Apparatus for measuring lift forces based upon differential pressure between surfaces of an aircraft

• US 5,737,222 A
• Filed: 10/06/1995
• Issued: 04/07/1998
• Est. Priority Date: 11/18/1992
• Status: Expired due to Term

• Current Assignee: Aers/Midwest Incorporated
• Original Assignee: Aers/Midwest Incorporated
• Inventors: Palmer, Steven D.
• Primary Examiner(s): LOUIS JACQUES, JACQUES H
• Application Number:
  US08/540,262
• Time in Patent Office: 914 Days
• Field of Search: 364/424.03, 364/424.01, 364/435, 364/439, 364/427, 364/428, 364/551.01, 73/178 R, 73/178 T, 73/9, 73/65.06, 73/182, 73/861.65, 73/179, 244/12.1, 244/181, 244/182, 244/194, 244/204, 244/73 C, 244/219, 244/183, 244/23 R, 244/207, 244/208, 244/12.5, 244/45 R, 244/55, 244/198, 244/76 R, 244/195 , 244/203, 244/91, 244/199, 244/12.3, 244/53.3, 340/959, 340/967, 340/968, 340/960, 340/945, 180/116, 180/117
• US Class Current: 701/4
• CPC Class Codes: B64D 15/20 Means for detecting icing or initiating de-icing
• CPC Class Codes: B64D 43/02 for indicating aircraft speed or stalling conditions
• CPC Class Codes: G01M 9/06 Measuring arrangements specially adapted for aerodynamic testing

Abstract

An apparatus for measuring the lift generated by airfoils of an aircraft. This real-time analysis is accomplished by measuring a differential pressure between the upper and lower lift surfaces of the airfoils. The apparatus a) measures an actual differential pressure between the upper and lower lift surfaces for a given aircraft speed, b) transmits this actual differential pressure measurement to a computer, c) compares the actual differential pressure measurement with an optimal pressure differential for the same aircraft speed, and d) evaluates performance of the aircraft based on the result of the comparison. The apparatus comprises a fixed array of differential pressure sensor mechanisms for measuring actual pressure differentials and a computer for comparing optimal differential pressure measurements to the actual differential pressure measurements. Each sensor mechanism preferably contains a piezoelectric sensor that communicates with the upper and lower lift surfaces.

Claims

1. An apparatus for evaluating forces affecting an aircraft the apparatus comprising:

means for measuring an actual differential pressure between air pressures acting on two aircraft surfaces;

means for obtaining an actual aircraft speed;

means for storing differential pressure measurements for various actual aircraft speeds;

means for comparing said actual differential pressure measurement for said actual aircraft speed with the stored differential pressure measurement for that actual aircraft speed; and

means for evaluating performance of the aircraft based on the result of the means for comparing.

2. The apparatus of claim 1, wherein said comparing means is a computer, said storing means is a computer database, and said actual differential pressure measuring means comprises a pressure sensor located between an upper lift surface and a lower lift surface and tubes for communicating the upper and lower lift surface pressures to said pressure sensor.

3. The apparatus of claim 2, wherein said actual differential pressure measuring means is an array of pressure sensors spaced across the lift surfaces, said array of sensors measuring a lift pattern for each of said lift surfaces.

4. The apparatus of claim 3, wherein the lift surfaces are wing and tail sections.

5. The apparatus of claim 4, wherein said array of pressure sensors comprises wing leading edge sensors, wing trailing edge sensors and tail leading edge sensors, wherein one of said tubes for each of said wing and tail leading edge sensors communicates with the upper lift surface between said leading edge and an apex of the upper lift surface.

6. The apparatus of claim 5, further comprising means for comparing actual differential pressure measurements of said wing trailing edge sensors for said actual speed with a recognized stall differential pressure measurement for said actual speed to determine whether a potential stall condition is imminent.

7. The apparatus of claim 2, wherein said pressure sensor is a piezoelectric sensor.

8. The apparatus of claim 4, further comprising means for comparing a lift pattern of one wing with a lift pattern of a second wing to determine whether balanced lift patterns are being developed.

9. The apparatus of claim 4, further comprising means for comparing said actual differential pressure measurements of said wing pressure sensors with actual differential pressure measurements of said tail pressure sensors to determine if proper for-to-aft lift is being developed.

10. The apparatus of claim 1, further comprising means for storing actual differential pressure measurements for said various actual speeds for future comparison, said actual differential pressure measurements forming actual optimal differential pressure measurements for said various actual speeds, means for comparing a future actual differential pressure measurement for said actual speed with said actual optimal differential pressure measurement for said actual speed.

11. The apparatus of claim 10, further comprising means for informing the flight crew of anomalies between said future actual differential pressure measurement and said actual optimal differential pressure measurement.

12. The apparatus of claim 1, further comprising means for storing recognized anomaly differential pressure measurements of a recognized anomaly condition for various actual speeds, means for comparing said actual differential pressure measurements for said actual speed with said recognized anomaly differential pressure measurement for said actual speed to determine whether said recognized anomaly condition exists, and means for informing the flight crew when said recognized anomaly condition exists.

13. The apparatus of claim 1, further comprising means for displaying said actual differential pressure measurements onboard said aircraft.