24results about "Power plant construction" patented technology

A novel multi-rotor aircraft motor mounting arm assembly used to improve stiffness, durability, strength, and thrust efficiency of the motor mount arm while providing harmonic isolation of motor and prop vibrations.

An aircraft assembly is disclosed having a wing and an engine mounting pylon. An aft end of the engine mounting pylon is connected to the wing by a spigot and at least one fastener. The aircraft assembly is configured such that, during operation of the aircraft assembly on an aircraft, the spigot transfers only lateral load between the engine mounting pylon and the wing and the at least one fastener transfers only vertical load between the engine mounting pylon and the wing.

An assembly including a wing with a pressure-side panel and a suction-side panel through which two bores pass, an engine pylon including a blade with three bores and two fastening lugs, each of which has a sixth bore, two first shackles fastened between the blade and the suction-side panel, two second shackles fastened between the blade and the suction-side panel and two fittings, which are fastened beneath the pressure-side panel and each have a female clevis for housing a fastening lug therein.

An engine support assembly for operatively connecting an engine to an aircraft, the aircraft, the aircraft having a support frame surrounded by opposing first and second skins. The engine support assembly broadly comprises first and second support structures. The first support structure is secured to the support frame and extends away from the first skin. The second support structure is releasably connected to the first support structure and releasably connected to the engine.

The invention discloses a battery tank structure of an unmanned aerial vehicle (UAV) and relates to the technologies of battery tank structures of UAVs. The battery tank structure can solve the problem of large space occupation of a battery tank of an existing UAV. A main battery tank body is of a rectangular structure, is placed in the middle of a UAV body, the side wall of the tank body is provided with a plurality of positioning holes, and a battery locking mechanism is fixed by the positioning holes and fixedly connected to a battery after the battery is inserted into the battery tank; byfixing the battery locking mechanism to the positioning holes in different positions, the position of the battery in the whole UAV body is adjusted, and correspondingly the position of the gravity center of the UAV body is adjusted. The structure is mainly used for UAVs.

An aircraft wing includes a center wing section having a continuous structure that spans beyond a first side of an aircraft fuselage and beyond a second side of the aircraft fuselage. The aircraft wing also includes a first outboard wing section attached to a first end of the center wing section by a first truss system that is accessible via a first closeout panel. The first end of the center wing section in on the first side of the aircraft fuselage. The aircraft wing also includes a second outboard wing section attached to a second end of the center wing section by a second truss system that is accessible via a second closeout panel. The second end of the center wing section is on the second side of the aircraft fuselage.

The present disclosure relates to a drive device (500) for driving a propeller (402) of an aircraft (100). The drive device includes a first electric drive motor (520A), a second electric drive motor (520B), and a supporting frame (510) which includes a first mounting section (512) to which the first electric drive motor (520A) is mounted, a second mounting section (513) to which the second electric drive motor (520B) is mounted, and at least one strut (516) which interconnects the first mounting section (512) and the second mounting section (513) such that the supporting frame (510) provides a cage-like structure. The first electric drive motor (520A) and the second electric drive motor (520B) are operatively couplable to the propeller (402). The present disclosure further relates to a supporting frame (510), an aircraft (100), and a method for installing a drive device (500) into an aircraft (100).

The present disclosure relates to a battery assembly (300) configured to be mounted within at least one wing (200) of at least one aircraft (100). The battery assembly (300) includes at least one battery module (302) which includes at least one battery cell (460). The battery assembly (300) further includes at least one mounting structure (400) configured to mount the battery module (302), along a mounting side (402) of the battery module (302), to at least one support structure (207) within the wing (200). The battery assembly (300) is free of a mounting structure for mounting the battery module (302) along a second side (403) of the battery module (302), the second side (403) being substantially opposite from the mounting side (402). The present disclosure further relates to wing (200) of an aircraft (100), an aircraft (100), and method for installing a battery assembly (300).

A low drag nacelle and pylon fairing for an aircraft includes a fairing configured to provide a low drag connection between a pylon and a nacelle. The fairing includes an aft-facing face formed between the nacelle and a trailing edge of the pylon with the aft-facing face being configured with a vent for exhausting air in the same direction as engine jet exhaust flow. The fairing includes aerodynamically formed curves providing a larger aft-facing face compared with traditional fairing arrangements. A substantial improvement in drag reduction is achieved by venting air into the space immediately beyond the aft-facing face.

Apparatus and methods for transonic truss-braced wing aircraft are disclosed herein. An example aircraft disclosed herein includes a fuselage and a wing supported by a truss. The truss includes a pylon coupled to and extending from the fuselage and a strut attached to the wing. An engine is coupled to the pylon.

In some embodiments, an electric aircraft may include a plurality of flight components including a plurality of control surfaces; a plurality of lift propulsors; at least a thrust propulsor; and a plurality of electric motors configured to power the plurality of propulsors; a flight controller, communicatively connected to a pilot input and flight components. In some embodiments, a flight controller may be configured to receive control datum from a pilot input; and generate an output datum as a function of the control datum.

To suppress noise of a cruise rotor.SOLUTION: A propulsion force generation device comprises a propeller section 30 which has a propeller 34 and a duct 38 covering a periphery of the propeller 34. The duct 38 is made up of a cylinder 50 arranged around the propeller 34, a hub 52 arranged inside the cylinder 50, and a plurality of duct stators 54 radially extended from the hub 52 to the cylinder 50. The hub 52 and each duct stator 54 are arranged posterior to the propeller 34.SELECTED DRAWING: Figure 2

To provide fairings to support engines relative to wings of an aircraft, and methods for reducing drag.SOLUTION: A wing comprises a fairing 130 covering a pylon to connect to an engine. The fairing defines a horizontal plane, a first plane perpendicular to a longitudinal axis, and a second plane perpendicular to the longitudinal axis and aft of the first plane. A reference line is defined as the longitudinal axis when projected onto the horizontal plane. The fairing includes a fairing body defining an aerodynamic surface. The aerodynamic surface has an outboard portion and an inboard portion. The inboard portion is configured such that the first plane intersects the horizontal plane and the aerodynamic surface of the inboard portion at a first intersection point. The first intersection point is laterally displaced from the reference line by a first distance. The second plane intersects the horizontal plane and the aerodynamic surface of the inboard portion at a second intersection point. The second intersection point is laterally displaced from the reference line by a second distance, which is greater than the first distance.SELECTED DRAWING: Figure 2

Obtaining high-speed horizontal flying drones and other aircraft [Solution] By providing a drone with wings for horizontal flight, an aircraft is obtained that can fly horizontally at high speed and carry goods over long distances.

The invention relates to a suspension assembly for a turbomachine (10), the assembly comprising: • - a beam (12) for the attachment thereof to an aircraft pylon (13), the beam (12) comprising a first portion (12a) and a second portion (12b) each carrying a half-housing (16a, 16b) jointly defining a ball joint housing (17); • - a ball joint nut (16) rotatably hingedly enaged in the ball joint housing (17); and • - a cylindrical portion (14) intended to be attached to a fixed portion (15) of the turbomachine (10) hinged to the ball joint housing (17) and mounted so as to be pivotable about its axis (X) in the ball joint nut (16), wherein the suspension assembly (11) further comprises a retaining ring (23) surrounding the two half-housings (16a, 16b) around the entire circumference thereof, the retaining ring (23) being provided to perform a safety function in the event of the failure of at least one element of the suspension assembly (11).

A joint for aircraft electrical pack or battery pack for attaching the electrical pack to an aircraft component is disclosed. The electrical pack includes a surface having a dovetail dowel integrally formed thereon, and a dovetail rail is attached to the aircraft component. The electrical pack is mounted and assembled to the aircraft component by securing the dovetail dowel to the dovetail rail forming a dovetail joint. The aircraft component may be an engine pylon.

To provide a combined engine that can smoothly perform flow path switching, and an aircraft.SOLUTION: A combined engine, which is mounted on an aircraft, comprises: a first engine corresponding to a first speed range; a second engine corresponding to a second speed range faster than the first speed range; a flow path part having a first flow path which is an air flow path in the first engine, and a second flow path which is an air flow path in the second engine; and a switching part which can switch opening / closing of the first flow path in the flow path part. The switching part has: a rotation component which is rotatable between a first position at which the first flow path is opened and a second position at which the first flow path is closed; and a slide component which slides thereby rotating the rotation component between the first position and the second position.SELECTED DRAWING: Figure 3

To provide an aircraft capable of stabilizing by arranging internal combustion engines inside a shell in good balance.SOLUTION: An aircraft 10 includes a shell 12, wings (rear wings 16) arranged over the shell 12, a pylon 32 for connecting the wings to the shell 12, and multiple internal combustion engines 58 stored in the shell 12. The pylon 32 traverses the shell 12 and is fixed to an upper part and a lower part of the shell 12, and a first internal combustion engine (first engine 58 L) and a second internal combustion engine (second engine 58R) in the multiple internal combustion engines 58 are arranged symmetrically with the pylon 32 as the center, and fixed to the pylon 32.SELECTED DRAWING: Figure 3

A brushless DC motor is integrated with an aeropropulsive thrust generator that is hubless, not in tandem (co / counter) rotating propeller disks, and not having magnetic bearings.

To provide an aircraft that can perform high-speed horizontal flight and vertical takeoff and landing.SOLUTION: An aircraft includes a vertical ascent / descent and horizontal flight propeller and a horizontal flight wing. The aircraft can ascend and descend by rotating the horizontal flight wing vertically and fly horizontally at high speed by rotating the horizontal flight wing horizontally, furthermore can fly a long distance while loading an object thereon.SELECTED DRAWING: Figure 14

An enclosure for an aircraft powerplant includes an air inlet, an air outlet, and at least one sidewall forming the enclosure and fluidly connecting the air inlet and the air outlet. The enclosure further includes a cavity configured to house at least one component of the aircraft powerplant. The cavity is within the enclosure and formed by the at least one sidewall. The enclosure further includes a noise reduction chamber comprising a plurality of channels configured to permit air to pass through the noise reduction chamber.

In some embodiments, an electric aircraft may include a plurality of flight components including a plurality of control surfaces; a plurality of lift propulsors; at least a thrust propulsor; and a plurality of electric motors configured to power the plurality of propulsors; a flight controller, communicatively connected to a pilot input and flight components. In some embodiments, a flight controller may be configured to receive control datum from a pilot input; and generate an output datum as a function of the control datum.

To provide an aircraft of electrically-driven multiple rotors with an engine for electric power generation in which respective components are arranged in consideration of contacting with scattered engine debris in a case of rotor burst of the engine.SOLUTION: An aircraft 10 comprises: a gas turbine 44 which drives an electric generator 46; an electric motor 20 V5_1 which drives a rotor 18 V5; and an electric motor 20 V7_2 which drives a rotor 18 V7. The gas turbine 44 is arranged at a position overlapping with a rear wing 14b in a front-back direction of an airframe 12, and a high voltage harness 80 V5_1 transmitting electric power to the electric motor 20 V5_1 inside of the rear wing 14b is alienated from a high voltage harness 80 V7_2 transmitting electric power to the electric motor 20 V7_2 in the front-back direction of the airframe 12.SELECTED DRAWING: Figure 3