444 results about "Fuselage" patented technology

An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft comprises a fuselage extending between the forward end of the aircraft and the aft end of the aircraft; a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; an unducted turbofan engine including an unducted fan defining a fan diameter; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a leading edge and including a first inflection point along the leading edge, the first inflection point defining a first radius of curvature that is less than 5 times the fan diameter and greater than 0.1 times the fan diameter.

The utility model relates to a variable-configuration tilting quad-rotor unmanned aerial vehicle which comprises rotors (1), motors (2), main wings (3), a fuselage (4), a vertical fin (7), a power supply unit (8), a control unit (9), tilting steering engines (10), driving rocker arms (11), tilting connecting rods (13), tilting rod supports (16), front tilting rods (17), rear tilting rods, front driven rocker arms (18) and rear driven rocker arms. The tilting mechanism is simple in configuration form, the appearance of the whole tilting mechanism is not greatly changed in the tilting process, and the pneumatic influence in the tilting process is relatively small. When the rotors tilt forwards, a conventional rotor fixed wing aircraft mode is adopted, when the rotors tilt upwards, a conventional four-rotor unmanned aerial vehicle mode is adopted, and various modes and modes such as vertical take-off and landing, hovering and forward flying can be achieved.

An autonomous flying device achieving a large payload and a long continuous flight time and also accurately adjust position and orientation while flying. The device includes: a main rotor and the like that provide main thrust; a sub rotor and the like that controls the orientation; an engine that generates energy for rotating the main rotor and the like and the sub rotor and the like; and an arithmetic control device that controls rotation of the sub rotor and the like. Also, the main rotor and the like are rotated by being drivingly connected to the engine, whereas the sub rotor and the like are rotated by motors driven by electric power generated from generator and the like operated by the engine. Further, when orientation control to tilt the fuselage is performed, the arithmetic control device increases the output distribution ratio of the sub rotor to above the output distribution ratio of the sub rotor when hovering is performed.

The invention discloses a carbon fiber fuselage structure layering optimization design method and system, and relates to the technical field of material structure intelligent design, and the method comprises the steps: importing a three-dimensional CAD model of a fuselage structure, collecting physical field input parameters, integrating and generating a digital engineering package, and carrying out the temperature field calculation through a thermal coupling solver based on the digital engineering package, the method comprises the following steps: acquiring temperature distribution of a fuselage, mapping the temperature distribution of the fuselage into a thermal stress field through a thermoelastic constitutive equation, performing vector superposition on the thermal stress field and a mechanical load to generate a comprehensive stress cloud picture, starting asymmetric layering design for a high-stress region based on the comprehensive stress cloud picture, and verifying mechanical balance of layering angle combination through a balance optimization algorithm. And obtaining a layering optimization scheme. The thermal deformation sensitivity is accurately evaluated by using the thermal-mechanical coupling solver and the finite element disturbance analysis method, and thermal deformation can be effectively predicted and controlled, so that the dimensional stability and the surface quality of a final product are improved.

The present invention discloses a flapping-wing aircraft capable of catapult takeoff and having a sweep-torsion mechanism, belonging to the field of aircraft technology. The aircraft comprises: a fuselage frame, left and right flapping wings, a passive torsion mechanism, a sweep mechanism, a catapult takeoff mechanism, a transmission flapping mechanism, and a tail rudder, wherein: a passive torsion mechanism and a sweep mechanism are provided at the roots of the left and right flapping wings, the catapult takeoff mechanism is provided in the middle of the fuselage, and a hip joint, thigh, ankle joint, calf, foot, and toe joint are provided from top to bottom, the inner and outer sides of the hip joint are controlled by a servo motor for relative rotation, the ankle joint and toe joint are provided with elastic energy storage torsion springs, a synchronous pulley and its drive mechanism are provided between the outer side of the hip joint and the outer side of the ankle joint to control the relative rotation between the thigh and the calf, and perform energy storage for catapult takeoff. In summary, the aircraft can perform catapult takeoff flight, and can perform passive torsion and sweeping motions during the flapping of the wings, which helps to increase the flapping wing lift and the overall payload of the aircraft.

The utility model discloses a water area propeller and water area movable equipment. The water propeller is used for connecting a water carrier to propel the water carrier to move in the water. The water area propeller comprises a body and an operation device. A propelling device used for outputting propelling force for propelling the water area carrier to move is arranged at the end of the machine body. The operation device is rotationally connected to the end, away from the propelling device, of the fuselage body through a transverse connecting shaft, can be folded or unfolded with the fuselage body and is used for being operated by a user to control the water area propeller to operate. The operation device is provided with a first locking unit, the machine body is provided with a second locking unit, and when the operation device and the machine body are in a folded state, the first locking unit and the second locking unit lock the operation device and the machine body at the position between the transverse connecting shaft and the propelling device. And a suspension beam capable of loading the fuselage main body is formed between a locking position of the operating device between the first locking unit and the second locking unit and a connecting position of the operating device on the transverse connecting shaft.

An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.

The utility model discloses a water area propeller and water area movable equipment. The water area propeller comprises a machine body, an operation device and a locking module. A propelling device used for outputting propelling force for propelling the water area carrier to move is arranged at the end of the machine body. The operation device is rotationally connected to the end, away from the propelling device, of the fuselage body through a transverse connecting shaft, can be folded or unfolded with the fuselage body and is used for being operated by a user to control the water area propeller to operate. The locking module comprises a first locking unit and a second locking unit, and the first locking unit and the second locking unit are arranged in the operation device and the machine body respectively. The locking module locks the operation device and the machine body main body at the position between the transverse connecting shaft and the propelling device through the insertion force between the first locking unit and the second locking unit, and the operation device forms a cantilever beam capable of loading the machine body main body between the transverse connecting shaft and the locking module.

An autonomous flying device achieving a large payload and a long continuous flight time and also accurately adjust position and orientation while flying. The device includes: a main rotor and the like that provide main thrust; a sub rotor and the like that controls the orientation; an engine that generates energy for rotating the main rotor and the like and the sub rotor and the like; and an arithmetic control device that controls rotation of the sub rotor and the like. Also, the main rotor and the like are rotated by being drivingly connected to the engine, whereas the sub rotor and the like are rotated by motors driven by electric power generated from generator and the like operated by the engine. Further, when orientation control to tilt the fuselage is performed, the arithmetic control device increases the output distribution ratio of the sub rotor to above the output distribution ratio of the sub rotor when hovering is performed.

A device to control movement of fluid that is emitted from an aircraft engine that is mounted to a wing of an aircraft. The device includes a support member positioned on an exterior of the aircraft and having an elongated shape with a first end connected to the wing and a second end connected to the fuselage. The support member has a first sectional size. A deflector shield is mounted to the support member and positioned on the exterior of the aircraft. The deflector shield has a larger sectional size than the support member. The deflector shield has an outer edge that extends around the support member and is positioned radially outward from the support member.

The utility model belongs to the technical field of agricultural unmanned aerial vehicles, and particularly relates to a bionic agricultural pesticide spraying aircraft. Comprising a fuselage and n supporting legs evenly distributed around the fuselage, n is an even number larger than or equal to 4, and each supporting leg is provided with a set of propellers driven by a motor; a plurality of independent pesticide bins are arranged in the machine body, an outlet of each pesticide bin is connected with a mixing box in the machine body through a water path, a metering pump is connected into the water path, a stirring device is arranged in the mixing box, a plurality of nozzles are evenly distributed on the periphery of the machine body, an outlet pipeline of the mixing box is divided into branches with the same number as the nozzles, and the branches are connected with the nozzles in a one-to-one mode. A booster pump is mounted on the branch; depth cameras are distributed outside the fuselage and used for acquiring environment images, and the aircraft controls a flight path according to the environment images; the unmanned aerial vehicle adopts a partitioned pesticide bin and octopus bionic eight-rotor design, and has high pesticide mixing capacity and stable flight control performance.

An aerial and preferably marine vehicle intended to operate in its principal mode near the surface of water or land employing the Wing-in-Ground Effect (WIG) and capable to take-off and land vertically (VTOL) by means of thrust vectoring, which vehicle has a wing arranged at the lowermost part of the fuselage, propulsion units comprising four rotatable pylons extending transversely in pairs on both sides of the upper part of the fuselage, four elongated nacelles mounted on the outer tips of said pylons, which nacelles contain electric motors (E) and provided with propellers at their extremities, so that the rotation of the pylons results in turning the nacelles and thrust of propellers from substantially vertical, ensuring take-off and landing, to substantially horizontal providing a flight mode, retractable hydroskis for emergency landing on water, while said propulsion units and said wing are spaced apart vertically and horizontally and do not overlap.

The invention discloses a guide wall for airplane ground test run, which comprises a U-shaped barrier part enclosing an airplane, the barrier part comprises a side guide wall corresponding to the side of the airplane and a rear guide wall corresponding to the tail of the airplane, the side guide wall comprises a windward side and a leeward side, and the leeward side is connected with a fixing frame. The fixing frame is connected with a ground anchor bolt to support the side flow guide wall, and the rear flow guide wall is fixedly connected with ground concrete; the length of the side flow guide wall exceeds the position of the nose during the test run of the airplane, and an air inlet channel is arranged at the side flow guide wall corresponding to the side wing during the test run of the airplane, penetrates through the side flow guide wall and supplements airflow to the engine close to the side wing of the air inlet channel; by arranging the air inlet channel, air flow is introduced from the side face of the aircraft directly facing the engines, the problem that the test is affected by insufficient air suction of the double engines due to the fact that the side face flow guide wall is far longer than the fuselage is solved, the internal and external pressure difference of the flow guide wall is reduced, and test run of the aircraft is facilitated.

The electric hydrofoil watercraft according to the invention provides detachable and hermetic electrical connection via contact pins for cables providing power to underwater propulsion means between above-water platform and one side of the mast and between the fuselage of the hydrofoil and the other side of the mast.

The invention discloses welding equipment for furnace end production based on plasma, and relates to the technical field of plasma welding, the welding equipment comprises a machine body, a workbench and a welding mechanism, the machine body is provided with a horizontal module, the horizontal module is provided with a lifting module, and the lifting module is connected with the workbench; compared with existing welding equipment for furnace end production, the sealing mechanism is arranged, the sealing mechanism is composed of the sealing cover, the movable plate and other components, on one hand, waste gas is prevented from flowing into the external environment, and on the other hand, interference of external factors to the welding process is reduced; the distance between the spherical joint and the axis of the sealing cover can be adjusted at any time, so that the sealing mechanism can be normally used when the plasma welding head is used for welding furnace end main bodies and furnace end lining covers with different sizes; through cooperation of the clamping assembly and the supporting assembly, furnace end bodies of different sizes can be horizontally fixed.

Truss-braced wing aircraft engine mounting and associated systems are disclosed. An example aircraft includes a fuselage including a central structural section, a wing extending from the fuselage, a truss extending from the central structural section and coupled to the wing, a pylon coupled to the central structural section, and an engine coupled to the pylon, wherein the pylon is positioned at an angle substantially 45 degrees from a horizontal plane and a vertical plane.

The invention relates to a heat dissipation air duct of a liquid cooling radiator of a piston engine, which not only meets the low resistance requirement of the aerodynamic configuration of an aircraft, but also meets the heat dissipation power requirement of the engine. Comprising an external fairing and an internal heat dissipation air channel, the external fairing is matched with the appearance of a machine body and completely wraps the internal heat dissipation air channel, the internal heat dissipation air channel is divided into a front cold air inlet area, a middle radiator area and a rear hot air flow guide area, and the front cold air inlet area is connected with the external fairing; a radiator is fixed in the middle radiator area, the rear hot air flow guide area and the outer fairing are of an integrated structure, an air guiding opening is formed in the front portion of the outer fairing, an engine air inlet is formed in the left side of the middle of the outer fairing, and an engine exhaust opening is formed in the right side of the middle of the outer The heat dissipation air channel is provided with the independent internal heat dissipation air channel and the external fairing, so that the heat dissipation efficiency can be ensured, and the external pneumatic appearance can be ensured to be smooth.

A connecting rod coupling device for attaching a component to an aircraft fuselage and / or stiffening the fuselage has a first coupler, and a second coupler couplable to the first coupler. The first coupler has an elongate body with a first channel on a lateral surface along a first longitudinal axis. The second coupler has a hollow-cylindrical portion, which, on an inner face along a second longitudinal axis, has a second channel complementing the first channel. The hollow-cylindrical portion has a radial cutout through which the elongate body is radially insertable into the second channel from outside the hollow-cylindrical portion. The second coupler has a closure body, which closes the radial cutout, and can be positioned removably in the cutout to complete the second channel on a radially internal face. The second coupler also has an element, pushable onto the hollow-cylindrical portion to secure the closure body on the hollow-cylindrical portion.

A vertical take-off and landing aircraft includes a fuselage, at least one propulsion system, at least four lift propellers and at least two fixed wing planes. The fixed wing planes which are located behind the most forward lift propellers are located above the lift propellers. The lift propellers are distributed on either side of at least one of the fixed wing planes and on either side of the fuselage such that the lift propellers are longitudinally separated by at least the magnitude of the chord of the fixed wing plane located therebetween, and are laterally separated by at least the width of the fuselage located therebetween. At least one of the fixed wing planes has a variable span and the aircraft includes a control system for varying this span in flight.

The invention belongs to the technical field of aircraft design, and discloses an amphibious aircraft water surface sliding speed reduction, turning and resistance reduction system and method.The system comprises two water baffles, and the two water baffles are arranged on the two sides of a hull structure below an aircraft waterline respectively and located between an aircraft belly fault step and a tail fault step; when the opening angle is small, the two water baffles form an air cavity at the rear portion through the ventilation effect to form the drag reduction effect, when the opening angle is large, the two water baffles reduce the exciting force caused by vortex falling, and the two water baffles are embedded in a groove of the rear fuselage when being forbidden to conform to the overall shape of the aircraft. The water baffles are innovatively arranged on the two sides of the hull structure of the seaplane, resistance or turning torque or a resistance reduction air cavity can be generated by changing the hydrodynamic shape of the seaplane when the seaplane slides on water, and the sliding process of the seaplane is controlled.

The invention relates to the technical field of inspection unmanned aerial vehicles, in particular to intelligent inspection unmanned aerial vehicle equipment. The unmanned aerial vehicle comprises a vehicle body, four propellers are fixedly connected to the top of the vehicle body, a supporting table is fixedly connected to an inner cavity of the vehicle body, a motor is fixedly connected to an inner cavity of the supporting table, the output end of the motor is rotationally connected with lighting equipment, and a rotating supporting assembly is arranged on the surface of the output end of the motor; the rotary supporting assembly is located at the lower end of the lighting equipment and used for supporting the lighting equipment to rotate. When the motor drives the lighting equipment to rotate, the adjusting assembly and the condensing lens assembly can be synchronously driven to rotate, at the moment, when light rays emitted by the lighting equipment pass through the condensing lens assembly, the light rays are converged into more concentrated and stronger light beams, and therefore rails, sleepers and surrounding facilities are clearly illuminated; therefore, the high-definition camera in the machine main body can rapidly record, and meanwhile, the motor drives the lighting equipment, the adjusting assembly and the condensing lens assembly to synchronously rotate.

The utility model discloses a control surface control mechanism of a V-tail unmanned aerial vehicle, which comprises a pair of control surface main bodies which are arranged in a V shape, and the included angle between the two control surface main bodies is 90 degrees; the main shaft is vertically arranged on the end faces of the ends, close to each other, of the control surface main bodies; and the control assembly is used for controlling the pair of main shafts to rotate synchronously. The utility model has the following advantages and effects: after being assembled, the control mechanism is completely hidden in the fuselage of the aircraft, so that the flight resistance is not additionally increased; differential motion and homodromous motion of the two control surface main bodies are respectively driven by the same motor, so that the deflection consistency of the control surface main bodies on the two sides can be ensured.

The wide-speed-range tailless variable-structure aircraft comprises an aircraft body, the aircraft body comprises an aircraft body-fixed wing fusion body and variable-structure wing rudders, the variable-structure wing rudders are symmetrically arranged on the two sides of the aircraft body-fixed wing fusion body, and a wing body fusion body layout is integrally formed; the fuselage-fixed wing fusion body is connected with the variable-structure wing rudder through a driving mechanism, and the variable-structure wing rudder can deflect in the axial direction of the fuselage; the tail of the fuselage-fixed wing fusion body is provided with a trailing edge rudder, the trailing edge rudder of the fuselage-fixed wing fusion body achieves pitching channel control through same-direction deflection, and under the condition that the channel coupling coefficient is smaller than 1.5, rolling channel control is achieved through differential deflection. The problem that the yaw channel operation stability characteristic is insufficient under the tailless layout condition is solved, and the wide-speed-range operation performance of the aircraft is effectively improved; compared with other variable-structure aircrafts in which additional variables are introduced, the combination of the variable-structure wing rudder and the trailing edge rudder is simple and efficient, and the burden on a control system is small.

This invention provides a combined adjustable sub-beam structure, including a main sling, a main beam assembly, a sub-beam assembly, and a fuselage sling. The main sling is fixed above both ends of the main beam assembly, and the sub-beam assembly is suspended below both ends of the main beam assembly via auxiliary slings. The fuselage sling is suspended below the sub-beam assembly. This combined adjustable sub-beam structure has the following advantages: during aircraft emergency rescue, the longitudinal length of the required lifting equipment can be adjusted according to the aircraft type. The adjustment can be achieved by increasing or decreasing the number of sub-beams and adjusting the number and position of the sub-beam positioning holes, enabling the rescue of various aircraft types.

The invention relates to the technical field of unmanned aerial vehicles, in particular to a water-land-air triphibian unmanned aerial vehicle which comprises a water-land-air unmanned aerial vehicle body and further comprises a positioning assembly, unmanned aerial vehicle blades are arranged at the top of the water-land-air unmanned aerial vehicle body, an underwater propeller is arranged on the rear side of the bottom of the water-land-air unmanned aerial vehicle body, and propeller blades are arranged on the back face of the underwater propeller. A working box is fixedly connected to the middle of the bottom of the water-land-air unmanned aerial vehicle body, the positioning assembly comprises first supporting springs, the first supporting springs are fixedly connected to the left side and the right side of the bottom in the working box, and a lifting shell is fixedly connected to the top ends of the first supporting springs. When the body of the water-land-air unmanned aerial vehicle makes contact with the water surface, the elastic arc-shaped plates make contact with the water surface and expand outwards, the contact area between the elastic arc-shaped plates and the water surface is increased, the weight of the body is dispersed, the local pressure is remarkably reduced, the unmanned aerial vehicle is prevented from sinking, the expanded elastic connecting plates form a structure similar to a hydrofoil, transverse stability is provided, and the rollover risk caused by waves is effectively resisted.

The utility model relates to the related technical field of agriculture and forestry machinery, in particular to a pepper tip artificial harvesting machine which comprises a machine body, and a collecting and falling clamping mechanism is arranged on the surface of one side of the machine body. According to the artificial pepper tip harvesting machine, through the arrangement of the collecting and falling clamping mechanism, when pepper tips need to be collected, the collecting and falling clamping mechanism is fixed to the machine body through a push rod, a first rotating arm and a second rotating arm rotate and are fixed at a certain angle, during operation, rotating arm clamps and clamping blocks are matched with each other, and a collecting bag is supported in front of the machine body; when part of pepper tips jump out of the machine due to various reasons in the collecting process, the jumped pepper tips fall into the collecting bag, resource waste is reduced, rotation of the first rotating arm around the fixing ring and rotation of the second rotating arm around the first rotating arm are achieved through the rotating shaft, the first rotating arm, the second rotating arm and the rotating shaft are made of austenitic stainless steel materials, and the cost is reduced. The strength and corrosion resistance of the mechanism are guaranteed, and stable work in a complex harvesting environment is guaranteed.

The utility model relates to the technical field of unmanned aerial vehicle surveying and mapping, in particular to an unmanned aerial vehicle surveying and mapping device which comprises an unmanned aerial vehicle and is used for surveying and mapping a rural terrain. Clamping heads are arranged on the outer walls of the two ends of the arms; the protection assembly comprises an installation frame installed at the outer end of the vehicle arm in a sleeving mode, an arc-shaped frame is arranged on the outer side of the installation frame, a support is fixed between the bottom of the arc-shaped frame and the outer wall of the installation frame, and clamping grooves are formed in the two ends of the installation frame and matched with the clamping heads; in the use process of the unmanned aerial vehicle, the propellers can be protected through the protection assemblies, and the propellers are prevented from being accidentally touched in the use process; moreover, the protection assemblies can be installed on the vehicle arm by matching the clamping grooves with the clamping heads, so that the protection assemblies can be quickly disassembled and assembled, and when a certain protection assembly is damaged, only the damaged protection assembly needs to be replaced, so that the maintenance cost is reduced.

The invention discloses a multi-mode self-rotating tailstock type vertical take-off and landing aircraft. Multi-mode motion comprises a multi-axis mode, a self-rotating mode and a fixed wing mode. The unmanned aerial vehicle comprises a fuselage, a variable collective pitch structure and four symmetrical wings on the two sides; the wing type of each wing is a symmetrical wing type, the tail end of each wing is a full-moving wing tip, and each wing is provided with a driver; the driver is a propeller driven by a motor; each wing, the driver and each full-motion wingtip can rotate by + / -90 degrees around a rotating shaft in the spanwise direction of the wing, and switching among multiple modes and attitude control are achieved. The aircraft disclosed by the invention has more flexible maneuvering capability, has vertical take-off and landing performance of a multi-axis mode, efficient hovering performance of a spinning mode and high-speed cruising performance of a fixed wing mode, can meet different flight requirements, and has better environment adaptability.

The invention provides a posture adjusting method, system and equipment for a cold regenerator and a medium, and belongs to the technical field of cold regenerator control, the method comprises the following steps: descending four supporting legs of the cold regenerator before construction, enabling the whole machine to be horizontal, enabling a milling hub to be flush with the ground, and recording the heights of the four supporting legs as zero point heights; lowering the milling hub to a target cutting depth, and collecting initial values of a left-right inclination angle, a front-back inclination angle, four support leg oil cylinder pressures and an engine load rate corresponding to the zero point height; in the construction process, the real-time values of the left-right inclination angle, the front-back inclination angle, the pressure of the four supporting leg oil cylinders and the engine load rate are collected in real time; the change of the real-time value relative to the initial value is compared, the state of the corresponding supporting leg is judged to be pressed to the obstacle or the pit, the corresponding supporting leg ascends or descends till the collected real-time value recovers to the initial value, and automatic adjustment of the posture of the cold regenerator is completed. The machine body can be automatically kept horizontal, it is guaranteed that the cutting depth is stable, and construction precision and efficiency are improved.

An air injection assembly for an aircraft is provided. The aircraft includes a fuselage extending longitudinally between a front end and a rear end, and a boundary layer intake fan mounted to the fuselage at the rear end of the fuselage. The air injection assembly includes a plurality of injection ports defined on a surface of the fuselage at locations upstream of the boundary layer intake fan. Supplemental airflow is provided to the injection ports through a fluid passageway, and the supplemental airflow is injected into the injection ports to displace at least a portion of the relatively high-velocity boundary layer airflow. In this manner, the airflow entering the boundary layer intake fan is more uniform, has less vortex distortion, and has a lower average velocity.