Side to side tilting aircraft seat mechanism
An aircraft seat includes infinitely adjustable, lateral tilt control within a specified range. The aircraft seat includes a stationary support, a tilting frame rotatably or translatably attached to the stationary base, and a tilt control mechanism to adjust the tilt within the defined range and positively lock the frame without back-driving. The tilt control mechanism may include a plurality of linkages connected to the stationary support and the tilting frame, and to each other via a threaded block; a threaded shaft adjusts the linkages and thereby adjust the tilt. Alternatively, the tilt control mechanism comprises a curved rack and a pinion. The threaded block and threaded shaft, or the rack and pinion define ACME threads to prevent back-driving.
1. An aircraft seat comprising:
a stationary support;
a tilting frame; and
a tilt control mechanism comprising:
a first linkage;
a second linkage;
a threaded block; and
a threaded shaft,
wherein:
the stationary support and tilting frame are connected and configured to translate from a left tilting orientation to a right tilting orientation;
the first linkage is connected to the stationary support at a first end and the threaded block at a second end;
the second linkage is connected to the tilting frame at a first end and the threaded block at a second end; and
the threaded shaft is configured to engage the threaded block and translate the threaded block from a first orientation wherein the first end of the first linkage and the first end of the second linkage are distally disposed to a second orientation wherein the first end of the first linkage and the first end of the second linkage are proximally disposed.
2. The aircraft seat of claim 1 , wherein the threaded block and threaded shaft each define ACME threads.
3. The aircraft seat of claim 1 , wherein the tilting frame defines at least one chair control channel disposed to allow a corresponding chair control to pass through, and allow the tilting frame to tilt while the corresponding chair control remains stationary relative to the stationary support.
4. An aircraft seat tilting mechanism comprising:
a stationary support;
a tilting frame; and
a tilt control mechanism comprising:
a first linkage;
a second linkage;
a threaded block; and
a threaded shaft,
wherein:
the stationary support and tilting frame are connected and configured to translate from a left tilting orientation to a right tilting orientation;
the first linkage is connected to the stationary support at a first end and the threaded block at a second end;
the second linkage is connected to the tilting frame at a first end and the threaded block at a second end; and
the threaded shaft is configured to engage the threaded block and translate the threaded block from a first orientation wherein the first end of the first linkage and the first end of the second linkage are distally disposed to a second orientation wherein the first end of the first linkage and the first end of the second linkage are proximally disposed.
5. The aircraft seat tilting mechanism claim 4 , wherein the threaded block and threaded shaft each define ACME threads.
6. The aircraft seat tilting mechanism claim 4 , wherein the tilting frame defines at least one chair control channel disposed to allow a corresponding chair control to pass through, and allow the tilting frame to tilt while the corresponding chair control remains stationary relative to the stationary support.