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JP-7857283-B2 - Multi-segment oblique-wing aircraft

JP7857283B2JP 7857283 B2JP7857283 B2JP 7857283B2JP-7857283-B2

Inventors

  • ジョーベン ビバート
  • ベンジャミン ジョン ブレイエ
  • グレゴール ベブル ミキッチ

Assignees

  • ジョビー エアロ インク

Dates

Publication Date
20260512
Application Date
20210916
Priority Date
20200916

Claims (20)

  1. An aircraft equipped with angled wings, The aforementioned oblique flight wing comprises a central wing segment, a forward wing segment, and a rear wing segment. The central wing segment comprises a leading edge and a trailing edge, the leading edge and the trailing edge being parallel to each other at an angle of no more than 10 degrees along their respective lengths. The forward wing segment is connected to the first end of the center wing segment and has a leading edge and a trailing edge, and the average spanwise tangent of the quarter chord of the forward wing segment has a sweep angle that is 10 degrees or more different from the average spanwise tangent of the quarter chord of the center wing segment . The rear wing segment is connected to the second end of the center wing segment and has a leading edge and a trailing edge, and the average spanwise tangent of the quarter chord of the rear wing segment has a sweep angle that differs by 10 degrees or more from the average spanwise tangent of the quarter chord of the center wing segment , in the opposite direction to that of the front wing segment. An aircraft characterized by the following features.
  2. The aircraft according to claim 1, further, The central wing segment is substantially thicker than the forward wing segment and the rear wing segment. An aircraft characterized by the following features.
  3. The aircraft according to claim 2, further, In the cruising configuration, the forward wing segment has a sweep angle of forward sweep in the range of 15 to 35 degrees, the center wing segment has a sweep angle of 35 to 65 degrees, and the rear wing segment has a sweep angle of rear sweep in the range of 25 to 45 degrees. An aircraft characterized by the following features.
  4. The aircraft according to claim 2, further, An aircraft characterized in that, in a cruising configuration, the forward wing segment has a sweep angle of forward sweep in the range of 0 to 60 degrees, the center wing segment has a sweep angle of 25 to 75 degrees, and the rear wing segment has a sweep angle of rear sweep in the range of 0 to 60 degrees.
  5. The aircraft according to claim 2, further, The ratio of the relative thickness of the center wing segment to the relative thickness of the forward wing segment and to the relative thickness of the rear wing segment is in the range of 1.5 to 10. An aircraft characterized by the following features.
  6. The aircraft according to claim 3, further, The ratio of the relative thickness of the center wing segment to the relative thickness of the forward wing segment and to the relative thickness of the rear wing segment is in the range of 1.5 to 10. An aircraft characterized by the following features.
  7. The aircraft according to claim 2, wherein the aircraft further, Multiple propulsion pylons connected to the aforementioned oblique flight wing, Multiple thrust elements coupled to the aforementioned propulsion pylon, An aircraft characterized by being equipped with the following features.
  8. The aircraft according to claim 6, wherein the aircraft further, Multiple propulsion pylons connected to the aforementioned oblique flight wing, Multiple thrust elements coupled to the aforementioned propulsion pylon, An aircraft characterized by being equipped with the following features.
  9. The aircraft according to claim 8, further, The thrust element is rotatably coupled to the oblique flight wing so that it can rotate from the takeoff position to the cruising position. An aircraft characterized by the following features.
  10. The aircraft according to claim 7, further, The rear wing segment is curved rearward and has a wingtip that is coupled to the rearward propulsion pylon or propulsion nacelle to form an auxiliary pitch control surface. An aircraft characterized by the following features.
  11. The aircraft according to claim 8, further, The rear wing segment is curved rearward and has a wingtip that connects to the rearward propulsion pylon or propulsion nacelle to form an auxiliary stabilizing surface. An aircraft characterized by the following features.
  12. The aircraft according to claim 7, further, The aircraft further comprises an auxiliary pitch control surface or a stabilizing surface, wherein the auxiliary pitch control surface connects two or more propulsion pylons or propulsion nacelles to an aerodynamic surface. An aircraft characterized by the following features.
  13. The aircraft according to claim 8, further, The aircraft further comprises an auxiliary pitch control surface or a stabilizing surface, wherein the auxiliary pitch control surface connects two or more propulsion pylons or propulsion nacelles to an aerodynamic surface. An aircraft characterized by the following features.
  14. The aircraft according to claim 7, further, The trailing edges of one or more of the propulsion pylons form aerodynamic control surfaces that can be deflected to provide lateral control authority. An aircraft characterized by the following features.
  15. The aircraft according to claim 8, further, The trailing edges of one or more of the propulsion pylons form aerodynamic control surfaces that can be deflected to provide lateral control authority. An aircraft characterized by the following features.
  16. The aircraft according to claim 1, further, The rear wing segment has a wingtip that forms a C-shaped portion. An aircraft characterized by the following features.
  17. The aircraft according to claim 16, further, The wingtip of the aforementioned C-shaped portion includes an aerodynamic control surface. An aircraft characterized by the following features.
  18. The aircraft according to claim 2, further, The rear wing segment has a wingtip that forms a C-shaped portion. An aircraft characterized by the following features.
  19. The aircraft according to claim 18, further, The wingtip of the aforementioned C-shaped portion includes an aerodynamic control surface. An aircraft characterized by the following features.
  20. The aircraft according to claim 3, further, The rear wing segment has a wingtip that forms a C-shaped portion. An aircraft characterized by the following features.

Description

The present invention relates to an aircraft, and more particularly to an aircraft having a multi-segment oblique flight wing design. Cross-reference of related applications This application claims priority to U.S. Provisional Patent Application No. 63/078,903 filed on 16 September 2020 by Bebble Mikick et al., which is incorporated herein by reference in its entirety. In 1958, R. T. Jones suggested that aircraft with asymmetrically swept (angled) wings would offer many advantages at high transonic and low supersonic speeds. However, angled wing configurations presented technical challenges, as they lacked the rigid stability and controllability of conventional tails. Problems that the invention aims to solve What is needed is an aircraft with angled wings that can support large cargo and passenger loads while maintaining stability during high-speed flight. Means for solving the problem The invention provides a multi-segment oblique-wing aircraft having three distinct segments, including two outer wing segments and a center wing segment. The center wing segment is thicker vertically and may be designed to hold the pilot and passengers. The outer wing segments become considerably thinner and tapered as they extend outward from the center of the wing. The multi-segment oblique -wing aircraft may be adapted to rotate in a high-speed flight configuration or to take off and cruise at a constant angle. For certain flights, the center wing segment may rotate to a local sweep angle of 90 degrees. This is a diagram of a conventional aircraft having rotatable wings.This is a diagram of an aircraft with oblique wings that have a rotating wing.This is a diagram of a multi-segment oblique-wing aircraft according to several embodiments of the present invention.This is a diagram of a multi-segment oblique-wing aircraft according to several embodiments of the present invention.This figure shows the coordinate system of an oblique flight wing according to several embodiments of the present invention.This figure shows wing designs for oblique flight wings according to several embodiments of the present invention.This is a diagram of an oblique flight wing in a takeoff configuration according to some embodiments of the present invention.This is a diagram of a high-speed configuration oblique flight wing according to several embodiments of the present invention.This is a diagram of a fully rotated oblique flight wing according to some embodiments of the present invention.This is a diagram of an oblique flight wing having a central wing segment perpendicular to the direction of airflow, according to some embodiments of the present invention.This is a perspective view of a multi-segment oblique -wing aircraft with fixed orientation and external auxiliary control surfaces, according to some embodiments of the present invention.This is a top view of a multi-segment oblique -wing aircraft with fixed orientation and external auxiliary control surfaces, according to some embodiments of the present invention.This is a side view of a fixed-orientation, multi-segment oblique -wing aircraft with external auxiliary control surfaces, according to some embodiments of the present invention.This is a rear view of a fixed-orientation, multi-segment oblique -wing aircraft equipped with external auxiliary control surfaces, according to some embodiments of the present invention.This is a perspective view of a multi-segment oblique -wing aircraft with fixed orientation and internal auxiliary control surfaces, according to some embodiments of the present invention.This is a top view of a fixed-orientation multi-segment oblique -wing aircraft with an internal auxiliary control surface, according to some embodiments of the present invention.This is a top view of a multi-segment oblique -wing aircraft with fixed orientation and internal auxiliary control surfaces, according to some embodiments of the present invention.This is a rear view of a fixed-orientation, multi-segment oblique -wing aircraft equipped with an internal auxiliary control surface, according to some embodiments of the present invention.This is a perspective view of a fixed-orientation multi-segment oblique flight wing aircraft having winglet auxiliary control surfaces, according to some embodiments of the present invention.This is a top view of a fixed-orientation multi-segment oblique flight wing aircraft having winglet auxiliary control surfaces, according to some embodiments of the present invention.This is a side view of a fixed-orientation multi-segment oblique flight wing aircraft having winglet auxiliary control surfaces, according to some embodiments of the present invention.This is a rear view of a fixed-orientation multi-segment oblique flight wing aircraft having winglet auxiliary control surfaces, according to some embodiments of the present invention. In designing high-speed aircraft, it is necessary to balance design objectives, particularly those centered on high-speed