Spoiler with releasable portion

Patent metadata

Field	Value
Publication number	US-10926865-B2
Application number	US-201816216769-A
Country	US
Kind code	B2
Filing date	Dec 11, 2018
Priority date	Dec 11, 2018
Publication date	Feb 23, 2021
Grant date	Feb 23, 2021

Abstract

A spoiler mechanism for an aircraft includes a spoiler fore-section and a spoiler aft-section. The spoiler fore-section includes a forward end configured to couple to a wing structure of an aircraft and a hinge end. The hinge end includes a first hinge coupling and a first retainer portion. The spoiler aft-section includes a second retainer portion and a second hinge coupling coupled to the first hinge coupling of the spoiler fore-section. The first retainer portion and the second retainer portion are configured to engage one another when the spoiler aft-section is aligned with the spoiler fore-section, and the first retainer portion and the second retainer portion are configured to disengage from one another responsive to the spoiler aft-section pivoting upward relative to the spoiler fore-section.

First claim

What is claimed is:

1. A spoiler mechanism for an aircraft, the spoiler mechanism comprising:
a spoiler fore-section including a forward end configured to couple to a wing structure of an aircraft and including a hinge end, the hinge end including a first hinge coupling and a first retainer portion; and
a spoiler aft-section including a second retainer portion and a second hinge coupling coupled to the first hinge coupling of the spoiler fore-section, wherein the first retainer portion and the second retainer portion are configured to engage one another when the spoiler aft-section is aligned with the spoiler fore-section, and the first retainer portion and the second retainer portion are configured to disengage from one another responsive to the spoiler aft-section pivoting upward relative to the spoiler fore-section.

2. The spoiler mechanism of claim 1 , wherein the first retainer portion includes a retainer catch and the second retainer portion includes a resilient retainer clip.

3. The spoiler mechanism of claim 1 , wherein the first retainer portion is disposed proximate a lower surface of the spoiler fore-section and the first hinge coupling is disposed proximate an upper surface of the spoiler fore-section, and wherein the second retainer portion is disposed proximate a lower surface of the spoiler aft-section and the second hinge coupling is disposed proximate an upper surface of the spoiler aft-section.

4. The spoiler mechanism of claim 1 , wherein the spoiler fore-section further comprises an actuator coupling and a pivot coupling, the actuator coupling configured to couple to an actuator and the pivot coupling configured to pivotally connect the spoiler fore-section to the wing structure, the actuator coupling and a pivot coupling arranged such that the spoiler fore-section and the spoiler aft-section are rotatable in a first rotational direction from a neutral position responsive to extension of the actuator and are rotatable in a second rotational direction from the neutral position responsive to retraction of the actuator.

5. The spoiler mechanism of claim 4 , wherein, during operation of the aircraft, the rotation of the spoiler fore-section and the spoiler aft-section in the first rotational direction from the neutral position extends the spoiler fore-section and the spoiler aft-section into a bulk airflow to reduce lift generated by the wing structure.

6. The spoiler mechanism of claim 4 , wherein the rotation of the spoiler fore-section and the spoiler aft-section in the second rotational direction from the neutral position extends the spoiler fore-section and the spoiler aft-section in a droop configuration toward a flap of the aircraft.

7. The spoiler mechanism of claim 1 , wherein the first retainer portion and the second retainer portion, when disengaged, are resettable manually by application of a downward force on the spoiler aft-section.

8. The spoiler mechanism of claim 1 , wherein the first hinge coupling, the first retainer portion, the second hinge coupling, and the second retainer portion are positioned such that a force applied to the spoiler aft-section by bulk airflow over the wing structure during operation tends to reinforce engagement of the first retainer portion and the second retainer portion with one another.

9. An aircraft comprising:
a wing structure;
a spoiler mechanism including:
a spoiler fore-section including a forward end coupled to the wing structure and including a hinge end, the hinge end including a first hinge coupling and a first retainer portion; and
a spoiler aft-section including a second retainer portion and a second hinge coupling coupled to the first hinge coupling of the spoiler fore-section, wherein the first retainer portion and the second retainer portion are configured to engage one another when the spoiler aft-section is aligned with the spoiler fore-section, and the first retainer portion and the second retainer portion are configured to disengage from one another responsive to the spoiler aft-section pivoting upward relative to the spoiler fore-section; and

a flap coupled to the wing structure.

10. The aircraft of claim 9 , wherein the first retainer portion includes a retainer catch and the second retainer portion includes a resilient retainer clip.

11. The aircraft of claim 9 , wherein:
the first retainer portion is disposed proximate a first surface of the spoiler fore-section and the first hinge coupling is disposed proximate a second surface of the spoiler fore-section, the first surface of the spoiler fore-section closer to the flap than is the second surface of the spoiler fore-section, and
the second retainer portion is disposed proximate a first surface of the spoiler aft-section and the second hinge coupling is disposed proximate a second surface of the spoiler aft-section, the first surface of the spoiler aft-section closer to the flap than is the second surface of the spoiler aft-section.

12. The aircraft of claim 9 , wherein, during operation, rotation of the spoiler fore-section and the spoiler aft-section in a first rotational direction from a neutral position extends the spoiler fore-section and the spoiler aft-section into a bulk airflow to reduce lift generated by the wing structure.

13. The aircraft of claim 12 , wherein rotation of the spoiler fore-section and the spoiler aft-section in a second rotational direction from the neutral position extends the spoiler fore-section and the spoiler aft-section in a droop configuration toward the flap.

14. The aircraft of claim 9 , wherein the spoiler fore-section includes a composite material and the first retainer portion includes a metal fitting coupled to the composite material, and wherein the second retainer portion includes a metal tab.

15. The aircraft of claim 9 , further comprising an actuator coupled to the wing structure and to the spoiler mechanism, the actuator configured to cause rotation of the spoiler fore-section and the spoiler aft-section, the actuator comprising an overpressure valve configured to release responsive to a first force applied to the actuator, and wherein the first retainer portion and the second retainer portion, when engaged, interact with a retention force configured to release due to application of a threshold force to the spoiler aft-section, wherein the threshold force is insufficient to cause release of the overpressure valve.

16. The aircraft of claim 9 , wherein the first retainer portion is spaced apart from a lower surface of the spoiler fore-section such that, when the first retainer portion is disengaged from the second retainer portion by upward movement of the flap, the flap is not able to contact the first retainer portion.

17. A method of controlling a spoiler mechanism of an aircraft, the method comprising:
extending a flap from a wing structure of an aircraft;
deploying a spoiler mechanism from the wing structure in a droop configuration toward the flap, the spoiler mechanism including:
a spoiler fore-section including a forward end coupled to the wing structure and including a hinge end, the hinge end including a first hinge coupling and a first retainer portion; and
a spoiler aft-section including a second retainer portion and a second hinge coupling coupled to the first hinge coupling of the spoiler fore-section, wherein the first retainer portion and the second retainer portion are configured to engage one another when the spoiler aft-section is aligned with the spoiler fore-section, and the first retainer portion and the second retainer portion are configured to disengage from one another respon

Assignees

• Boeing Co

Inventors

• Tsai Kevin
• Reinhart Donald Drew

Classifications

• Y02T50/40

  Weight reduction · CPC title

• B64C9/20 Primary

  by multiple flaps · CPC title

• B64C9/12

  surfaces of different type or function being simultaneously adjusted · CPC title

• B64C9/323

  associated with wings · CPC title

• B64C9/16 Primary

  at the rear of the wing · CPC title