Flight control mechanisms and methods of operating aircraft with flight control mechanisms

Patent metadata

Field	Value
Publication number	US-10704496-B2
Application number	US-201715601540-A
Country	US
Kind code	B2
Filing date	May 22, 2017
Priority date	May 22, 2017
Publication date	Jul 7, 2020
Grant date	Jul 7, 2020

Abstract

Provided are flight control mechanisms, such as omnidirectional thrust mechanisms (OTMs), and methods of using such mechanisms. These mechanisms may be positioned in wings, tails, or other components of aircraft. A mechanism may comprise a center member and top and bottom panels. The center member may comprise two curved segments joint at a center edge. The top and bottom panels may be independently pivotable relative to the center member. At high speeds, the top panel and/or the bottom panel may be pivoted outward to change the lift, drag, roll, and/or other flight conditions. The mechanism may also include a gas nozzle to direct compressed gas to the center member. The center member and/or the top and bottom panels redirect this gas resulting in forces in one of four directions, which are used for controlling the aircraft at low speeds, down to hover.

First claim

What is claimed is:

1. A flight control mechanism of an aircraft, the flight control mechanism comprising:
a center member, comprising a top edge and a bottom edge, wherein a first axis defining a centerline of the flight control mechanism is defined to run through the center member;
a top panel, pivotable relative to the center member around a top pivot axis,
wherein the top pivot axis is disposed above the first axis,
wherein the top edge of the center member extends toward the top panel,
wherein the top panel is pivotable relative to a top flush orientation of the top panel such that, in a first pivoted position, a portion of the top panel is disposed below the first axis, and
wherein, in the top flush orientation, the top panel is coplanar with a top wing surface of the aircraft;

a bottom panel, pivotable relative to the center member around a bottom pivot axis,
wherein the bottom pivot axis is disposed below the first axis,
wherein the bottom edge of the center member extends toward the bottom panel,
wherein the bottom panel is pivotable relative to a bottom flush orientation of the bottom panel such that, in a second pivoted position, a portion of the bottom panel is disposed above the first axis, and
wherein, in the bottom flush orientation, the bottom panel is coplanar with a bottom wing surface of the aircraft;

a top actuator, coupled to the top panel and operable to pivot the top panel, independently from the bottom panel; and
a bottom actuator, coupled to the bottom panel and operable to pivot the bottom panel, independently from the top panel.

2. The flight control mechanism of claim 1 , wherein the center member further comprises a center edge extending between the top edge and the bottom edge of the center member.

3. The flight control mechanism of claim 2 , wherein the center edge protrudes past a plane extending through the top edge and the bottom edge of the center member.

4. The flight control mechanism of claim 2 , wherein the center member has a shape comprising two curved segments connected at the center edge.

5. The light control mechanism of claim 4 , wherein each of the two curved segments connected at the center edge has a parabolic shape or a circular shape.

6. The flight control mechanism of claim 4 , wherein the two curved segments have identical shapes.

7. The flight control mechanism of claim 4 , wherein an angle between the two curved segments at the center edge is between about 1° and 25°.

8. The flight control mechanism of claim 1 , wherein the top panel is configured to pivotably couple to a top wing component, and wherein the bottom panel is configured to pivotably couple to a bottom wing component.

9. The flight control mechanism of claim 1 , wherein at least one of the top panel or the bottom panel is pivotably coupled to the center member.

10. The flight control mechanism of claim 1 , wherein both the top panel and the bottom panel are pivotably coupled to the center member.

11. The flight control mechanism of claim 1 , wherein the top panel and the bottom panel is pivotable at least 20° in one direction relative to a longitudinal axis of the flight control mechanism and at least 60° in the other direction relative to the longitudinal axis.

12. The flight control mechanism of claim 1 , wherein the top actuator is coupled to the top panel using a top rod connected to a top pivot bearing of the top panel and a roller bearing extending within a linear slot.

13. The flight control mechanism of claim 1 , wherein the top actuator is a linear actuator.

14. The flight control mechanism of claim 1 , wherein the top actuator is a rotating actuator.

15. The flight control mechanism of claim 1 , further comprising a nozzle directed at the center member.

16. The flight control mechanism of claim 15 , wherein the nozzle is directed along a longitudinal axis of the flight control mechanism.

17. The flight control mechanism of claim 15 , wherein the center member further comprises a center edge extending between the top edge and the bottom edge of the center member, and the center edge extends along a longitudinal axis of the flight control mechanism, and wherein the flight control mechanism further comprises a valve connected to the nozzle and operable to control flow of gas from a gas turbine engine of the aircraft to the nozzle.

18. The flight control mechanism of claim 1 , wherein the top panel contacts the bottom panel in the first pivoted position and/or the bottom panel contacts the top panel in the second pivoted position.

19. A method of operating an aircraft, the method comprising:
determining a flight speed of the aircraft, the aircraft comprising a first flight control mechanism positioned in a first wing and a second flight control mechanism positioned in a second wing;
wherein each of the first flight control mechanism and the second flight control mechanism comprises:
a center member, wherein a first axis defining a centerline of the flight control mechanism is defined to run through the center member;
a top panel, pivotable relative to the center member,
wherein the top panel is disposed above the first axis in a first resting position,
wherein the top panel is pivotable relative to a top flush orientation of the top panel such that, in a first pivoted position, a portion of the top panel is disposed below the first axis, and
wherein, in the top flush orientation, the top is coplanar with a top wing surface of the aircraft;

a bottom panel, pivotable relative to the center member,
wherein the bottom panel is disposed below the first axis in a second resting position,
wherein the bottom panel is pivotable relative to a bottom flush orientation of the bottom panel such that, in a second pivoted position a portion of the bottom panel is disposed above the first axis, and
wherein, in the bottom flush orientation, the bottom panel is coplanar with a bottom wing surface of the aircraft; and

a nozzle directed at the center member;

determining a flight condition of the aircraft selected from the group consisting of a no-change condition, a lift-change condition, a roll-change condition, a drag-change condition, an aft-force condition, a forward-force condition, and a yaw-change condition;
determining an operating condition of the nozzle of each of the first flight control mechanism and the second flight control mechanism, based on the flight speed of the aircraft and the flight condition of the aircraft;
determining an orientation of each of the top panel and the bottom panel of each of the first flight control mechanism and the second flight control mechanism, based on the flight speed of the aircraft and the flight condition of the aircraft;
positioning each of the top panel and the bottom panel of each of the first flight control mechanism and the second flight control mechanism according to the determined orientation; and
operating the nozzle of each of the first flight control mechanism and the second flight control mechanism in accordance with the determined operating conditions.

20. A short takeoff and vertical landing (STOL) aircraft comprising:
a flight control system;
a wing;
a tail;
a turbine engine; and
a flight control mechanism positioned on the wing or the tail, the flight control mechanism comprising:
a center member, wherein a first axis defining a centerline of the flight control mechanism is defined to run through the center member;
a top panel, pivotable relative to the center member based on input from the flight cont

Assignees

• Boeing Co

Inventors

• Lee Robert Michael

Classifications

• B64D33/04 Primary

  of exhaust outlets or jet pipes · CPC title

• F02K1/002

  with means to modify the direction of thrust vector (F02K1/54 takes precedence; thrust vectoring of rockets F02K9/80) · CPC title

• B64C9/323

  associated with wings · CPC title

• B64C13/16

  actuated automatically, e.g. responsive to gust detectors · CPC title

• B64C2009/005

  Ailerons · CPC title