370results about "Air-flow influencers" patented technology

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.

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.

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 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 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 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.

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 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.

A thermal management system (TMS) 100 for an aircraft comprising an air inlet 310 which receives ambient air from an external environment, an air outlet (120, figure 1) providing fluid communication b

The invention discloses a control surface structure with a tangential air blowing seam in the technical field of control surface structures, and particularly comprises a control surface supporting beam, a control surface front edge and a control surface rear edge are arranged on the control surface supporting beam, an air blowing cavity is formed in the control surface front edge, the air blowing seam is formed in the joint of the control surface front edge and the control surface rear edge, and the air blowing seam communicates with the air blowing cavity; the lower surface of the air blowing seam is flush with the control surface rear edge, and the air blowing direction of the air blowing seam faces the tangential direction of the control surface rear edge. The air blowing direction of the air blowing gap faces the tangential direction of the control surface rear edge, so that flow separation inhibition of air on the upper surface of the control surface rear edge is better completed, the lift coefficient of the control surface structure is effectively improved, and improvement of the overall lift coefficient of an aircraft is affected.

The invention relates to a wing assembly (10) in the form of a propeller of a fixed-wing aircraft or a gyroplane, or in the form of a rotor blade of a main and / or auxiliary rotor of an aircraft with wings, a helicopter, or a gyroplane, or in the form of a rotor blade of a wind turbine rotor. The wing assembly (10) comprises a main wing (12) and a leading edge slat (14) attached to it in front of the main wing (12) opposite to a flow direction (22), such that a gap (16) with a flow inlet (18) and a defined, fixed flow outlet (20) is formed between the leading edge slat (14) and the main wing (12).Viewed in a vertical cross-section along the flow direction (22), the length (D) of a section (32) of the leading edge slat (14) extending forward against the flow direction (22) beyond a length (A) of the main wing (12) is at least 20% of the total length (C) of the wing assembly (10) in the flow direction (22). It is proposed that the flow inlet (18) be larger than the flow outlet (20) so that an airflow (24) in the gap (16) creates a Bernoulli effect.

A wing assembly 10 for an aircraft, comprising a fixed wing 18 and a wing tip device 12 rotatable about a joint assembly 16. The wing assembly is configurable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. The wing assembly 10 comprises joint-bordering structure located adjacent the joint assembly 16, the joint-bordering structure comprising a rib 34, an upper cover 26 and a lower cover. The joint assembly comprises a moveable panel 32. The panel 32 comprises a first hard stop element 38a, and the joint-bordering structure comprises a second hard stop element 40a. The first hard stop element 38a is integrally formed in the panel 32, and the second hard stop element 40a is integrally formed in one of the rib 34, the upper cover 26 or the lower cover of the joint-bordering structure. The hard stop elements 38a, 40a may be configured to self-align.

This mold for molding a sheet member comprises a molding surface with which a material of the sheet member comes into contact. A plurality of recessed structural bodies extending in a first direction are formed on the molding surface so as to be aligned along a second direction intersecting the first direction. At least one of a corner section of a first recessed structural body from among the plurality of recessed structural bodies and a boundary section of the first structural body and a second recessed structural body from among the plurality of recessed structural bodies that is adjacent thereto in the second direction includes a curved surface. If the curvature radius of the curved surface is denoted as R, the pitch of the plurality of recessed structural bodies is denoted as P, and the depth of the plurality of recessed structural bodies from the molding surface is denoted as H, the mold satisfies a first condition of "1 µm < R < 7 µm", and satisfies at least one of a second condition of "5 µm < P < 200 µm" and a third condition of "2.5µm < H < 100 µm".

A panel for an active laminar flow control arrangement may comprise a longitudinal wall (434) and one or more division walls (428) extending from the longitudinal wall (434) and extending between the first end (491) and the second end (492). The panel may be coupled to a nacelle outer skin (312) via a plurality of adhesive fasteners (326, 322) preinstalled onto an inner surface (314) of the outer skin (312) and onto stiffeners (382) and / or stringers (384) associated with the outer skin (312).

The invention belongs to the field of rotor control, and particularly relates to a cooperative control device and method for a rotor blade tip vortex and a dynamic stall vortex. Wherein the cooperative control device comprises a self-sustaining synthetic jet exciter and a pressurizing synthetic jet exciter; the pressurizing channel is arranged in the rotor wing and is communicated with the self-sustaining jet flow channel and the pressurizing jet flow inlet; a control valve I is arranged in the pressurizing channel; a control valve II is arranged on the self-sustaining jet flow inlet, and a one-way valve is arranged in the pressurizing jet flow inlet. The self-sustaining synthetic jet exciter and the pressurizing synthetic jet exciter are integrated, the pressurizing channel and the valve system which are internally communicated are utilized, cooperative and adjustable control over the rotor blade tip vortex and the dynamic stall vortex is achieved, the aerodynamic performance can be effectively improved without an external air source, and noise and vibration are restrained.

The invention belongs to the field of aircraft design, and particularly relates to a long-endurance aircraft layout design structure which is characterized in that a fuselage is divided into three sections which are arranged side by side, and wings are divided into three sections which are connected end to end; the fuselages are connected with the adjacent wings through rotating shafts, and the adjacent fuselages are connected through rotating shafts; the adjacent wings can be driven to be close to or away from each other by controlling the rotating shafts to rotate; the fuselage and the wings can form a hangar storage form, a take-off and landing operation form and an air flight form. Firstly, the hangar storage form size of the long-endurance airplane is compact, the spanwise size is favorably controlled, and the airplane can be conveniently stored in the hangar and subjected to other operations; secondly, design constraints such as geometric dimensions, lift force characteristics, control capacity and load impact are considered in the take-off and landing operation form, and the aircraft is supported to complete catapult-assisted take-off and landing arresting operation. Finally, the span-chord ratio of the air flight form is large, the aerodynamic efficiency is improved, and the mission ability of the aircraft is enhanced.

A swirl recovery vane with acoustic treatment including a leading edge and a trailing edge opposite chordwise from the leading edge; an attachment region opposite spanwise from a tip region; a span dimension extending between the attachment region and the tip region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the swirl recovery vane; an acoustic zone integrally formed within the swirl recovery vane. A gas turbine engine includes the swirl recovery vane with acoustic treatment. A process forms the swirl recovery vane with acoustic treatment.

Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan in the nozzle duct in a mixer-ejector scheme. Mixer-ejectors mix the boundary layer flow to increase mass flow.

This invention discloses a rotor assembly, a rotor assembly storage method, and a drone, comprising: an arm folding unit, one end of which is connected to the drone body; an arm, connected to the other end of the arm folding unit; a propeller motor mounting base, connected to the free end of the arm; a propeller drive motor, mounted on the propeller motor mounting base; and a propeller blade, connected to the rotational output end of the propeller drive motor. The arm folding unit is used to fold the arm, placing it in a folded state, and to unfold the arm, placing it in an unfolded state. This invention achieves automatic and orderly folding, storage, and unfolding of the arm and propeller blades through the arm folding unit and the propeller storage unit, thereby solving the problem of manual folding required in ordinary folding drones.

Heterogeneous distribution of leading edge slots. The present invention relates to a row of turbomachine blades (120a, 120b, 130a, 130b) arranged around a central axis (X). This row of turbomachine blades (120a, 120b, 130a, 130b) comprises a first set of blades (120a, 130a) each with a set of leading edge slots (200), as well as at least a second set of blades (120b, 130b) none of which has a set of leading edge slots (200) substantially identical to the set of leading edge slots (200) of each blade (120a, 130a) of the first set of blades (120a, 130a). We also obtain a heterogeneous distribution of the leading edge slots (200) on the different blades (120a, 120b, 130a, 130b) of this row. Figure for the abbreviation: Fig. 3C.

A manned / unmanned aerial vehicle adapted for vertical takeoff and landing which is configured to be easily disassembled and reassembled. The aerial vehicle may be assembled with different wings based upon flight needs, which may be based upon cargo mass and flight duration, for example. The aerial vehicle may utilize structural booms within components, and may allow for decoupling of boom sections to facilitate disassembly. The aerial vehicle may utilize electric motors and store power in batteries. A method of customizing a configuration of an unmanned aerial vehicle based upon flight profile factors such as duration, stability, and maneuverability. A method of disassembling an aerial vehicle for storage and / or transport.

An intentional fluid manipulation apparatus (IFMA) assembly that includes an upstream intentional momentum shedding apparatus (IMSA) configured to impart a first induced velocity to a local free stream flow during a nominal operation requirement. The upstream IMSA creates a streamtube. The IFMA includes a downstream IMSA, with some or all of the downstream IMSA being located in a downstream portion of the streamtube. The downstream IMSA imparts a second induced velocity to the local free stream flow within the streamtube. The second induced velocity at the location of the downstream IMSA has a component in a direction opposite to the direction of the first induced velocity at the location of the downstream IMSA.

The utility model provides a swing positioning mechanism, and relates to the field of variable-angle pneumatic layout test mechanisms. The swing positioning mechanism comprises a swing body and a fixing frame, the swing body swings around a rotating shaft, a first positioning hole system, a second positioning hole system and a third positioning hole system are formed in the swing body, the first positioning hole system comprises a plurality of first positioning holes, the second positioning hole system comprises a plurality of second positioning holes, and the third positioning hole system comprises a plurality of third positioning holes; the positioning angle values of the second positioning holes and the third positioning holes are different and fall into the positioning angle interval of the adjacent first positioning holes; a plurality of positioning insertion mechanisms corresponding to the first positioning holes, the second positioning holes and the third positioning holes are arranged on the fixing frame, and the positioning insertion mechanisms drive the positioning pins to be inserted into the corresponding positioning holes. According to the swing positioning mechanism, the function of indexing locking of the swing body at a small positioning angle can be achieved, and the large-load indexing locking requirement of the mechanism is met.

The invention provides a pneumatic drag reduction system and method for a carrying tool, and the system comprises the carrying tool which moves in the X direction; the excitation unit is used for generating unsteady pneumatic excitation, is arranged on the surface of the carrying tool and is located at the front section of the carrying tool, and the excitation unit comprises at least one exciter, and each exciter sprays gas in the X direction; each exciter injects gas towards the front of the vehicle, and all the injected gases form unsteady pneumatic excitation. A low-pressure area is generated through active control of a flow field at the front end of an object, so that high pressure generated by an airflow stagnation effect is counteracted to achieve resistance reduction.

A nacelle inlet (10) that includes an inner flow surface (61) and an outer flow surface (62). A turbulator surface (50) is positioned along the inner flow surface (61) and includes a roughened surface with the turbulator surface (50) configured to transition laminar airflow along the inner flow surface (61) upstream from the turbulator surface (50) to turbulent airflow downstream from the turbulator surface (50).