133 results about "Tailplane" patented technology

1. Name of the design product: ship tail wing. 2. Use of the design product: used for reducing the lift generated at the tail of the ship when sailing, thereby stabilizing the ship body. 3. Design points of the design product: in shape. 4. Picture or photo best indicating the design points: perspective view 1.

1. Name of the designed product: tail wing (ideal i8). 2. Use of the designed product: used for car tail wing, belonging to automobile parts. 3. Design points of the designed product: in shape. 4. Picture or photo that best shows the design points: perspective view.

A tail fin assembly for an aircraft having a tail fin with a front side-member, a plurality of ribs, wherein the ribs are positioned along the front side-member, wherein each rib has a foot which is integral with the front side-member and a head which is integral with the foot, at least one piece of piping extending along the front side-member and at the rear of each head, and a housing which is secured on the heads.

The application provides a hole waterproof rubber capsule adapting to construction error of structure mutation, which comprises a rubber capsule accommodated in a steel tank when not pressurized and tightly engaged with the outer contour of a jacking pipe after swelling, the rubber capsule is communicated with a pressurizing pipe, the steel tank is arranged on the end wall of a working well, a pre-buried ring frame is arranged in the end wall, the steel tank and the rubber capsule are arranged around the outer contour of the jacking pipe, the wall thickness of the rubber capsule is uniform at the smooth structure of the jacking pipe, at the sharp corner of the jacking pipe structure or the sharp corner of the pre-buried ring frame, the capsule wall of the rubber capsule is processed into a flying wing structure which can be connected with the sharp corner after swelling according to the shape of the sharp corner. The flying wing type capsule wall of the rubber capsule has corresponding ductility and wear resistance, the size of the flying wing meets the construction error requirement, the wing corner can be pushed to the structure mutation position under the condition of error working condition with the pressurization of the rubber capsule and the ductility of the capsule wall, the waterproof gap is filled, so that the wing corner and the wing surface can match the structure contour within a certain error range.

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

This invention discloses an ice-breaking load testing device and calculation method for the tail fin of an underwater vehicle model, relating to the field of polar submersible ice-breaking performance testing technology. The device includes a tail column with tail fins equidistantly mounted around its perimeter. A first tension / compression force sensor is installed at the upper middle of the front side of the tail column, with a distance from the tail column's central axis equal to 2 / 3 of the cross-sectional radius. A second tension / compression force sensor is installed on the left side of the bottom front side of the tail column, and a third tension / compression force sensor is installed on the right side of the bottom front side of the tail column. This invention allows for support from a fixed external end during use, enabling the measurement of applied forces. It also maintains the shape characteristics of the model's tail fin and allows for direct external sensor deployment, improving the efficiency and accuracy of data collection during operation.

This invention discloses a drifting glider, belonging to the technical field of marine monitoring equipment. The drifting glider includes a fuselage, a nose section, a tail section, and a tail fin. Its key feature is that a first through-slot is formed through its two opposite sides. A first power generation component capable of displacement is housed within the first through-slot. The first power generation component includes a solar panel assembly with solar panels that are movable relative to the first through-slot. This drifting glider can cruise in a fixed sea area for extended periods, acquiring data over a specific area. It features multiple operating modes, long endurance, and strong maneuverability.

The present application relates to the field of ship power technology, in particular to a rigid jet sail ship wind propulsion system, comprising a rotating base, a cylinder tower, an aerodynamic function module and a driving and control unit. The aerodynamic function module is the core, containing a wing body and a tail wing, the wing body is fixed to the cylinder tower and reserves an air duct, integrates a fan, and the rear jet port is communicated with the air duct; the tail wing realizes stable rotation through a swing arm shaft, a mounting seat and a spherical fixing seat. The driving and control unit cooperates with a wind direction sensor to accurately control each component. The system can effectively delay the airflow separation of the wing surface, improve the wind energy utilization efficiency, realize the reduction of ship fuel and carbon emissions, and is much better than the traditional technology, and has high structural rigidity, strong fatigue resistance, can lock the tail wing attitude, stable operation, significantly prolongs the service life, and adapts to the energy-saving propulsion needs of various ships.

This invention relates to the field of unmanned aerial vehicle (UAV) technology and discloses a high-efficiency underwater UAV. The UAV is equipped with an adjustable power drive mechanism and an observation mechanism, and internally features a high-strength, lightweight internal frame and a satellite navigation system. The adjustable power drive mechanism employs a tail-mounted power unit, tail fin, and multiple side-mounted adjustable propellers in a coordinated layout. The propellers can achieve pitch, rotation, and angle adjustment, satisfying multi-attitude control requirements such as hovering, turning, climbing, and diving, with stable thrust and flexible maneuverability. It is equipped with a deep-sea pressure-resistant transparent protective cover and a sonar positioning device, combined with satellite navigation for precise positioning and navigation, providing strong protection and environmental awareness capabilities. This invention solves the problems of traditional UAVs, such as single power source, insufficient maneuverability, and limited observation capabilities. It possesses advantages such as high-efficiency navigation, precise control, strong environmental adaptability, and reliable structure, making it suitable for deep-sea exploration, engineering inspection, environmental monitoring, and other operational scenarios.

This invention discloses a quad-wing flapping-wing aircraft with a symmetrical wheeled linear drive mechanism and its control method, relating to the field of flapping-wing aircraft technology. It includes a frame, a power input unit, a tail fin drive unit, a wing drive unit, and a triboelectric sensing unit. The triboelectric sensing unit is connected to the wing drive unit, and the wing drive unit is connected to the power drive unit. The power drive unit is mounted on the frame, and the lower part of the frame is connected to the tail fin drive unit. This invention employs the aforementioned quad-wing flapping-wing aircraft and control method with a symmetrical wheeled linear drive mechanism. The power input unit can amplify the flapping amplitude of the crank rocker arm; simultaneously, the flapping-wing aircraft integrates a triboelectric sensing unit, which facilitates attitude control of the tail fin drive unit, enabling roll, yaw, and hovering movements.

1. The name of the design product: tail wing (Xpeng-X9). 2. The use of the design product: used for car tail wing, belongs to automobile parts. 3. The design points of the design product: in shape. 4. The picture or photo that best indicates the design points: perspective view.

An aircraft structure includes a fuselage, a tail structure, a hinge support structure, and at least one internal actuator. The tail structure is pivotally attached to the fuselage and includes a tailcone and horizontal stabilizers fixed to the tailcone. Each of the horizontal stabilizers have a stabilizer leading edge and a stabilizer trailing edge and extend in opposite directions from the tailcone, forming an H-tail or a U-tail configuration. The hinge support structure is fixed at least partially within the fuselage, pivotally coupling the fuselage and the tail structure. The at least one internal actuator actuates the tail structure, rotating the stabilizer leading edge up and down relative to the fuselage, thereby trimming the horizontal stabilizers for aircraft stabilization.

This invention relates to a deep-sea towed body for deploying an L-shaped linear array, comprising a towed body shell, a slanted tail fin, a horizontal tail fin, a support frame, a horizontal linear array, a vertical linear array, a tow cable, a counterweight, an electronics compartment, a battery compartment, and heading and depth sensor compartments. The towed body shell is flat and teardrop-shaped, formed by horizontally laying out two standard airfoils of different lengths staggered forward and backward in the longitudinal and port / starboard sections of the towed body. The slanted tail fin is laid out at an angle based on the standard airfoils, and its interior is filled with pressure-resistant buoyancy material. This invention, using a tow cable, can be used to deploy an L-shaped linear array at depths up to 7000m, and to power the sensors within the array and facilitate signal acquisition and transmission.

HIGH-STABILITY, HIGH-AGILITY THREE-SAILING SURFACE AIRCRAFT The three-sail aircraft (1), (2), and (3) is equipped with movable flaps (6), (7), and (8) on each of the lifting surfaces. The flaps of the upstream lifting surface (6) are connected to the flaps of the main wing (7) by a rigid linkage with a deflection angle ratio of 50%. The forces on the downstream lifting surface (horizontal tail) (3) reverse between takeoff (negative lift) and cruise (positive lift). Stabilizing fins (5) are positioned at the rear of the fuselage in the lower section at an angle of 30° to the aircraft's centerline. A weighted control rod (22) located in the vertical tail (4) provides stabilization for the aircraft in the presence of severe turbulence.The propulsion system is located at the rear of the fuselage and consists of either a piston engine driving a multi-bladed propeller, one or two turboshaft engines driving a multi-bladed propeller or two contra-rotating propellers, a turbojet engine, or one or two electric motors driving a multi-bladed propeller or two contra-rotating propellers. This aircraft can be piloted either by a human pilot on board or by an electronic computer controlled from the ground or autonomously.

The utility model is specifically related to a wind power generation technical field, specifically related to a wind gathering cover automatic wind guiding device, specifically, the utility model is provided with: the sleeve center axis is fixed in the sleeve top surface, the rotary cover is nested in the sleeve, and the rotary cover is based on the first universal ball / second universal ball movable contact in the top surface / outer lateral surface of the sleeve, the wind gathering cover is fixed in the rotary cover top surface, and the strip tail wing is fixed in the rotary cover outer lateral surface, under the condition of satisfying that the extension direction of the strip tail wing is opposite to the windward surface of the wind gathering cover, when the wind direction changes obviously, the wind drives the rotation of the strip tail wing, and at the same time, the rotary cover rotates correspondingly under the rolling action of the first universal ball and the second universal ball, until the windward surface of the wind gathering cover faces the direction of the wind, so as to realize that the windward surface of the wind gathering cover is adjusted in combination with the real-time wind direction of the outside world, so as to improve the wind power generation efficiency.

This invention relates to a tail fin structure with independent pitch and roll movements, comprising a pitch mechanism, a roll mechanism, and a connecting mechanism. The pitch mechanism includes a pitch servo and a pitch linkage, while the roll mechanism includes a roll servo and a transmission gear. The connecting mechanism includes a universal joint and a universal joint limiter. The pitch servo drives the tail fin to pitch movement via the pitch linkage. The roll servo drives the universal joint to rotate via the transmission gear, with the tail end of the universal joint connected to the tail fin to complete the roll movement. The rotation center of the pitch mechanism coincides with the center of the universal joint, and the left and right swing degrees of freedom of the universal joint are limited by the universal joint limiter, achieving independent control of pitch and roll movements. This invention allows for completely independent roll and pitch movements, significantly reducing the control precision requirements of the motor. The invention has a simple structure and reasonable design. The single-plane tail fin structure of this invention has strong wind resistance during flight and also has advantages such as low inertial load on the motor and high drive efficiency.

The application belongs to the field of aerospace technology, and particularly relates to a vertical take-off and landing horizontal flight combined power unmanned aerial vehicle, which comprises a fuselage, main wings, rotors, horizontal tail wings and movable vertical tail wings; the main wings are symmetrically connected to the middle part of the fuselage, and the rotors are symmetrically connected to the main wings on the two sides; the horizontal tail wings are symmetrically connected to the tail part of the fuselage, and the movable vertical tail wings are connected to the upper part of the tail part of the fuselage; a pressure measuring device is arranged on the movable vertical tail wings; the pressure measuring device collects the pressure on the two sides of the movable vertical tail wings to a flight control system, and the flight control system calculates the pressure difference between the left and right sides to control the deflection of the movable vertical tail wings. The cruising efficiency of the unmanned aerial vehicle is improved, the driving device and structure thereof are relatively simple and light compared with the full-motion vertical tail wing. Meanwhile, the unmanned aerial vehicle also has the cruising efficiency of a fixed-wing aircraft and the low requirement for a take-off and landing site of a rotor vertical take-off and landing aircraft.

This application discloses an inflatable tail fin for an airship made of polyethylene film, characterized by comprising: a spherical membrane made of polyethylene film; reinforcing ribs for securing the spherical membrane; and longitudinally extending partitions welded into the cavity of the spherical membrane, wherein the longitudinal direction refers to the direction from the root of the tail fin to the tip of the tail fin; and multiple partitions arranged laterally within the cavity of the spherical membrane. This application also discloses a method for manufacturing an inflatable tail fin for an airship made of polyethylene film. This solves the problem that polyethylene film cannot withstand high pressure.

The application provides a tail rudder driving device, and relates to the technical field of unmanned aerial vehicles.The tail rudder driving device comprises a transmission assembly, a driving mechanism and a rudder assembly.The transmission assembly comprises a first transmission arm, a transmission shaft and a second transmission arm.The first transmission arm is fixedly connected with the transmission shaft, and the transmission shaft is movably connected with the second transmission arm to adjust the length of the second transmission arm.The minimum length of the second transmission arm is greater than that of the first transmission arm.The driving mechanism is fixedly connected with the first transmission arm and is used for driving the first transmission arm to rotate.The rudder assembly is fixedly connected with the second transmission arm, so that the driving mechanism drives the rudder to rotate through the first transmission arm, the transmission shaft and the second transmission arm.Because the length of the second transmission arm is greater than that of the first transmission arm, according to the torque transmission principle, the torque is amplified through the length difference when the torque is transmitted through the transmission assembly, so that the tail rudder driving device with a small volume installed in the fuselage can output greater torque and meet the deflection requirements of the rudder.

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.

This invention discloses a tail fin deflection mechanism and an aircraft, relating to the field of aircraft attitude control technology. It includes a first shape memory alloy wire and a reset component. The end of the first shape memory alloy wire is fixedly connected to the fuselage. Both the first shape memory alloy wire and the reset component are connected to the tail fin. At a first temperature, the tail fin is in a first position. When the first shape memory alloy wire is heated from the first temperature to a second temperature, the first shape memory alloy wire contracts and drives the tail fin to rotate from the first position to the second position against the force of the reset component. The reset component provides a reset force to the tail fin to rotate from the second position to the first position. The aircraft includes a fuselage, a tail fin, and the aforementioned tail fin deflection mechanism. This invention uses a tail fin, a reset component, and a first shape memory alloy wire to form the tail fin deflection mechanism, resulting in a small number of parts, a very simple overall structure, and a simple assembly process.

1. Name of this design product: Three-wheeled vehicle tail wing. 2. Purpose of this design: for use in tricycles. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: a 3D model.

The application provides a target projectile and an aircraft. The target projectile comprises a head part in a conical shape, a projectile body comprising at least one engine body section, a first engine body section close to the head part being connected to the head part, a tail part arranged at an end of the engine body section away from the head part and comprising at least two tail wings distributed around an axis of the engine body section, and a rudder part arranged at an end of the first engine body section close to the head part and comprising at least two rudder wings distributed around an axis of the first engine body section, wherein in a first plane perpendicular to the axis of the engine body section, the orthographic projection of the at least two rudder wings is staggered with the orthographic projection of the at least two tail wings. The application realizes controllable supersonic flight of the target projectile in a large airspace and a wide speed range, with a flight height of 0.1-20 km and a flight speed of 0.3-2.4 Ma.

The application discloses a vertical take-off and landing fixed-wing aircraft based on thrust vector nozzles, which comprises four engines, four thrust vector nozzles, a wing, a fuselage, a T-shaped tail wing and a support; four sets of power devices adopt a four-point isosceles trapezoidal symmetrical layout, and front and rear power devices are symmetrically arranged about the gravity center of the whole machine. The transverse spacing of the front power device is 2.5-3 times that of the rear power device, the spanwise projection is located at 40%-60% of the wing span length, and the height is matched with the wing leading edge to realize jet flow lift increase; the height and horizontal position of the rear power device are optimized to ensure stable air intake. The thrust vector nozzle takes the horizontal axis of the fuselage as the 0° reference, the vector angle adjustment range is not less than -95°-+15°, and the hovering, mode transition and steady switching of the flat flight are realized through differential adjustment. The application cancels the tilting mechanism, reduces the structural dead weight, reduces the aerodynamic interference, and improves the cruising speed and flight safety.