Turboelectric arresting gear

• US 20060131462A1
• Filed: 12/20/2004
• Published: 06/22/2006
• Est. Priority Date: 12/20/2004
• Status: Abandoned Application

• Current Assignee: General Atomics, Inc.
• Original Assignee: General Atomics, Inc.
• Inventors: Holland, Leo D., Rodriguez, Carmelo
• Application Number:
  US11/017,435
• Publication Number:
  US 20060131462A1
• Time in Patent Office: Days
• US Class Current: 244/110.G
• CPC Class Codes: B64F 1/029 using a cable or tether

Abstract

An arresting gear for quickly decelerating a moving object includes an elongated shaft that defines a rotation axis. A tapered drum that is wound with a purchase cable is mounted on the shaft for rotation about the axis. The drum and the shaft are rotated during the pay out of cable from the drum as the moving object engages and then pulls on the cable. The arresting gear includes an energy-dissipating fluid turbine, such as a water twister, that is mounted on the shaft to apply a torque on the shaft that acts to decelerate the rotating shaft. To complement the energy-dissipating fluid turbine, an electric motor is coupled to the shaft for creating a decelerating torque on the shaft. An electric motor control system is configured to use motor rotation feedback from the electric motor to pay out the cable from the drum at a substantially constant tension.

Claims

1. A system for controlling the pay out tension of a line used to decelerate a moving object, said system comprising:

an elongated shaft defining a rotation axis;

a drum configured to allow a portion of the line to be wound thereon, said drum mounted on said shaft for rotation about said axis;

an energy-dissipating fluid turbine mounted on said shaft for creating a decelerating torque on said shaft when said line is pulled by the moving object; and

an electric motor mounted on said shaft for creating a decelerating torque on said shaft when said line is pulled by the moving object.

2. A system as recited in claim 1 further comprising a mechanical brake for creating a decelerating torque on said shaft when said line is pulled by the moving object.

3. A system as recited in claim 2 wherein said mechanical brake comprises a disk brake system having a disk mounted on said shaft.

4. A system as recited in claim 1 wherein said moving object is a landing aircraft and said line is a steel cable.

5. A system as recited in claim 1 further comprising an inverter, a capacitor bank, at least one resistor and an electric motor control system configured to energize said electric motor using said inverter to produce an accelerating torque on said shaft after said line is initially pulled by said moving object to provide a smooth engagement between the line and object and thereafter feed power from said motor to said capacitor bank and said resistor to decelerate said shaft.

6. A system as recited in claim 1 further comprising an electric motor control system configured to use motor rotation feedback from said electric motor to pay out said line from said drum at a substantially constant tension.

7. A system as recited in claim 1 wherein said drum is tapered.

8. A system as recited in claim 1 wherein said electric motor is an induction motor.

9. A system as recited in claim 1 wherein said energy-dissipating fluid turbine is a water twister.

10. An arresting gear comprising:

a pendant positionable for engagement with an arresting hook on a landing aircraft;

a first line and a second line, each line extending from said pendant;

a first arresting engine coupled with said first line; and

a second arresting engine having a shaft coupled to said second line, said second arresting engine having an energy-dissipating fluid turbine mounted on said shaft for creating a decelerating torque on said shaft when said second line is pulled by the landing aircraft and an electric motor mounted on said shaft for creating a decelerating torque on said shaft when said second line is pulled by the landing aircraft.

11. An arresting gear as recited in claim 10 wherein said pendant is a steel cross pendant.

12. An arresting gear as recited in claim 10 wherein said second line is a synthetic purchase cable.

13. An arresting gear as recited in claim 10 wherein said shaft is a first shaft, said first arresting engine comprises a second shaft coupled to said first line, said first arresting engine comprises an energy-dissipating fluid turbine mounted on said second shaft for creating a decelerating torque on said second shaft when said first line is pulled by the landing aircraft, and said first arresting engine comprises an electric motor mounted on said first shaft for creating a decelerating torque on said second shaft when said first line is pulled by the landing aircraft.

14. An arresting gear as recited in claim 10 wherein said second arresting engine comprises a tapered drum to couple said shaft to said second line.

15. An arresting gear as recited in claim 10 wherein said second arresting engine further comprises a mechanical brake for creating a decelerating torque on said shaft when said second line is pulled by the landing aircraft.

16. An arresting gear as recited in claim 10 wherein said electric motor is an induction motor.

17. An arresting gear as recited in claim 10 wherein said energy-dissipating fluid turbine is a water twister.

18. An arresting engine for controlling the pay out of a line used to arrest a landing aircraft, said arresting engine:

a shaft;

a means for coupling the line to said shaft wherein said shaft rotates during pay out of said line from said shaft;

an energy-dissipating fluid turbine for creating a decelerating torque on said shaft during pay out of said line from said shaft; and

a motor for creating a decelerating torque on said shaft during pay out of said line from said shaft.

19. An arresting engine as recited in claim 18 further comprising a mechanical brake for creating a decelerating torque on said shaft when said line is pulled by the landing aircraft.

20. An arresting engine as recited in claim 18 further comprising an electric motor control system configured to cause said electric motor to produce an accelerating torque on said shaft after said line is initially pulled by said landing aircraft followed by a decelerating torque on said shaft.