11 results about "Wing membrane" patented technology

The invention discloses an intelligent ski suit based on a wing-mounted structure and ice and snow culture symbols, and belongs to the technical field of ice and snow sports. The intelligent ski suit comprises a suit body; the wing-mounted structure module is connected with the garment body and used for providing extra lift force and stability for the skiing process; the intelligent control module is arranged on the garment body, is in communication connection with an external system and is used for providing electronic fence, position tracking, falling alarm and low-body-temperature alarm functions for the skiing process; the ice and snow culture symbols are printed on the garment body; each wing-mounted structure module comprises a fishbone-shaped framework arranged inside and telescopic wing films wrapping the inner side and the outer side of the fishbone-shaped framework, and the wing-mounted structure modules are connected between the trunk and the armholes and can be hidden relative to the garment body. The aerodynamics characteristic of sliding can be effectively improved through the wing-mounted structure, the sliding stability is improved, the falling risk caused by the out-of-control posture is reduced, and the ice and snow cultural symbols have the decorative function and the high-recognition-degree safety identification function.

This invention discloses a miniature biomimetic folding flapping wing system and its aircraft, belonging to the field of flapping wing aircraft. It includes a flapping wing, comprising wing veins and a wing membrane adhered to the wing veins. The wing veins are arranged radially, with gaps between adjacent veins, forming a flexible hinge with the wing membrane. A horizontal rod is provided on the spandex side of the folding wing to apply torque to the wing veins for unfolding and contraction, and a vertical rod is provided on the chordal side of the folding wing for connection to the fuselage of the flapping wing aircraft. The flexible hinge formed by the wing veins and wing membrane ensures the regular folding of the wing without adding extra mass.

The application discloses a kind of aircraft structures with repeatable jumping and gliding function, it is related to the field of jumping glider aircraft.The application reduces the additional mass caused by increasing the jumping structure and effectively improves the jumping height of the glider.The aircraft includes a fuselage, a pair of wings and a wing membrane connected to the wings.The fuselage includes a head shell, a base shell and a plurality of carbon fiber rods connected between the two, a jumping drive assembly is provided between the head shell and the base shell for bending the carbon fiber rods, and a folding drive assembly is provided in the base shell for folding the wings.The application effectively improves the movement range of the glider and expands its application range.

The invention discloses a wing of a bionic flapping-wing aircraft capable of inhabiting in a manner of being perpendicular to a wall surface. The wing comprises a connecting component, a supporting framework and a wing membrane, the connecting component is of a four-fork branch supporting arm structure of a forked structure, the tail end of each supporting arm is provided with a long hole used for fixing the supporting framework, and the center boss is provided with a rudder arm connecting hole used for being connected with a driving component. The supporting framework comprises a main force bearing beam, sub-components distributed in a radial mode, transverse fixing wing ribs and rear wing supporting wing ribs distributed in an annular mode. The wing film is adhered to the surface of the supporting framework to form a front wing area and a rear wing area of the wing; wherein the outer contour of the front wing area is constructed to have the curvature radius which is continuously reduced from the wing root to the wing tip, and a variable curvature radius layout is formed; and the hip angle curvature radius of the rear wing area is 50mm. Through structural innovation, the aerodynamic efficiency, the structural stability and the collaboration with inhabiting components of the wing are effectively improved, and the wing is particularly suitable for a bionic flapping-wing aircraft needing to inhabit on a vertical wall surface.

The application discloses a land-air amphibious bionic robot, and belongs to the technical field of robots. The existing land-air amphibious robot has large overall quality and volume, and the ground walking flexibility still needs to be improved. The application comprises a body, a leg mechanism and a wing-leg mechanism. The leg mechanism is provided with two rear legs and is symmetrically arranged at the rear side of the body. The wing-leg mechanism comprises two wing legs and two wing membranes. The two wing legs are symmetrically arranged at the front side of the body and can bend knees and step. The two wing membranes are symmetrically arranged at the left and right sides of the body. Each wing membrane is installed on the body and the wing leg and the rear leg on the same side and can be folded and unfolded. When the two wing membranes are unfolded, the two wing legs are driven to drive the two wing membranes to swing up and down synchronously. The wing membrane is subjected to the upward lifting force of air, so that the robot can fly in the air. When the two wing membranes are folded, the two wing legs and the two rear legs are driven to bend knees and step, so that the robot can walk on land. The application is mainly used for the execution of complex environment tasks.

Disclosed in the present invention is a modular whole ornithopter structure, comprising a fuselage plate, a driving module, wings and a tail wing, wherein a mounting hole configured for the assembly of the driving module is provided at the front end of the fuselage plate; mounting brackets are arranged at intervals on the back of the fuselage plate; mounting slots are provided at the top of the mounting brackets; a horizontal flexible pressing plate is inserted into all the mounting slots; and wing membranes of the wings are tightly pressed between the mounting brackets and the flexible pressing plate; a shoulder connector and a rear-end connector are provided at the shoulder and the tail of each wing, respectively, and the shoulder connectors and the rear-end connectors are both rotationally arranged on the fuselage plate; the tail wing is provided with a tail-wing fixing member; a tail wing connector is detachably provided at the rear end of the fuselage plate, and the tail wing connector is provided with a servo; and the tail-wing fixing member is rotationally coupled to the servo by means of a universal joint and a linkage mechanism. In the present invention, large-area planar components and small-volume three-dimensional components are subjected to complete mounting decoupling, thereby minimizing the transportation cost of the whole ornithopter, and facilitating the assembly, disassembly and maintenance.

The application discloses a gas release valve device and a control method of a bird wing membrane flap structure, which comprises a shell, a piston, a left end bionic gas release valve, a middle bionic gas release valve and a right end bionic gas release valve, and the upper and lower end faces of the shell are respectively provided with an exhaust port and an air inlet. The bionic gas release valve device is connected by the left end bionic gas release valve, the right end bionic gas release valve and the middle bionic gas release valve through the piston and a connecting column, the piston can slide in the piston pin seat, and the opening and closing control of the gas release valve is realized. The gas release valve device is inspired by the bird wing membrane flap structure, a pressure difference exists on both sides of the gas release valve, the membrane flap structure is bent, when the pressure difference exceeds a critical value, the long and short flaps of the membrane flap are separated to form an air duct, the gas is discharged, and the effect of protecting the airplane engine is achieved. The gas release valve device is simple in structure, stable and reliable, low in cost and easy to popularize.

This invention discloses a foldable flapping wing structure with a large fold-out ratio. This flapping wing structure mimics the wings of a katydid, achieving both storage and deployment through a folding mechanism. By employing a bistable composite material wing rod instead of a conventional wing rod, the flapping wing's deployment and retraction motion can be achieved using the inherent "folding" and "stretching" stable equilibrium states of the bistable wing rod material. Through this folding mechanism, the fold-out ratio of this flapping wing structure can reach over 10, significantly reducing the aircraft's storage size and greatly improving portability. This effectively solves the problems of large storage space and easily damaged wing membranes in flapping-wing micro-aircraft. When the flapping-wing micro-aircraft is in use, the flapping wing structure can be unfolded from its folded state. This design helps improve the ease of use, deployment versatility, and adaptability to complex environments of flapping-wing micro-aircraft, expanding its application scenarios.

The invention relates to the technical field of micro bionic flapping wing flying robots, in particular to a bionic flexible foldable flapping wing micro robot. Comprising a robot body and two flexible wings arranged on the left side and the right side of the robot body. The flexible wing comprises a wing root rotating shaft, a flexible wing membrane, an asymmetric micro joint, a wing leading edge and wing veins, the wing root rotating shaft is fixedly connected with one end of the wing leading edge, and one or more wing veins are arranged below the wing leading edge to jointly form a framework; the flexible wing membrane covers the framework and is connected with the framework; the asymmetric micro-joints are arranged at the joints of the front edges of the wings and veins, and the asymmetric micro-joints are of asymmetric structures, so that the flexible wings present different flexible responses in the up-down flapping movement directions. The asymmetric deformation in the upward and downward flapping directions is realized, so that the aerodynamic efficiency of the flapping wing flight is obviously improved, and the bionic flight effect of increasing the lift force and reducing the resistance can be realized without adding an additional mechanical structure.

The invention relates to the technical field of aviation, in particular to a flapping wing mechanism regulation and control device, an aircraft and a regulation and control method, and aims to solve the technical problems that in the prior art, the same rigidity distribution of wings on the two sides cannot be guaranteed, so that the wings on the two sides generate different thrust and control torque under the same flapping motion; therefore, the maneuverability and the flight efficiency of the ornithopter are influenced. The flapping wing mechanism regulation and control device comprises a wing membrane tension degree regulation assembly, a wing membrane angle regulation assembly, a wing membrane and a wing framework, the wing membrane is pasted on the wing framework, the wing membrane tension degree regulation assembly is fixed on the wing framework, and the wing membrane angle regulation assembly is rotationally connected with the wing membrane tension degree regulation assembly. The flapping wing mechanism regulation and control device, the aircraft and the regulation and control method are used for regulating the rigidity of the flapping wing mechanism.

The utility model discloses an elastic tail fin structure which comprises a fiber base layer, a plurality of resin bonding layers and a plurality of fiber middle layers are fixed on two sides of the fiber base layer, the resin bonding layers and the fiber middle layers are alternately arranged, and the lengths of the resin bonding layers and the fiber middle layers are gradually reduced. The elastic tail fin structure has the advantages that the multiple fiber middle layers are stacked on the two sides of the fiber base layer through the resin bonding layers to form the boneless tail fin, and compared with a tail fin structure with a fin bone and a wing membrane combined, the elastic tail fin has better elasticity and toughness, and the propelling efficiency can be improved; and the whole tail fin is of a structure with a thick front end and a thin rear end, so that the elastic coefficient of the tail fin structure is gradually reduced from the root of the front end to the tip of the rear end, elastic potential energy can be better stored at different speeds and pendulum frequencies, and the propelling efficiency is improved. The elastic tail fin can be applied to water sports equipment such as a surfboard and a power floating plate and is used for providing auxiliary thrust and improving user experience.