Aircraft ground power unit

• US 6,424,891 B1
• Filed: 03/30/2000
• Issued: 07/23/2002
• Est. Priority Date: 03/31/1999
• Status: Expired due to Term

• Current Assignee: United States Air Force
• Original Assignee: United States Of America As Represented By The Secretary Of The Air Force
• Inventors: Sargent, Paul E., Hurley, Timothy C., Iselo, Michael J., Brown, Anthony N.
• Primary Examiner(s): Camby, Richard M.
• Application Number:
  US09/538,527
• Time in Patent Office: 845 Days
• Field of Search: 701/3, 701/29, 701/35, 280/838, 280/839, 280/837
• US Class Current: 701/29
• CPC Class Codes: B64F 1/34 for starting propulsion plant
• CPC Class Codes: B64F 1/352 Mobile units
• CPC Class Codes: B64F 1/364 Mobile units
• CPC Class Codes: G01M 17/00 Testing of vehicles testing fluid tightness G01M3/00; testing elastic properties of bodies or chassis, e.g. torsion-testing, G01M5/00; testing alignment of vehicle headlight devices G01M11/06; testing of engines G01M15/00

Abstract

An Aircraft Ground Power Unit (“AGPU”) is a mobile vehicle, preferably self-propelled, on which is mounted an enclosure. Within the enclosure are a number of subsystems, each of which provides a service required by a stationary aircraft for servicing and diagnostic testing prior to flight. Such services include electrical power, hydraulic power, engine-start capability (bleed-air), conditioned air (hot or cold) for the aircraft'"'"'s equipment recesses or interior, and nitrogen to inflate struts and operate power tools. The control, status, configuration, and automation of all of the subsystems contained within the enclosure are consolidated under computer control. The enclosure and the subsystems contained therein can be readily mounted on and dismounted from the vehicle.

Claims

1. Apparatus for servicing an aircraft, which comprises:

a self-propelled vehicle;

a service unit detachably mounted to said vehicle;

said service unit further comprising a computer,

said computer comprising a first capability for executing a program stored in a database, said database being particular to a chosen aircraft, and a second capability comprising communicating with, configuring, controlling and monitoring said service unit and said chosen aircraft when servicing said chosen aircraft; and

said service unit being capable of providing a plurality of outputs,

said outputs comprising pneumatic, fluidic and electrical aircraft servicing outputs.

2. Apparatus as in claim 1, wherein said service unit further comprises:

a prime mover that produces a power output and a bleed-air output;

coupled to said power output;

a hydraulic pump for producing a fluid hydraulic pressure output; and

a generator for producing an alternating current;

a rectifier for converting said alternating current to direct current;

a source of nitrogen; and

connecting means to provide at least one of said plurality of outputs to said chosen aircraft.

3. Apparatus as in claim 2, wherein said service unit further comprises:

at least one first transducer for monitoring said service unit;

at least one second transducer for monitoring said chosen aircraft;

said at least one first and second transducers communicating with said computer; and

an interface to facilitate an operator'"'"'s interaction with said computer.

4. Apparatus as in claim 2, further comprising:

detachably mounted to said service unit, an air cycle machine whose input is coupled to said prime mover'"'"'s bleed-air output.

5. Apparatus as in claim 2, further comprising a valve to regulate said bleed-air output.

6. Apparatus as in claim 1, wherein said service unit is within an enclosure.

7. Apparatus as in claim 2, wherein said connecting means includes a hook-up panel having at least one connector effective for detachably connecting said service unit to said chosen aircraft.

8. Apparatus as in claim 1, wherein said vehicle further comprises:

a motor;

traction means for moving said vehicle over improved and unimproved terrain;

a transmission for supplying power from said motor to said traction means; and

an internal fuel reservoir.

9. Apparatus for servicing an aircraft, which comprises:

at least one program installed in at least one computer;

an aircraft servicing database stored in said at least one computer;

a service unit configured according to said database to service a chosen aircraft in response to instructions in said at least one program;

wherein said service unit provides a plurality of pneumatic, fluidic and electrical aircraft servicing outputs, said aircraft servicing outputs further comprising;

bleed air,

pressurized hydraulic fluid,

nitrogen,

alternating current,

direct current; and

said service unit further comprising a means for detachably mounting on a self-propelled vehicle.

10. Apparatus for servicing an aircraft, which comprises:

at least one computer;

a first means, interactive with said at least one computer, for configuring

at least one service unit to service a chosen aircraft,

said first means further comprising a second means for executing within said at least one computer, a program stored in a database, said database being particular to said chosen aircraft; and

a third means, interactive with said first means and said second means, for communicating with, controlling and monitoring said service unit and said chosen aircraft when servicing said chosen aircraft.

11. Apparatus as in claim 10, further comprising an operator interface, said operator interface being interactive with said at least one computer, said first, said second and said third means.

12. Apparatus as in claim 11, further comprising a display means interactive with said operator interface.

13. A method for servicing an aircraft, comprising the steps of:

installing at least one program in at least one computer;

storing an aircraft servicing database in said at least one computer;

configuring a service unit according to said database to service a chosen aircraft; and

applying said service unit to service said chosen aircraft as directed by said at least one program, wherein said step of applying further comprises the step of;

providing a plurality of pneumatic, fluidic and electrical aircraft servicing outputs to said chosen aircraft.

14. The method of claim 13, wherein said step of applying further includes the step of instructing said computer via an operator interface.

15. The method of claim 13, further including, prior to said step of configuring, detachably mounting said service unit on a self-propelled vehicle.

16. The method of claim 13, wherein said step of configuring further includes the step of instructing said computer via an operator interface.

17. The method of claim 13, wherein said step of applying further includes the step of informing an operator via a display.