267 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 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 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 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.

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 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 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.

A composite airfoil (104) including an airfoil portion (110), a first tow (160, 180), and a second tow (162, 182). The first tow (160, 180) has a first set of fibers (160, 186). The second tow (162, 182) has a second set of fibers (162, 188). Each fiber of the first set of fibers (160, 186) has a first centerline axis (144, 192) and a first bulk modulus. Each fiber of the second set of fibers (162, 188) has a second centerline axis (146, 194) and a second bulk modulus.

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.

1. Name of the design product: Compound-wing vertical takeoff and landing aircraft. 2. Use of the design product: Mainly used for air transportation within and between cities, capable of carrying passengers and goods. It can also be used for emergency rescue, medical transportation, logistics, military use, etc. 3. Design key points of the design product: Lies in the shape. 4. Picture or photo that best shows the design key points: Perspective view.

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.