Movable wing for weight and balance management
A wing and fuselage technology that is applied in the field of aircraft and can solve problems such as the impact of payload and fuel carrying capacity, and the net reduction in aircraft capability and efficiency.
Active Publication Date: 2018-10-23
INSITU INC
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- Summary
- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
Problems solved by technology
Despite balancing the vehicle, ballast negatively impacts payload and fuel carrying capacity when the vehicle reaches its maximum takeoff weight limit
an increase in aircraft weight that has no positive effect on fuel or payload capacity results in a net decrease in aircraft capability and efficiency
Method used
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Embodiment Construction
[0024] figure 1 An exemplary aerial vehicle 10 is shown in the form of an unmanned aerial vehicle (UAV) 10 , or drone, in which a movable airframe according to the present disclosure may be implemented. In an illustrative example, aircraft 10 may include fuselage 12 having nose 14 at the forward end and tail 16 at the rear end having engine housings to drive propellers 18 and generate 10 thrust. A longitudinal axis 20 passes through the fuselage 12 from nose 14 to tail 16 and a transverse axis 22 perpendicular to longitudinal axis 20 extends from wing tip to wing tip. The aircraft 10 also includes a wing assembly 24 formed from a central wing 26 having a left wing 28 and a right wing 30 extending outward therefrom in a transverse direction, and an empennage 36 extending rearwardly and having an empennage mounted therebetween. The left truss 32 and the right truss 34. Fuselage 12 may be mounted to wing assembly 24 in a manner that allows forward and aft movement of fuselage ...
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The invention relates to a movable wing for weight and balance management. The aircraft includes a fuselage having a longitudinal axis, a wing assembly, and a fuselage positioning mechanism operatively connecting the fuselage to the wing assembly. The fuselage positioning mechanism is operable to move the fuselage relative to the wing assembly in a longitudinal direction parallel to the longitudinal axis between a fuselage maximum forward position and a fuselage maximum aft position. When the aircraft for flight, a position of a center of gravity of the aircraft relative to a center of lift isdetermined. The fuselage can be moved relative to the wing assembly to bring the center of gravity within an allowable range of distances from the center of lift to balance the aircraft for flight. The fuselage positioning mechanism can be automated to allow adjustment of the fuselage position during the flight of the aircraft.
Description
technical field [0001] The present disclosure relates generally to aircraft, and more particularly to aircraft having movable wings for weight and balance management that compensate for payload weight and position by shifting the aircraft's center of gravity relative to the center of lift , without or reducing the need for ballast. Background technique [0002] The weight and balance of an aircraft are the most critical factors affecting its flight safety. An aircraft whose center of gravity (COG) is not within permissible limits relative to the aircraft's center of lift (COL) is inefficient and dangerous to fly. Responsibility for proper weight and balance control begins with the engineers and designers who design the aircraft, and extends to the aviation technicians who maintain the aircraft, the loadmaster responsible for loading payload and fuel on board the aircraft, and ultimately to the pilots who operate the aircraft. [0003] In determining the weight and balance ...
Claims
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IPC IPC(8): B64C1/30B64C17/02
CPCB64C17/02B64U30/16B64U40/20B64C3/38B64C2211/00B64C1/26B64U10/25B64U30/00B64U50/13B64C39/024
Inventor M·D·格拉布P·J·孔兹W·D·古德里奇
Owner INSITU INC