367 results about "Composite wing" patented technology

The invention discloses an efficient flight control system of a low-altitude manned unmanned aerial vehicle based on tilting composite wings, and relates to the technical field of unmanned aerial vehicle control systems. The low-altitude manned unmanned aerial vehicle efficient flight control system based on the tilting composite wings comprises an initialization and pre-check module, a vertical take-off and landing control module, a transition flight control module, an obstacle avoidance and path planning module and a landing control module. Through integration of vertical take-off and landing, smooth transition to cruise, intelligent obstacle avoidance, path planning and other modules, autonomous and efficient flight in a complex environment is realized, and the application scene of the unmanned aerial vehicle is greatly widened. Meanwhile, the accurate flight control and data post-processing analysis capability not only guarantees the safety and comfort of passengers, but also promotes the continuous optimization of the system performance through the real-time performance evaluation and feedback mechanism. In addition, the aerial refueling / charging technology is supported, the cruising ability is prolonged, and the task execution continuity and flexibility are enhanced.

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 relates to the technical field of ecological environment monitoring, and discloses intelligent eagle equipment and an ecological environment monitoring method, and the intelligent eagle equipment comprises a data obtaining module which is used for obtaining ecological environment images, temperature data and point cloud data of a target area at different distances through employing a multi-focal-segment fusion algorithm; the data processing module is used for performing parallel processing on the acquired data by adopting a quantum circuit algorithm; the remote transmission module is used for transmitting the collected data and the processed data to a ground control station in real time so as to make decisions and determine monitoring task requirements through the ground control station; the monitoring path planning module is used for receiving monitoring task requirements, selecting a path planning algorithm according to terrain complexity, performing path planning on a target area in combination with the collected data, and converting a path planning result into a control instruction through a ground control station; and the unmanned aerial vehicle platform comprises a composite wing unmanned aerial vehicle and a multi-rotor unmanned aerial vehicle, and is used for carrying other modules and receiving the control instruction of the ground control station to carry out flight monitoring.

A turbine engine includes a fan and a turbomachine defining an engine centerline. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbine engine also includes a set of composite airfoils circumferentially arranged about the engine centerline. 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.

According to the modularized traffic tool with multiple take-off modes, through the innovative split modularized design, the form of the traffic tool can be flexibly changed between an automobile and an aircraft, the flight state and the land running state are switched, and more novel passenger and freight application scenes can be expanded through cooperation of the independent carrying cabin modules. By utilizing the tiltable ducted fan mechanism and by virtue of boosting of the autonomous traveling chassis, the composite wing flight module can realize vertical take-off and landing, and wing lift force can be provided for short-distance taxiing take-off and landing to reduce energy consumption, so that the purposes of large voyage and high load are finally realized. The foldable fixed wing, the horizontal tail and the telescopic tail wing structure ensure that the traffic tool is small in size when running and parking on the land, so that the requirements of existing urban and rural roads and traffic safety laws and regulations can be met, and actual popularization is more facilitated.

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 composite airfoil assembly for a gas turbine engine. The composite airfoil assembly includes a composite airfoil defined by a core and a skin. The composite airfoil assembly further includes cladding. The core defines a core exterior, where the skin is applied to at least a portion of the core exterior. The cladding is prepared before being coupled or adhered to the composite airfoil.

A turbine engine includes a fan and a turbomachine defining an engine centerline. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbine engine also includes a set of composite airfoils circumferentially arranged about the engine centerline. 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 discloses a composite wing unmanned aerial vehicle transition process control method based on a fractional order sliding mode, and particularly relates to the field of composite wing unmanned aerial vehicle flight control. A Newton-Euler equation is adopted to carry out integrated modeling on a composite wing unmanned aerial vehicle transition process, and a longitudinal nonlinear mathematical model is deduced; designing a novel fractional order reaching law by combining a double-power reaching law and a fractional order calculus thought on the basis of a traditional exponential power reaching law, and constructing a pitch angle, air speed and four-rotor height fractional order sliding mode controller; and force and torque of the four-rotor system and the fixed-wing system are distributed by adopting an airspeed weight control distribution strategy, so that output of an actuator is solved. The sliding mode variable structure control is applied to the transition control of the composite wing unmanned aerial vehicle, and the proposed fractional order sliding mode control method improves the dynamic quality of the system, reduces the control steady state error, improves the robustness of the flight control system of the composite wing unmanned aerial vehicle, and realizes the stable control of the transition process.

A composite airfoil assembly for a gas turbine engine. The composite airfoil assembly includes a composite airfoil having opposite pressure and suction sides and opposite leading and trailing edges. The pressure side and the suction side extend axially between the leading edge and the trailing edge. The composite airfoil has a laminate skin that is applied to at least a portion of a core. A first cladding and a second cladding, having adjacent segments, are located on the pressure side or the suction side of the composite airfoil.

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 butt joint guiding device of a split type composite wing hovercar, which comprises a shell of a circular truncated cone type structure, and the lower bottom surface of the shell is connected with the bottom of a flying body; the locking devices are symmetrically arranged in the shell in a sliding mode, and the locking devices can selectively retract into or penetrate out of the two sides of the shell; one end of the second butt joint mechanism is connected with the passenger compartment, and a containing cavity is formed in the second butt joint mechanism; wherein the shell is matched with the containing cavity, and the locking device and the second butt joint mechanism can be selectively clamped or separated. The system has the advantages that accurate and rapid butt joint between the flight unit and the passenger compartment can be achieved, rapid switching between the flight mode and the driving mode of the hovercar is achieved, and the butt joint precision and reliability are high.

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.

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 wing manufacturing, and provides an aircraft static aeroelastic wind tunnel test model composite wing manufacturing process, which comprises the following steps: firstly analyzing the assembly structure of a wing main body, the partition structure of the skin of the wing main body and the structural form of a wing skeleton, the wing skeleton comprising a root joint, a front beam, a rear beam, a stiffening beam and ribs; the root joint is connected with the front beam, the rear beam and the reinforcing beam in a mode of combining glue joint with screws, ribs on the wing framework are connected with the front beam, the rear beam and the reinforcing beam, and the composite skin is connected with the main beam, the ribs and the root joint through screws. A mature and reliable production process is summarized, and the process starts from design and manufacturing of a forming mold of wing composite skin, skin forming, beam frame forming, design and manufacturing of a beam frame assembling mold and detection of the skin, the beam frame and the wing, and the aircraft static aeroelastic wind tunnel test model wing machining process is formed. And the whole wing has relatively high strength and bearing effect.

The forming process comprises the following steps: S1, respectively paving prepreg on a tool, and curing to form a composite material front spar and a composite material rear spar; s2, laying prepreg on the front edge rib foam core material to form a front edge rib; s3, a steering engine mounting groove is formed in the middle rib foam core material, an embedded block is placed in the steering engine mounting groove, then prepreg is laid and pasted, the prepreg at the position corresponding to the mounting groove is cut off, and a middle rib is formed; s4, prepreg is laid on the trailing edge rib foam core material, and a trailing edge rib is formed; s5, the front edge rib, the front spar, the middle rib, the rear spar and the rear edge rib are spliced, and connecting pieces with a plurality of metal joints are connected to the front spar and the rear spar; s6, integrally wrapping and paving the wing skin prepreg to form a composite material wing preform; and S7, paving demolding cloth, a non-porous isolating membrane, a breathable felt and a vacuum bag on the wing preform, placing the wing preform in a mold, closing the mold, pressurizing, vacuumizing, heating, completing co-curing, demolding, and opening a connecting hole to obtain the integrated composite material wing.

The utility model discloses a composite wing unmanned aerial vehicle power arm, belongs to the technical field of unmanned aerial vehicles, and solves the problems that an existing power arm is redundant in structure, large in weight and high in cost. And the upper skin comprises a plurality of layers of mutually attached twill carbon cloth. The lower skin comprises a plurality of layers of mutually attached twill carbon cloth, and two motor base installation grooves are formed in the lower skin. The main force bearing framework comprises a motor base beam, four beams and a plurality of power arm frames. And the four beams are arranged in a rectangular array. The multiple power arm frames are arranged in the inner space formed by the four beams at intervals in the length direction of the beams, and each power arm frame is connected with the four beams. The two ends of the two beams connected with the lower skin are each connected with a motor base beam. And the shape of the motor base beam is matched with the outer wall of the motor base mounting groove. And a motor mounting seat is mounted in each motor seat mounting groove. The structure redundancy phenomenon is avoided, the weight of the power arm is reasonably distributed, and the weight and cost of the power arm are reduced.

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.

A composite airfoil assembly for a gas turbine engine, the composite airfoil assembly comprising a composite airfoil, a first cladding, and a second cladding. The composite airfoil having a core comprising a composite structure having a core bulk modulus and a laminate skin applied to at least a portion of an exterior of the core. The first cladding and the second cladding are coupled to an outer surface of the composite airfoil.

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. The composite airfoil assembly has an airfoil outer surface defining opposing pressure and suction sides that extend between a leading edge and a trailing edge. A composite airfoil assembly includes: a braided core; a skin applied to at least a portion of the exterior of the core; and a cladding positioned adjacent the trailing edge, leading edge, root, or tip wherein a portion of the skin outer surface defines a first portion of the airfoil outer surface and a cladding outer surface defines a second portion of the airfoil outer surface.

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 utility model discloses a composite material wing lightning protection structure which comprises a main conduction path, a wing tip protection net, a wing root protection net, a magnetometer protection net and a fuel tank protection mechanism, the wing tip protection net, the wing root protection net, the magnetometer protection net and the fuel tank protection mechanism are connected with the main conduction path, the main conduction path is located on the surface of a wing, and the wing root protection net is connected with an electrostatic discharge device. The fuel tank protection mechanism comprises a composite material adhesive film layer, an aluminum net layer, copper net layers and a carbon fiber one-way belt, the composite material adhesive film layer is connected with the main conduction path, the aluminum net layer is installed on a fuel tank filler cap, the copper net layers comprise the first copper net layer and the second copper net layer, the first copper net layer and the second copper net layer are connected with the aluminum net layer and the main conduction path respectively, and the carbon fiber one-way belt is installed on the fuel tank filler cap. The wing tip protection net, the wing root protection net and the main conduction path are all metal nets, the use of lightning protection metal nets is reduced, the weight of the fuselage is reduced, the cost is reduced, and a good lightning protection effect is achieved.