799results about "Air-flow influencers" patented technology

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.

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.

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.

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.

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 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.

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.

A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotor assemblies, tandem wings, and forward thrust propellers. The vertical lift rotor assemblies, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotor assemblies and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotor assemblies provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.

According to this invention, an aerial vehicle can be provided that reduces the effect of wind in a given direction striking its frame during flight of the aerial vehicle, thereby improving fuel consumption and stability. The aerial vehicle of this invention is equipped with a flight part including a frame to which a plurality of rotor blades including at least a propeller and a motor are connected, wherein the frame includes a right frame and a left frame extending side by side in the front-rear direction of the aerial vehicle, and at least one of the right frame and the left frame has a substantially wing-shaped portion with a leading edge located outside the aerial vehicle and a trailing edge located inside the aerial vehicle relative to a vertical center line in the frame. The substantially wing-shaped shape is a symmetrical wing shape.

An aircraft includes an aircraft heat source; a propulsion system including an electric propulsion engine, the electric propulsion engine including an electric motor and a fan rotatable by the electric motor, the electric propulsion engine further defining a fan air flowpath; a thermal management system including a heat source exchanger in thermal communication with the aircraft heat source, a heat sink exchanger in thermal communication with the fan air flowpath of the electric propulsion engine, and a thermal distribution bus extending from the heat source exchanger to the heat sink exchanger; and a control system operably connected to the thermal management system for selectively thermally coupling the heat sink exchanger with the heat source exchanger.

The invention belongs to the technical field of morphing aircraft structure design, and particularly relates to a deformable fuselage structure for a hypersonic speed environment, which comprises a deformable fuselage frame and a deformable fuselage skin, the deformable machine body frame comprises a sliding groove section, a sliding key section, a corrugated beam, a height-variable supporting column and a length-variable 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 deformable fuselage skin comprises a deformable supporting framework, sliding scales and an S-shaped heat insulation plate. The shape and the section size of the fuselage can be greatly changed by controlling the shape and the section size of the fuselage, so that the large-size fuselage can provide enough space to carry more fuel, the small-size fuselage section reduces flight resistance and improves the fuel utilization rate, the thermal insulation skin prevents pneumatic heat from being transmitted into the fuselage, and the fuselage is easy to implement based on existing materials and mature processes.

The invention relates to the technical field of vehicle active control, in particular to a vehicle stabilizing system based on active airflow compensation and a control method, and the system comprises a distributed airflow generation array unit, a multi-source sensing system unit, an intelligent control unit and an energy management unit. Directional compensation airflow is generated through the distributed airflow generation array unit, the multi-source sensing system unit monitors a flow field and motion parameters in real time, the intelligent control unit fuses a hybrid control strategy and reinforcement learning to achieve dynamic compensation and algorithm iteration, and the energy management unit recycles braking energy and optimizes distribution. The stability and response speed of the vehicle in a complex environment are remarkably improved, meanwhile, the airflow utilization rate is increased through the gradient porous material, energy consumption is reduced through reverse airflow power generation, and efficient and energy-saving active stable control is achieved.

The invention discloses a blade tip blowing method for lift augmentation of a rotor unmanned aerial vehicle, belongs to the technical field of lift augmentation of rotor unmanned aerial vehicles, and aims to solve the problem of insufficient lift force caused by vortex induced resistance generated by a blade tip vortex of a traditional rotor unmanned aerial vehicle. Transverse distributed jet flow is arranged on the 25% c-75% c section of the blade end face airfoil profile (the jet flow is blown out at the double blade tip speed, the two blades symmetrically apply the jet flow, and the jet flow is conveyed through a titanium alloy guide pipe). During design, jet parameters are simulated and optimized through pneumatic modeling (multiple reference coordinate systems and SST k-omega turbulence models), working conditions are dynamically adapted, and vorticity analysis and lift comparison verification are combined. According to the scheme, blade tip vortexes can be damaged, resistance is reduced, lift force is improved, meanwhile, flight stability is guaranteed, and multiple flight working conditions are adapted.

A wing structure is disclosed having a first span portion including a depth that reduces in a spanwise outward direction, and a second span portion outboard of the first span portion and having a substantially uniform spanwise depth D3. The second span portion may be non-tapered, and may include parallel fore and aft spar portions. In some embodiments the non-tapered portion supports a movable wing tip device. A wing assembly and an aircraft are also disclosed.

The invention discloses an intelligent flow control method and system for an air-breathing high-speed aircraft, and relates to the field of flow control of aerodynamic performance of aircrafts, and the intelligent flow control method comprises the following steps: S1, arranging a suction module on a compression surface of an air inlet channel of the aircraft and / or a position, which is easy to cause flow separation, in the aircraft; s2, an air blowing module is arranged in the area, needing drag reduction, of the outer surface of the aircraft; and S3, the air source obtained through control of the driving module from the suction module is conveyed to the air blowing module through a regulating valve through the control system. According to the intelligent flow control method for the air-breathing type high-speed aircraft, air-source-free carrying of aircraft flow control is achieved, suction and blowing flow control can be achieved at the same time, namely, the aerodynamic performance of an air inlet channel is improved through suction, the aerodynamic performance of the outer surface of the aircraft is improved through blowing, and resistance is reduced.

A propulsion system for an aircraft can include an electric power source and an propulsion assembly having a propulsor. An electric power bus can electrically connect the electric power source to the propulsion assembly. The electric power source can be configured to provide electrical power to the electric power bus. An inverter converter controller can be positioned along the electric power bus and can be electrically connected to the electric power source at a location downstream of the electric power source and upstream of the electric propulsion assembly.

The present invention relates to the technical field of aircraft wall friction resistance control, and discloses a laminar / turbulent friction resistance integrated control device and method based on a micro-blowing surface. Multiple components of the control device work together to intelligently adjust the opening and closing of the micro-blowing unit under laminar or turbulent conditions, and dynamically adjust the working mode of the micro-blowing unit by real-time monitoring the boundary layer state of the aircraft surface. Under laminar conditions, the micro-blowing unit does not generate micro-blowing, and reduces drag through the porous surface; under turbulent conditions, the micro-blowing unit generates micro-blowing, and isolates the turbulent structure from the wall through micro-airflow, thereby reducing turbulent friction. Through this intelligent adjustment, the system can optimize the drag performance according to the actual flight environment, thereby improving flight efficiency and saving energy.

A system is provided for an aircraft. This aircraft system includes an aircraft and an air system. The airframe includes a body and a vane connected to the body. The vane projects spanwise away from the body to a vane tip. The vane extends longitudinally between a leading edge and a trailing edge. The vane extends laterally between a first vane side and a second vane side. The air system includes a circuit inlet, a circuit outlet and an air circuit. The circuit inlet is arranged with the body and laterally offset from the vane. The circuit outlet is arranged with the vane. The air circuit extends within the airframe from the circuit inlet to the circuit outlet.

An example carriage is configured for mounting to an unmanned aerial vehicle. The carriage generally includes a housing assembly configured for mounting to the unmanned aerial vehicle, a movable grip mounted to the housing assembly for movement between a capturing position and a releasing position, a latch device, and a driver. The latch device has a latching state and an unlatching state, is configured to retain the movable grip in the capturing position when the latch device is in the latching state, and is configured to permit movement of the movable grip from the capturing position to the releasing position when in the unlatching state. The driver is operable to transition the latch device from the latching state to the unlatching state.