1101results about "Air-flow influencers" patented technology

An aircraft wing is disclosed having a fixed wing with a tip, and a wing tip device rotatably mounted on a hinge at the tip of the fixed wing, such that the wing tip device is rotatable about the hinge, and an actuation system for rotating the wing tip device about the hinge. The actuation system includes a motor, at least one geared rotary actuator, a reduction gearbox, a clutch for selectively decoupling rotation of the motor from rotation of the geared rotary actuator, the geared rotary actuator is driveable by the motor and arranged to convert rotary motion into a different rotary motion and is arranged to rotate the wing tip device relative to the tip of the fixed wing. The clutch is coupled to the geared rotary actuator by a shaft and the shaft is fixed in rotation to a mass disposed radially outwardly from the shaft.

An aircraft may comprise ducted fans. The ducted fans may be an array of ducted fans. An array of ducted fans may be integrated in a wing of the aircraft. A ducted fan may be integrated in a horizontal tail of the aircraft. The wing may include a movable edge, such as a flap, to provide both exhaust area and flow turning control. The movable edge may be articulated by pivoting the movable edge. The movable edge may be extended and retracted.

In an aircraft wing structure where space and weight considerations are a principal concern, there may be significant challenges in providing a moveable slat and / or a spoiler, particularly in combination with one another. A control device for an aircraft includes upper and lower flaps pivotably mountable adjacent to a slot in a wing behind a leading edge, wherein the control device is operable in a lift configuration to move the upper and lower flaps towards each other to abut opposing surfaces of the slot, to permit airflow along the slot.

An aircraft has a boom, a propulsion assembly coupled to a first end of the boom, and a first wing coupled to a second end of the boom. The first wing can be coupled to the boom by a (first) articulated joint. The propulsion assembly can be coupled to the boom by a (second) articulated joint. The articulated joints can provide various adjustments between the wing(s) and the boom (e.g., stowed, deployed, anhedral, dihedral, sweep, angle of attack, collective pitch control, the cyclic pitch control, etc.) and between the propulsion system and the boom (e.g., to move between vertical flight and horizontal flight). A payload can be connected to the boom with one of the articulated joints whereby the articulated joint adjusts a position of the payload during flight to maintain desired flight characteristics and stabilize the payload.

An aircraft wing is provided having a fixed wing with a gulled wing tip rotatably mounted at the tip thereof, the gulled wing tip extending below a wing plane defined by the end of the fixed wing such that the centre of gravity of the gulled wing tip is located below the wing plane. Lowering the centre of gravity of the gulled wing tip has been found to reduce the onset of flutter. The gulled wing tip may be gulled about a hinge axis where it meets the fixed wing, or may be otherwise folded or curved to lower the centre of gravity of the gulled wing tip.

Vertical take-off and landing (VTOL) aircraft of the fixed-wing type, comprising a centre section defining a centreline of the aircraft, and a pair of wings, arranged on either side of the centre section, wherein the wings extend longitudinally from the centre section away from and mutually symmetrical with respect to a plane of symmetry extending through the centreline, wherein each wing comprises a main wing section extending longitudinally from the centre section, wherein the main wing section is configured for generating lift in an upward direction, a wingtip section extending longitudinally from the main wing section in a downwards sloping manner with respect to the main wing section, and a control surface provided in the wingtip section.

The remote sensing surveying and mapping unmanned aerial vehicle wind resistance device structurally comprises an unmanned aerial vehicle, a remote sensing surveying and mapping instrument and a wind resistance device, the remote sensing surveying and mapping instrument is arranged at the bottom of the unmanned aerial vehicle, and the wind resistance device is installed on the top end face of the unmanned aerial vehicle; the unmanned aerial vehicle comprises a wind-resistant frame, fixed insertion blocks, a flow guide groove and a flow guide structure, the two fixed insertion blocks are arranged at the bottom of the wind-resistant frame, and the fixed insertion blocks are connected to the top end face of the unmanned aerial vehicle in an inserted mode. The diversion trench is in an open state, and airflow can flow backwards through the diversion trench, so that the wind resistance of the unmanned aerial vehicle during flight is improved, and the terrain surveying and mapping stability of the remote sensing surveying and mapping instrument is improved.

A modular vertical take-off and landing aircraft for transporting persons and / or loads, comprising a flight module with multiple drive units arranged on a supporting framework structure, each drive unit having an electric motor and a propeller operatively connected to the electric motor, a transport module having a conveying pod and a connection device for connecting the conveying pod to the flight module. The connection device has an elongated shaft, one end of which is attached to the conveying pod, and a coupling device for connecting the flight module to another end of the elongate shaft of the transport module.

An aircraft with a folding wing tip arrangement and first and second wiring harnesses extending between a fixed wing and a wing tip device is disclosed. It is desirable to transfer power and / or data into a folding wing tip, which presents challenges such as repeated exposure to potentially harsh environmental conditions, with movement, and / or with changes in tensional loads. The wiring harnesses include a plurality of conductors and are arranged to transmit electrical power and / or data to the wing tip device. The sleeve includes two channels to receive the harnesses, the position of the channels being fixed, relative to one another, such that the harnesses are held apart.

An electrostatic thruster for producing thrust by charging gas and / or liquid particles using a high voltage potential, the electrostatic thruster comprises at least two thruster cells, wherein each thruster cell comprises: - at least one emitter, - at least one collector, wherein the at least one collector is spaced from the at least one emitter by a thruster cell gap, wherein the electrostatic thruster further comprises a power source electrically connected to the at least one emitter and the at least one collector of each thruster cell, wherein the power source is configured to apply a voltage between the at least one emitter and the at least one collector of each thruster cell, wherein the at least two thruster cells are positioned in parallel to form a thruster cell array, wherein the thruster cell array further comprises an intermediate electrode powered by a current source that generates a substantially constant current.

An assembly is provided for an aircraft. This assembly includes a first propulsor rotor, a powerplant and a propulsion system housing. The powerplant is configured to drive rotation of the first propulsor rotor about an axis. The propulsion system housing includes an inner structure and an outer structure with a bypass flowpath radially between the inner structure and the outer structure. The bypass flowpath is downstream of the first propulsor rotor and extends axially along the inner structure and the outer structure within the propulsion system housing. The inner structure extends axially along and circumferentially around the powerplant. The outer structure extends axially along and partially circumferentially about the first propulsor rotor to cover an outer periphery of a first circumferential sector of the first propulsor rotor. A remaining second circumferential sector of the first propulsor rotor is open to an environment outside of the propulsion system housing.

Systems, devices, and methods for an aircraft having a fuselage; a wing extending from both sides of the fuselage; a first pair of motors disposed at a first end of the wing; and a second pair of motors disposed at a second end of the wing; where each motor is angled to provide a component of thrust by a propeller attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.

An aircraft wing is disclosed having a fixed wing with a tip, and a wing tip device rotatably mounted on a hinge at the tip of the fixed wing, such that the wing tip device is rotatable about the hinge, and an actuation system for rotating the wing tip device about the hinge. The actuation system includes a motor, at least one geared rotary actuator, a reduction gearbox, a clutch for selectively decoupling rotation of the motor from rotation of the geared rotary actuator, the geared rotary actuator is driveable by the motor and arranged to convert rotary motion into a different rotary motion and is arranged to rotate the wing tip device relative to the tip of the fixed wing. The reduction gearbox is positioned between the clutch and the geared rotary actuator along a drive train between the motor and the geared rotary actuator.

The invention relates to a control method for improving the anti-interference performance of an aircraft based on jet flow, belongs to the technical field of anti-interference of fixed-wing aircrafts, and solves the technical problems that a passive flow control method in the prior art cannot adjust the control effect according to the current situation in actual use and is poor in control effect under non-design working conditions. According to the control method, the requirement for safe and stable operation of the aircraft in complex environments such as water surface take-off and landing and gust disturbance is considered, and the active flow control lift-augmentation and drag-reduction method for jet wing circular rector control is used; the lift coefficient of the aircraft can be improved to the maximum extent, and meanwhile, the wave resistance or wind resistance of the aircraft is improved in a stable maneuverability mode.

The invention relates to the technical field of aircraft control, in particular to an airfoil gust retarding feedforward control method based on a circular rector control technology, which comprises the following steps: modifying the shape of the rear edge of an NACA0012 airfoil, and arranging jet holes in the rear edge to form a circular rector control airfoil; performing a fluid simulation experiment on the circular rector control airfoil based on the gust speed, and constructing a model of the airfoil lift coefficient disturbed by the gust speed; performing a fluid simulation experiment on the circular rector control airfoil based on the jet flow momentum coefficient, and constructing a model of which the airfoil lift coefficient is controlled by the jet flow momentum coefficient; based on the model, obtaining a gust slowing-down feedforward control model of which the input quantity is the vertical gust speed and the output quantity is the jet flow momentum coefficient; controlling jet flow of a trailing edge by adopting the gust slowing-down feedforward control model to complete gust slowing-down control of the circular rector control airfoil; the method can improve the ability of the aircraft to resist the gust disturbance environment.

There is provided an acoustic black hole comprising: in a first axis, a variation from a first characteristic to a second characteristic, along a line; in a second axis different to the first axis, a variation from a first characteristic to a second characteristic, along the second axis.

Systems, devices, and methods for an aircraft having a fuselage; a wing extending from both sides of the fuselage; a first pair of motors disposed at a first end of the wing; and a second pair of motors disposed at a second end of the wing; where each motor is angled to provide a component of thrust by a propeller attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.

An unmanned aerial vehicle according to certain embodiments generally includes a chassis, a power supply mounted to the chassis, a control system operable to receive power from the power supply, at least one rotor operable to generate lift under control of the control system, and a winch mounted to the chassis. The winch includes a reel and a motor. The reel has a line wound thereon, the line having a free end. The reel includes a circumferential channel in which a wound portion of the line is wound onto the reel. The circumferential channel includes an inner portion, an outer portion, and a passage connecting the inner portion and the outer portion. The motor is operable to rotate the reel under control of the control system to thereby cause the line to wind onto and off of the reel, thereby causing the free end of the line to raise and lower.

The turbulence friction resistance reduction device based on array type corona micro-blowing comprises a corona discharge cavity plate (1) and a discharge electrode (2). A plurality of cylindrical inclined micro holes are formed in the front face of the corona discharge cavity plate (1) and serve as corona discharge anodes, the cylindrical inclined micro holes are distributed in the front face of the corona discharge cavity plate (1) in an array mode, and the inclined directions of the cylindrical inclined micro holes are changed in a staggered mode. The high-voltage direct-current power supply (4) generates direct-current high voltage and applies the direct-current high voltage to the discharge electrode (2), plasma (6) is generated between the discharge electrode (2) and the corona discharge cavity plate (1), two oblique jet flows of each discharge group are coupled to form spirally-rising jet flows, a normal blowing effect is generated in a flow field, and turbulent friction resistance reduction is achieved. The invention further provides a turbulence friction resistance reduction device and method based on array type corona discharge. The sensor is arranged in a flow field to collect flow field data, the flow field state is sensed in real time, the corona discharge mode is controlled, the optimal resistance reduction effect is kept in the rapidly-changed flow field state, and the resistance reduction adaptability is further improved.

The utility model belongs to the technical field of flexible structure design, and particularly relates to a perimeter-variable fuselage frame structure which comprises sliding groove sections, sliding key sections, corrugated beams, height-variable supporting columns and length-variable supporting rods. The corrugated beams are arranged on the outer sides of the sliding key sections and the sliding groove sections and are provided with wave crest and wave trough structures; the sliding key sections and the sliding groove sections are located on the inner sides of the corrugated beams, arranged at intervals and distributed in a staggered mode. The corrugated beams, the sliding key sections and the sliding groove sections are all of arc-shaped structures, and wave crests and wave troughs of the corrugated beams are arranged in the radial direction of the arc-shaped structures; the sliding key section and the sliding groove section are mutually nested to form an arc-shaped supporting sliding way, and the wave trough of the corrugated beam slides on the arc-shaped supporting sliding way; the height-variable supporting column and the length-variable supporting rod are hinged to the two ends of the sliding key section respectively. The shape of the fuselage can be greatly changed, the large-size fuselage can provide a large space to carry more fuel, and the small-size fuselage is beneficial for reducing flight resistance and improving the fuel utilization rate.

The invention belongs to the technical field of flexible structure design, and particularly relates to a variable-arc-length arched beam structure which comprises a sliding groove section, a sliding key section, a corrugated beam, a variable-height supporting column and a variable-length supporting rod. The corrugated beams are arranged on the outer sides of the sliding key sections and the sliding groove sections and are provided with wave crest and wave trough structures; the sliding key sections and the sliding groove sections are located on the inner sides of the corrugated beams, arranged at intervals and distributed in a staggered mode. The corrugated beams, the sliding key sections and the sliding groove sections are all of arc-shaped structures, and wave crests and wave troughs of the corrugated beams are arranged in the radial direction of the arc-shaped structures; when the shape and the arc length of the arched beam are changed, the variable-height supporting columns and the variable-length supporting rods can automatically generate height changes, then the sliding key sections and the sliding groove sections are driven to relatively slide, and meanwhile the corrugated beams evenly distribute the arc length changes to the positions between the adjacent wave crests, so that external loads are evenly distributed to the arched beam. Therefore, the size of the fuselage is correspondingly reduced along with fuel consumption.

A wing assembly for an aircraft is disclosed having an actuation assembly configured to move a wing tip device between a flight configuration and a ground configuration. The actuation assembly includes at least two linear actuation devices mounted within the wing assembly. A wing and a wing tip device for the wing assembly, and an aircraft comprising the wing assembly, wing or wing tip, are also disclosed.

A wing assembly for an aircraft, the wing assembly having a fixed wing and a wing tip device moveably mounted at the end of the fixed wing. A wiring harness extends between the fixed wing and the wing tip device, a length of the wiring harness being encased in a length of protective sleeve. The protective sleeve is pre-shaped, for example pre-molded, to follow a path along a helical curve.

An aircraft wing tip that is movable by an actuator between a flight configuration, and a ground configuration which has a shorter wingspan for use in ground-based operations. Lugs that connect to arms of the actuator are integrally formed as part of the primary structure of either the fixed wing or outboard wing section, such as a folding tip section.

A multi-rotor unmanned aerial vehicle (100) comprises: a central body (10); two pairs of first arms (20) rotatably connected to the central body (10) and located on opposite sides of the central body (10); a plurality of rotor devices (30) mounted on the first arms (20), the rotation axis (21) of each first arm (20) being tilted relative to the pitch axis (101), the roll axis (102) and the yaw axis (103) of the multi-rotor unmanned aerial vehicle, and each first arm (20) The rotation axis (21) is arranged obliquely relative to the first arms (20); each pair of first arms (20) can be in an expanded state or a folded state; in the expanded state, each pair of first arms (20) is radially expanded relative to the central body (10); in the folded state, each pair of first arms (20) is in an up-and-down folded state, and the rotation axis (31) of the rotor device (30) of each pair of first arms (20) is substantially coplanar to prevent interference with components such as the central body (10) or to prevent occupying a large space.

The invention relates to a rapid cross-medium aircraft capable of realizing sustainable operation by utilizing solar energy to electrolyze seawater, which comprises a tail shell, a gas tank shell, an arm folding layer shell, a midship shell, a resistance reduction shell and a head shell which are sequentially arranged from top to bottom, and a mechanical control system is clamped in the arm folding layer shell; the sustainable energy supply system is used for sustainably generating, storing and providing hydrogen and oxygen; the ballast part of the ballast propulsion system is used for adjusting the buoyancy and the gravity center position of the aircraft, and the propulsion part is used for the aircraft to achieve rapid water outlet through hydrogen-oxygen mixed ignition; the underwater drag reduction system is used for providing drag reduction bubbles during underwater cruise of the aircraft; the pipeline part of the main pipeline system is used for conveying seawater, hydrogen and oxygen. According to the device, great explosive force can be obtained in a short time, the cross-medium aircraft is helped to quickly water out, stable and quick water out of the cross-medium aircraft is achieved, and hydrogen and oxygen need to be continuously supplied in the operation process.

The present invention provides an electric power inspection UAV, which includes: a body, an equipment compartment body, and an inspection camera; wherein the equipment compartment body is arranged on the body, and the inspection camera is arranged in the equipment compartment body in a movable manner; a pair of movable wing panels are provided at the compartment opening of the equipment compartment body; the movable wing panels are connected to the equipment compartment body along the compartment opening wall of the equipment compartment body in a sliding manner; both sides of the equipment compartment body are rotatably connected with a wing panel fixing mechanism. The present invention supports the sliding movable wing panels through the wing panel fixing mechanism, and drives the movable wing panels to rotate to an inclined upward position to form a V-shaped structure, which helps to achieve a wind-breaking and diverting effect during flight, thereby achieving the purpose of reducing wind resistance, reducing energy consumption, and improving inspection endurance.

The invention provides a fixed-wing aircraft, which takes a Karsi vertical coordinate system as a reference, takes a first plane formed by an X axis defined by the sailing direction of the fixed-wing aircraft and a Z axis defined by the gravity direction of the fixed-wing aircraft as a symmetry plane, and comprises an aircraft head, a fixed-wing aircraft body and a fixed-wing aircraft body, a fuselage; the main wing comprises a connecting part positioned at the rear part of the main wing, and the connecting part is used for connecting an air propulsion device; the air propulsion devices are connected with the main wings, each air propulsion device comprises an air guiding pipe, an air thruster and an air spraying pipe which are connected front and back in the X-axis direction, each air guiding pipe comprises an air inlet connected with the connecting part of the corresponding main wing, and the air inlets are used for guiding air into the air propulsion devices. According to the fixed-wing aircraft provided by the invention, the total lift force of the wings can be improved during cruising, and meanwhile, the maneuvering capability for supporting the fixed-wing aircraft to realize vertical / or short-distance take-off and landing and hovering is also provided.

A wing assembly has a flexible cover which is movable between an extended position and a retracted position. In the extended position the flexible cover covers the leading edge of the wing assembly, thereby protecting the front of the wing assembly from impact by dirt or debris and preserving the smoothness of its surface. In the retracted position the flexible cover does not cover the leading edge of the wing assembly.

The invention relates to a wing lift augmentation and steerage enhancement device and method based on discrete jet flow, and belongs to the technical field of active flow control of aircrafts. The wing lift augmentation and steerage enhancement device comprises an engine gas source guide pipeline and a jet flow exciter; an outlet of the engine gas source guide pipeline is communicated with an inlet of the jet exciter; a jet flow outlet and a blocking block are arranged at the outlet position of the jet exciter at intervals. According to the active flow control method based on discrete jet flow arrangement, different control effects are achieved, adjustable parameters include the jet flow intensity, the jet flow blocking ratio and the like, and the lift coefficient and the control surface efficiency can be improved by increasing the jet flow momentum coefficient; different optimal jet flow blocking ratios exist under different conditions, and the blocking ratio needs to be adjusted to an optimal value to optimize aerodynamic performance. Meanwhile, compared with steady jet control, the method is higher in efficiency and less in air source demand.