36results about How to "Aerodynamic Effects" patented technology

The invention discloses an engine mobile cover and an engine reverse thrust device, relates to the technical field of aero-engines, and solves the technical problems of complex structure and inconvenience for maintenance in the prior art. The engine mobile cover comprises a mobile cover body part, a reset mechanism and at least one blocking door, wherein a blocking surface is arranged on one side surface of the blocking door; the blocking door is movably connected with the mobile cover body part, and can rotate around the movable connection position to an opening position and a closing position relative to the mobile cover body part; and the reset mechanism is arranged between one side surface, opposite the blocking surface, of the blocking door and the mobile cover body part, and can apply enough reset force to the blocking door to rotate the blocking door from the opening position to the closing position. The engine reverse thrust device comprises a core engine hood, a blade grid component, a blade grid support ring, a driving mechanism and the engine mobile cover provided by the invention. According to the invention, the structure of the engine reverse thrust device is simplified and optimized.

The invention relates to a horizontal tail front edge for a bird strike-resisting airplane. An upper honeycomb sandwich layer, a lower honeycomb sandwich layer, a front edge reinforcing member and an aerofoil lining layer are arranged among spans on the horizontal tail front edge in a spanwise mode along a horizontal tail of the airplane; one angle of the front edge reinforcing member is positioned at the front end of the horizontal tail front edge; the upper honeycomb sandwich layer and the lower honeycomb sandwich layer which are in a shape of a parallelogram are fixed on upper and lower internal surfaces of a horizontal tail skin respectively, the edge of one vertex angle of each honeycomb sandwich layer is fixed with surfaces of the front edge reinforcing member and the horizontal tail skin respectively, and the edge of the other vertex angle is fixed with the surfaces of the horizontal tail skin and the aerofoil lining layer; and the honeycomb sandwich layers and the front edge reinforcing member are coated between the aerofoil lining layer and the internal surfaces of the horizontal tail skin by the aerofoil lining layer. In the horizontal tail front edge, birds are cut by the front edge reinforcing member, the impact force of the birds is absorbed by the honeycomb sandwich layers, and an internal structure of the horizontal tail front edge is protected against damage bythe aerofoil lining layer. The horizontal tail front edge is also suitable for vertical tails, aerofoil front edges and all beam edges which are likely to be subjected to bird strike on the airplane.

The purpose of this application is to disclose a drone for panoramic shooting, especially suitable for panoramic shooting, including a control device, a power supply, an electric device electrically connected to the power supply, and a propeller connected to the electric device, characterized in that, It also includes a shell and a fuselage body connected in the shell, the electric device and the propeller are connected to the fuselage, the shell is a hollow structure, the shell is provided with a camera, the control device is connected with the The electric device and the camera device are electrically connected, and the electric device and the propeller are located inside the shell; the scheme of using the middle frame and two hollow hemispheres effectively protects the fuselage of the UAV and prevents possible damage to the UAV due to collision. At the same time, it also improves the safety and effectively avoids possible injuries to pedestrians when falling or falling.

A wing leading edge that can improve the anti-bird impact performance of the aircraft. A small front beam is added inside the wing leading edge, and the front ribs arranged on the small front beam are closely attached to the additional skin. During the impact, it has a strong supporting effect on the front edge skin and the additional skin, which increases the structural rigidity and maintains the structural shape as much as possible; during the deformation process, the additional skin will drive the front rib to undergo plastic deformation, thereby absorbing more energy . The rear rib with an inclined angle can not only increase the structural rigidity, but also help to buffer the impact of the bird body and protect the beam web. The invention fully considers the weight requirements of the aircraft structure, and reasonably arranges the weight of the structure. Compared with the original structure, the thickness of the front skin and ribs is halved, which is used to increase the small front beam, additional skin, and redesign wing ribs. The weight of the structure is reduced by 3% compared with the original structure, which effectively improves the anti-bird impact performance of the leading edge of the wing.

A reflector antenna adapted for use with a mobile platform, in particular with an aircraft. The reflector antenna includes an antenna aperture, a first signal processing subsystem located closely adjacent the antenna aperture exteriorly of the mobile platform, a two channel coaxial rotary joint for allowing rotation of the antenna aperture about an azimuthal axis, and a second antenna signal processing subsystem located within the interior of the mobile platform. A feedhorn of the antenna aperture is disposed within an opening at a coaxial center of a main reflector to allow a longer length feedhorn to be employed without physically interfering with a subreflector of the antenna aperture. The first antenna signal processing subsystem includes separate channels for processing vertically polarized RF energy and horizontally polarized RF energy. The second antenna signal processing subsystem includes a transmit subsystem for amplifying and phase shifting transmit signals being sent to the antenna aperture for transmission, and a receive subsystem for processing received RF signals to provide right hand circularly polarized and left hand circularly polarized signals.

A method for providing a wind turbine blade (1) with lightning protection, the method comprising the steps of: providing a lightning protection cover (2) comprising a non-conductive medium (3) and a conductive medium (4) embedded in the non-conductive medium (3), providing a blade body (5), and attaching the lightning protection cover (2) to the blade body (5).An effective lightning protection isthus provided.

The present invention is applicable to the technical field of anti-icing, and provides an anti-overflow device, which includes a slit arranged on the windward side of the wing, at least one airtight cabin, an exhaust pipe and an injection port; the airtight cabin is arranged on the side of the slit Below; one end of the exhaust pipe extends into the airtight chamber, and the other end is connected to the ejection port; the ejection port is set on the suction peak or the high wind speed surface of the area where there is no direct collection of liquid water on the aerodynamic surface. The invention provides slits on the windward side of the wing, combined with the air suction scheme for the wing in the artificial laminar flow control, sucks the overflow water into the airtight cabin under the slit, mixes the overflow water and gas, and then passes through the ejection port It is discharged, and the ejection port is set on the suction peak of the aerodynamic surface where there is no direct collection of liquid water or the surface with high wind speed, such as the maximum thickness of the wing, the discharged water droplets will no longer collide with the aerodynamic wall surface, avoiding the recurrence of water droplets At the same time, the gas discharged tangentially will not increase the resistance of the aircraft in flight, and will not adversely affect the aerodynamic performance.

The invention discloses an airplane stall recovery device, which is capable of replacing an original airplane tail cone in an airplane stall test. The airplane stall recovery device comprises a shell, a parachute outlet mechanism, a load-carrying support and a plurality of long booms, wherein the shell is the same as the replaced airplane tail cone in shape; the parachute outlet mechanism is located above behind the interior of the shell; a stall parachute is put in the parachute outlet mechanism; the load-carrying support is located at the rear side of the interior of the shell and is connected with the parachute outlet mechanism; the load-carrying support is capable of transmitting the load of the parachute outlet mechanism to the shell of the recovery device; the long booms extend from the surface of the inner side of the shell to the joint of a stall device and a fuselage; and the long booms can be connected with the load-carrying structure of the fuselage so as to transmit the load on the shell of the recovery device to the fuselage. According to the airplane stall recovery device disclosed by the invention, the original airplane tail cone is integrally replaced in an airplane stall / tail spin trial flight test, and moreover, an appearance which is the same as the original airplane tail part is basically kept, thus, the pneumatic performance when airplane stall / tail spin trail flight is performed cannot be influenced.

The invention discloses an engine movable cover and an engine thrust reverser, and relates to the technical field of aeroengines. The technical problem of complex structure and inconvenient maintenance in the prior art is solved. The movable hood of the engine includes a movable hood body, a reset mechanism and at least one choke door. One side of the choke door is provided with a choke surface. Rotate to the open position and the retracted position relative to the main body of the moving cover; the reset mechanism is arranged between the side of the choke door away from the choke surface and the main body of the moving cover, and the reset mechanism can exert sufficient force on the choke door to make the flow choke The return force for the door to rotate from the open position to the stowed position. The engine thrust reverser includes a core machine cover, a blade cascade assembly, a blade cascade support ring, a driving mechanism and the engine moving cover provided by the invention. The invention is used to simplify and optimize the structure of the engine thrust reverser.

The invention discloses a flapping wing capable of automatically folding and unfolding for a flapping wing type micro aerial vehicle. The flapping wing consists of a power device, two hydraulic pipes, a plurality of creases, a plurality of supporting rods, a wing membrane and two folding devices, and the folding and unfolding of the flapping wing are realized by adopting a hydraulic principle. According to the flapping wing, the two hydraulic pipes and the plurality of supporting rods form wing veins of a bionic flapping wing, and the wing membrane is adhered to the bionic wing veins to form a wing surface. The flapping wing pumps liquid into different liquid chambers by virtue of a micro flow pump to generate a pressure so as to drive the flapping wing to fold up or unfold. The flapping wing disclosed by the invention has the beneficial effects of reducing the transverse size of flapping wing type micro aerial vehicle when the flapping wing type micro aerial vehicle does not fly, reducing the spaces required for carrying, transportation and storage, reducing transportation requirements, conveniently protecting the flapping wing of the aerial vehicle from being damaged, favorably replacing a damaged flapping wing to improve the service life of the micro aerial vehicle.

The invention discloses a grid seam air film cooling structure with a spool-type spoiler column and double rounded outlets, which is composed of a lip plate, a spool-type spoiler column, and a bottom plate. The lip plate and the bottom plate form a two-dimensional seam structure. In the two-dimensional seam structure, the spool-type spoiler column is used to guide the flow and strengthen the structure; the spool-type spoiler column is arranged in a straight row or fork row, and the exit of the grid seam is a double-rounded structure, and the outside of the lip plate and the bottom plate The profile surface is even, reducing the impact on the aerodynamic performance of the blade. The spool-type spoiler column eliminates the low-speed reflux vortex behind the turbulent column, effectively improving the heat transfer intensity inside the grid seam; the spool-type spoiler column greatly increases the heat exchange area in the grid seam, and the Enhanced heat transfer; effectively reduce the aerodynamic loss of the cold air in the seam, and enhance the flow direction coverage of the cold air. The double-rounded structure of the outlet of the grid seam prevents the cold air from being directly injected into the mainstream after leaving the grid seam, and effectively adheres to the area near the wall surface, enhancing the adhesion ability of the air film behind the seam.