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Wing tilt actuation system for electric vertical take-off and landing (VTOL) aircraft

A technology of aircraft and electric motors, applied in vertical take-off and landing aircraft, electric vehicles, wing adjustment, etc., can solve problems such as extra weight

Active Publication Date: 2020-06-02
AMSL INNOVATIONS PTY LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

A disadvantage of this aircraft concept is that each motor is actuated independently, requiring separate actuators for each motor
As mentioned above, this requires significant additional weight for the actuation motor system

Method used

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  • Wing tilt actuation system for electric vertical take-off and landing (VTOL) aircraft
  • Wing tilt actuation system for electric vertical take-off and landing (VTOL) aircraft
  • Wing tilt actuation system for electric vertical take-off and landing (VTOL) aircraft

Examples

Experimental program
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Embodiment Construction

[0073] A vertical take-off and landing (VTOL) aircraft 10 is disclosed. As depicted in the figures, in the preferred embodiment there are two pairs of wings. That is, the front wings 20 , 22 and the rear wings 30 , 32 . Each front wing 20 , 22 is attached to a laterally opposing region of the fuselage 24 . Similarly, each rear wing 30 , 32 is attached to a laterally opposite region of the fuselage 24 . In the embodiments shown in the figures, the aircraft 10 is depicted as a single or two-seat aircraft 10 . However, larger multi-person embodiments are also conceivable. Aircraft 10 may be controlled from within by a pilot, or alternatively, it may be remotely controlled.

[0074] In the embodiment shown in the figures, the distal portions of the front wings 20, 22 and rear wings 30, 32 are connected to a connecting member or web 42 so that the two pairs of wings 20, 22, 30, 32 define a box. shaped wing or closed wing structure.

[0075] In another embodiment (not shown), ...

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PUM

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Abstract

A vertical take-off and landing (VTOL) aircraft (10) comprises a fuselage (24) first and second forward wings (20, 22) and first and second rearward wings (30, 32), each wing having a fixed leading edge (25, 35) and a trailing control surface (50) which is pivotal about a generally horizontal axis. Electric rotors (60) are mounted to the wings (20, 22, 30, 32), the electric rotors (60) being pivotal with the trailing control surface (50) between a first position in which each rotor (60) has a generally vertical axis of rotation, and a second position in which each rotor (60) has a generally horizontal axis of rotation; wherein at least one of the wings (20, 22, 30, 32) has a first and a second electric rotor (60) which are each mounted having non-parallel axes of rotation so that the thrust lines of the first and second electric rotors are different.

Description

technical field [0001] The present disclosure relates to a wing pitch actuation system for an electric vertical takeoff and landing (VTOL) aircraft. In particular, the present invention relates to wing pitch actuation systems and mechanisms for electric VTOL aircraft with passenger and / or military applications. Background technique [0002] VTOL aircraft can take off and land vertically or at an angle close to vertical. Aircraft of this type include helicopters and certain fixed wing aircraft, often used in military applications. Advantageously, VTOL aircraft allow takeoff and landing in confined spaces, which eliminates the need for large runways and allows takeoff and landing in smaller spaces and on aprons such as ship decks and buildings and other structures. [0003] A helicopter is an aircraft in which both lift and thrust are provided by rotors. Some issues associated with helicopters can be problematic in certain applications, such as high levels of noise output. ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C29/00B64C27/52B64C9/16B64D27/40
CPCB64C29/0033B64C27/52B64D27/24B64C2027/8227B64C39/068B64D27/40B64C9/18B64C15/00Y02T50/40Y02T10/72Y02T50/60B64D27/402B64D27/34B64D27/31B64D31/16B64C9/00B64C13/00B64C27/28B64C29/00B64C27/80B64C3/38B60L2200/10B64C1/1407B64C27/82B64C39/024B64C23/069B64C13/02B64C9/16Y02T50/10B60L15/20
Inventor A·D·摩尔
Owner AMSL INNOVATIONS PTY LTD
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