METHOD FOR EXPANDING AIRCRAFT CENTER OF GRAVITY LIMITATIONS

• US 20150100227A1
• Filed: 10/08/2014
• Published: 04/09/2015
• Est. Priority Date: 10/09/2013
• Status: Abandoned Application

• Current Assignee: Nance C. Kirk
• Original Assignee: Nance C. Kirk
• Inventors: Nance, C. Kirk
• Application Number:
  US14/509,482
• Publication Number:
  US 20150100227A1
• Time in Patent Office: Days
• US Class Current: 701/124
• CPC Class Codes: B64D 2045/008 Devices for detecting or indicating hard landing
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: G01M 1/125 of aircraft

Abstract

A method which creates a justification basis to expand an aircraft'"'"'s Center of Gravity limitations, which are established by the aircraft designer; relating to aircraft landing gear strength assumptions. Strut load sensors such as pressure sensors are mounted in relation to each of the landing gear struts to monitor, measure and record aircraft landing gear strut compression loads. A history of measured landing gear load values is compiled and related to any assumed landing gear loads, which define the life-cycle limit of the landing gear, allowing relief from existing aircraft Center of Gravity limitation caused by landing gear strength assumptions to further expanded CG limitations beyond current limits, based on measured landing gear loads.

Claims

1. A method of expanding a center of gravity (CG) limitation of an aircraft, the aircraft having landing gear struts, the aircraft having a first CG limitation that is determined by a designer of the aircraft, the first CG limitation based upon assumed loads on the landing gear struts, comprising the steps of:

a) operating the aircraft;

b) during the operation of the aircraft, measuring the loads on the landing gear struts;

c) determining if the measured loads have exceeded the assumed loads;

d) if the measured loads have not exceeded the assumed loads, then determining a second CG limitation that exceeds the first CG limitation;

e) operating the aircraft at an expanded CG which exceeds the first CG limitation but is within the second CG limitation.

2. The method of expanding a center of gravity (CG) limitation of an aircraft of claim 1, wherein the step of measuring the loads on the landing gear struts further comprises measuring the pressure in the landing gear struts.

3. The method of expanding a center of gravity (CG) limitation of an aircraft of claim 1, wherein the step of measuring the loads on the landing gear struts further comprises measuring acceleration of the landing gear struts.

4. The method of expanding a center of gravity (CG) limitation of an aircraft of claim 1, wherein the step of measuring the loads on the landing gear struts further comprises measuring strain in the landing gear struts.

5. The method of expanding a center of gravity (CG) limitation of an aircraft of claim 1, further comprising the step of continuing to measure the loads on the landing gear struts while operating the aircraft at the expanded CG to determine a load history of the landing gear struts.

6. The method of expanding a center of gravity (CG) limitation of an aircraft of claim 5, further comprising the step of comparing the measured loads applied on the landing gear struts to the assumed loads on the landing gear struts, to further identify any exceedance.

7. The method of expanding a center of gravity (CG) limitation of an aircraft of claim 6, further comprising the step of comparing the measured loads on the landing gear struts with the assumed loads on the landing gear struts, to verify landing gear strength assumptions have not be reached nor exceeded.

8. The method of expanding a center of gravity (CG) limitation of an aircraft of claim 1, wherein if the measured loads have exceeded the assumed loads, then reducing a life limit of the landing gear struts or reducing the expanded CG limitation.

9. The method of expanding a center of gravity (CG) limitation of an aircraft of claim 1, wherein the first and second CG limitations are aft CG limitations.

10. The method of expanding a center of gravity (CG) limitation of an aircraft of claim 1, wherein operating the aircraft at the expanded CG consumes less fuel than operating the aircraft at a CG that is within the first CG limit.