Variable slat displacement using spanwise actuator
An aircraft wing includes a fixed structure and a linear hydraulic slat actuator attached to the fixed structure. The linear hydraulic slat actuator is oriented spanwise along the aircraft wing. The aircraft wing also includes an actuator output link and a slat attached to the actuator output link. The aircraft wing also includes a bell-crank coupled to the linear hydraulic slat actuator and to the actuator output link. In response to spanwise movement of the linear hydraulic slat actuator, the bell-crank is configured to move the actuator output link in a different direction that enables the slat to move between a retracted position and an extended position.
1 . An aircraft wing comprising:
a support rib defining an aperture extending therethrough, the support rib having a first contour that is complimentarily shaped with respect to a second contour of a leading edge of the wing;
a linear hydraulic slat actuator having at least a portion thereof extending through the aperture of the support rib, wherein the linear hydraulic slat actuator is oriented in a first direction, the first direction being spanwise along the aircraft wing;
an actuator output link;
a slat attached to the actuator output link; and
a bell-crank rotatably coupled to: (i) the support rib, (ii) the linear hydraulic slat actuator and (iii) the actuator output link, wherein, in response to spanwise movement of the linear hydraulic slat actuator, the bell-crank is configured to move the actuator output link in a second direction different from the first direction that enables the slat to move between a retracted position and an extended position.
2 . The aircraft wing of claim 1 , wherein the bell-crank comprises:
a first arm coupled to the linear hydraulic slat actuator, wherein a first length of the first arm defines a bell-crank radius; and
a second arm coupled to the actuator output link, wherein a second length of the second arm defines a second bell-crank radius.
3 . The aircraft wing of claim 2 , wherein an input stroke length associated with the linear hydraulic slat actuator is based on the first bell-crank radius, and wherein an output stroke length associated with the actuator output link is based on the second bell-crank radius.
4 . The aircraft wing of claim 2 , wherein the first bell-crank radius is the same as the second bell-crank radius.
5 . The aircraft wing of claim 2 , wherein the first bell-crank radius is different than the second bell-crank radius.
6 . The aircraft wing of claim 5 , wherein the second bell-crank radius is greater than the first bell-crank radius.
7 . The aircraft wing of claim 5 , wherein the second bell-crank radius is smaller than the first bell-crank radius.
8 . The aircraft wing of claim 1 , wherein the support rib is further coupled to the linear hydraulic slat actuator.
9 . The aircraft wing of claim 1 , wherein the support rib, the linear hydraulic slat actuator, and the bell-crank are positioned within a compartment at the leading edge of the wing.
10 . The aircraft wing of claim 1 , wherein the first contour includes a first vertex that is positioned adjacent a second vertex of the second contour of the leading edge of the wing.
11 . The aircraft wing of claim 1 , wherein the support rib includes a portion having a curvature that matches the leading edge of the wing.
12 . The aircraft wing of claim 1 , wherein the first contour and the second contour are in contact with one another.
13 . A method of fabricating an aircraft wing, the method comprising:
coupling a linear hydraulic slat actuator to a support rib defining an aperture extending therethrough, the support rib having a first contour that is complimentarily shaped with respect to a second contour of a leading edge of the wing, the linear hydraulic slat actuator having at least a portion thereof extending through the aperture of the support rib, wherein the hydraulic slat actuator is oriented in a first direction, wherein the first direction is spanwise along the aircraft wing;
rotatably coupling a bell-crank to the support rib;
rotatably coupling the bell-crank to the linear hydraulic slat actuator;
rotatably coupling an actuator output link to the bell-crank, the output link oriented in a second direction different from the first direction; and
coupling a slat to the actuator output link, wherein, in response to spanwise movement of the linear hydraulic slat actuator, the bell-crank moves the actuator output link in the second direction that enables the slat to move between a retracted position and an extended position.
14 . The method of claim 13 , wherein the linear hydraulic slat actuator is coupled to a first arm of the bell-crank, and wherein the actuator output link is coupled to a second arm of the bell-crank, wherein a first length of the first arm defines a first bell-crank radius, and wherein a second length of the second arm defines a second bell-crank radius.
15 . The method of claim 14 , wherein an input stroke length associated with the linear hydraulic slat actuator is based on the first bell-crank radius, and wherein an output stroke length associated with the actuator output link is based on the second bell-crank radius.
16 . The method of claim 14 , wherein the first bell-crank radius is the same as the second bell-crank radius.
17 . The method of claim 14 , wherein the first bell-crank radius is different than the second bell-crank radius.
18 . An aircraft comprising:
a fuselage; and
an aircraft wing attached to the fuselage, the aircraft wing comprising:
a support rib defining an aperture extending therethrough, the support rib having a first contour that is complimentarily shaped with respect to a second contour of a leading edge of the wing;
a linear hydraulic slat actuator having at least a portion thereof extending through the aperture of the support rib, wherein the linear hydraulic slat actuator is oriented in a first direction, the first direction being spanwise along the aircraft wing;
an actuator output link;
a slat attached to the actuator output link; and
a bell-crank rotatably coupled to: (i) the support rib, (ii) the linear hydraulic slat actuator and (iii) the actuator output link, wherein, in response to spanwise movement of the linear hydraulic slat actuator, the bell-crank is configured to move the actuator output link in the second direction different from the first direction that enables the slat to move between a retracted position and an extended position.
19 . The aircraft of claim 18 , wherein the bell-crank comprises:
a first arm coupled to the linear hydraulic slat actuator, wherein a first length of the first arm defines a first bell-crank radius; and
a second arm coupled to the actuator output link, wherein a second length of the second arm defines a second bell-crank radius.