3results about How to "Enough lift" 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 application discloses a bionic sinusoidal leading edge wing for aerial docking of tandem wing unmanned aerial vehicles, and belongs to the field of aircraft design and mechanics. The bionic sinusoidal leading edge wing for aerial docking comprises a wing main body and a bionic sinusoidal leading edge structure arranged near a wing tip of the wing main body. The application is suitable for unmanned aerial vehicles, low-speed fixed wings and airfoils requiring induced vortex control capability. The application can weaken the wing tip vortex energy, reduce the wing root bending moment of the wing, thereby reducing the operation difficulty in the docking process of the unmanned aerial vehicle, and through the reserved flat wing section, the lift coefficient and the lift-drag ratio of the wing under the small attack angle and low Reynolds number working condition are ensured from being obviously reduced.

The application relates to the field of aircrafts, and provides a tilt-rotor matrix distributed aircraft and a carrying device. According to the tilt-rotor matrix distributed aircraft provided by the application, a support arm and a wing are simultaneously arranged, the working states of the support arm and the wing are decoupled, the wing is always in a fixed state, the tilting of rotors is realized by the rotation of the support arm, the support arm tilts together with a rotor assembly arranged thereon, the downwash airflow of the rotor assembly is always kept from being blocked as much as possible, the rotor lift loss is reduced, the wing in the fixed state obtains sufficient lift by increasing the level flight speed during the tilting of the rotor, and the tilting process is smoothly transferred. The rotor assemblies are connected with the fuselage through the support arms, the distance between the rotor assemblies and the support parts of the fuselage is short, the support stiffness of the fuselage to the support arms is large, the rotary flutter problem between the rotor assemblies and the support arms is easily weakened by adjusting the stiffness design of the support arms, the rotary flutter boundary speed is improved, and a larger level flight speed is obtained.