METHOD TO RECOVER NON-RECOGNIZED ERRORS IN AIRCRAFT WEIGHT DETERMINATIONS TO INCREASE WEIGHT AND CENTER OF GRAVITY LIMITATIONS FOR REGULATED AIRCRAFT

• US 20170116617A1
• Filed: 10/27/2015
• Published: 04/27/2017
• Est. Priority Date: 10/27/2015
• Status: Active Grant

• Current Assignee: Nance C. Kirk
• Original Assignee: Nance C. Kirk
• Inventors: Nance, C. Kirk
• Granted Patent: US 10,089,634 B2
• Time in Patent Office: Days
• CPC Class Codes: G01G 19/07 for weighing aircraft
• CPC Class Codes: G06Q 30/018 Certifying business or products

Abstract

A method of establishing a justification basis to Aircraft Regulatory Authorities, to allow a regulated aircraft to operate at increased maximum weight limitations, through the statistical identification of non-recognized weight errors being allowed in today'"'"'s aircraft weight determination methods, with the recovery and utilization of the non-recognized weight errors to increase weight limitations through a Regulatory Authority finding of an Equivalent Level of Safety. A system for use in measuring aircraft weight and center of gravity, providing a method to reveal non-recognized weight errors. Sensors are attached to the landing gear struts, so to periodically and randomly measure and monitor aircraft weight and center of gravity.

Claims

1. A method of obtaining a change in certification weight limits of an aircraft model from a Regulatory Authority, the aircraft model comprising plural aircraft, each aircraft of the aircraft model capable of carrying a payload, the aircraft model having a first maximum weight limit, comprising the steps of:

a. For an aircraft of the aircraft model near the first maximum weight limit, obtaining statistical data on the weight of the payload carried by the aircraft;

b. Repeating step a) for a number of flights of aircraft of the aircraft model;

c. For the same respective flights, obtaining computed data on the weight of the payload;

d. For each flight, comparing the statistical data on payload weight to the computed data on payload weight and determining a weight error;

e. Using the statistical weight data, the computed weight data and the weight error, obtaining certification from the Regulatory Authority for the aircraft model to operate within the amount of the weight error and above the first maximum weight limit.

2. The method of claim 1 wherein the step of obtaining statistical data on the eight of the payload carried by the aircraft further comprises the step of using a random number generator to provide the payload weights, the random number generator using a predetermined mean and, a predetermined standard deviation.

3. The method of claim 1 wherein, the step of obtaining statistical data on the weight of the payload carried by the aircraft further comprises the step of measuring the actual weights of the payloads.

4. The method of claim 1 wherein the step of obtaining computed data on the weight of the payload further comprises the step of using Regulatory Authority prescribed weights in a load build up method.

5. The method of claim 1 wherein the first maximum weight limit comprises a first maximum to weight limit.

6. The method of claim 1 wherein the first maximum weight limit comprises a first maximum landing weight limit.

7. The method of claim 1 wherein the first maximum weight limit comprises a first maximum zero-fuel weight limit.

8. The method of claim 1 wherein the first maximum weight limit comprises a first maximum ramp weight limit.

9. The method of claim 1 further comprising the step of determining when an aircraft of the aircraft model is near the first maximum weight limit by obtaining computed weight data for aircraft of the aircraft model.

10. A method of planning for operations of an aircraft model so that individual aircraft of the aircraft model operate within acceptable maximum weight limitations, comprising the steps of:

a. Operating aircraft of the aircraft model and obtaining and using computed weights of the aircraft to operate the aircraft and ensure the aircraft is within the maximum weight limitations, the computed weights of the aircraft comprising assumptions of payload weights;

b. Sampling the operations of the aircraft of the aircraft model by measuring the weight of at least some of the aircraft of the aircraft model;

c. For the sampled operations, comparing the measured weights to the computed weights and determining a weight error;

d. Using the weight error to modify the assumptions of payload weights and using the modified weight assumptions to determine improved computed weights of the aircraft in subsequent aircraft operations.

11. The method of claim 10 wherein the assumptions of payload wet its comprises passenger weights.

12. The method of claim 10 wherein the assumptions of payload weights comprises baggage weights.

13. The method of claim 10 wherein the step of measuring the weight of at least some of the aircraft of the aircraft model further comprises the step of measuring the weight supported by landing gear of the aircraft.

14. A method of operating an aircraft the aircraft having a first maximum take-off weight limitation based upon Regulatory Authority certification limits, comprising the steps of:

a) Before dispatching the aircraft for flight, operations, determining a computed weight of the aircraft, the computed weight comprising assumptions as to weights of a payload on the aircraft;

b) Identifying weight error in computed payload weights of the, aircraft, the computed payload weights using assumed weights for payload;

c) Determining that the computed weight of the aircraft is within the first maximum take-off limitation plus the weight error;

d) Dispatching the aircraft if the computed weight of the aircraft is below the sum of the first maximum take-off limitation and the weight error, periodically obtaining the measured aircraft take-off weight through a weight verification reliability program database;

e) comparing the computed aircraft take-off weight to the measured aircraft take-off weight stored within the weight verification reliability program;

f) identifying from the measured aircraft weight, the non-recognized weight errors allowed by the computed aircraft take-off weight;

g) identifying the statistical error found in the compiled payload weight assumptions;

h) based upon use of measured aircraft take-off weight, operating the aircraft at a higher, second maximum take-off weight equivalent to some portion of the statistical error in the assumptions of the non-recognized weight.

15. The method of claim 14 wherein the aircraft belongs to an aircraft model which aircraft model comprises substantially similar aircraft, further comprising the steps of:

a) Sampling the operations of the aircraft of the aircraft model by measuring the weight of at least some of the aircraft of the aircraft model;

b) For the sampled operations, comparing the measured weights to the computed weights and verifying that the aircraft take-off weight is below the sum of the first maximum take-off limitation and the weight error.

16. The method of claim 14 further comprising the step of using the weight error to increase corresponding aircraft center-of-gravity limitations.