631results about "Air-flow influencers" patented technology

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 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.

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, 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.

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 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.

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.

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.

The invention discloses an electric vertical take-off and landing manned aircraft which comprises an aluminum alloy rack, a second carbon fiber tube and supporting legs, one side of the aluminum alloy rack is connected with a right guardrail, the other side of the aluminum alloy rack is rotationally connected with a left guardrail through a winding shaft seat, and a vibration reduction assembly comprises a vibration reduction seat arranged on the first carbon fiber tube in a sleeving mode. The upper vibration reduction seat and the lower vibration reduction seat are fastened through bolts at the penetrating positions of the first carbon fiber pipes and the aluminum alloy rack, the rubber vibration reduction pads absorb high-frequency vibration energy through elastic deformation of the rubber vibration reduction pads, direct transmission of vibration to the rack is effectively blocked, the second carbon fiber pipes can be rotationally folded through the hinge seats, the transverse size of the whole machine is greatly reduced after folding, and the whole machine is more compact in structure. The occupied area is remarkably reduced, storage in a narrow space is facilitated, pushing can be achieved only by pressing down the tail end during transition on the flat ground, extra tools or complex operation procedures are not needed, the gravity center of the machine body is naturally transferred to the supporting wheels along with posture adjustment in the pushing process, and transition flexibility and efficiency are improved.

An airframe for a projectile having a cylinder having a bottom spring and a piston within the cylinder is provided. The cylinder has a locking assembly having a housing. A leaf spring is in the housing and coupled thereto. The housing has a limiter where the leaf spring operatively couples with the limiter and the limiter biases the leaf spring. The piston is moveable relative to the cylinder between a retracted configuration and expanded configurations. The piston has a housing where the piston moves between the retracted configuration and the expanded configurations when the piston housing receives a fluid. The piston has a groove that receives the leaf spring. The groove can align with the leaf spring in one expanded configuration where the piston groove receives the leaf spring thereby locking the piston with cylinder. In another expanded configuration, the leaf spring is outside the piston groove.

An apparatus and system are provided to provide transpiration cooling for an airframe. An airframe includes a body that contains circuitry, a phase change material (PCM) that changes phase to a gas when cooling the circuitry, a fluid reservoir that retains the PCM in liquid and gaseous form, a vapor reservoir that retains the gas, a thermal sensor that detects a temperature of an external surface of the body, and a controller that control ejection of the gas from the vapor reservoir based on the temperature to control a thickness of a boundary air layer at the external surface. The controller also controls flow of the gas from the fluid reservoir to the vapor reservoir via a valve based on pressure in the vapor reservoir detected by a pressure sensor.

The invention provides a combined jet course control surface of an aircraft, and belongs to the technical field of active flow control. The control surface comprises a jet exciter and a circular rector exciter which are mounted on a wing; the jet exciter is located in the middle section area of the upper surface of the wing and provided with a first jet outlet located in the upper surface, and the included angle between the outlet direction of the first jet outlet and the corresponding incoming flow direction of the wing is larger than 90 degrees. The circular rector exciter is located in the trailing edge area of the upper surface of the wing and provided with a second jet flow outlet located in the upper surface, and the included angle between the outlet direction of the second jet flow outlet and the corresponding incoming flow direction of the wing is smaller than 90 degrees. The jet flow exciter and the circular rector exciter are combined to achieve the control effect of stabilizing lift force and increasing resistance, longitudinal and transverse torque coupling is reduced, decoupling design of a control surface is achieved, the course control effect of a combined mechanical control surface is formed, the control effect is improved, meanwhile, coupling of the torque control characteristic and the attack angle is reduced, and the control characteristic is improved.

Leading edge slotted blade row. The invention relates to a blade row (120) comprising at least one blade (120) having at least one leading edge slot (200) delimited by two lateral slot surfaces (210). A radius of curvature (RBA1) at the leading edge (BA) of a first profile (P1) located between said two lateral slot surfaces (210) is greater than a radius of curvature (RBA2) at the leading edge (BA) of a second profile (P2) adjacent to the at least one slot (200). Figure for the abstract: Fig. 5A.

This invention provides a combined jet gas supply system and method for aircraft, relating to the field of jet control technology. The invention includes a first gas source from the leading edge stagnation point of the aircraft, used to supply gas to the nozzle; a second gas source from the aircraft's auxiliary power system, used to supply gas to the nozzle; and a gas source regulation system for regulating the gas supply from the first and second gas sources to the nozzle, thereby regulating the temperature and flow rate of the jet gas ejected from the nozzle. Compared with existing technologies, this invention has the advantage of improving the jet flow rate supply capability and meeting the jet gas flow rate requirements in complex multi-mission flight environments.

The pine wood nematode disease unmanned aerial vehicle monitoring and positioning device comprises an unmanned aerial vehicle body, a mounting block is mounted at the bottom of the unmanned aerial vehicle body, and an auxiliary flight stabilizing structure for improving flight stability by means of airflow is arranged in the mounting block; the bottom of the mounting block is provided with a plugging structure for cooperating with the auxiliary flight stabilization structure, and the bottom of the mounting block is connected with a box body in the middle of the plugging structure. According to the pine wood nematode disease unmanned aerial vehicle monitoring and positioning device and method, cooperative work of the flight stabilizing structure and the blocking and triggering structure is assisted, an airflow channel is optimized, the flight stability of the unmanned aerial vehicle under the conditions of complex terrains and severe weather is enhanced, energy consumption is reduced, and the endurance time is prolonged. In addition, the device is provided with a wireless communication module and a network adapter, and collected and processed data can be transmitted to a ground control station or a cloud server in real time.

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 discloses a monomer structure and a resistance reduction structure. The monomer structure comprises a monomer structure base body and a groove structure on the monomer structure base body. In the extending direction of the groove structure, the depth of the groove structure is gradually reduced from the center to the two sides, the flow speed of the center area is high, the deep groove can reduce the direct contact area of fluid and the surface of the base body, and friction resistance is reduced; the flow velocity on the two sides is low, the shallow grooves can avoid formation of retention eddy current, local energy loss is reduced, and resistance reduction uniformity in the flowing direction is achieved; the depth of the grooves is gradually reduced from the central groove to the grooves on the two sides in parallel to the extending direction of the groove structure, the central groove plays a main role in diversion, and the deep design can strengthen the'groove effect '; the grooves on the two sides assist in shunting, fluid channeling between the adjacent grooves can be avoided through the shallow design, and the overall flowing stability is improved. The trench structure is optionally a continuous structure or a discontinuous structure.

Consisting of a flap-type aerodynamic surface on the wing(s) (2) above the fuselage (1) of an aircraft with control surfaces (5) of the wing (2), the length of the device in the wing span direction being greater than or equal to the mid-chord of the flap, and comprising a thrust propeller engine (4), converting it into a propulsive flapper (3).