Aircraft video monitor deployment and retraction apparatus

• US 5,743,487 A
• Filed: 04/12/1996
• Issued: 04/28/1998
• Est. Priority Date: 04/12/1996
• Status: Expired due to Fees

• Current Assignee: Hollingsead International Incorporated
• Original Assignee: Hollingsead International Incorporated
• Inventors: Rice, Mark X.
• Primary Examiner(s): GRANT, WILLIAM ALEXANDER
• Application Number:
  US08/631,102
• Time in Patent Office: 746 Days
• Field of Search: 244/118.5, 244/129.1, 244/1 R, 312/242, 312/245, 312/246, 312/248, 312/7.2, 307/9.1, 307/119
• US Class Current: 244/1.00R
• CPC Class Codes: B64D 11/0015 Arrangements for entertainment or communications, e.g. radio, television
• CPC Class Codes: B64D 11/00153 Monitors mounted on or in the seat other than the seat back
• CPC Class Codes: B64D 11/003 Stowage devices for passengers' personal luggage

Abstract

A video monitor is deployed from an aircraft overhead storage compartment via a monitor-drive shaft selectively connected to an electric motor and retracted back into the compartment by a spring connected to the shaft. The monitor has limited rotational movement in both directions relative to the shaft. A bump sensor detects when the monitor has moved from its deployed position relative to the shaft as a result of being struck by a passenger and trips a solenoid. The solenoid, in turn, disengages the monitor-drive shaft from the motor and allows the spring to return the monitor to its stores position.

Claims

1. In a video monitor deployment and retraction apparatus for use in an aircraft overhead storage compartment, the combination comprising:

a) a monitor frame adapted to be mounted in the compartment;

b) a monitor-drive shaft rotatably mounted in the frame;

c) a monitor movable between a stored position and a deployed position;

d) a first coupling mechanism for connecting the monitor to the monitor-drive shaft, when enabled, to cause the monitor to rotate with the shaft while allowing the monitor to move through a predetermined angle in either direction relative to the shaft in response to an external force applied to the monitor;

e) an electric motor;

f) a second coupling mechanism for coupling the motor to the monitor-drive shaft, when enabled, whereby the motor, when energized, rotates the monitor-drive shaft and monitor to the deployed position;

g) a first position sensor for sensing when the monitor is in the deployed position;

h) means responsive to the first position sensor for deenergizing the motor;

i) a spring coupled to the monitor-drive shaft for biasing the shaft in a direction to return the monitor to the stored position when the second coupling mechanism is disabled;

j) a second position sensor comprising a bump sensor for sensing when the monitor has moved through said predetermined angle relative to the monitor-drive shaft; and

k) means responsive to the bump sensor for disabling the second coupling mechanism.

2. The invention of claim 1 wherein the second coupling mechanism includes a solenoid, the second coupling mechanism being enabled when the solenoid is energized.

3. The invention of claim 2 further including a controller for reenergizing the motor and the solenoid a preset time after the monitor has been returned to its stored position as a result of the monitor being moved through said predetermined angle.

4. The invention of claim 2 wherein the first coupling mechanism includes at least one spring interposed between the monitor-drive shaft and the monitor.

5. The invention of claim 4 wherein each of the first and second position sensors include a hall-effect transducer.

6. The invention of claim 4 wherein the second coupling mechanism further includes a first planetary-gear unit having a casing and arranged to connect the motor to the monitor-drive shaft when the casing is prevented from turning.

7. The invention of claim 6 wherein the second coupling mechanism further includes a latch which in response to the energization of the solenoid selectively engages the casing to prevent rotation thereof.

8. The invention of claim 7 wherein the second coupling mechanism further includes a spring which biases the latch in a direction to disengage the casing of the first planetary-gear unit.

9. The invention of claim 7 further including a second planetary gear unit interposed between the motor and the first planetary-gear unit.

10. In a video screen deployment and retraction apparatus for use in an aircraft overhead compartment the combination which comprises:

a) a housing adapted to be mounted in the compartment;

b) an electric motor mounted in the housing;

c) a video screen rotatably mounted in the housing between a stored position and a deployed position;

d) a screen-deployment shaft, the screen being coupled to the deployment shaft for rotation therewith while allowing limited rotational movement between the screen and the shaft;

e) a screen-bump sensor which provides a bumped screen signal when the screen has moved through a predetermined angle in either direction relative to the deployment shaft; and

f) a screen-deployment-shaft-coupling mechanism which selectively connects the motor to the deployment shaft whereby the motor when connected to the deployment shaft can rotate the screen to its deployed position, the coupling mechanism being responsive to the bumped screen signal to disconnect the motor from the deployment shaft.

11. The invention of claim 10 wherein the screen-deployment-shaft-coupling mechanism includes a planetary-gear unit having a casing and arranged to connect the motor to the deployment shaft when the casing is prevented from rotating.

12. The invention of claim 11 wherein the screen-deployment-shaft-coupling mechanism further includes a latch which selectively engages the casing to restrain the rotation thereof.

13. The invention of claim 12 wherein the screen-deployment-shaft-coupling mechanism further includes a solenoid for moving the latch into engagement with the casing, when energized, and a spring to disengage the latch from the casing of the planetary-gear unit when the solenoid is deenergized.

14. The invention of claim 13 further including a spring to retract the screen to its stored position when the latch is disengaged from the casing of the planetary-gear unit.

15. The invention of claim 14 wherein the solenoid is deenergized in response to the bumped screen signal.

16. The invention of claim 15 further including a second planetary-gear unit interposed between the motor and the gear unit of the screen-deployment-shaft-coupling mechanism.

17. The invention of claim 15 further including a controller for reenergizing the motor and the solenoid a preset time after the screen has been returned to its stored position as a result of the screen being moved through said predetermined angle.