493results about "Wings" patented technology

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 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.

A leading-edge device for an aerodynamic component is disclosed having a first skin element having an inner surface and an aerodynamic outer surface, and further includes a second skin element having an inner surface and an aerodynamic outer surface. The leading-edge device includes a first coupling element protruding from the inner surface of the first skin element and a second coupling element protruding from the inner surface of the second skin element. The first and second coupling elements are coupled to each other in a coupling region. The first skin element and the first coupling element are formed as a single-piece structure.

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 invention relates to a variable-gauge knitted flexible inflatable wing and a preparation method thereof, and relates to the technical field of aircrafts. The variable-gauge knitted flexible inflatable wing comprises a variable-gauge knitted base body, an airtight film covering layer, a shaping film covering layer and an air nozzle, the upper surface layer and the lower surface layer of the variable-gauge knitted base body are connected through spacing wires, and the spacing wires are knitted through an empty needle to form a telescopic structure; the airtight film covering layer covers the outer surface of the variable-gauge knitted base body to form a closed air cavity; the shaping film coating layer covers the outer surface of the airtight film coating layer and is at least used for restraining deformation of the airtight film coating layer, and the thickness of the shaping film coating layer is larger than that of the airtight film coating layer; the air nozzle is communicated with the air cavity. Through the telescopic spacing wires, the wings are tightly folded after being deflated, and the transportation and storage convenience is improved; during inflation, the spacing wires accurately control the distance between the upper layer and the lower layer, and high-precision control over the aerodynamic configuration is achieved in combination with constraint of the sizing film coating layer.

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.

The present disclosure relates to the technical field of aerospace, and provides a machining method for high-aspect-ratio model part of ultra-high strength steel for wind tunnel test. The machining method includes the following steps: a) selecting a material; b) performing preliminary treatment, such as forging and solid solution heat treatment, on the material; c) performing rough milling to obtain a wing main body profile, process reference blocks, and grooves and holes with large sizes on a molded surface; d) performing finish milling on all machining features of a wing main body; e) removing all process reference blocks except the first process reference block; f) performing aging treatment when the wing main body is lifted; h) removing a process reference block at a wing main body root; and h) performing shaping treatment on the wing main body.

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.

In some embodiments, an electric aircraft may include a plurality of flight components including a plurality of control surfaces; a plurality of lift propulsors; at least a thrust propulsor; and a plurality of electric motors configured to power the plurality of propulsors; a flight controller, communicatively connected to a pilot input and flight components. In some embodiments, a flight controller may be configured to receive control datum from a pilot input; and generate an output datum as a function of the control datum.

A tape structure for use in automated fiber placement method to manufacture a composite structure includes a first layer and a second layer connected to the first layer with the first layer being configured as a support layer and the second layer being configured as a pre-impregnated layer, wherein the first layer is removable from the second layer during or after placement of the second layer on the composite structure to be manufactured, an automated fiber placement device an automated fiber placement method and a composite structure manufactured in the method.

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 relates to the technical field of aviation equipment, and discloses a wing-shaped structure suitable for anti-icing and deicing, which comprises a shell and an electric heating piece, an electric heating piece is arranged in a shell, a first heating layer is formed on the upper wing face and the lower wing face of the inner wall of the shell, a second heating layer is formed on the front edge of the inner wall of the shell, the first heating layer and the second heating layer are electrically connected, and the first heating layer and the second heating layer are connected with an external power source through an electrode layer so that power can be supplied to the electric heating piece, and temperature distribution of different parts can be controlled. After the electrode layer conducts electricity, a first temperature area is formed on the first heating layer, a second temperature area is formed on the second heating layer, and the temperature of the first temperature area is lower than that of the second temperature area, so that it is guaranteed that the front edge of the airfoil structure is kept at the high temperature, and the deicing and anti-icing requirements are met. According to the airfoil structure suitable for anti-icing and deicing, differentiated heating can be conducted according to icing characteristics of different parts of the airfoil structure, it is guaranteed that the anti-icing and deicing requirements are met, meanwhile, energy consumption is reduced, and the energy utilization rate is increased.

An electric vertical take-off and landing (eVTOL) aircraft can enhance energy efficiency, safety, and operational range. A deployable wing structure can provide aerodynamic lift during horizontal flight, reducing reliance on energy-intensive propellers. Integrated flexible solar panels capture solar energy, contributing additional power and optimizing energy management. The wing system also includes an emergency descent mode, doubling as a glide-assist device for controlled landings during critical failures. The system offers modular configurations for various missions, ensuring adaptability and improved flight performance. The eVTOL can be implemented with systems and methods for mitigating motion sickness. The systems integrate tactile feedback systems into wearable devices and environmental components. Sensors detect motion and environmental changes, and a computing device can generate corresponding tactile feedback signals. Tactile actuators embedded in the devices or components provide non-visual motion cues, such as pressure, vibration, and haptic feedback, to resolve sensory mismatches between the vestibular and proprioceptive systems.

Composite material protection from UV degradation is disclosed by providing a co-cured composite material substrate co-cured with a UV / visible light-resistant fiberglass layer to form co-cured composite materials for exclusively imparting UV / visible light-resistant properties to co-cured composite material substrates for use in UV / visible light-resistant vehicle fuel tank assemblies.

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.

The invention discloses an aircraft low-noise bionic flap based on side edge local turbulent flow and a design method, and belongs to the field of aircraft design. The high lift device is composed of a slat and a main wing, the high lift device comprises an inner flap, an outer flap, a noise reduction system and a driving system, the inner flap and the outer flap are installed on the high lift device, the noise reduction system is arranged at the end, close to the outer flap, of the inner flap, and the noise reduction system is driven by the driving system located in the inner flap; the noise reduction system comprises bionic nodules and asymmetric wingtip end plates, the bionic nodules are arranged on the end face of the inner flap, and the asymmetric wingtip end plates are arranged on the two sides of the inner flap. Aiming at the problems of influence on aerodynamic performance, generation of extra noise and complex structure in a flap side edge noise reduction method, the invention provides an aircraft low-noise bionic flap based on side edge local turbulent flow, and the effect of reducing intermediate-frequency broadband noise of the flap is achieved while the aerodynamic performance of a high lift device is ensured.

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 a method of inspecting an aircraft fuel tank fastener assembly. The assembly includes: a fuel tank having a fuel chamber; a fastener including a head and a tail at opposite ends of the fastener; and a cap inside the fuel chamber, where the cap surrounds the tail of the fastener. The method comprises the following steps: heating the tail part of the fastener; obtaining a thermal image of the tail of the fastener; and inspecting a thermal image of the tail of the fastener.

The present invention discloses a wing noise control device and control method based on jet-coupled serrations. The device is based on a passive wing noise control structure formed by a serration group located at the trailing edge of the wing, and an active wing noise control structure is arranged in the wing cavity. The active wing noise control structure is an active air path control structure, in which an air pipe is arranged in the wing cavity, one end of the air pipe is connected to the hollow serrations in the serration group, and the other end of the air pipe is connected to an external air source. The external air source introduces airflow into the hollow serrations in the serration group through the air pipe, and uses the tip holes and root holes of the serrations as jet holes, forming a one-to-one correspondence between the tip jet and the root jet, thereby achieving active wing noise control. Compared with a single active or passive control method, the present invention can achieve more significant noise reduction effects across the entire frequency range and under all operating conditions, further improving the acoustic performance of the wing, while also having lower energy consumption, high reliability, and simple operation.

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.