Multi-parameter air data sensing technique

• US 5,610,845 A
• Filed: 08/30/1994
• Issued: 03/11/1997
• Est. Priority Date: 08/30/1994
• Status: Expired due to Fees

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Filipkowski, Richard C., Slabinski, Robert J.
• Primary Examiner(s): Ramirez, Ellis B.
• Assistant Examiner(s): KEMPER, MELANIE A
• Application Number:
  US08/298,456
• Time in Patent Office: 924 Days
• Field of Search: 364/565, 364/558, 364/571.02, 364/571.03, 364/424.01, 364/424.06, 324/160, 324/166, 73/182, 73/178 H, 244/17.13, 416/31
• US Class Current: 702/144
• CPC Class Codes: G01P 13/02 Indicating direction only, e.g. by weather vane
• CPC Class Codes: G01P 5/14 by measuring differences of pressure in the fluid

Abstract

Static pressure sensing and free airstream temperature sensing is obviated in a method for determining aircraft velocity relative to an airmass by utilizing a static pressure and temperature component present in pressure variations sensed by a total pressure sensor located on a rotating arm mounted on the fuselage of an aircraft. A harmonic analysis of a quasi-sinusoidal total pressure variation includes a determination of steady state and both first and second harmonic components. These harmonic components are used to determine the static pressure, the free airstream temperature and the aircraft airspeed without separately sensing these parameters.

Claims

1. A method of providing an airspeed signal indicative of a velocity of an aircraft relative to an air mass surrounding the aircraft relative to a frame of reference fixed in the aircraft, the aircraft having at least one sensor for providing a sensed pressure signal as a sensed air data parameter that is indicative of pressure at a rotating member and a sensed periodic reference signal indicative of the rotating member periodically passing a reference position relative to the frame of reference, comprising the steps of:

selectively sampling the magnitude of the sensed pressure signal according to the position of the rotating member for each of a plurality of subrevolution intervals, and providing sampled pressure signals having magnitudes indicative of said magnitude of the sensed pressure signal during each of said plurality of subrevolution intervals, as determined with respect to the sensed periodic reference signal;

providing, in response to said sampled pressure signals, multiple order harmonic component pressure signals having magnitudes indicative of multiple order harmonic component representations of the pressure at the rotating member; and

utilizing the multiple order harmonic component pressure signals for determining aircraft velocity, for providing the airspeed signal having a magnitude indicative thereof thereby using only one sensed air data parameter in said method of providing said airspeed signal.

2. The method of claim 1, wherein the multiple order harmonic component pressure signals are indicative of steady state, first harmonic and second harmonic components of the sensed pressure signal.

3. The method of claim 1, further comprising the step of determining static pressure from the multiple order harmonic component pressure signals for providing a static pressure signal.

4. The method of claim 1, further comprising the step of determining a temperature component of the sensed pressure signal.

5. An apparatus for providing an airspeed signal indicative of a velocity of an aircraft relative to an air mass surrounding the aircraft relative to a frame of reference fixed in the aircraft, the aircraft having a plurality of sensors for providing a sensed pressure signal as a sensed air data parameter that is indicative of pressure on a rotating member and a sensed periodic reference signal indicative of the rotating member periodically passing a reference position relative to the frame of reference, comprising:

pressure sampling means for selectively sampling the magnitude of the sensed pressure signal according to the position of the rotating member for each of a plurality of subrevolution intervals determined with respect to the sensed periodic reference signal, said sampling means providing sampled pressure signals having magnitudes indicative of said magnitude of the sensed pressure signal during each of said plurality of subrevolution intervals;

multiple order harmonic component pressure determination means, responsive to said sampled pressure signals, for providing multiple order harmonic component pressure signals having magnitudes indicative of multiple order harmonic component representations of the pressure on the rotating member; and

aircraft velocity determination means, responsive to said multiple order harmonic component pressure signals, for providing the airspeed signal having a magnitude indicative thereof thereby using only one sensed air data parameter in said apparatus for providing an airspeed signal.

6. The apparatus of claim 5, wherein the multiple order harmonic component pressure signals are indicative of steady state, first harmonic and second harmonic components of the sensed pressure signal.

7. The apparatus of claim 6, wherein the apparatus further comprises static pressure determination means, responsive to the multiple order harmonic component pressure signals, for providing a static pressure signal indicative of a static pressure at the rotary member.

8. The apparatus of claim 6, wherein the apparatus further comprises free airstream temperature determination means, responsive to the multiple order harmonic component pressure signals, for providing a free airstream temperature signal indicative of a free air temperature at the rotary member.

9. The apparatus of claim 8, wherein the free airstream temperature determination means determines temperature from the multiple order harmonic pressure component signals for providing the free airstream temperature signal.

10. A method for determining air data parameters for an aircraft, comprising the steps of:

sensing total pressure at a selected position on a rotating member of the aircraft, for providing a sensed total pressure signal as a sense air data parameter; and

processing the sensed total pressure signal for providing at least two air data parameter signals from among a plurality of air data parameter signals including an aircraft velocity signal indicative of aircraft velocity relative to an air mass, a static pressure signal indicative of static pressure of the air mass, and a free airstream temperature signal indicative of free airstream temperature of the air mass, thereby using only one sensed air data parameter in said method of determining air data parameters for an aircraft.

11. The method of claim 10, wherein said step of processing the sensed total pressure signal comprises the steps of providing, in response to said sensed total pressure signal, multiple order harmonic component pressure signals having magnitudes indicative of harmonic component representations of the total pressure on the rotating member and utilizing the multiple order harmonic component pressure signals for determining said at least two airdata parameter signals.

12. The method of claim 11, wherein the multiple order harmonic component pressure signals are indicative of steady state, first harmonic and second harmonic components of the sensed total pressure signal.

13. An apparatus having a rotary member, comprising:

multiple order harmonic component pressure determination means, and responsive to a sensed pressure signal indicative of a sensed pressure at the rotary member, for providing a first order harmonic component pressure signal indicative of a first order harmonic component of the sensed pressure at the rotary member, and further providing a second order harmonic component pressure signal indicative of a second order harmonic component of the sensed pressure at the rotary member; and

velocity determination means, responsive to the first order harmonic component pressure signal, and further responsive to the second order harmonic component pressure signal, for providing a velocity determination signal indicative of the velocity of the apparatus.

14. An apparatus according to claim 13, wherein said multiple order harmonic component pressure determination means further provides a steady state component pressure signal indicative of a steady state component of the sensed pressure at the rotary member;

and

wherein the apparatus further comprises static pressure determination means, responsive to the first order harmonic component pressure signal, and further responsive to the second order harmonic component pressure signal, and further responsive to the steady state component pressure signal, for providing a static pressure signal indicative of a static pressure at the rotary member.

15. An apparatus according to claim 13, wherein said harmonic component pressure determination means further provides a steady state component pressure signal indicative of a steady state component of the sensed pressure at the rotary member;

and

wherein the apparatus further comprises free airstream temperature determination means, responsive to the first order harmonic component pressure signal, and further responsive to the second order harmonic component pressure signal, and further responsive to the steady state component pressure signal, for providing a free airstream temperature signal indicative of a free airstream temperature at the rotary member.

16. An apparatus according to claim 14, wherein the apparatus further comprises free airstream temperature determination means, responsive to the first order harmonic component pressure signal, and further responsive to the second order harmonic component pressure signal, and further responsive to the steady state component pressure signal, for providing a free airstream temperature signal indicative of a free airstream temperature at the rotary member.