3results 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 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