Flap angle measurement system for an active rotor control system

• US 6,295,006 B1
• Filed: 04/16/1999
• Issued: 09/25/2001
• Est. Priority Date: 04/16/1999
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Kohlhepp, Fred W.
• Primary Examiner(s): SWARTHOUT, BRENT
• Application Number:
  US09/293,628
• Time in Patent Office: 893 Days
• Field of Search: 340/945, 340/946, 701/3, 701/14, 244/17.11, 244/17.13, 244/212, 244/215, 734/62, 731/47, 731/78.H
• US Class Current: 340/946
• CPC Class Codes: B64C 2027/7266 actuated by actuators
• CPC Class Codes: B64C 27/001 Vibration damping devices
• CPC Class Codes: B64C 27/615 including flaps mounted on blades
• CPC Class Codes: Y02T 50/30 Wing lift efficiency

Abstract

A flap angle measurement system is disclosed for a helicopter rotor blade. The blade includes a trailing edge and a flap hinged to at least a portion of the trailing edge about a pivot axis. The flap angle measurement system includes a Hall effect sensor mounted to the trailing edge of the rotor blade. The Hall effect sensor has a sensing face. A magnet is mounted to the flap at a location spaced apart from the pivot axis. The magnet has a pole axis that is located parallel to the sensing face of the Hall effect sensor. A power source supplies power to the Hall effect sensor. A controller receives output signals from the Hall effect sensor which are indicative of the location of the magnet with respect to the sensing face of the Hall effect sensor. The position of the flap relative to the trailing edge is determined based on the received signals from the Hall effect sensor. In one embodiment of the invention, there is a second Hall effect sensor mounted on the other end of the flap. The sensing face of the second Hall effect sensor points in a direction opposite from the sensing face of the first Hall effect sensor.

Claims

1. A flap angle measurement system for a helicopter rotor blade, the rotor blade including a trailing edge and a flap hinged to at least a portion of the trailing edge, the flap being pivotable about a pivot axis, the flap angle measurement system comprising:

a first Hall effect sensor mounted to the trailing edge of the rotor blade adjacent to an inboard end of the flap, the first Hall effect sensor having a sensing face;

a first magnetic element mounted to the flap on an inboard end at a location spaced apart from the pivot axis, the first magnetic element having a pole axis, the first magnetic element being positioned such that the pole axis is parallel to the sensing face of the first Hall effect sensor;

a second Hall effect sensor mounted to the trailing edge adjacent to an outboard end of the flap, the second Hall effect sensor having a sensing face, the sensing face of the second Hall effect sensor pointing in a direction that is opposite from the direction that the sensing face of the first Hall effect sensor points;

a second magnetic element mounted to the flap at a location spaced apart from the pivot axis and on the outboard end, the second magnetic element having its pole axis positioned parallel to the sensing face of the second Hall effect sensor;

a power source for supplying power to the Hall effect sensor; and

a controller for receiving output signals from the Hall effect sensors indicative of the location of the first magnetic element with respect to the sensing face of the first Hall effect sensor and of the location of the second magnetic element with respect to the sensing face of the second Hall effect sensor.

2. A flap angle measurement system according to claim 1 wherein the sensing face of the first Hall effect sensor points substantially upward and the sensing face of the second Hall effect sensor points substantially downward.

3. A rotor blade for a helicopter with a flap measurement system, the rotor blade comprising:

a leading edge;

a trailing edge;

a flap hingedly mounted to at least a portion of the trailing edge about a pivot axis;

a flap angle measurement device mounted to the rotor blade for detecting the angular position of the flap with respect to the trailing edge, the flap angle measurement device including

a first Hall effect sensor mounted to the trailing edge of the rotor blade adjacent to an inboard end of the flap, the first Hall effect sensor having a sensing face,

a first magnetic element mounted to the flap on the inboard end at a location spaced apart from the pivot axis, the first magnetic element having its pole axis positioned parallel to the sensing face of the first Hall effect sensor,

a second Hall effect sensor mounted to the trailing edge adjacent to an outboard end of the flap, the second Hall effect sensor having a sensing face, and

a second magnetic element mounted to the flap at a location spaced apart from the pivot axis and on the outboard end, the second magnetic element having its pole axis positioned parallel to the sensing face of the second Hall effect sensor;

power source for supplying power to the flap measurement device; and

a controller for receiving output signals from the Hall effect sensors indicative of the location of the first magnetic element with respect to the sensing face of the first Hall effect sensor and of the location of the second magnetic element with respect to the sensing face of the second Hall effect sensor.

4. A rotor blade according to claim 3 wherein the sensing face of the first Hall effect sensor points in a direction that is opposite from the direction that the sensing face of the second Hall effect sensor points.

5. A rotor blade according to claim 3 wherein the sensing face of the first Hall effect sensor points substantially upward and the sensing face of the second Hall effect sensor points substantially downward.

6. A flap angle measurement system for a helicopter rotor blade, the rotor blade including a trailing edge and a flap hinged to at least a portion of the trailing edge, the flap being pivotable about a pivot axis, the flap angle measurement system comprising:

a first Hall effect sensor mounted to the trailing edge of the rotor blade adjacent to a first lateral side of the flap, the first Hall effect sensor having a sensing face;

a first magnet mounted to the flap at a location spaced apart from the pivot axis, the first magnet having a pole axis, the first magnet being positioned such that its pole axis is parallel to the sensing face of the first Hall effect sensor;

a second Hall effect sensor mounted to the trailing edge of the rotor blade adjacent a second lateral side of the flap, the second Hall effect sensor having a sensing face;

a second magnet mounted to the flap at a location spaced apart from the pivot axis, the second magnet having a pole axis, the second magnet being positioned such that its pole axis is parallel to the sensing face of the second Hall effect sensor;

a power source for supplying power to the first and second Hall effect sensors; and

a controller for receiving output signals from the first and second Hall effect sensors indicative of the location of the respective magnets with respect to the Hall effect sensors.