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.

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.