Apparatuses and methods for flight control surfaces
An aircraft apparatus comprises a flight control surface, an actuation assembly, a link, and an arm. The actuation assembly transitions the flight control surface between a stowed configuration and a deployed configuration. The link is pivotably coupled to a support and comprises a stop surface. The arm is connected to the flight control surface and is pivotally coupled to the link. The arm comprises a contact surface arranged to engage the stop surface to limit pivotal movement of the arm relative to the link and thus define the deployed configuration of the flight control surface. A method comprises translating an arm and a flight control surface in a first direction towards a deployed configuration while simultaneously rotating a link. The method further comprises bringing the arm and the stop surface of link into contact to stop translation of the arm at the deployed configuration of the flight control surface.
1 . An aircraft apparatus, comprising:
a flight control surface;
an actuation assembly operatively coupled to the flight control surface and configured to operatively transition the flight control surface between at least a stowed configuration and a deployed configuration;
a link comprising a first end region and a second end region opposite the first end region, wherein the link has a first end region pivot axis arranged at the first end region and operably couple to a support, and a second end region pivot axis arranged at the second end region, wherein the link is configured to rotate about the first end region pivot axis, and wherein the link comprises a stop surface; and
an arm operatively connected to the flight control surface and pivotally coupled to the second end region of the link about the second end region pivot axis, wherein the arm is configured to translate towards the deployed configuration as the link rotates about the first end region pivot axis, wherein the arm comprises a contact surface that is arranged to engage the stop surface to limit pivotal movement of the arm relative to the link and thus define the deployed configuration of the flight control surface.
2 . The aircraft apparatus of claim 1 , wherein the link comprises two limbs, and wherein the arm and the stop surface are arranged between the two limbs.
3 . The aircraft apparatus of claim 1 , wherein the arm rotates relative to the link as the arm translates in a first direction toward the deployed configuration.
4 . The aircraft apparatus of claim 1 , wherein the link has a link longitudinal axis, and wherein the stop surface is angled relative to the link longitudinal axis.
5 . The aircraft apparatus of claim 1 , wherein the contact surface is a first contact surface, wherein the link comprises a link surface, wherein the arm comprises a second contact surface, wherein the second contact surface engages the link surface in the deployed configuration.
6 . The aircraft apparatus of claim 5 , wherein the link has a link longitudinal axis, and wherein the link surface and the stop surface are arranged at different angles relative to the link longitudinal axis.
7 . The aircraft apparatus of claim 5 , wherein the link comprises a link side, and wherein the link surface is arranged on the link side.
8 . The aircraft apparatus of claim 5 , wherein the link has a link longitudinal axis, and wherein the link surface is oriented parallel to the link longitudinal axis.
9 . The aircraft apparatus of claim 1 , further comprising a wear surface attached to the stop surface.
10 . An aircraft comprising:
a wing:
a flight control surface arranged on the wing;
an actuation assembly operatively coupled to the flight control surface and configured to operatively transition the flight control surface between at least a stowed configuration and a deployed configuration;
a link comprising a first end region and a second end region opposite the first end region, wherein the link has a first end region pivot axis arranged at the first end region and operably couple to a support, and a second end region pivot axis arranged at the second end region, wherein the link is configured to rotate about the first end region pivot axis, and wherein the link comprises a stop surface; and
an arm operatively connected to the flight control surface and pivotally coupled to the second end region of the link about the second end region pivot axis, wherein the arm is configured to translate towards the deployed configuration as the link rotates about the first end region pivot axis, wherein the arm comprises a contact surface that is arranged to engage the stop surface to limit pivotal movement of the arm relative to the link and thus define the deployed configuration of the flight control surface.
11 . The aircraft of claim 10 , wherein the actuation assembly is configured to apply force to the flight control surface; and the link and the arm are configured to guide movement of the flight control surface.
12 . The aircraft of claim 10 , wherein the link is a first side link, wherein the arm is a first arm, wherein the flight control surface comprises a first side and a second side opposite the first side, and wherein the first arm is operatively coupled to the first side of the flight control surface; and
wherein the aircraft further comprises: a second arm and a second side link, wherein the second arm is operatively coupled to the second side of the flight control surface, and wherein the actuation assembly is arranged between the first arm and the second arm.
13 . The aircraft of claim 10 , wherein the arm comprises a third contact surface and the link comprises a second direction stop surface, wherein the second direction stop surface is arranged to engage the third contact surface to limit pivotal movement of the arm in a second direction relative to the link and thus define the stowed configuration of the flight control surface.
14 . The aircraft of claim 10 , wherein the link comprises a link surface and the link has a link longitudinal axis, wherein the arm comprises a first contact surface and a second contact surface and the arm has an arm longitudinal axis, wherein the second contact surface engages the link surface in the deployed configuration, and wherein the link surface and the stop surface are arranged at different angles relative to the link longitudinal axis.
15 . The aircraft of claim 10 , wherein the link has a link longitudinal axis and the link comprises a link surface and a link side, and wherein the link surface is arranged on the link side, and wherein the link surface is oriented parallel to the link longitudinal axis.
16 . A method of operating an aircraft apparatus, the method comprising:
translating an arm and a flight control surface in a first direction towards a deployed configuration while simultaneously rotating a link,
wherein the link comprises a stop surface, wherein the link comprises a first end region and a second end region opposite the first end region, and wherein the link has a first end region pivot axis arranged at a support and a second end region pivot axis,
wherein the arm comprises a contact surface, wherein the arm is pivotally coupled to the second end region of the link about the second end region pivot axis, and wherein the stop surface contacts the contact surface at the deployed configuration; and
bringing the arm and the stop surface into contact to stop translation of the arm at the deployed configuration of the flight control surface.
17 . The method of claim 16 , wherein the stop surface is arranged parallel to the contact surface at the deployed configuration.
18 . The method of claim 16 , wherein the arm comprises a first contact surface and a second contact surface, wherein the link comprises a link surface, and
the method further comprises bringing the second contact surface and the link surface into contact to stop translation of the arm at the deployed configuration.
19 . The method of claim 18 , wherein the second contact surface is oriented parallel to the link surface in the deployed configuration.
20 . The method of claim 16 , further comprising translating the arm and the flight control surface in a second direction toward a stowed configuration, while simultaneously rotating the link.