16 results about "Wingspan" patented technology

A vertical take-off and landing aircraft (1) comprises a fuselage (2), at least one propulsion system (5), at least four lift propellers (10), and at least two fixed wing planes (20, 30, 40), the fixed wing planes (30, 40) located rearward of the forwardmost lift propellers (10) being located above the lift propellers (10). The lift propellers (10) are distributed on either side of the fixed wing planes (30) and on either side of the fuselage (2) such that the lift propellers (10) are separated in the longitudinal direction by at least the size of the chord (Cl, C2) of the fixed wing planes located between the lift propellers (10) and in the lateral direction by at least the width (L1, L2) of the fuselage (2) located between the lift propellers (10). At least one of the fixed wing planes (30) has a variable wingspan and the aircraft (1) comprises a control system for varying the wingspan in flight.

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 temperature monitoring unit may be removably installed inside an aircraft wing structure for monitoring temperature conditions along the span of the wing. The wing structure has a temperature-sensitive device (162) for monitoring a temperature con- dition, which is attached to a support frame (173). The support frame and attached temperature-sensitive device may be installed as a unit within the wing structure. The support frame may be configured for sliding engagement inside the wing structure, for example, with a set of tracks.

The application discloses a vertical take-off and landing fixed-wing aircraft based on thrust vector nozzles, which comprises four engines, four thrust vector nozzles, a wing, a fuselage, a T-shaped tail wing and a support; four sets of power devices adopt a four-point isosceles trapezoidal symmetrical layout, and front and rear power devices are symmetrically arranged about the gravity center of the whole machine. The transverse spacing of the front power device is 2.5-3 times that of the rear power device, the spanwise projection is located at 40%-60% of the wing span length, and the height is matched with the wing leading edge to realize jet flow lift increase; the height and horizontal position of the rear power device are optimized to ensure stable air intake. The thrust vector nozzle takes the horizontal axis of the fuselage as the 0° reference, the vector angle adjustment range is not less than -95°-+15°, and the hovering, mode transition and steady switching of the flat flight are realized through differential adjustment. The application cancels the tilting mechanism, reduces the structural dead weight, reduces the aerodynamic interference, and improves the cruising speed and flight safety.

An aircraft (10) comprising: a starboard swept wing (14A) and a port swept wing (14B), each swept wing having an inner wing section (26A) comprising an integrated payload fuselage (20) and an outer wing section (30A) for extending the wingspan and providing lift; the inner wing section comprising: a rear spar (40) disposed close to a trailing edge (22A) of each inner wing section to carry loads along each inner wing section; a wing surface (30), in which the wing surface is substantially shaped as an aerofoil, and in which the wing surface comprises a rear fairing (62) disposed behind the rear spar, and near to the trailing edge, and in which the wing surface comprises an upper curved portion (50) which has a substantially arcuate cross section, a front curved portion (52) which has a substantially arcuate cross section, and a lower wing surface, the upper curved portion meeting the rear spar at a rear of the upper curved portion, and the upper curved portion meeting the front curved portion at a front of the upper curved portion, and the front curved portion meeting the lower wing surface at a front of the lowerwing surface, a cabin structure (32) in each inner wing, in which the cabin structure comprises one or more floor beams (36) and a rear wall defined by the rear spar; in which the lowerwing surface comprises a front lower curved portion (117), in which the front lower curved portion is substantially arcuate in profile and extends from a front edge of the floor beam(s) of the cabin structure towards the rear wall; in which the lower wing surface of each inner wing extends below a first line A, the first line being a line on the rear wall of the cabin structure where a projection of the arcuate front lower curved portion of the wing surface meets the rear wall, and in which a rear lower portion of the lower wing surface meeting the front lower portion and continuing the lowerwing surface to a second line, which is spaced from and below the first line.

Part-span shrouds for pitch controlled aircrafts are disclosed herein. An example A gas turbine engine disclosed herein includes a disk, a first pitch controlled airfoil coupled to the disk, a second pitch controlled airfoil coupled to the disk, the second pitch controlled airfoil circumferentially adjacent to the first pitch controlled airfoil, and a part-span shroud including a first portion extending from the first pitch controlled airfoil, the first portion including a slot, a second portion extending from the second pitch controlled airfoil towards the first pitch controlled airfoil, and a tie rod including a first end rotatably coupled to the first portion, and a second end rotatably coupled to the second portion, and a pin disposed in the slot, the pin coupling the first portion to the tie rod, the pin circumferentially translatable within the slot.

Rotor blade (36) comprising a blade (37), wherein the rotor blade (36) is configured for use with a turbomachine (10), the blade (37) comprising: a constriction distribution (D0), measured in a narrowest region in a passage (38) between adjacent rotor blades (36), in which adjacent rotor blades (36) extend transversely across the passage (38) between opposing walls (40, 42) to interact aerodynamically with a fluid flow; and wherein the constriction distribution (D0) is defined by a trailing edge (46) of the blade (37), wherein the constriction distribution (D0) is configured to reduce aerodynamic losses and improve aerodynamic loads on the blade (37);characterized in that the constriction distribution (D0) extends essentially linearly from a constriction / constriction mid-span value of approximately 82% at approximately 5% span to a constriction / constriction mid-span value of approximately 115% at approximately 90% span, a constriction / constriction mid-span value of approximately 110% at approximately 95% span, and a constriction / constriction mid-span value of approximately 82.5% at approximately 100% span; and the span at 0% is located on a radially inner section of the airfoil (37), while a span at 100% is located on a radially outer section of the airfoil (37), and the constriction / constriction mid-span value is 100% at approximately 50% to 55% span.

The invention relates to the technical field of aviation, and particularly provides a foldable / unfoldable triangular fixed wing with a hybrid structure and an aircraft comprising the wing. The triangular wing supporting framework comprises a sliding rail, a wing leading edge beam, a wing trailing edge beam and a wing trailing edge beam sliding hinge assembly, and further comprises a skin stabilizing rib, and when the wing supporting framework is unfolded to the maximum wingspan, the skin stabilizing rib is limited and locked by the rotating sleeve connecting assembly. The number of rod pieces of the wing supporting framework structure is greatly reduced, the wing lift force is mainly generated by the inflatable skin, and therefore the wing structure is simple, and the weight of the wing is light.

An aircraft wing assembly with a fixed wing and a wing tip device are disclosed. The wing tip device is moveable between a flight configuration and a ground configuration. In the ground configuration the span of the aircraft wing assembly is reduced. The fixed wing includes a fixed wing lug and the wing tip device comprises a wing tip lug. A locking pin is provided. In the flight configuration the fixed wing lug and wing tip device lug are aligned such that the locking pin may be inserted through the fixed wing lug and wing tip device lug into a locking position to lock the wing tip device in the flight configuration. The locking pin is hollow and includes a heating element.

The application belongs to the field of aircraft technology, and particularly relates to a foldable air cushion type compound wing tri-copter unmanned aerial vehicle, which comprises an airplane power system, a guide vane span linkage conversion mechanism and a variable air cushion structure. With the aid of the variable air cushion structure, different forms of changes are well adapted to the movement of the unmanned aerial vehicle in different modes on land, water surface and in the air. With the aid of the rotatable wings and arms, the passability of the unmanned aerial vehicle when running on land and water surface is improved. The variable guide cover in the variable air cushion structure is well adapted to the shape requirement of the unmanned aerial vehicle in flight in the air. A single power element is adopted, and the rotation of the rotatable wings, the front and rear rotating arms and the extension of the front guide cover, the left guide cover, the right guide cover and the rear guide cover are synchronously completed through mechanical structure, so that the stability of the system is greatly improved, and the robustness is high.

The application discloses a kind of high integration tilting rotor wing type drive fly integrated integrated driving units and control method.The unit highly integrates wheel wing type wheel assembly, differential bevel gear type actuator, active hydraulic suspension and includes multi-stage telescopic wing and helical swing cylinder wing expansion assembly.The core innovation is to realize active damping, configuration overturn and wing expansion and contraction power reuse using hydraulic actuation mechanism.The system has three working modes: land mode, the mechanism performs steering and driving action through the wheel;Vertical take-off and landing mode, the mechanism is overturned as a whole, vertical lift is generated by rotating the wheel wing and the attitude is adjusted by vector deflection;Fixed-wing flight mode, the wing is expanded to provide lift, the wheel wing is tilted to provide aerodynamic thrust, and the flight attitude is adjusted by adjusting the wheel wing deflection angle and thrust difference instead of traditional rudder surface control.The application significantly improves the hardware reuse rate and system integration of flying car, realizes the integrated design of wheel wing and the hybrid integrated design of rotor and fixed wing.

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.

This invention discloses a mother-daughter type split-type flight-assisted aircraft, relating to the field of aircraft technology. It includes a large-wingspan UAV, on which a wireless signaler is fixed, and a fairing is fixed to the nose of the UAV. A mounting base is provided on the outer side of the fairing and is fixed to the aircraft. The fairing is respectively provided with a transmission component and a locking component for locking the mounting base. The transmission component includes a servo motor embedded in the fairing, and the locking component includes a circuit breaker fixed to the servo motor. The inner side of the fairing is respectively provided with a pressurization component and a pneumatic thrust component for boosting the mounting base. The pressurization component includes a second electric push rod rotating within the fairing. This invention, based on rapid locking and unlocking conditions using both electromagnetic and mechanical means, achieves a reusable, low-cost boosting effect for small and medium-sized aircraft during short-distance takeoff.

The application discloses an anti-crosswind vertical take-off and landing unmanned aerial vehicle and an anti-crosswind method thereof, and relates to the technical field of unmanned aerial vehicles. The anti-crosswind vertical take-off and landing unmanned aerial vehicle comprises an unmanned aerial vehicle body and a wind speed and direction instrument which is arranged separately from the unmanned aerial vehicle body. The unmanned aerial vehicle body comprises a fuselage, a flight control machine arranged in the fuselage, wings arranged on both sides of the fuselage, a propeller arranged in front of the wings, a motor in transmission connection with the propeller, a rudder surface arranged behind the wings, and a rudder in transmission connection with the rudder surface. The wind speed and direction instrument is in communication connection with the flight control machine, and the flight control machine is in cable connection with the motor and the rudder. The wind speed and direction information is measured by the wind speed and direction instrument, and the rudder is controlled to deflect and the motor is controlled to rotate according to the wind speed and direction information, attitude information and height information, so as to control the heading, height and yaw of the aircraft, make the wing span length direction consistent with the crosswind direction, and avoid landing of the aircraft in the case that the attitude is inclined without the need of a pilot to control and without the need of relying on the experience of the pilot.

The present invention provides an extreme STOL aircraft comprising: a fuselage and a wing having port and starboard wing sections. Each wing section has a body with upper and lower surfaces, leading and trailing edges, and a wingspan, i.e., the distance between a wing section tip and a wing section root connected to the fuselage, and flap covers.The aerodynamic elements integrated into the wing sections include Fowler flaps, which have leading and trailing edges and a span; flap rails, wherein the flap rails are external to the wing section body, extend rearward beyond the trailing edge of the wing section, and are configured to allow the Fowler flaps to rotate or deflect and to translate or extend and retract; Frise ailerons, wherein the Frise ailerons are located outside the Fowler flaps; and spoilers located above the leading edge of the Fowler flaps when the flaps are in the fully extended position.

A vertical take-off and landing aircraft which uses fixed rotors for both VTOL and forward flight operations. The rotors form a synthetic wing and are positioned to achieve a high span efficiency. The rotors are positioned to even out the lift across the span of the synthetic wing. The synthetic wing may also have narrow front and rear airfoils which may provide structural support as well as providing lift during forward flight. The wing rotors are tilted forward and provide some forward propulsion during horizontal flight.