Aircraft side ledge table deployment system
An aircraft side ledge table deploying mechanism including a table mounted to a pivot plate. The pivot plate being able to slide in a linear channel. The pivot plate is forced upwards by the release of a torsion spring. The torsion spring is able to be released when a lid is pivoted to a past open position. When the pivot plate translates upwards the table protrudes from an aircraft side ledge and a user may grasp the table and move it to a deployed position.
1 . An aircraft table deployment system comprising:
a lid arm operatively connected on a first end to a lid and on a second end pivotally connected to a first end of a cam rod;
the cam rod being pivotally connected on a second end to a pivotally mounted cam;
a table supported in between a first linear guide channel and a second linear guide channel wherein the first linear guide channel and the second linear guide channel are linearly aligned and directly oppose each other;
the table being operatively connected to at least one torsion spring wherein the torsion spring forces the table to a deployed position;
the lid pivoting to a past open position and pivoting the cam allowing the torsion spring to drive the table to the deployed position.
2 . The deployment system of claim 1 wherein the first linear guide channel and the second linear guide channel each include siding wherein the siding forms the sides of the first and second linear guide channels.
3 . The deployment system of claim 1 wherein the table is supported by a pivot plate and the pivot plate includes a pivot mount configured to track within siding of the first and second linear guide channels.
4 . The deployment system of claim 3 wherein the siding and the pivot mount may or may not include gear teeth configured to track the pivot mount within the first and second linear guide channels.
5 . The deployment system of claim 3 wherein the torsion spring drives the pivot mount along the first and second linear guide channels such that the table escapes a cavity to be oriented by a user to a stowed position, partially deployed position, or fully deployed position.
6 . The deployment system of claim 1 wherein the first and second linear guide channels are shaped to track the table in a single plane from a stowed position to a deployed position.
7 . The deployment system of claim 1 wherein an extension spring is mounted to the cam and positions the cam to engage with the table.
8 . The deployment system of claim 1 wherein a damper allows the lid to pivot to a closed position, an open position, and the past open position.
9 . The deployment system of claim 1 wherein the table is supported and concealed within a cavity.
10 . The deployment system of claim 9 wherein the cavity is mounted to an aircraft structure.
11 . An aircraft working surface deployment system, the system comprising:
a working surface wherein the working surface is concealed within a cavity and supported by a linear guide channel aligned in a single plane;
the working surface being operatively coupled to at least one torsion spring wherein the torsion spring forces the working surface to escape from the cavity;
a cam pivotally mounted to the linear guide channel wherein the cam pivots to locked and unlocked orientations;
the cam being pivoted to an unlocked orientation when a lid is pivoted to a past open position allowing the torsion spring to force the working surface to escape from the cavity; and
a cam rod operatively connected at a first end to the lid and pivotally mounted at a second end to the cam.
12 . The deployment system of claim 11 wherein the cam includes a tabbed end configured to engage with the working surface when the cam is in a locked orientation.
13 . The deployment system of claim 11 wherein the working surface is supported by a pivot mount and a lip extension when fully removed from the cavity.
14 . The deployment system of claim 11 wherein the working surface is stabilized by guide rails when the working surface is being removed from the cavity.
15 . The deployment system of claim 11 wherein the cavity is formed within an inboard furniture panel.
16 . An aircraft working surface deployment system, the system comprising:
a lid operatively connected to a cam rod wherein the lid is operatively connected to a first end of the cam rod;
a cam pivotally mounted to a second end of the cam rod wherein the cam is engaged with a working surface in a locked orientation;
the working surface supported by a linear guide channel wherein the working surface tracks along the linear guide channel in a single plane;
the lid being able to pivot to a past open position to shift the cam rod and pivot the cam to disengage with the working surface in an unlocked orientation.
17 . The deployment system of claim 16 wherein a first pivot mount and a second pivot mount engage with the linear guide channel on opposing sides wherein the first pivot mount is positioned on one side of a pivot plate and the second pivot mount is positioned on an opposite side of the pivot plate.
18 . The deployment system of claim 17 wherein the pivot plate is mounted to an underside of the working surface.
19 . The deployment system of claim 16 wherein at least one torsion spring drives the working surface out of a cavity when the cam is pivoted to an unlocked orientation.