5results about "Power plant construction" patented technology

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.

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

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