Login| Sign Up| Help| Contact|

Patent Searching and Data


Title:
IN FLIGHT REFUELING PROBE FOR AN AIRCRAFT
Document Type and Number:
WIPO Patent Application WO/2014/133632
Kind Code:
A4
Abstract:
An in flight refueling probe 20 for an aircraft includes a circular shaped hollow tubular member 22, 31, 46 having a first end attached to the aircraft and a second end extending from the aircraft terminating in an external convex shape 66 with a plurality of first holes 87B equally spaced thereabout. A cylindrical member 70 having a first end with an internal curved surface convex shaped end 73 of the tubular member with a plurality of second holes 87A there through in alignment with the plurality of first holes in the second end of the tubular member with fasteners 86 installed in the holes joining the cylindrical member to the tubular member. The fasteners have a strength limited to a value that will break under a specific load on the probe. A nozzle assembly 90 is mounted to the second end of the cylindrical member for coupling to the receptacle on a fuel dispensing aircraft.

Inventors:
THORNTON, Hope, T. (10856 Canarywood Court, San Diego, California, 92131, US)
LANG, Warren (5208 Sanddollar Court, San Diego, California, 92130, US)
HOLT, Bryan (5822 Mission Center Road, Unit FSan Diego, California, 92123, US)
Application Number:
US2013/074802
Publication Date:
December 31, 2014
Filing Date:
December 12, 2013
Export Citation:
Click for automatic bibliography generation   Help
Assignee:
NORTHROP GRUMMAN SYSTEMS CORPORATION (2980 Fairview Park Drive, Falls Church, Virginia, 22042-4511, US)
International Classes:
B64D39/06
Attorney, Agent or Firm:
HARRIS, Christopher, P. (Tarolli, Sundheim Covell & Tummino LLP,1300 East Ninth Street,Suite 170, Cleveland Ohio, 44114, US)
Download PDF:
Claims:
AMENDED CLAIMS

received by the International Bureau on 01 December 2014 (01.12.14)

CLAIMS

1. An in flight refueling probe for an aircraft to be refueled by a fuel dispensing aircraft having receptacle for connecting to the refueling probe said refueling probe comprising:

a circular shaped tubular member having first and second ends, said first end mounted to the aircraft and said second end extending from the aircraft, said tubular member having an internal passage extending from said first end to said second end with said second end terminating in an external convex shape, said external convex shaped second end having a plurality of first holes equally spaced thereabout, wherein said external convex shaped end of said tubular member is spherical shaped;

a nozzle assembly mounted to said first end of said cylindrical member for coupling to said receptacle on fuel dispensing aircraft;

a cylindrical member having first and second ends, said first end having an internal concave surface engaged with said external convex shaped end of said tubular member; said first end of said cylindrical member having a plurality of second holes there through in alignment with said plurality of first holes in said second end of said tubular member, wherein said concave end of said cylindrical member is spherical shaped; and

a plurality of fasteners extending through said first and second holes joining said first end of said cylindrical member to said second end of said tubular member; the fasteners having a strength limited to a value that will break under a specific load on said nozzle.

2. The in flight refueling probe as set forth in Claim 1 , wherein sealing means are incorporated between said concave and said convex surface.

3. The in flight refueling probe as set forth in Claim 1, wherein said fasteners are rivets.

9

4. A structure comprising:

a first structural element, said first structural element is a circular shaped tubular member having first and second ends, said tubular member having an internal passage extending from said first end to said second end with said second end terminating in an external convex shape, said external convex shaped second end having a plurality of first holes equally spaced thereabout, wherein said external convex shaped end of said tubular member is spherical shaped; a second structural element, said second structural element is a cylindrical member having first and second ends, said first end having an internal concave surface engaged with said external convex shaped end of said tubular member; said first end of said cylindrical member having a plurality of second holes there through in alignment with said plurality of first holes in said second end of said tubular member, wherein said concave end of said cylindrical member is spherical shaped; and

a plurality of fasteners joining said first and second structural elements together, said plurality of fasteners extending through said first and second holes joining said first end of said cylindrical member to said second end of said tubular member; the fasteners having a strength limited to a value that will break under a specific load to said first or second member.

5. The structure as set forth in Claim 4, wherein sealing means are incorporated between said concave and said convex surface.

6. The structure as set forth Claim 5, wherein said fasteners are rivets.

7. The in flight refueling probe as set forth in Claim 1, wherein said refueling probe further comprises an elastic band, said elastic band positioned over said plurality of fasteners and configured to prevent said plurality of fasteners from separating from said first end of said cylindrical member.

10