316results about "Wings" patented technology

A wing fuselage joint for an aircraft having joining members which include a first configuration and a second configuration. The joining members of the first configuration include a platform and bracket configured to pivot in a lateral plane and translate in a longitudinal direction. The joining members of the second configuration include a platform and bracket configured to pivot in a longitudinal plane and translate in a lateral direction. The joining members of either configuration join the fuselage structure and the spar of an aircraft together.

The invention discloses a vertical take-off and landing aircraft with improved linked wing tilting ducted fan layout, and belongs to the technical field of pneumatic and power systems of vertical take-off and landing aircrafts. The aircraft comprises an improved joined wing structure layout and a tilting ducted fan system integrally designed with the improved joined wing structure layout. The improved joined wing structure layout comprises a front wing, a rear wing, a vertical connecting wing surface, a vertical stabilizer and a fuselage. The front wing is divided into a front wing inner side wing surface and a front wing outer side wing surface by a vertical connecting wing surface, and adopts a sweepback wing belt dihedral structure; two ends of the rear wing are respectively arranged above the front wing through a vertical connecting wing surface, the middle part of the rear wing is arranged above the tail part of the fuselage through a vertical stabilizer, and the rear wing adopts a forward swept wing structure; the tilting ducted fan system comprises a front wing integrated ducted fan flap 7, a rear wing integrated ducted fan lifting control surface 9 and a tail propelling ducted fan 16. The core problems that pitching of a traditional connected wing is out of control, the weight of a tilting structure is large, and the energy efficiency is low are solved.

An aircraft wing includes a fixed structure and a linear hydraulic slat actuator attached to the fixed structure. The linear hydraulic slat actuator is oriented spanwise along the aircraft wing. The aircraft wing also includes an actuator output link and a slat attached to the actuator output link. The aircraft wing also includes a bell-crank coupled to the linear hydraulic slat actuator and to the actuator output link. In response to spanwise movement of the linear hydraulic slat actuator, the bell-crank is configured to move the actuator output link in a different direction that enables the slat to move between a retracted position and an extended position.

The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.

A wing for an aircraft, comprising a main wing and a high lift assembly which includes a body, and an assembly connecting the body to the main wing, so the body is movable between a retracted position and an extended position. The assembly comprises a track extending along a longitudinal axis between first and second ends, with an intermediate portion therebetween. A roller bearing ensures that the track moves along the longitudinal axis. The roller bearing comprises bearing units, each mounted to the main wing and having a bearing surface for engaging the elongate track. The units include a first and second end units and an intermediate unit wherein, relative to the longitudinal axis, the intermediate unit is positioned between the first end unit and the second end unit. The elongate track comprises a recessed portion which, in the retracted position, aligns the intermediate unit.

The invention provides an electric heating shock-resistant leading edge and a using method thereof.The electric heating shock-resistant leading edge comprises an outer side skin, a leading edge heating layer, a leading edge inner skin, an energy absorption structure layer, an energy absorption inner skin, ribs and a control module which are sequentially arranged in a stacked mode from outside to inside, the energy absorption structure comprises a Z-shaped body and a supporting body, one end of the supporting body is connected with the end of the Z-shaped body, the other end of the supporting body is connected with a bent portion of the Z-shaped body, the Z-shaped body is connected to the front edge inner skin, the supporting body is made of negative thermal expansion materials, and a probe is arranged at the position, corresponding to the supporting body, of the rib and comprises a pressure sensor and a distance monitor. And the probe and the front edge heating layer are electrically connected to the control module. The electric heating deicing function of bird impact resistance and automatic control of the front edge structure is achieved, the temperature control reliability is improved, the structural weight is reduced, and the technical problems of temperature control, bird impact resistance, structural weight reduction and the like are solved.

An assembly for an aircraft having an upper fitting fastened to a structure of the wing of the aircraft, a lower fitting fastened to a pressure-side panel of the wing, an engine pylon with two lateral panels mounted so as to articulate on the lower fitting, a starboard-side link rod and a port-side link rod mounted so as to articulate between the lateral panel that is on the same side and the upper fitting, and a stud having a proximal end secured to a rear rib of the engine pylon and a distal end mounted in an aperture of the lower fitting through an annular linear connection.

An aircraft assembly is disclosed including a wing structure, and a pipe assembly rotatably coupled to the wing structure by a fixture arrangement. The pipe assembly extends along a longitudinal direction, the fixture arrangement configured to restrict movement of at least a portion of the pipe assembly in the longitudinal direction relative to the wing structure and allow rotation of the pipe assembly relative to the wing structure.

An aircraft propulsion system includes a hybrid-electric power plant for delivering power to an air mover for propelling an aircraft. The hybrid-electric power plant includes a heat engine operatively connected to a first air mover, and an electric motor operatively connected to a second air mover. The second air mover is positioned on a wing of the aircraft outboard from the heat engine. A method for reducing trailing vortices includes powering a first air mover of an aircraft with a heat engine during a take-off stage, a climb stage, a cruise-stage and / or a descent stage. The method includes powering a second air mover of the aircraft with an electrical motor during the take-off stage and / or the climb stage. The method includes freewheeling the second air mover during the cruise stage and / or the descent stage to generate mechanical energy and reduce wing tip vortices.

The invention discloses a preparation method of a bionic vibration reduction structure of an aircraft wing leading edge, relates to the technical field of aircraft wings, and completes establishment of a bionic kangaroo jumping structure, a bionic origami honeycomb structure and a bionic woodpecker spiral structure based on three-dimensional modeling software. A bionic kangaroo jumping structure, a bionic origami honeycomb structure and a bionic woodpecker spiral structure are regionally filled into a traditional aircraft wing entity model in Magics software, and based on a laser powder bed melting technology, nickel-titanium alloy powder is used for printing and forming the filled traditional aircraft wing entity model; and preparing a PU-MXene mixed solution, and plating the PU-MXene mixed solution on the surface of the printed and formed solid model of the wing of the traditional aircraft through an electrochemical deposition method. The effects of damping the leading edge of the aircraft wing, improving the rigidity, absorbing sound, reducing noise and being super-hydrophobic are achieved.

The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.

The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.

An assembly comprising a longitudinal member of an aircraft wing, where the longitudinal member has a contact wall which is penetrated by first bores, each passing through the contact wall parallel to a longitudinal direction, an engine pylon which is arranged at the end of the longitudinal member in the longitudinal direction and having an upper longitudinal member which, for each first bore, is penetrated by a second bore which is aligned with the first bore, and a nut and a screw for each pair of a first bore and a second bore, which are aligned, where the screw is screwed into the nut successively via the first bore and the second bore, sandwiching the upper longitudinal member and the contact wall.

The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.

To provide systems and methods for assembly line processing of wing panels of an aircraft.SOLUTION: In a method of inputting wing panels 150 into an assembly line 100, the assembly line 100 has several work stations 120. The wing panels 150 are oriented in a manner so that leading edges 155 are all on a first side 166 of the work stations 120, whereas trailing edges 157 are all on a second side 165 of the work stations 120. A first portion of the work stations 120 is dedicated to wing panel leading edge 155 processing, whereas a second portion of the work stations 120 is dedicated to wing panel trailing edge 157 processing. In the system and the method, the wing panels 150 advance in a processing direction 181 in the assembly line 100.SELECTED DRAWING: Figure 1A

The invention relates to the technical field of thermal protection composite materials, in particular to a thin-wall gradient thermal protection structure and application. The thermal protection structure sequentially comprises, along a thickness direction, an outer surface layer; the ablation-resistant layer is composed of at least one layer of quartz fiber cloth, and the distance d between the outer side face of the quartz fiber cloth and the outer surface layer is larger than 0 mm and smaller than or equal to 0.3 mm; the heat insulation layer is positioned on the inner side of the ablation-resistant layer; the total thickness of the thermal protection structure is smaller than or equal to 5 mm, and the overall density of the thermal protection structure is smaller than or equal to 0.6 g / cm. According to the thin-wall gradient thermal protection structure, under the extreme lightweight constraint that the thickness is smaller than or equal to 5 mm and smaller than or equal to 0.6 g / cm < 3 >, the extra thermal insulation gain larger than or equal to 5% is obtained through the principle of gradient layering and millimeter-level near-wall ablation resistance.

The invention belongs to the technical field of aircraft wing design, and particularly relates to an upper single flat and straight wing box section upper wall plate without partitioning in the spanwise direction and the chordwise direction. Comprising a left side upper wall plate, a right side upper wall plate and a shape correction area enabling the overall aerodynamic configuration curvature to be continuous. A plurality of stringers are arranged on the upper wall plate of the upper single straight wing box section, the spanwise axes of all the stringers are perpendicular to the plane of symmetry of the airplane, and the web planes of all the stringers are perpendicular to the local theoretical appearance; a plurality of wall plate large openings are formed in the chordwise middle of an upper wall plate of the upper single straight wing box section, the center lines of the wall plate large openings are parallel in the spanwise direction, and reinforcing areas are arranged on the peripheral sides of the wall plate large openings; transition areas are formed among the left upper wall plate, the right upper wall plate and the shape correction areas, the tail ends of part of the stringers are located in the transition areas and are subjected to beveling transition treatment, and the edge parts of the wall plates located in the transition areas are subjected to reinforcement treatment.

A handling system for imparting a desired longitudinal conformation, for example a twist or skew, into a longitudinal component, for example a composite stringer for an aircraft wing, comprises a rigi

The utility model discloses an ear piece joint and aviation equipment relates to aviation equipment technical field, this ear piece joint includes: single ear horizontal joint is connected with the inner section beam, and single ear horizontal joint is the sheet structure of horizontal arrangement, and single ear horizontal joint is equipped with the through hole, double ear horizontal joint is connected with the outer section beam, and double ear horizontal joint is U shape structure, and the both ends of double ear horizontal joint are horizontal arrangement and are equipped with through -hole, fastener is passed through in through -hole and through -hole and is used for realizing the detachable connection of single ear horizontal joint and double ear horizontal joint. The ear piece joint and aviation equipment provided by the application, through the both ends of single ear horizontal joint and double ear horizontal joint are horizontal arrangement, and the upper and lower of fastener are crossed and can realize the connection of single ear horizontal joint double ear horizontal joint, can satisfy the demand that wing needs quick dismounting and quick recovery.

This invention relates to the field of biomimetic impact-resistant composite materials technology, specifically to an impact-resistant sandwich composite laminate with a multi-layered structure inspired by the giant toothed ant and its preparation method. The impact-resistant sandwich composite laminate comprises multiple fiber tube layers and multiple fiber cloth layers, wherein one fiber tube layer is located between two fiber cloth layers; the fiber cloth layers include multiple unidirectional fiber cloth layers and / or multiple woven fiber cloth layers; each fiber tube layer includes at least one columnar fiber tube layer, and each columnar fiber tube layer is composed of an array of multiple columnar fiber tubes arranged in a vertically aligned bundle along its thickness direction. This invention enhances the interlayer bonding strength and load-bearing capacity through the interfacial wave-locking effect of the woven fiber cloth and the interlayer interlocking effect of the columnar fiber tubes. It exhibits excellent impact resistance and energy absorption characteristics, and is not easily delaminated under impact loads, demonstrating high load-bearing capacity and strong damage tolerance, providing promising applications in the field of impact protection.

The invention belongs to the technical field of composite material weaving, and particularly relates to an electric heating material woven tubular structure, electric heating material woven cloth and an electric heating layer structure. The braided structure is composed of an outer-layer glass fiber tubular structure and an inner-layer carbon nano tube conductive wire, the carbon nano tube conductive wire is wrapped in the glass fiber tubular structure in a spiral winding mode, and a composite material braided bundle which is high in strength, insulated, light in weight and conductive is formed. The two-dimensional woven bundle is further made into woven cloth, the surface heating function is achieved through the good conductivity of the woven cloth, and the method is particularly suitable for heating assembly arrangement of structural parts such as complex curved surfaces or airfoils. The technology overcomes the defects of traditional heating materials in the aspects of shape adaptability and strength, and has wide application prospects.

An inflatable structure includes an inflatable bag and a telescopically extendable strut. The strut is disposed in the bag.

Disclosed herein is an aircraft with engines positioned so as to avoid damage to other components of the aircraft. The aircraft may include a blended wing body aircraft. The engines may be positioned aft of a pressure vessel of the aircraft. The engines may be positioned aft of and / or above a fuel store of the aircraft. Such engine positioning may reduce the likelihood of damage to a pressure vessel and / or fuel store in the event of engine failure.

A battery support body may include a bracket extending in a front-rear direction and a shock absorber, which may extend in the front-rear direction and may be coupled to the bracket in a direction crossing the front-rear direction. At least a portion of the shock absorber may be provided in the form of foam.

The invention belongs to the field of aircraft structure design, and particularly relates to a wing body butt joint structure participating in fuselage longitudinal load transfer. The structure comprises a plurality of wing body butt joint angle boxes which are arranged in parallel; the first wing body butt joint belt plate is used for lapping two wing body butt joint corners on the outer side; the second wing body butt joint belt plate is used for lapping two wing body butt joint corners on the inner side; the wing body butt joint angle box, the first wing body butt joint belt plate and the second wing body butt joint belt plate jointly form a frame type butt joint structure; the upper side of the frame type butt joint structure is connected with the central wing upper wall plate and the fuselage upper wall plate, and the lower side of the frame type butt joint structure is connected with the central wing lower wall plate and the fuselage lower wall plate. The front side of the frame-type butt joint structure is connected with the central wing spar, and the rear side is connected with the longitudinal side wall of the fuselage. The shearing force and the bending moment between the fuselage and the wings are mainly transmitted through the wing body butt joint structure connected with the central wing spar, and the wing is simple in structure, mature in manufacturing process, low in cost, easy to assemble and light in weight.

The invention discloses a low-loss high-efficiency aircraft control surface jet flow exciter in the technical field of jet flow flowing control, and particularly comprises a jet flow cavity and a jet flow seam, the jet flow cavity is arranged in a control surface in the spanwise direction of the control surface, and the jet flow seam is arranged on the upper surface of the control surface in the spanwise direction of the control surface; a transition runner is arranged between the jet flow seam and the jet flow cavity, one end of the transition runner is communicated with the jet flow seam, the other end of the transition runner is communicated with the jet flow cavity, and the transition runner partially extends into the jet flow cavity. By means of the mode that the transition flow channel extends into the jet flow cavity, flow separation at the joint position of the transition flow channel and the jet flow cavity is effectively avoided, so that it is guaranteed that compressed air can restrain flow separation on the control surface, and the lift coefficient of the whole aircraft is increased.

A structure for transferring a lateral load of an engine pylon to an aircraft wing includes a first component having a generally longitudinally oriented first flange extending outward from a first base portion that is attachable to or integrated with the wing, a second component having one or more raised portions extending outward from a second base portion that is attachable to or integrated with the engine pylon, and a bushing with a base plate and one or two arms. The bushing may be disposed in contact with a wall portion with part of the first flange disposed within the bushing, or in contact with a raised portion with part of the bushing disposed between the first flange and a second flange, such that the engine pylon is substantially restrained against lateral movement with respect to the wing.

The invention relates to a novel wingtip winglet of an aircraft. The installation angle of the winglet is a forward swept wing, and the winglet is a dihedral winglet. Compared with other winglets, the novel winglet has more excellent aerodynamic characteristics, the vortex phenomenon of the wingtip of a large wing of an aircraft can be reduced, the resistance of the aircraft is reduced, and the lift force of the aircraft is increased.

A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the central casing and a lower end of the front wall, and a complementary front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar.