aircraft

The VTOL aircraft design with propeller devices on fuselage/wings and a flight control system using a pitch trim control element addresses size/weight/visibility issues by eliminating the bow lift unit, enabling stable flight control and easy cabin access.

DE102024102444A1Pending Publication Date: 2025-07-31DR ING H C F PORSCHE AG
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Patent Information

Application Number
DE102024102444
Authority / Receiving Office
DE · DE
Patent Type
Applications
Current Assignee / Owner
Filing Date
2024-01-29
Publication Date
2025-07-31

AI Technical Summary

Technical Problem

Existing VTOL aircraft with a front lift unit are large, heavy, and obstruct visibility and ingress/egress to the passenger cabin, necessitating a design that reduces size, weight, and improves visibility while maintaining stable flight control.

Method used

Aircraft design with propeller devices on the fuselage and wings, a flight control system featuring a pitch trim control element and tailerons/rudder for stability, eliminating the need for a bow lift unit, and allowing propellers to pivot between vertical and horizontal orientations.

Benefits of technology

Reduces aircraft size and weight, enhances cabin visibility, and simplifies ingress/egress, while achieving stable horizontal flight control through the pitch trim control element and tailerons/rudder combination.

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Abstract

An aircraft having a fuselage (12), two wings (14, 16) arranged on two opposite sides of the fuselage (12), a plurality of propeller devices (22, 24, 26, 28, 30, 32, 34, 36) arranged on the fuselage (12) and / or on the wings (14, 16), and a flight control system (40), wherein the aircraft neutral point (N) is arranged in front of the aircraft center of gravity (S) in the horizontal forward flight direction (HV), wherein the flight control system (40) comprises at least one taileron (48, 50), at least one aileron (42, 44), and at least one pitch trim control element (46) pivotable about a rotation axis (O) aligned in the transverse direction of the aircraft, wherein the flight control system (40) is designed such that the aircraft in a horizontal flight phase is trimmed by the pitch trim control element (46) and the flight control is carried out by the at least one taileron (48, 50) and the at least one aileron (42,44) is carried out.
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Claims

[1] Aircraft with a hull (12), two wings (14, 16) arranged on two opposite sides of the fuselage (12), a plurality of propeller devices (22, 24, 26, 28, 30, 32, 34, 36) arranged on the fuselage (12) and / or on the wings (14, 16), and a flight control system (40), characterized by , that the aircraft neutral point (N) is arranged in front of the aircraft's center of gravity (S) in the horizontal forward flight direction (HV), wherein the flight control system (40) comprises at least one taileron (48, 50), at least one aileron (42, 44) and at least one pitch trim control element (46) which is pivotable about an axis of rotation (O) which is aligned in the transverse direction of the aircraft, wherein the flight control system (40) is designed such that the aircraft is trimmed in a horizontal flight phase by the pitch trim control element (46) and the flight control is carried out by the at least one taileron (48, 50) and the at least one aileron (42, 44). [2] Aircraft according to claim 1, characterized byin that two propeller devices (34, 36) designed as ducted propellers are arranged in the rear region of the fuselage (12), wherein the pitch trim control element (46) is arranged in the transverse direction between the propeller devices (34, 36). [3] Aircraft according to claim 2, characterized by that the propeller devices (34, 36) are pivotable between a horizontal orientation and a vertical orientation about a transverse axis. [4] Aircraft according to claim 2 or 3, characterized by that on one side of the propeller devices (34, 36) arranged in the rear region, a taileron (48, 50) facing away from the pitch trim control element (46) is arranged. [5] Aircraft according to one of the preceding claims, characterized by that three propeller devices (22, 24, 26, 28, 30, 32) designed as ducted propellers are arranged on each wing (14, 16). [6] Aircraft according to one of the preceding claims, characterized by in that a passenger cabin (18) is arranged in a front region of the fuselage (12), wherein the inclination trim control element (46) is adjustable depending on a load of the passenger cabin (18).

Citation Information

Patent Citations

  • DE102020109331A1