System for onboard lift analysis and apparatus therefor

• US 5,457,630 A
• Filed: 11/18/1992
• Issued: 10/10/1995
• 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): Teska, Kevin J.
• Assistant Examiner(s): LOUIS JACQUES, JACQUES H
• Application Number:
  US07/978,347
• Time in Patent Office: 1,056 Days
• Field of Search: 364/424.03, 364/424.02, 364/424.01, 364/551.01, 364/426.01, 364/435, 364/433, 364/434, 364/473, 364/476, 364/427, 364/424.06, 244/201, 244/203, 244/194, 244/195, 244/12.1, 244/198, 180/116, 180/117, 73/178
• US Class Current: 701/3
• 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

A method and 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 system comprises the steps of: a) measuring an actual differential pressure between the upper and lower lift surfaces for a given aircraft speed, b) transmitting this actual differential pressure measurement to a computer, c) comparing the actual differential pressure measurement with an optimal pressure differential for the same aircraft speed. 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. A system for evaluating lift development of lift surfaces of an aircraft, the system comprising the steps of:

measuring an actual pressure being exerted on at least one lift surface,

obtaining actual aircraft speed,

transmitting said actual pressure measurement and said actual speed to a computer, said computer having a database containing optimal pressure measurements for various speeds,

comparing said actual pressure measurement for said actual speed with an optimal pressure measurement for said actual speed to determine whether proper lift is being developed.

2. The system of claim 1, wherein said actual pressure measurement is a differential pressure measurement between an upper lift surface and a lower lift surface.

3. The system of claim 2, wherein said step of measuring actual pressure is performed by an array of sensors that measure an actual lift pattern of the aircraft, and further comprising the steps of:

measuring said actual lift pattern for said actual speed;

transmitting said actual lift pattern to said computer, said computer database having optimal lift patterns for various actual speeds; and

,

comparing said actual lift pattern with an optimal lift pattern for said actual speed to determine whether proper lift is being developed.

4. The system of claim 3, wherein said lift surfaces are wings and tail sections of an aircraft.

5. The system of claim 4, wherein a separate actual lift pattern is developed for each of said wings, and further comprising the step of comparing each of said actual wing lift patterns with each other to determine whether properly balanced lift is being developed.

6. The system of claim 4, wherein said actual pressure measurement of said wings are compared with said actual pressure measurements for said tail sections to determine whether proper for-to-aft lift is being developed.

7. The system of claim 4, wherein said wings have a trailing edge and a sensor is located near said trailing edge to determine whether a stall condition exists.

8. The system of claim 1, further comprising the steps of:

storing actual pressure measurements for said various actual speeds to develop actual optimal pressure measurements for future comparison; and

,

comparing future actual pressure measurements for a given actual speed with said actual optimal pressure measurement for said given actual speed to determine whether proper lift is being developed.

9. The system of claim 1, further comprising the steps of determining whether said actual pressure measurement is abnormal and informing a flight crew when said actual pressure measurement is abnormal.

10. The system of claim 9, further comprising the steps of:

storing recognized abnormal pressure measurements for various speeds;

comparing said actual abnormal pressure measurement for said actual speed with a recognized abnormal pressure measurement for said actual speed to determine a possible cause of said actual abnormal pressure measurement; and

,

informing said flight crew of said possible cause of said abnormal pressure measurement.

11. The system of claim 10, further comprising the step of informing said flight crew of an appropriate countermeasure to said recognized abnormal pressure measurement.

12. The system of claim 9, further comprising the step of permanently storing said abnormal pressure measurement in said computer and transmitting said abnormal pressure measurement to a ground facility.

13. The system of claim 1, wherein said lift surfaces can be manipulated into various configurations, and said optimal pressure measurements are further correlated to said various lift surface configurations by said computer database, and said system comprises the additional steps of determining an actual lift surface configuration for said actual speed, and comparing said actual pressure measurement for said actual lift surface configuration and speed with said optimal pressure measurement for said actual lift surface configuration and speed to determine whether proper lift is being developed.

14. The system of claim 1, wherein said optimal pressure measurements are further correlated to various fluid conditions by said computer database, and said system further comprises the step of determining actual fluid conditions for said actual speed, and comparing said actual pressure measurement for said fluid conditions and said actual speed with said optimal pressure measurement for said actual fluid conditions and said actual speed to determine whether proper lift is being developed.

15. The system of claim 1, wherein said optimal pressure measurements are further correlated to various aircraft angles of attack and ground effects by said computer database, and said system further comprises the step of determining an actual angle of attack and ground effect for said actual speed, and comparing said actual pressure measurement for said actual angle of attack, actual ground effect and actual speed with said optimal pressure measurement for said actual angle of attack, actual ground effect and actual speed to determine whether proper lift is being developed.