11 results about "Morphing wing" patented technology

This invention relates to an integrated variable camber wing based on a piezoelectric-driven torsional cubic superstructure, comprising a wing skeleton and a skin. The wing skeleton includes multiple torsional cubic superstructures arrayed along the wing chord direction. Each torsional cubic superstructure is a cube formed by an array of multiple unit-cell torsional superstructures. Adjacent unit-cell torsional superstructures in the wing length and thickness directions share a straight rod, while adjacent unit-cell torsional superstructures in the wing width direction share four Z-shaped piezoelectric rods. Each unit-cell torsional superstructure is a cube formed by an array of four cell units, with adjacent cell units sharing a straight rod. Each cell unit includes Z-shaped piezoelectric rods and straight rods. Two Z-shaped piezoelectric rods are connected to the two ends of two straight rods. Each Z-shaped piezoelectric rod at both ends of the torsional cubic superstructure is connected to the skin. When all the Z-shaped piezoelectric rods of the unit-cell torsional superstructure undergo compressive deformation in the height direction, the unit-cell torsional superstructure undergoes torsional deformation, thus causing the torsional cubic superstructure to undergo torsional deformation. By converting the compressive deformation of the cellular unit into the torsional deformation of the compressive-torsional cubic superstructure, the wing camber is changed, and the drive components are eliminated, thus realizing the lightweight design of the morphing wing.

The application discloses a kind of torsion wing structure and aircraft, it is related to the field of morphing wing technology, including linear drive device, wing rib and pressure-torsion coupling cell, wing rib and pressure-torsion coupling cell are multiple, multiple wing ribs are arranged along the wing span direction interval, and pressure-torsion coupling cell is equipped between two adjacent wing ribs;Pressure-torsion coupling cell includes intermediate connecting component and the load-bearing end block fixedly connected with the two ends of intermediate connecting component, load-bearing end block is fixedly connected with adjacent wing rib, and all wing ribs and pressure-torsion coupling cell form wing main body;The first end wing rib of wing main body is used to be fixedly connected with fuselage;Two load-bearing end blocks of pressure-torsion coupling cell are connected with linear drive device;Linear drive device can make the two load-bearing end blocks of each pressure-torsion coupling cell approach each other or away from each other, to make intermediate connecting component torsion deformation and drive wing rib around wing span torsion by load-bearing end block.The application has the effect of "lightweight-structure simplification-aerodynamic efficiency-high life-low maintenance cost".

A fixed-wing aircraft (10) includes: a fuselage (14), a closed wing (16), a first actuator device (22), and a first connector device (24). The closed wing (16) is coupled to the fuselage (14) and has a wingtip (18) and a first deformable wing portion (20). The first actuator device (22) is arranged to supply a first input torque to the first connector device (24) when the first actuator device (22) is actuated, and the first connector device (24) is arranged to apply a first output torque to the first deformable wing portion (20) when the first input torque is supplied to the connector device. The first deformable wing portion (20) is arranged to elastically deform when the first output torque is applied to the first deformable wing portion (20). The closed wing (16) forms an outer support (26) at the wingtip (18), which is arranged to counteract the first output torque.

The application provides a dynamic simulation method for a wheel-rail variable telescopic wing structure design. The structure suitable for the dynamic simulation method comprises a base, fixed wings symmetrically arranged on the base, a movable wing provided with a wheel set, the movable wing being used to move along the fixed wings through the wheel set, a driving and transmission mechanism assembly used to drive the movable wing to extend and retract relative to the fixed wings, and the driving and transmission mechanism assembly being connected with the movable wing. The change of the lift area is realized through the extension and retraction of the movable wing relative to the fixed wings, so that the limitations of the traditional fixed configuration wing are overcome, the aspect ratio of the wing and the change of the lift area are realized, and the multi-working condition adaptation capability of the aircraft is greatly improved.

This invention belongs to the field of variable wing technology and discloses a lightweight integrated aerodynamic drive system and a deformable wing. The aerodynamic drive system includes: a double-acting cylinder integrated with the valve bodies of a normally open and normally closed electromagnetic directional valve via a cylinder head; a combined valve comprising an inflation valve and a pressure reducing valve; the inflation valve is located above the pressure reducing valve, with its valve body integrated with the pressure reducing valve's valve body, and its outlet flow channel directly connected to the pressure reducing valve's inlet flow channel; the pressure reducing valve is located on the top of the front cylinder head of the double-acting cylinder, and is connected to the normally open electromagnetic directional valve via a gas-sealed connection, directly docking with a gas cylinder. This system combines optimized gas path design and hardware integration, integrating energy and drive functions, resulting in a compact and lightweight structure. It can adapt well to the requirements of limited installation space, significantly improving the system's adaptability to various operating conditions, thereby enhancing the aircraft's flight performance.

This invention discloses a bird-inspired wing-shaped deformable aircraft that can move across media. Using birds such as pelicans, which possess transmedia capabilities, as biomimetic prototypes, and based on research into their water-entry and exiting behaviors and morphological characteristics, an innovative structural design scheme for a biomimetic deformable wing aircraft is proposed. Based on the biomechanical mechanisms of multi-joint linkage in bird skeletons and the hydrophobic properties of feathers, the aircraft employs a deformable wing and tail design; combined with lightweight materials and a multi-degree-of-freedom actuation strategy, it achieves efficient coordination between dynamic morphological switching and transmedia motion.

This invention relates to a design method for a deformable wing skeleton structure capable of multi-dimensional deformation. The method includes the following steps: S1, generating structural parameters to obtain the wing skeleton structure; S2, solving the structural driving layout of the wing skeleton structure based on a genetic algorithm to obtain an optimized wing skeleton structure; S3, calling the structural nonlinear force analysis method and the given driving structural displacement shape calculation method to calculate the displacement and subsequent shape of the optimized wing skeleton structure from the initial airfoil to the target airfoil; S4, determining whether the deformation quality of the displacement and subsequent shape from the initial airfoil to the target airfoil is qualified. If yes, outputting the total control quantity required from the initial airfoil to the target airfoil; otherwise, returning to S1. Compared with the prior art, this invention has advantages such as meeting the diverse design requirements of multi-dimensional wing deformation.

This invention discloses a control method for an adaptive deformable wing based on Hessian vector product, belonging to the field of aircraft design technology. The method includes: S1, defining the wing's design variables; S2, updating the design variables using an optimizer based on gradient information; S3, updating the wing's geometry using the FFD geometric parameterization method and adjusting the fluid computation grid; S4, calculating the aerodynamic performance data and first-order gradient of sample points using the fluid computation grid after perturbation of the design variables; S5, calculating the robust objective function and perturbation vector, and calculating the total gradient using the Hessian vector product module; S6, determining whether the wing configuration determined by the design variables has converged based on the robust objective function and the total gradient. If converged, the wing configuration is taken as the final robust optimal wing design; otherwise, the total gradient is used as gradient information, and the process returns to S2. This achieves a balance between efficiency and accuracy, ensuring the reliability and economy of the aircraft in actual operation.

The present application relates to a kind of shape memory alloy driven deformable wings, belong to aircraft wing technical field, solve the shape of existing wing fixed cannot adjust the problem of wing lift according to aircraft maneuverability demand.A kind of shape memory alloy driven deformable wings, comprising: head wing part, wing main part, shape memory alloy wire and tail wing part;The front and rear ends of the wing main part are respectively fixedly connected with the head wing part and tail wing part;The wing main part includes: elastic skin and deformable framework;The elastic skin cover is arranged in the outside of the deformable framework;Two ends of the shape memory alloy wire are respectively connected with the head wing part and tail wing part by passing through the deformable framework;When the shape memory alloy wire is contracted by temperature influence, it can pull the deformable framework to occur elastic deformation.The present application realizes that wing is deformed and recovers in the process of flight, can provide better maneuverability while improving flight efficiency.