Mechanical vibration deicing system

• US 8,517,313 B2
• Filed: 08/07/2008
• Issued: 08/27/2013
• Est. Priority Date: 08/08/2007
• Status: Active Grant

• Current Assignee: Amihay Gornik
• Original Assignee: Amihay Gornik
• Inventors: Gornik, Amihay
• Primary Examiner(s): Collins, Timothy D
• Assistant Examiner(s): Stehle, Jamie S
• Application Number:
  US12/672,459
• Publication Number:
  US 20110210207A1
• Time in Patent Office: 1,846 Days
• Field of Search: 244/134.R, 244/134.A, 244/134.F
• US Class Current: 244/134.R
• CPC Class Codes: B64D 15/16 by mechanical means
• CPC Class Codes: B64D 15/20 Means for detecting icing or initiating de-icing

Abstract

An aircraft deicing system including at least one motor operative to drive at least one eccentric mass in rotational motion and at least one displacer coupled to at least one location on at least one aircraft surface and coupled to the at least one eccentric mass such that forces produced by the rotational motion of the eccentric mass are applied to the at least one displacer, causing the at least one displacer to displace the at least one aircraft surface in a plurality of directions at each of the at least one location, thereby causing disengagement of ice from the at least one aircraft surface.

Claims

1. An aircraft deicing system comprising:

at least one motor operative to drive at least one eccentric mass in rotational motion; and

at least one displacer fixed to at least one location on at least one aircraft surface and rotatably supporting a shaft about which said at least one eccentric mass moves in rotational motion, thereby producing inertial forces which are applied via said shaft to said at least one displacer, causing said at least one displacer to displace said at least one aircraft surface in a plurality of directions at each of said at least one location, said plurality of directions corresponding to changing positions of said eccentric mass as it moves in rotational motion about said shaft, thereby causing disengagement of ice from said at least one aircraft surface.

2. An aircraft deicing system according to claim 1 and wherein said at least one displacer is operative in a cyclic manner, wherein each cycle corresponds to a 360 degree rotation of said eccentric mass about said shaft, wherein in each cycle said at least one displacer is operative to displace said at least one aircraft surface in a plurality of directions at each of said at least one location.

3. An aircraft deicing system according to claim 1 and also comprising:

at least one ice thickness sensor, employing at least one of an acceleration sensor and a strain gage for sensing an ice thickness responsive characteristic of said at least one aircraft surface, by sensing displacement of said at least one aircraft surface responsive to said inertial forces produced by motion of said eccentric mass; and

at least one controller responsive to an output of said at least one ice thickness sensor indicating said ice thickness responsive characteristic of said at least one aircraft surface for governing the operation of said at least one motor.

4. An aircraft deicing system according to claim 1 and wherein said at least one motor drives said at least one eccentric mass in rotational motion about a first axis and at least a portion of at least one of said at least one eccentric mass is selectably displaceable along a second axis generally perpendicular to said first axis.

5. An aircraft deicing system according to claim 1 and wherein

said at least one motor comprises a plurality of motors, each of which is operative to drive an eccentric mass in rotational motion;

and

said at least one displacer comprises a plurality of displacers, each of which is coupled to a location on said aircraft surface and coupled to said eccentric mass such that forces produced by said rotational motion of said eccentric mass are applied to said displacer, causing said displacer to displace said aircraft surface in a plurality of directions at said location.

6. An aircraft deicing system according to claim 5 and wherein each of said plurality of motors and said eccentric mass and displacer associated therewith is operated in a predetermined sequence with respect to others of said plurality of motors, eccentric masses and displacers associated therewith, thereby causing disengagement of ice from said at least one aircraft surface.

7. An aircraft deicing system according to claim 6 and wherein said predetermined sequence produces displacement of said aircraft surface which proceeds therealong in a wavelike progression.

8. An aircraft deicing system according to claim 1 and wherein said at least one aircraft surface comprises a leading edge of a wing.

9. An aircraft comprising:

an airframe including at least one aircraft surface;

at least one motor operative to drive at least one eccentric mass in rotational motion; and

at least one displacer fixed to at least one location on at least one aircraft surface and rotatably supporting a shaft about which said at least one eccentric mass moves in rotational motion, thereby producing inertial forces which are applied via said shaft to said at least one displacer, causing said at least one displacer to displace said at least one aircraft surface in a plurality of directions at each of said at least one location, said plurality of directions corresponding to changing positions of said eccentric mass as it moves in rotational motion about said shaft, thereby causing disengagement of ice from said at least one aircraft surface.

10. An aircraft according to claim 9 and wherein said at least one displacer is operative in a cyclic manner, wherein each cycle corresponds to a 360 degree rotation of said eccentric mass about said shaft, wherein in each cycle said at least one displacer is operative to displace said at least one aircraft surface in a plurality of directions at each of said at least one location.

11. An aircraft according to claim 9 and also comprising:

at least one ice thickness sensor, employing at least one of an acceleration sensor and a strain gage for sensing an ice thickness responsive characteristic of said at least one aircraft surface, by sensing displacement of said at least one aircraft surface responsive to said inertial forces produced by motion of said eccentric mass; and

at least one controller responsive to an output of said at least one ice thickness sensor indicating said ice thickness responsive characteristic of said at least one aircraft surface for governing the operation of said at least one motor.

12. An aircraft according to claim 9 and wherein said at least one motor drives said at least one eccentric mass in rotational motion about a first axis and at least a portion of at least one of said at least one eccentric mass is selectably displaceable along a second axis generally perpendicular to said first axis.

13. An aircraft according to claim 9 and wherein

said at least one motor comprises a plurality of motors, each of which is operative to drive an eccentric mass in rotational motion;

and

said at least one displacer comprises a plurality of displacers, each of which is coupled to a location on said aircraft surface and coupled to said eccentric mass such that forces produced by said rotational motion of said eccentric mass are applied to said displacer, causing said displacer to displace said aircraft surface in a plurality of directions at said location.

14. An aircraft according to claim 13 and wherein each of said plurality of motors and said eccentric mass and displacer associated therewith is operated in a predetermined sequence with respect to others of said plurality of motors, eccentric masses and displacers associated therewith, thereby causing disengagement of ice from said at least one aircraft surface.

15. An aircraft according to claim 14 and wherein said predetermined sequence produces displacement of said aircraft surface which proceeds therealong in a wavelike progression.

16. An aircraft according to claim 9 and wherein said at least one aircraft surface comprises a leading edge of a wing.