AIRCRAFT LIFT TRANSDUCER

• US 20150175270A1
• Filed: 12/23/2013
• Published: 06/25/2015
• Est. Priority Date: 12/23/2013
• Status: Active Grant

• Current Assignee: Safe Flight Instrument LLC
• Original Assignee: Safe Flight Instrument Corporation
• Inventors: GREENE, Randall A., TISEO, Joseph S.
• Granted Patent: US 9,637,243 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 11/001 Shrouded propellers
• CPC Class Codes: B64C 15/02 the jets being propulsion jets
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: G01D 5/2006 by influencing the self-induction of one or more coils G01D5/22 takes precedence
• CPC Class Codes: G01L 1/14 by measuring variations in capacitance or inductance of electrical elements, e.g. by measuring variations of frequency of electrical oscillators
• CPC Class Codes: G01M 9/06 Measuring arrangements specially adapted for aerodynamic testing

Abstract

An aircraft lift transducer may include a vane, actuator, an LC circuit, and a processor. The vane may be positioned on the leading edge of a wing of the aircraft, where the angle defined by the chord of the wing and the vane changes when the aircraft angle of attack changes. The actuator may be associated with the vane and change position when the angle defined by the vane and the chord changes. The LC circuit may include an induction coil spaced from the actuator and an oscillator. The oscillation frequency of the LC circuit may change when the position of the actuator changes. The processor may receive the change in the oscillation frequency and may determine a corresponding change in an available lift of the aircraft.

Claims

1. An aircraft lift transducer comprising:

a vane positioned on a leading edge of a wing of the aircraft, the vane and the wing defining an angle that changes when an angle of attack of the aircraft changes,

an actuator associated with the vane, the actuator having a position that changes when the angle defined by the vane and the wing changes,

an LC circuit comprising an induction coil spaced from the actuator and an oscillator, the LC circuit having an oscillation frequency that changes when the position of the actuator changes, and

a processor receiving a change in the oscillation frequency and determining a corresponding change in an available lift of the aircraft.

2. The lift transducer of claim 1, wherein the actuator and the induction coil are spaced by a distance that changes when the angle defined by the vane and the wing changes.

3. The lift transducer of claim 1, wherein the actuator and the induction coil are spaced by a fixed distance and wherein the actuator is shaped.

4. The lift transducer of claim 1, wherein the vane is located in proximity to a stagnation point of the wing and wherein the angle defined by the vane and the wing changes when a location of the stagnation point changes.

5. The lift transducer of claim 1, wherein the aircraft'"'"'s available lift is utilized to determine an angle of attack of the aircraft.

6. The lift transducer of claim 1 comprising a capacitor connected in parallel to the induction coil.

7. The lift transducer of claim 1 comprising a temperature sensor.

8. A method of determining an aircraft'"'"'s available lift comprising:

measuring an oscillation frequency change of an LC circuit comprising an oscillator and an induction coil spaced from an actuator, the actuator having a position and a change in the position causing the oscillation frequency change, wherein

a wing of the aircraft and a vane positioned on the leading edge of the wing define an angle, a change in the angle causing the change in the position of the actuator, a change in the angle of attack causing the change in the angle defined by the vane and the wing, and

determining a change in the available lift from the oscillation frequency change.

9. The method of claim 8, wherein the actuator and the induction coil are spaced by a distance that changes when the angle defined by the vane and the wing changes.

10. The method of claim 8, wherein the actuator and the induction coil are spaced by a fixed distance and wherein the actuator is triangular.

11. The method of claim 8, wherein the vane is located in proximity to a stagnation point of the wing and wherein the angle defined by the vane and the wing changes when a location of the stagnation point changes.

12. The method of claim 8 comprising utilizing the aircraft'"'"'s available lift to determine an angle of attack of the aircraft.

13. The method of claim 8, wherein a capacitor is connected in parallel to the induction coil.

14. The method of claim 8 comprising measuring an ambient temperature and adjusting the measured oscillation frequency.

15. An aircraft lift transducer comprising:

a vane positioned on a leading edge of a wing of the aircraft, the vane and the wing defining an angle that changes when an angle of attack of the aircraft changes,

a compressor associated with the vane, the compressor having a position that changes when the angle defined by the vane and the wing changes,

an LC circuit comprising an induction coil and an oscillator, the LC circuit having an oscillation frequency that changes when the induction coil is compressed by the compressor, and

a processor receiving a change in the oscillation frequency and determining a corresponding change in an available lift of the aircraft.

16. The lift transducer of claim 15, wherein the vane is located in proximity to a stagnation point of the wing and wherein the angle defined by the vane and the wing changes when a location of the stagnation point changes.

17. The lift transducer of claim 15, wherein the aircraft'"'"'s available lift is utilized to determine an angle of attack of the aircraft.

18. The lift transducer of claim 15 comprising a capacitor connected in parallel to the induction coil.

19. The lift transducer of claim 15 comprising a temperature sensor.