29 results about "Composite wing" patented technology

The utility model discloses a kind of quick-release connection components for composite wing unmanned aerial vehicle, including fuselage and fixed wing installed on fuselage, both sides of fixed wing are equipped with mounting seat, and detachable multi-rotor mounting frame is installed on mounting seat.The beneficial effects of the utility model are as follows: by setting first spring, first lifting rod and installation pipe cooperation can make first lifting rod and first lifting plate can be lifted along installation pipe, drive the first locking groove on locking block and the locking block on fixed wing are inserted and locked, complete the quick installation of fuselage and fixed wing, second lifting rod is inserted into second locking groove under the action of second spring, complete the locking installation of mounting seat and multi-rotor mounting frame, so as to realize the quick installation and disassembly of multi-rotor on multi-rotor mounting frame, facilitate the disassembly and transportation of unmanned aerial vehicle, avoid wing damage in the process of transportation, knock damage, prolong the service life of unmanned aerial vehicle wing.

This invention provides a vertical takeoff and landing (VTOL) compound wing unmanned aerial vehicle (UAV), comprising a fuselage, with wings on both sides of the middle section of the fuselage. Each wing includes a middle wing section and an outer wing section. One end of the middle wing section is connected to the fuselage, and the outer wing section is connected to the other end of the middle wing section. A foldable cantilever is mounted on the side of the middle wing section, and a central propeller is mounted at the end of the foldable cantilever. A tail fin and a tail propeller are located at the tail of the fuselage, and a vertical tail is located at the bottom of the fuselage. This invention offers the following advantages: the cantilever of the VTOL compound wing UAV features a multi-level self-locking connection, ensuring reliable locking and excellent anti-loosening performance. The self-locking connection mechanism integrates multiple locking structures such as hinges, self-locking nuts, self-locking rods, and locking arc plates. After deployment, it achieves mechanical self-locking, effectively resisting flight vibrations, strong wind loads, and maneuvering impacts, preventing loosening, and ensuring high safety.

A kind of composite airfoil wallboard sharp corner numerical control processing auxiliary support tooling, including support, telescopic rod, support block, telescopic rod screw, external screw, base, clamp and flexible clamp adsorption column, wherein, the telescopic rod top rotatably mounted with support block, the support block end head is left for the threaded hole for being connected with composite airfoil wallboard by external screw, the telescopic rod bottom is connected fastening with support by telescopic rod screw, and guide rail is arranged on telescopic rod;The upper portion of the base rotatably mounted with support, and the lower portion of the base is rotatably fixed on the flexible clamp adsorption column of flexible clamp platform of numerical control five-axis gantry machining center by clamp.This application effectively solves the bottleneck problem that composite airfoil wallboard sharp corner cannot be numerically controlled processing, through test cutting to test piece, the support of composite airfoil wallboard sharp corner is stable, greatly improves the machining efficiency and quality of part, realizes the accurate edge cutting manufacturing of composite airfoil wallboard.

This invention discloses a stable flight control method for heavy-load unmanned aerial vehicles (UAVs) with compound wing configurations, relating to the field of UAV flight control technology. This invention utilizes a third-order nonlinear ESO to unify all internal and external disturbances, such as rotor-fixed-wing coupling disturbances, wind field disturbances, and model uncertainties caused by load changes, into a total disturbance for real-time estimation and feedforward compensation. This eliminates the need for precise modeling of complex coupled aerodynamic models and load change models, significantly reducing modeling difficulty. Simultaneously, it achieves full compensation for both matched and mismatched disturbances, significantly improving the anti-disturbance capability and robustness of heavy-load compound wing UAVs under strong disturbance scenarios, and solving the problems of attitude instability under sudden load changes, coupling disturbances, and complex wind fields.

1. The name of the design product: composite wing unmanned aerial vehicle. 2. The use of the design product: for unmanned aerial vehicle. 3. The design points of the design product: in shape. 4. The picture or photo that best indicates the design points: perspective view 2.

1. The name of the design product: composite wing electric aircraft (2). 2. The use of the design product: for manned flight, sightseeing, transportation of goods, rescue, etc. 3. The design points of the design product: in shape. 4. The picture or photo that best indicates the design points: perspective view 1.

The present application relates to the technical field of compound-wing aircraft. Disclosed are a compound-wing aircraft yaw control method and yaw control system, a flight device and a storage medium. The compound-wing aircraft yaw control method of the present application comprises: acquiring rotor motor health status information in real time, and, on the basis of the rotor motor health status information, starting a tail propulsion control strategy for a tail propulsion motor, so as to achieve active yaw of the aircraft and maintain the current flight speed of the aircraft. In the compound-wing aircraft yaw control method of the present embodiment, when the rotor motor fails, yaw control is assisted by means of the tail propulsion motor, thus reducing the control burden of the rotor motor, and accordingly improving the handling performance.

This invention relates to the field of charging management technology, specifically to a hybrid power energy management method and system for a compound-wing unmanned aerial vehicle (UAV). The method acquires real-time UAV status data to determine the flight mode; when in fixed-wing cruise mode, it predicts the maximum engine load rate based on the current sliding window and calculates a safe charging boundary value that does not consume flight power; it predicts the remaining cruise duration and the remaining battery charge at the end of the mission landing, and combines this with a safety threshold to determine the urgency of battery charging; it inputs real-time battery temperature, internal resistance, and remaining charge into a mapping function and weights this to obtain a charging adaptability coefficient; finally, it combines the above boundary values, urgency level, and adaptability coefficient to obtain the actual charging power for cross-modal charging, performs battery charge verification before mode transition, and disconnects non-critical loads in case of failure. This invention achieves intelligent collaborative allocation of power energy across modes, significantly improving the energy utilization rate and flight safety of UAVs.

The utility model provides a kind of composite wing unmanned aerial vehicle, belong to unmanned aerial vehicle technical field, including the main body fuselage front part transversely arranged main wing, the vertical lift wing being respectively arranged in the left and right sides of main wing upper portion, the tail fin being arranged in the upper portion of main body fuselage tail portion, the bottom of each vertical lift wing is provided with a guide vertical board, the bottom of each guide vertical board is provided with a support column, the bottom of each support column is provided with a horizontal guide vane, the front and rear ends of the bottom of each horizontal guide vane are provided with a buffer component, the lower portion of main body fuselage rear portion is provided with auxiliary support, the utility model is through protruding and buffer plate, and instantaneous impact force is reduced to support leg, further reduce instantaneous impact force to horizontal guide vane by the shock-absorbing spring being set in support leg, finally, impact force is reduced to main wing by support column again, so that the impact force when landing of main body fuselage internal component is reduced, so the service life of equipment can be improved.

The application belongs to the field of aircraft technology, and particularly relates to a foldable air cushion type compound wing tri-copter unmanned aerial vehicle, which comprises an airplane power system, a guide vane span linkage conversion mechanism and a variable air cushion structure. With the aid of the variable air cushion structure, different forms of changes are well adapted to the movement of the unmanned aerial vehicle in different modes on land, water surface and in the air. With the aid of the rotatable wings and arms, the passability of the unmanned aerial vehicle when running on land and water surface is improved. The variable guide cover in the variable air cushion structure is well adapted to the shape requirement of the unmanned aerial vehicle in flight in the air. A single power element is adopted, and the rotation of the rotatable wings, the front and rear rotating arms and the extension of the front guide cover, the left guide cover, the right guide cover and the rear guide cover are synchronously completed through mechanical structure, so that the stability of the system is greatly improved, and the robustness is high.

The present application belongs to the technical field of intelligent operation and maintenance of photovoltaic power stations, and particularly relates to a high-precision photovoltaic module defect positioning method based on a composite-wing unmanned aerial vehicle, comprising the following steps: acquiring image data streams collected by the unmanned aerial vehicle in real time during inspection; using a defect recognition model deployed on the aerial vehicle to perform online processing and target recognition on the image data streams to detect suspected defect targets on the photovoltaic module and output pixel-level bounding box information of the suspected defect targets; when a defect target is recognized, the unmanned aerial vehicle is controlled to enter an automatic hovering state, and high-definition zoom image collection is performed on the defect target; the present application can realize accurate mapping from aerial images to ground module assets by fusing centimeter-level RTK positioning, visual geometric solving and high-precision GIS map matching technology, achieve a positioning effect of "what you see is what you get", and improve the decision-making efficiency of power station operation and maintenance through intelligent management of defect data.

1.The name of the design product: unmanned aerial vehicle (portable compound wing). 2.The use of the design product: the unmanned aerial vehicle can be used for reconnaissance, surveillance, communication relay, target positioning and other tasks. 3.The design points of the design product: the combination of shape, pattern and color. 4.The picture or photo that best indicates the design points: front view. 5.The design claimed contains color.

1. Name of the product in this design: Cargo Unmanned Aerial Vehicle (Vehicle-mounted Composite Wing Model). 2. Purpose of this design: This design is intended for use with cargo drones. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: 3D rendering 1.

A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

The application provides a composite wing unmanned plane with a vector motor seat, which comprises a frame, the frame comprises a left fuselage and a right fuselage, a front wing is connected between the front ends of the left fuselage and the right fuselage, aircraft vertical tails are fixed to the rear ends of the left fuselage and the right fuselage, an aircraft rear wing is fixed between the two aircraft vertical tails, and a first power unit is installed on the front wing. The application has the following beneficial effects: the front wing double motors of the application can be tilted, in the take-off stage, the front wing motors face downward, and the vertical take-off can be realized by cooperating with the double motors on the fuselage, in the take-off to cruising stage, the rear wing motors provide power, the fuselage and the front wing motors slowly reduce power until the unmanned plane can smoothly glide, at this time, the front wing double motors can be turned to face forward, the four motors simultaneously provide power for the unmanned plane, and the full attitude control of the plane can be realized through the motors and double wing rudders.

This disclosure relates to composite wing panels and methods of manufacturing them. Wing panels having composite wing skin and longitudinal spars are produced on a moving production line. The wing panels are formed on a mandrel that moves along the production line through stations where a laminator lays the wing skin and a pick-and-place machine places longitudinal spars supplied by a longitudinal spars feeder onto the wing skin.

A composite airfoil assembly for a turbine engine. The turbine engine has a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement. The composite airfoil assembly has an outer wall, a composite body, and a tip cap. The composite body at least partially defines the outer wall. The tip cap at least partially defines the outer wall.

The application provides a bus communication system and method based on a compound wing unmanned aerial vehicle power system, which comprises a bus repeater, a standard bus interface module, a double bus communication protocol module and a bus topology structure module; the bus repeater comprises a data transceiving module, a data processing module and a data storage module; the data transceiving module comprises a non-isolation unit and an isolation unit; the non-isolation unit is connected with a flight control navigation system; the isolation unit is connected with the standard bus interface module; the double bus communication protocol module comprises a bus competition processing protocol unit, a data analysis and distribution protocol unit and a fault processing protocol unit; the bus topology structure module adopts a tree topology and comprises a main bus and a plurality of branch buses; and the application can realize safe and efficient transmission of data between the power system and the flight control navigation system, improve the anti-interference ability, expandability and fault tolerance of the system.

This invention discloses a compound-wing unmanned aerial vehicle (UAV) capable of vertical takeoff, belonging to the field of UAV technology. It includes a fuselage, a first wing, a second wing, and a tail fin. The fuselage houses a power supply module and a control module. Ailerons are mounted on both the first and tail fins and are electrically connected to the control module. A second drive device is mounted on the fuselage, and a third drive device is mounted on the second wing. The first and second wings are rotatably connected. A counterweight wing is mounted on the second wing and is rotatably connected to the fuselage. The first drive device drives the first wing to flexibly adjust its angle within the range of -10° to 45° via a push rod. Combined with precise control from the main control board, the first wing can increase its takeoff angle in strong winds and automatically return to center using aerodynamic characteristics, effectively resisting external disturbances such as crosswinds and turbulence, and reducing the risk of rollover.

The application discloses a transition mode comprehensive weight intelligent control method for a compound wing unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicle flight control and intelligent control. In view of the problems of lift switching, nonlinear coupling, control chattering and stall risk in the transition from a rotor mode to a fixed wing mode, a dual-variable comprehensive weight distribution mechanism with airspeed dominance and angle of attack correction is adopted to construct rotor / fixed wing control weights which are continuous, smooth and meet the normalization constraint; meanwhile, the unmanned aerial vehicle is modeled as an integral nonlinear system, and strong robustness, low chattering and high precision integral control input solutions are realized through integral sliding mode control, neural network disturbance compensation and Moore-Penrose pseudo-inverse control distribution; finally, the control commands are distributed to the rotor, rudder and propulsion system according to the comprehensive weight, and the control dominance is smoothly transferred. The height and attitude stability, anti-interference ability and flight safety margin in the transition stage are improved, the engineering realizability is strong, and the method is suitable for mode transition control of various compound wing unmanned aerial vehicles.

The application discloses a multi-mode composite wing flying automobile and a control mode thereof. The flying automobile comprises a vehicle body module and three foldable flight modules in the vehicle body, which are a composite wing module located at both sides of the vehicle body, a tail wing module located at the top of the tail of the vehicle body, and a front rotor module located at the top of the front compartment of the vehicle body. The vehicle body module comprises a power battery, a driving motor and a hybrid engine. The vehicle body is provided with side cover plates at both sides thereof for opening and closing the composite wing accommodating cavities in the vehicle body. The top plate of the tail of the vehicle body is provided with a tail wing cover plate for opening and closing the tail wing accommodating cavities in the vehicle body. The top plate of the front compartment of the vehicle body is provided with a front rotor cover plate for opening and closing the front rotor accommodating cavities in the vehicle body. The flying automobile is provided with the vehicle body module and the flight modules in a matched mode to present a land driving mode, a vertical lifting mode, an air cruising mode and an emergency landing mode, and realizes multi-mode conversion.

The invention discloses a different-diameter four-tilt-rotor electric vertical take-off and landing aircraft, and relates to the technical field of electric vertical take-off and landing aviation. Comprising a fuselage, a sweepforward upper reverse front wing, a sweepback lower reverse rear wing, different-diameter tilting rotors, a redundant power system and a tilting mechanism, different-diameter rotors with large front parts and small rear parts are adopted, and wide-range variable pitch and variable rotating speed are matched to realize wide-speed-range efficient operation; the aerodynamic interference is reduced through the layout of the composite wings, and the safety margin is improved through redundant power and autorotation gliding design. The tilting rotor wing solves the problems that hovering and cruising performance of a traditional tilting rotor wing are mutually exclusive, interference is large, and safety is insufficient, has high aerodynamic efficiency, high speed, large voyage and high safety, and is suitable for urban air traffic, short-distance transportation and emergency rescue scenes.

This invention relates to the field of composite material manufacturing technology, and discloses a method for forming a composite material main spar for an airfoil, including: S1, mold design: designing a forming mold; S2, 0° sheet design; S3, 45° sheet design; S4, part placement; S5, bag making and vacuuming. This invention solves the problems of wrinkles in the flange strips and non-destructive delamination of the radius angle after forming the main spar in existing methods, enabling the forming of smaller radius angle features, fiber discontinuities, or large angle deviations. This invention uses an inverted male mold forming method for the main spar, utilizing its own gravity to eliminate flange wrinkles while also saving process costs. The sheet design method of this invention solves the problems of fiber discontinuities or large angle deviations, solves the problem of non-destructive delamination in the transition area, and improves placement efficiency. This invention also employs a combination of vacuuming and cold compaction processes, reducing the gap between layers and eliminating the shape deviation problems that may be caused by wrinkles on the vacuum bag surface in the male mold forming method, affecting assembly.

1. Name of the product in this design: Aircraft (Compound Wing Configuration Manned Electric Vertical Take-Off and Landing). 2. Purpose of this design: For use in manned electric vertical takeoff and landing aircraft. 3. The key design features of this product are its overall shape. 4. The image or photograph that best illustrates the design's key points: a 3D model.

This invention provides an assembly process method for reducing the amount of machining and fitting required for composite wing box components, comprising: S1: optimizing the arrangement of the positioning holes of the process lugs to reduce the amount of machining and fitting around the perimeter of the wall panel; S2: establishing an assembly geometric accuracy analysis model to optimize the tolerance allocation of each component of the wing box; S3: analyzing the error coupling relationship between the metal frame parts and the tooling positioning, establishing a force analysis model for the assembly process, and obtaining the amount of deformation in the shape of the metal frame; S4: analyzing the stress state of the upper composite wall panel to optimize the positioning and connection scheme, obtaining the tooling force-position flexibility adjustment amount and the deformation amount of the inner surface of the wall panel; S5: determining the amount of machining and fitting required for the metal frame shape based on the deformation of the frame shape and the inner surface of the skin, and iteratively adjusting the assembly process scheme if the requirements are not met. Through the fusion analysis of geometric and mechanical models, the assembly process is optimized and the amount of assembly deformation is predicted, and the machining and fitting required for the perimeter of the composite wing box component wall panel and the outer surface area of ​​the metal frame are designed in advance.