733 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 that defines a plurality of fan wakes; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a pylon fairing dihedral, wherein the pylon fairing dihedral is in a direction opposite the incoming fan flow swirl and associated sheared profiles of fan wakes upon arrival at the pylon leading edge.

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 aircraft includes a fuselage, a front wing and a rear wing provided to extend laterally from the fuselage for generating lift during cruise, a boom extending in a front-back direction supported by these wings to be spaced apart from the fuselage, a VTOL rotor supported on the boom and having one or more blades for generating thrust in a vertical direction during take-off and landing, a cooling system for cooling the VTOL rotor by using a radiator arranged within the boom, and an airflow guide structure provided in a part of the boom for guiding airflow generated by rotation of the blades to the radiator, and having an inlet provided on a side that faces toward a rotational direction of the blades relative to a rotational axis of the VTOL rotor, of a surface of the boom positioned below a plane of rotation of the blades.

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 arm-equipped unmanned aerial vehicle and a control method therefor, the arm-equipped unmanned aerial vehicle comprising a tilting quadrotor unmanned aerial vehicle, a mechanical arm, and a control module (7). The tilting quadrotor unmanned aerial vehicle comprises a fuselage, tilting driving devices and tilting arms, the mechanical arm being mounted below the fuselage, the control module (7) being mounted above the fuselage, and the tilting driving devices being respectively arranged on two sides of the fuselage. Each tilting driving device is in drive connection to a tilting arm, the tilting arms extending from the head of the fuselage to the rear of the fuselage, and the tilting driving devices being used for driving the tilting arms to rotate in a vertical plane. The two ends of each tilting arm are each provided with a rotor mechanism that can be driven to rotate. The mechanical arm, the tilting driving devices and the rotor mechanisms are all connected and driven by the control module (7).

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.

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 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 invention discloses alloy casting internal defect and material uniformity detection equipment, and relates to the technical field of detection.The detection equipment comprises a machine body, a detection chamber is arranged at the side end of the interior of the machine body, and a cabin door is arranged at the side end of the detection chamber. According to the ultrasonic coupling agent removing device for the alloy casting, the ultrasonic coupling agent in a detection completion area can be removed while defect detection is conducted on the alloy casting, so that it is ensured that after detection of the alloy casting is completed, a worker can directly take away the alloy casting, and then the detection efficiency is improved; the cleaning group is used for cleaning the ultrasonic coupling agent intercepted on the scraping plate and the residual coupling agent at the outlet end of the coating head, so that the situation that the subsequent detection work of the alloy casting is influenced by the solidification phenomenon of the ultrasonic coupling agent residual at the lower end of the coating mechanism due to the too long interval time of the next detection work is avoided.

The invention discloses an aircraft landing guiding method, a display system and an aircraft, and relates to the technical field of flight control. The aircraft landing guiding method comprises the steps that under the condition that it is detected that an aircraft meets tilting guiding conditions, a flight boundary indication image of the aircraft is generated, and the flight boundary indication image is used for reflecting a tilting transition flight corridor when the aircraft safely flies to a reference hovering point from a current air position; the aircraft comprises an aircraft body and a tilt rotor assembly, the tilt rotor assembly is arranged on the aircraft body and can rotate between a cruise position and a vertical take-off and landing position, and the reference hovering point is located above a landing destination; and displaying the flight boundary indication image on a display system of the aircraft. According to the invention, a pilot can control the aircraft in real time according to the flight boundary indication image, and the aircraft can be safely transited from a cruise flight stage to a vertical landing stage.

A solar powered plane configured to operate in the stratosphere includes a hinged vertical stabiliser that that pivots about a hinge; the stabiliser extends both above the fuselage and also below the fuselage, and the base of the vertical stabiliser includes a skid. The hinged vertical stabiliser is configured such that when the skid contacts the ground on landing, the top of the vertical stabiliser pivots forwards around the hinge point, minimising damage to the aircraft on landing. the skid includes a lightweight, replaceable sacrificial layer.

The invention discloses an aircraft landing guiding method, a display system and an aircraft, and relates to the technical field of flight control. The aircraft landing guiding method comprises the steps that under the condition that it is detected that an aircraft meets tilting guiding conditions, a flight boundary indication image of the aircraft is generated, and the flight boundary indication image is used for reflecting a tilting transition flight corridor when the aircraft safely flies to a reference hovering point from a current air position; the aircraft comprises an aircraft body and a tilt rotor assembly, the tilt rotor assembly is arranged on the aircraft body and can rotate between a cruise position and a vertical take-off and landing position, and the reference hovering point is located above a landing destination; and displaying the flight boundary indication image on a display system of the aircraft. According to the invention, a pilot can control the aircraft in real time according to the flight boundary indication image, and the aircraft can be safely transited from a cruise flight stage to a vertical landing stage.

The present application discloses an aircraft. The aircraft comprises a first wing and a second wing, a fuselage to which the first wing and the second wing are mounted, a first engine operatively mounted to the first wing, and a second engine operatively mounted to the second wing. The aircraft is configured to vertically take-off and land. The first engine and the second engine are used for both (i) vertical take-off and landing, and (ii) horizontal flight.

Various embodiments of a novel monocoque aerostructure quadcopter implemented as a vertical take-off and landing vehicle are described. In one example, a vertical take-off and landing vehicle includes a fuselage having a leading end positioned in a first horizontal plane and a trailing end positioned in a second horizontal plane that is vertically below the first horizontal plane. The vertical take-off and landing vehicle further includes a first arm assembly extending from the leading end of the fuselage in the first horizontal plane. The vertical take-off and landing vehicle further includes a second arm assembly extending from the trailing end of the fuselage in the second horizontal plane. The vertical take-off and landing vehicle further includes a first rotor assembly coupled to the first arm assembly and a second rotor assembly coupled to the second arm assembly.

A rotorcraft with at least one main rotor and a fuselage, comprising: a tail boom connected to the fuselage, the tail boom extending from the fuselage toward a duct-type portion; a shroud provided at the duct-type portion and forming a transverse duct; at least one ducted tail rotor rotatably arranged in the transverse duct, wherein the at least one ducted tail rotor comprises a plurality of rotor blades mounted to a rotatable rotor hub; and a stator with a gearbox fairing mounted to the shroud for supporting the rotatable rotor hub in the transverse duct, wherein the stator comprises at least one rotatable stator blade connecting the gearbox fairing to the shroud.

The present application discloses an aircraft configured for vertical take-off and landing and horizontal flight. The aircraft includes (i) a first nacelle fuel tank configured to hold a first fuel supply for a first engine and to selectively provide fuel to the first engine during both (a) a vertical take-off and landing, and (b) horizontal flight; (ii) a fuselage fuel tank, and (iii) a control system configured to redistribute fuel between the first nacelle fuel tank and the fuselage fuel tank.

The utility model relates to the technical field of ring rolling machines, in particular to a flange ring rolling machine which comprises a machine body, an axial ring rolling mechanism is arranged at one end of the machine body, a radial ring rolling mechanism is arranged at the other end of the machine body, and a driving device is erected on the machine body and located between the axial ring rolling mechanism and the radial ring rolling mechanism. The outer wall of the roller shaft is sleeved with a detachable roller sleeve, a supporting device is erected at the position, close to the driving device, in the machine body and comprises a supporting plate, a supporting block, a moving mechanism and a jacking mechanism, the supporting plate is fixedly connected with the moving end of the jacking mechanism, and the supporting block is fixedly connected with the fixed end of the jacking mechanism. The moving mechanism comprises a lead screw and a driving motor erected on the support, a driving shaft of the driving motor is fixedly connected with the lead screw, and the lead screw is sleeved with the supporting block, the problem that the use cost of the main roller is high is solved, and the effect of reducing the use cost of the main roller can be achieved through the detachable roller sleeve.

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.

A tank assembly for a helicopter is provided. The tank assembly includes a retractable tank for storing liquid or other substances. The retractable tank includes an upper frame structure. The tank assembly further includes an attachment mechanism attached to the upper frame structure and configured to engage a main rotor transmission of the helicopter to suspend therefrom. A helicopter including a fuselage, a main rotor transmission, and a tank assembly is also provided.

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.

The utility model provides a portable four-rotor unmanned aerial vehicle which comprises a vehicle body, four vehicle arms and four rotor assemblies, and one end of each vehicle arm is provided with one rotor assembly; a containing space is formed in the fuselage body, a first resistance reduction structure is formed at the front end of the fuselage body, and second resistance reduction structures are formed on the two sides of the fuselage body; a supporting structure is arranged at the bottom of the vehicle body, and the other end of each vehicle arm is connected with the supporting structure in a locking mode through a first locking piece. The four-rotor unmanned aerial vehicle has the advantages that wind resistance in the flying process can be effectively reduced, and therefore the flying speed of the four-rotor unmanned aerial vehicle can be increased; according to the four-rotor unmanned aerial vehicle, all the vehicle arms can be folded by simply disassembling the first locking pieces, and therefore the four-rotor unmanned aerial vehicle can be conveniently stored and transported.

A rotorcraft with at least one non-retractable wheel-type landing gear and a fuselage comprising a lower shell, an inner floor, and at least one lower fuselage compartment arranged between the inner floor and the lower shell, wherein the at least one non-retractable wheel-type landing gear is rigidly attached in the at least one lower fuselage compartment and comprises: at least one wheel; a shock absorber connected to the at least one wheel and comprising a shock absorber tube and a shock absorber rod telescopically mounted to the shock absorber tube; at least two mounting arms extending laterally from the shock absorber tube; and a mounting pin extending from the shock absorber tube toward a floor fitting provided at the inner floor, wherein the mounting pin is connected to the floor fitting.

The invention discloses a tilt rotor eVTOL aircraft, comprising: a fuselage provided with a gearbox connected with an intermediate shaft; the rotor system is in transmission connection with the middle shaft and is used for providing lift force for the fuselage; the rotor wing system comprises a main motor, a speed change assembly, a rotor wing body and a rotor wing shell, the main motor and the speed change assembly are installed in the rotor wing shell, the rotor wing body is arranged above the rotor wing shell, the main motor is connected with the rotor wing body through the speed change assembly, and the main motor is used for driving the rotor wing body to rotate; the tilting motor is mounted on the machine body, and a driving gear is mounted at the output end of the tilting motor; the driven gear is arranged on the middle shaft in a sleeving manner and is connected with the rotor wing shell; the driven gear is meshed with the driving gear, the driving gear drives the driven gear to rotate, the driven gear rotates to drive the rotor wing shell to rotate around the middle shaft, and then tilting of the rotor wing system is achieved. The tilt rotor eVTOL aircraft is compact in structure and light in weight, and the operation cost can be effectively reduced.

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.

An electrically powered multirotor aircraft that is adapted for vertical take-off and landing, comprising a fuselage, at least one aircraft lifting surface that is connected to the fuselage, at least one propeller that is connected to the at least one aircraft lifting surface, a sensor unit, a flutter reduction unit, and a settings adjustment device. The sensor unit is configured to generate sensor data that is indicative of flutter of the at least one aircraft lifting surface. The flutter reduction unit is configured to receive the sensor data to generate flutter reduction signals. The settings adjustment device is configured to receive the flutter reduction signals and to adjust current settings of the at least one propeller based on the flutter reduction signals to reduce flutter of the at least one aircraft lifting surface.

The invention discloses a multi-rotor aircraft with the thrust center and the gravity center coincident in all directions, and relates to the technical field of aircrafts, the aircraft comprises a rotor system and a fuselage system, the rotor system and the fuselage system are connected through a cross shaft, the center point of the cross shaft coincides with the center point of multi-rotor thrust, and the center point of the multi-rotor thrust coincides with the center point of the multi-rotor thrust. And the thrust center and the gravity center of the aircraft always coincide in the flight process. The rotor wing system comprises a rotor wing, a rotor wing shaft, a rotor wing shaft driving device, a support arm and a gravity center position adjusting device; the fuselage system comprises a cross shaft, a fuselage suspender, a fuselage, an inclination angle control telescopic rod and a landing bracket. The aircraft achieves multi-rotor vector propulsion through rotor inclination angle adjustment, has the advantages of being high in wind resistance, stable in flight attitude, rapid and sensitive in adjustment and the like, is suitable for the fields of multi-rotor unmanned aerial vehicles, vertical lifting fire rescue devices, agricultural plant protection aircrafts and the like, and can remarkably improve the flight efficiency and stability of the aircraft.

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.

Systems and methods for mechanically rotating an aircraft about its center-of-gravity (CG) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive angle of attack for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.