7results about How to "Increase lift coefficient" patented technology

This invention discloses a high lift-to-drag ratio, long-endurance, low-speed airfoil, revealing its maximum relative camber, maximum relative thickness, and the curve equations satisfied by its upper and lower edges. The origin of the coordinate system containing the airfoil is defined as the leading edge of the chord. The X-axis coincides with the chord line, pointing from the leading edge to the trailing edge of the airfoil. The Y-axis is perpendicular to the X-axis, pointing in the direction of the airfoil's curvature. The chord length is defined as C; therefore, the maximum relative camber is 6%C, and the maximum relative thickness is 4.5%C. The airfoil of this invention exhibits a higher lift-to-drag ratio and a higher lift coefficient while maintaining a lower drag coefficient. It reduces the weight of the wing structure, and its thin, curved shape results in a smaller internal wing cavity, optimizing aircraft weight while concentrating stress on the structure.

The invention relates to a large-skewness, large-retreat-amount and high-bearing double-slit flap mechanism and an aircraft. The double-slit flap mechanism comprises a driving mechanism, a sub-flap and a main flap. The driving mechanism comprises a rack, a linear driving part, a first rocker arm, a second rocker arm, a first connecting rod, a second connecting rod and a third connecting rod; the rack is arranged on the outer side wall of the duct, the lower end of the first rocker arm is hinged to the rack, and the upper end of the first rocker arm is fixedly connected with the sub-flap; one end of the second connecting rod can slide relative to the rack, the middle of the second connecting rod is hinged to the middle of the first rocker arm, the other end of the second connecting rod is hinged to one end of the third connecting rod, and the other end of the third connecting rod is hinged to the first connecting rod. The double-slit flap mechanism can meet the requirements for large retreating amount, large deflection angle and high aerodynamic load bearing, and the aerodynamic lift augmentation effect of an aircraft in the vertical take-off and landing stage is improved.

The present application relates to a kind of micro aircraft low-speed lift increasing wrinkle airfoil, including main wing, wind speed detection sensor, shape memory alloy wire, direct current power supply, remote control machine, the main wing is the wrinkle wing profile structure with lift increasing effect, the wind speed detection sensor is installed on main wing and the wind speed signal detected is passed to remote control machine, the shape memory alloy wire is electrically connected with direct current power supply, the shape memory alloy wire and direct current power supply are installed on main wing, the direct current power supply is connected with remote control machine and is controlled by remote control machine, the on-off electricity situation of shape memory alloy wire and direct current power supply is controlled by remote control machine, make main wing switch between wrinkle wing type and flat plate wing type.The present application can significantly improve the lift of micro aircraft wing, has the advantages such as controllable deformation, reliable structure, stable driving and low energy consumption.

The utility model relates to the technical field of wind power blades, in particular to an angle adjusting device of a wind power blade, which comprises a hub seat, a plurality of blades are arranged on the outer side of the hub seat, the blades are connected with the hub seat through a connecting assembly, a driving assembly used for driving the blades to rotate is arranged in the hub seat, and the driving assembly is connected with the hub seat. According to the utility model, the angles of the blades are adjusted through the driving assembly, and the blades are leveled when the wind is strong, so that the damage to the blades due to too high rotating speed of the strong wind is reduced, and the stable operation of equipment under the condition of various wind speeds is ensured; when the wind is small, the lift coefficient of the blades can be optimized by adjusting the angles of the blades and increasing the wind energy capture of the blades, and the energy conversion efficiency is improved.

The utility model relates to the technical field of air conditioners, in particular to an axial flow fan which comprises an installation disc, blades, a first reinforcing part and a second reinforcing part. The blades are arranged on the peripheral wall of the mounting disc; the first reinforcing part is arranged on the suction surface of the blade and is close to the front edge side of the blade; the first reinforcing part extends to the blade top of the blade from the blade root of the blade; the second reinforcing part is arranged on the suction surface of the blade and is close to the tail edge side of the blade; the second reinforcing part extends to the blade top of the blade from the blade root of the blade; the structural strength of the blades is improved, and therefore the strength requirement of the axial flow fan is met.

The invention discloses a flapping wing driving device, relates to the technical field of flapping wing aircrafts, and mainly aims to provide a flapping wing driving device with a wing shaft and a wing section for self-adaptive torsion. According to the main technical scheme, the flapping wing driving device comprises a rotating part, a rocker arm is arranged outside a first rod body in a sleeving mode, a protruding strip is arranged on the outer surface of a shaft body, one end of the shaft body is rotationally connected to the radial direction of the rocker arm, a base is arranged outside the rocker arm, one end of an inhaul cable is connected to the base, and the base is connected to one end of a tension spring body. The other end of the inhaul cable is wound outside the shaft body and is connected to the other end of the tension spring body; the shaft body penetrates through each shaft hole, the protruding strip penetrates through each displacement hole, the inflation pipes are arranged on the two sides of the protruding strip, a first space is formed between the protruding strip and the wing component, and the inflation pipes fill the first space; and the power part is connected to the inhaul cable. The flapping wing aircraft is mainly used for flapping wing flight.

This invention discloses an aircraft with an integrated fluid thrust vectoring nozzle and wing, comprising an integrated airfoil, an engine, an engine exhaust nozzle, and a fluid thrust vectoring nozzle; the engine is embedded within the integrated airfoil, and the engine exhaust nozzle is pre-deflected upwards. This aircraft with an integrated fluid thrust vectoring nozzle and wing effectively reduces the thickness of the wing's trailing edge, thereby reducing aft drag during flight; it is lightweight, has fewer moving parts, and exhibits fast deflection response, providing controllable pitching moment within the aircraft's cruise angle of attack; it improves the lift coefficient and control moment; and it enhances the aircraft's infrared stealth performance.