176 results about "Composite wing" patented technology

The invention discloses a hydrogen-electricity hybrid energy management method for a low-altitude operation composite wing unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicle energy management, and the method comprises the steps: S1, constructing an energy management system which comprises a working condition recognition module, an energy state monitoring module, a decision module and an execution module; s2, real-time operation parameters of the composite-wing unmanned aerial vehicle are collected through a working condition recognition module, and the current operation working condition of the composite-wing unmanned aerial vehicle is judged; s3, collecting real-time energy parameters of the hydrogen fuel cell and the power cell through an energy state monitoring module; s4, the decision module outputs a target energy supply strategy based on the current operation condition and the real-time energy parameters; and S5, the execution module controls the energy supply states of the hydrogen fuel cell and the power cell according to the target energy supply strategy. The three typical working conditions of the low-altitude operation composite wing unmanned aerial vehicle are accurately judged through the working condition recognition module, a decision matrix is constructed in combination with multi-dimensional energy parameters, dynamic matching of energy supply strategies is achieved, and the working condition adaptability is enhanced.

The invention discloses a composite wing unmanned aerial vehicle intelligent obstacle avoidance method and system based on deep learning, and the method comprises the steps: responding to an obstacle avoidance task signal, collecting multi-modal environment perception data, constructing a lightweight multi-modal fusion neural network model which comprises an encoder and a decoder, and carrying out the recognition of the multi-modal environment perception data through the encoder and the decoder; fusing the image sequence, the three-dimensional point cloud data and the circumferential sensing data through an encoder to obtain a fused feature tensor, decoding the fused feature tensor through a decoder, outputting a risk result based on an obstacle, inputting the risk result based on the obstacle and flight state parameters into a recurrent neural network controller together, and outputting the flight state parameters. And outputting the unmanned aerial vehicle flight control instruction vector, thereby obtaining an unmanned aerial vehicle control signal, controlling the unmanned aerial vehicle to avoid the obstacle, and obtaining an obstacle avoidance task completion result. The invention provides a composite wing unmanned aerial vehicle intelligent obstacle avoidance technology capable of realizing deep fusion of multi-mode perception, end-to-end intelligent decision and platform customization control.

The invention provides a composite wing unmanned aerial vehicle transition mode control method and system. The method comprises the following steps: acquiring wing surface deformation data of the composite wing unmanned aerial vehicle in a transition mode, and acquiring a vibration signal corresponding to the wing surface deformation data and real-time state information of a key component; on the basis of the vibration signal, the local stress increment at the joint of the wing is calculated, and in combination with the real-time state information, a fault risk level parameter is generated to predict a potential fault position and a fault evolution trend parameter of the composite wing unmanned aerial vehicle; when the potential fault position and the fault evolution trend parameter reach a preset safety condition, generating a high-speed trigger signal matched with the fault risk level parameter through a pulse technology so as to adjust a redundancy execution unit; the adjusted redundancy execution unit is started to complete fault-tolerant control in the transition mode; according to the method, synchronous intervention of the whole process of fault evolution and fault-tolerant control is realized, and active blocking of structural damage in mode switching of the composite wing unmanned aerial vehicle is guaranteed.

The invention provides an unmanned aerial vehicle composite wingtip structure with an antenna mounting function and an assembly method thereof. The unmanned aerial vehicle composite wingtip structure comprises a left interlayer skin 1 and a right interlayer skin 2, wherein each of the left interlayer skin 1 and the right interlayer skin 2 comprises an outer skin 18, a foam core 19 and an inner skin 20; the foam core 19 is positioned at the rear part of the wingtip; the outer skin 18 and the inner skin 20 are completely and symmetrically laid to form a pure laminate structure; the front beam supporting piece 3 and the rear beam supporting piece 4 are of a pure laminate box-shaped structure formed by completely and symmetrically laying fabric prepreg and are of a wingtip bearing structure. The lower portion of the front beam supporting piece 3 and the lower portion of the rear beam supporting piece 4 are each provided with a sunken area, and the sunken areas are installed on the front beam tail section 13 and the rear beam tail section 15 in an embedded mode. The antenna supporting piece 5 is of a pure laminate box-shaped structure formed by completely and symmetrically laying fabric prepreg, and is embedded in the front beam supporting piece 3 and the rear beam supporting piece 4; the antenna switching support 6 is a plate-shaped structural member and is in threaded connection with the antenna supporting member 5; and the skin folding strip 7 is laid outside the left interlayer skin 1 and the right interlayer skin 2.

A composite airfoil assembly for a turbine engine includes an airfoil defining an airfoil interior, and an inner support structure at least partially located within the airfoil interior. The inner support structure can include a first core, a second core, and at least one pin. A laminate overlay surrounds at least a portion of the inner support structure.

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 swept-back three-beam thin wing composite wing structure, which comprises a wing main body and an aileron installed in a wing main body mounting groove, the wing main body comprises a wing skeleton and a wing outer skin structure outside the wing skeleton; the wing skeleton comprises a longitudinal member unit and a transverse member unit, the longitudinal member unit comprises a front beam, a middle beam and a rear beam, the front beam and the middle beam and the middle beam and the rear beam are arranged at acute angles, the transverse member unit comprises a plurality of wing ribs arranged between the front beam and the middle beam, between the middle beam and the rear beam and on one side of the front beam towards the front of the fuselage; the front beam, the middle beam and the rear beam are all provided with a spar connecting head for connecting with the fuselage. The wing provided by the application adopts a three-beam structure, each wing beam has a mouth-shaped cross section, so that each wing beam forms a multi-wall form, can bear the bending moment and the torque brought by a large wing effective load, and the wing structure is light in weight, high in strength and good in integrity.

The invention discloses a composite wing unmanned aerial vehicle wing forming and tooling integrated device and method based on a thermoplastic composite material. A traditional separated forming mold and an assembly tool are integrated, the assembly tool comprises a modular mold unit with a forming molded surface, and positioning grooves used for accurately positioning a wing spar and a wing rib are prefabricated in the molded surface; an electric heating system is arranged in the mold, so that a uniform and controllable temperature field is provided for laying the thermoplastic composite material; and a distributed optical fiber sensor network is embedded and is used for monitoring the temperature and the pressure on line in the whole process. The skin is laid on the heated mold in situ and cooled and formed; placing the internal framework into the positioning groove; and the positioning pin holes in the die are pressed and pressed tightly to finish assembly. According to the method, the standard is unified, multiple positioning errors are eliminated, the manufacturing period is greatly shortened, the tool cost is reduced, the advantages of in-situ melting and integral forming of the thermoplastic composite material are fully played, and the manufacturing precision, the structural performance and the production efficiency of the wing are remarkably improved.

The invention discloses a combined wing and an aircraft, and belongs to the technical field of aircrafts. Comprising a trapezoidal wing, a multi-section wing and a spiral winglet, and the trapezoidal wing, the multi-section wing and the spiral winglet are sequentially connected in the direction from a wing root to a wingtip; the multi-section wing comprises a front-end wing and a rear-end wing, a wing gap is formed between the rear edge of the front-end wing and the front edge of the rear-end wing, and the attack angle of the rear-end wing is larger than that of the front-end wing; one end of the spiral winglet is smoothly connected with the wingtip of the front-end wing, the other end of the spiral winglet is smoothly connected with the wingtip of the rear-end wing, and the geometric center of the spiral winglet is located on the axis extension line of the trapezoidal wing; the spiral winglet is smoothly mounted at the wingtip position of the multi-section wing, so that the vortex of the wingtip of the trapezoidal wing can be effectively weakened, and the induced resistance is greatly reduced.

A control method for a compound wing aircraft (10). Flight modes of the compound wing aircraft (10) comprise a vertical take-off and landing mode, a cruise mode and a transition mode. A control system of the compound wing aircraft (10) comprises: a control module (1) and a flight control module (2), wherein the control module (1) comprises at least a first control component (11) and a second control component (12) that can be operated by a user. The control method comprises: controlling the first control component (11) to move within a certain range to send different commands to the flight control module (2) at different positions within the range, so as to respectively complete flight actions of the compound wing aircraft (10) under various flight modes (S101); and controlling the second control component (12) to move in a plurality of different directions to send different commands to the flight control module (2) in the different directions for respectively controlling flight parameters of the compound wing aircraft (10) under various modes, and controlling the speed or attitude of the compound wing aircraft (10) while controlling the first control component (11) (S102). The control method enables effective control of the compound wing aircraft (10) in multiple flight modes, with simple operation.

The invention discloses a composite wing unmanned aerial vehicle transition process control method based on reinforcement learning, and the method comprises the steps: building a composite wing unmanned aerial vehicle transition process control model based on a PPO reinforcement learning algorithm; in the transition process of the composite wing unmanned aerial vehicle, rotor wing virtual control force and torque output by a rotor wing mode controller, fixed wing virtual control force and torque output by a fixed wing mode controller, and rotor wing virtual control weight and fixed wing virtual control weight output by a composite wing unmanned aerial vehicle transition process control model are obtained; and after weighting processing is carried out, distribution execution is carried out, composite wing unmanned aerial vehicle transition process control parameters are obtained, and control over the composite wing unmanned aerial vehicle transition process is completed. According to the method disclosed by the invention, the stability of the subsystem is guaranteed by a classical control algorithm, and the method is oriented to multi-performance index optimization, so that the network training convergence of the transition process can be quickly realized, and the stable and high-energy-efficiency control of the strong environment adaptability of the transition process of the composite wing unmanned aerial vehicle is comprehensively realized.

1. The name of the design product: composite wing electric aircraft. 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.

The invention discloses a high-precision automatic detection platform for a vertical take-off and landing composite wing unmanned aerial vehicle before flight, and belongs to the technical field of navigation verification of aviation navigation equipment. The problem that in the prior art, qualitative detection mainly depends on a manual mode is solved, high-precision detection of the orientation and the attitude angle before takeoff of the unmanned aerial vehicle is achieved through the GNSS positioning and orientation unit and the course attitude detection control unit, the detection precision can reach + / -1 degree, the detection accuracy is greatly improved, and the detection precision is improved. Flight potential safety hazards caused by detection errors are basically eliminated, and reliable guarantee is provided for safe flight of the unmanned aerial vehicle; the unmanned aerial vehicle is placed on the flying inspection platform, all flying inspection can be completed by one person, a traditional manual detection mode is replaced, the influence of human factors on the detection result is reduced, and the accuracy and reliability of detection are improved; and real-time data is analyzed and processed in real time, potential problems are found in time, corresponding measures are taken, and the flight safety of the unmanned aerial vehicle is further guaranteed.

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.

The application discloses a UAV recovery and take-off platform, and belongs to the field of shipborne UAV cross-domain recovery equipment, which comprises an upper table assembly, a posture adjusting mechanism and a bottom base, the upper table assembly is used for bearing a UAV, the posture adjusting mechanism is connected with the upper table assembly, the bottom base can be connected on a docking platform and is connected with the posture adjusting mechanism, the posture adjusting mechanism comprises three posture adjusting arms, the upper end of each posture adjusting arm is connected with the upper table assembly, the lower end of each posture adjusting arm is slidably connected with the bottom base, a driving mechanism is arranged on each posture adjusting arm, when the driving mechanism works, the posture adjusting arm can be moved, the upper table assembly is subjected to a force by the posture adjusting arm, and the horizontal state of the upper table assembly is adjusted; the posture of the upper table assembly can be adjusted through the structural arrangement of the posture adjusting mechanism, the three-dimensional sea wave disturbance of ship body roll, pitch and yaw is decoupled, the short board of the compound wing UAV landing without power posture adjustment can be made up in a targeted manner, and the shipborne recovery stability and the limit working condition fault tolerance capability are improved.

A kind of 3D printing forming method of continuous fiber reinforced composite wing structure, first generate the three-dimensional model of wing structure, extract its aerodynamic profile;Then design the wing internal structure of multiple support point stress, as the forming basis of wing rib and spar;Then according to support point coordinates and wing aerodynamic profile, the path planning is carried out to wing internal structure, generates the 3D printing path of wing rib and spar;Then the theoretical weight of wing overall structure is calculated, if satisfying lightweight demand, then next structure forming is carried out;If not satisfied, then through re-determining structure design parameter, until satisfying lightweight demand;Then the forming of relevant structure is realized by 3D printing equipment, wing rib is connected with spar;Finally, the wing outer skin is formed on the basis of wing internal structure, thus the continuous fiber reinforced composite lightweight structure wing workpiece is obtained;The present application realizes the controllable design and rapid forming of super-lightweight, high specific performance, low-cost composite wing structure.

The composite wing unmanned aerial vehicle convenient to assemble comprises a vehicle body, wings are inserted into mounting grooves formed in the upper sides of the left end and the right end of the vehicle body, mounting frames are arranged at the lower ends of the wings, propellers are arranged at the upper ends of the mounting frames, and supporting frames are inserted into connecting grooves formed in the middle of the lower end of the vehicle body. Inserting holes are formed in the front end and the rear end of each wing respectively, and inserting grooves are formed in the upper sides of the front end and the rear end of the supporting frame respectively; and the fixing mechanism comprises connecting plates, inserting rods and inserting columns, the connecting plates are slidably connected with the bottom wall of the unmanned aerial vehicle body, and the inserting rods and the inserting columns are arranged on the upper sides and the lower sides of the ends, close to the center of the interior of the unmanned aerial vehicle body, of the connecting plates correspondingly. According to the aircraft, the wing and the supporting frame can be assembled in a traditional mode that the wing and the supporting frame are connected through a bolt body, the stability during flight is guaranteed, the time spent on assembly is shortened, and the assembly efficiency is further improved.

The invention discloses a TACAN platform verification system based on an unmanned aerial vehicle platform, and belongs to the technical field of aviation navigation verification. The problems that in the prior art, the verification comprehensive cost is high, and the task scheduling rate is limited by the limitation of a special environment are solved, the modular vertical take-off and landing composite wing unmanned aerial vehicle is adopted, an airborne-ground integrated task system is combined, and high efficiency, high precision and automation of TACAN unit verification are achieved; through a differential GNSS + RTK technology and Kalman filtering dynamic correction, centimeter-level positioning precision is ensured; a space-time alignment algorithm and a digital twinborn model are combined for comparison, so that accurate error analysis is realized; based on environmental interference compensation, the reliability in a complex environment is improved, and a three-dimensional visualization report visually presents a verification result; therefore, the comprehensive cost is lower, the operation rate is more flexible, the task capability in a special verification environment is filled, and the verification efficiency and precision are remarkably improved.

The application relates to the technical field of unmanned planes, and discloses a rescue unmanned plane based on a compound-wing vertical take-off and landing platform and a control method thereof. The method monitors the tension of a sling through a high-precision tension sensor, estimates and compensates for system disturbance caused by cable swing and crosswind by adopting a compound control strategy combining an extended state observer and a recursive sliding mode controller, dynamically adjusts the thrust distribution of a rotor and the included angle of a rotating plane, effectively suppresses the "nodding phenomenon" and cargo swing when the load suddenly increases, and significantly improves the flight stability and safety of the unmanned plane during the hoisting and rescue of materials.

The application relates to an electric field coupling charging device and system of a compound wing unmanned plane, the electric field coupling charging device comprises a transmitting device, a receiving device and a shielding device, the transmitting device is arranged on a landing platform, and the receiving device and the shielding device are arranged at the bottom of the fuselage of the compound wing unmanned plane; the transmitting device comprises a first polar plate, a first insulating layer, a second polar plate and a second insulating layer from top to bottom; the receiving device comprises a third insulating layer, a third polar plate, a fourth insulating layer and a fourth polar plate from top to bottom; the first polar plate comprises a plurality of first transmitting units which are uniformly distributed and have the same area, the third polar plate comprises a plurality of second transmitting units which are uniformly distributed and have the same area, and the first transmitting units and the second transmitting units are arranged in a staggered mode; the third insulating layer, the third polar plate and the fourth insulating layer are of the same shape and are all solid planes, and the fourth polar plate is hollow.

The invention relates to the field of aerospace, in particular to a telescopic composite wing which can be used for aerospace equipment such as hovercars and carrier-based aircrafts. The telescopic composite wing comprises a wing framework, a wing shell and a linear actuator, and further comprises a hidden propeller mechanism, the telescopic composite wing disclosed by the invention has the following beneficial effects that the shape and the size of the wing can be customized according to requirements; in a contraction state, the wings can be completely hidden, so that a limited space is reasonably utilized, and the whole wings are lighter than traditional wings; in the aspect of structural strength, the wing shell provides secondary bending torsion, the framework provides main bending torsion, and the framework is connected with the wing shell at each section and can synchronously stretch and retract, so that the synchronization degree is high, and the stability is strong; the rotary propellers are installed in the wing sections at the two ends of the wings, and the left and right lift force can be adjusted under the condition that the wings on the two sides are equal in length, so that the aircraft can achieve flight actions such as rolling, and the flight attitude controllability is high.

1. Name of the designed product: aircraft (double-tail strut composite wing layout vertical take-off and landing). 2. Use of the designed product: vehicle for air transportation or operation. 3. Design points of the designed product: in shape. 4. Picture or photo best indicating the design points: design 1 perspective view. 5. Design 1 is designated as the basic design.

The invention discloses an ultralight composite wing compression molding tool. The device comprises a base and detachable check blocks arranged at the two ends of the base, a cover plate covers the base and the check blocks, a wing cavity is formed among the cover plate, the base and the check blocks at the two ends, and the top face of the outer side of the cover plate and the top faces of the check blocks are connected and fixed through pressing blocks. The mold has the advantages that the detachable stop blocks are arranged at the two ends of the mold cavity and can be detached after molding is completed, so that constraint of the ends of the wing is released, demolding resistance is reduced, and product damage is avoided; the stop blocks are connected through countersunk screws, and the heads of the screws are lower than or flush with the surface of the base, so that interference on the molded surface is avoided, and the surface quality and aerodynamic performance of the wing are improved.

The invention relates to the technical field of small unmanned aerial vehicles, and discloses a vertical take-off and landing composite wing unmanned aerial vehicle based on flying wing layout, the vertical take-off and landing composite wing unmanned aerial vehicle comprises a fuselage, wings are fixedly connected to the exteriors of the two sides of the fuselage, vertical tails are fixedly connected to the exteriors of the wings, and mounting columns are fixedly connected to the interiors of one sides of the wings; the exterior of the mounting column is provided with double reverse propellers, the exterior of the fuselage is provided with an optical take-off and landing auxiliary module, the interiors of the wings are rotatably connected with lifting ailerons, the upper surfaces of the lifting ailerons are fixedly connected with mounting blocks I, and the exteriors of the mounting blocks I are rotatably connected with telescopic rods; and a second mounting block is rotationally connected to the outer portion of the telescopic rod, the bottom end of the second mounting block is mounted on the upper surface of the wing, and a supporting mechanism is mounted at the foot point. The lifting ailerons with the increased area are arranged on the rear edges of the wings, so that the unmanned aerial vehicle can quickly and stably complete vertical and horizontal attitude conversion in a narrow space.

This invention discloses a transient control method for compound-wing unmanned aerial vehicles (UAVs) based on fractional-order sliding mode control, specifically relating to the field of compound-wing UAV flight control. It employs the Newton-Euler equations to perform integrated modeling of the transient process of the compound-wing UAV, deriving a longitudinal nonlinear mathematical model. Based on the traditional exponential power reaching law, a novel fractional-order reaching law is designed by combining a double power reaching law and the concept of fractional-order calculus. A fractional-order sliding mode controller is constructed for pitch angle, airspeed, and quadrotor altitude. An airspeed weighted control allocation strategy is used to distribute the forces and torques between the quadrotor system and the fixed-wing system, thereby solving for the actuator output. This invention applies sliding mode variable structure control to the transient control of compound-wing UAVs. The proposed fractional-order sliding mode control method improves the dynamic quality of the system, reduces steady-state control errors, enhances the robustness of the compound-wing UAV flight control system, and achieves smooth control of the transient process.

The utility model relates to the technical field of helicopters, in particular to a vertical take-off and landing electric helicopter with composite wings. The vertical take-off and landing electric helicopter comprises a helicopter body, multiple sets of lift propellers are arranged on the front side and the rear side of the helicopter body correspondingly, multiple sets of lift propellers are arranged on the left side and the right side of the helicopter body correspondingly, a front push propeller is arranged on the rear side of the helicopter body, and the front push propeller and the lift propellers are driven by motors; rotary wings are arranged at the top of the aircraft body and controlled through a wing rotating mechanism. The foldable lift propellers are arranged on the left side and the right side of the helicopter body, so that the propeller pitch of the helicopter is increased, the crosswind resistance of the helicopter is improved, and the safety performance of the helicopter is improved; the rotating direction of the wings is controlled through the wing rotating mechanism, and the wings are locked and positioned. After the folding type lifting force paddles and the rotary type wings are folded, the helicopter can be parked in a single parking space and can take off and land on a single lane and the roadside of a road; when the wings are unfolded, the wings generate lift force, and the front propellers provide thrust.

The invention belongs to the technical field of aerospace equipment assembly, and discloses a composite material wing box section intelligent flexible adjustable assembly tool which comprises a tool frame. The positioning assembly is installed in the tool frame and comprises a lower wall plate positioning device, an upper beam positioning device, a lower beam positioning device, a left end rib positioning device, a right end rib positioning device and an upper wall plate positioning device which are used for clamping a lower wall plate, an upper beam plate, a lower beam plate, a left end rib plate, a right end rib plate and a first upper wall plate of the wing box structure respectively; the mounting assembly comprises a six-degree-of-freedom mechanical arm and a storage rack, a mounting part is arranged at the tail end of the six-degree-of-freedom mechanical arm, a second upper wall plate is placed on the storage rack, and the six-degree-of-freedom mechanical arm is used for mounting the second upper wall plate on the wing box structure through the mounting part; and the adjusting part is used for leveling the tool frame. According to the method, the assembly precision, efficiency and universality can be greatly improved, the structural damage risk is reduced, and reliable technical support is provided for assembly of composite material complex components.

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.