Then the key components of the launcher adapter for structural strength finite element analysis;Finally processing real emission experiment was carried out to verify emission index requirements.