225 results about "Composite wing" patented technology

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.

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 invention provides an air-ground integrated emergency communication system and method based on a cellular-free technology. The air-ground integrated emergency communication system comprises a composite wing unmanned aerial vehicle air communication / monitoring subsystem, a mooring unmanned aerial vehicle air communication / monitoring subsystem, a cellular-free emergency communication vehicle subsystem and a robot dog ground communication subsystem. The composite wing unmanned aerial vehicle air communication / monitoring subsystem realizes public network coverage through a 4G / 5G integrated base station, the mooring unmanned aerial vehicle air communication / monitoring subsystem realizes private network coverage through a cellular-free network, the cellular-free emergency communication vehicle subsystem realizes communication data processing and command scheduling, and the robot dog ground communication subsystem is used for ground blind area signal blind compensation. The composite wing unmanned aerial vehicle carries a high-power base station to realize wide-area public network coverage, and the public communication requirement is met; the mooring unmanned aerial vehicle provides private network coverage through a cellular-free network and supports command and dispatch of rescue workers; the emergency communication vehicle integrates a core network and transmission equipment, guarantees data processing and link backhaul, and can also provide space area private network coverage in a certain range. The robot dog fills the ground blind area.

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.

The invention provides a variable wing-shaped composite wing vertical take-off and landing unmanned aerial vehicle which is characterized in that a fuselage structure is a spatial tetrahedral structure, and the tetrahedral structure comprises a triangular bottom surface structure and a spatial triangular pyramid structure located above the triangular bottom surface structure; three bottom edges of the spatial triangular pyramid structure are three edges of the triangular bottom surface structure; the lift structure is arranged at the top of the straight line where the gravity center of the fuselage structure is located; the thrust structure provides thrust for flight of the unmanned aerial vehicle; the folding and unfolding horizontal wings can be folded and unfolded. Therefore, gravity center stability and structural strength are guaranteed through the space tetrahedron fuselage structure, the lift force structure provides lift force during vertical take-off and landing, the horizontal wings are folded to reduce interference, and the lift force structure is inclined to cooperate with the unfolded horizontal wings to improve aerodynamic efficiency during horizontal flight. The folding and unfolding horizontal wing capable of being dynamically adjusted can prevent attitude instability by actively adjusting pneumatic layout in low-altitude turbulent flow.

1. Name of the product of this design: UAV (QY‑X4 composite wing). 2. Application of this design product: used in the field of drones. 3. The key point of the design of this product lies in its shape. 4. The picture or photo that best illustrates the design points: Stereoscopic drawing 1.

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 invention relates to the technical field of aircrafts, and particularly discloses a tandem wing layout composite wing vertical take-off and landing aircraft which comprises a plate-rod thin-wall lifting body fuselage, a front wing, a rear wing, a power system, a flight control system and a power supply module, the power system comprises a first propelling device, a second propelling device and a third propelling device; the first propelling device is fixedly arranged in front of the plate-rod thin-wall lifting body; the second propelling device is fixedly arranged on the front wing, and the third propelling device is fixedly arranged on the rear wing; the first propelling device, the second propelling device and the third propelling device are electrically connected with the flight control system; the front wings and the rear wings are fixedly connected with the plate-rod thin-wall lifting body fuselage, and the front wings and the rear wings form a tandem wing layout; the composite wing vertical take-off and landing aircraft with the tandem wing layout is more uniform in aerodynamic force distribution and smaller in wing load, and the lift force efficiency can be effectively improved.

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.

The utility model relates to the technical field of gliders, in particular to a carbon beam composite material wing structure. The airfoil comprises an airfoil main beam and foam layers located at the two ends of the airfoil main beam, the airfoil is of a structure which is thick in the middle and thin at the two ends on the whole, the airfoil main beam and the foam layers are wrapped with a layer of airfoil skin, and the airfoil main beam and the airfoil handle are connected in an inserted mode and fastened through a binder and a bolt; a weight reduction structure is designed in a non-bearing area of the wing handle, so that the overall weight of the structure is reduced; the modulus of the high-modulus carbon fiber main beam can reach 200Gpa, so that the deformation in a bearing state is effectively controlled, and the structural modal of the airfoil is improved; the high-modulus carbon beams and the wing handles are connected in an inserted mode, bonded through epoxy glue and connected in a fastened mode through bolts, and the bearing force of the wing surfaces is effectively transmitted to wing handle connecting points; the outer skin of the airfoil is made of high-strength carbon fiber one-way material, the laying direction and number of fibers are designed according to calculated stress, the 0-degree fiber direction, the 90-degree fiber direction and the + / -45-degree fiber direction are configured, and the torsional strength of the airfoil is improved on the premise that the bearing requirement is met.

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 composite wing unmanned aerial vehicle wing locking dismounting connecting device which comprises a front wing and a rear wing, a fuselage is arranged between the front wing and the rear wing, first undercarriages are symmetrically installed on the two sides of the front wing, and undercarriage connecting pieces are fixedly installed on one sides of the two first undercarriages. A second undercarriage is fixedly installed on one side of the bottom of the undercarriage connecting piece, longitudinal connecting assemblies and vertical shaft connecting assemblies are arranged at the connecting positions of the fuselage and the front wings and the connecting positions of the fuselage and the rear wings, and the longitudinal connecting assemblies comprise fixed shells symmetrically installed on the sides, close to the fuselage, of the front wings and the rear wings; the connecting stability and reliability of the wings are improved, better vibration and impact absorption capacity is provided, the wing connecting device adapts to complex flight environments, the dismounting and mounting processes are simplified, the operation efficiency is improved, additional safety guarantee is provided, and accidental unlocking or loosening is avoided.

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.