External load mass rope of a rotorcraft

• US 9,845,154 B2
• Filed: 05/13/2015
• Issued: 12/19/2017
• Est. Priority Date: 05/14/2014
• Status: Active Grant

• Current Assignee: Airbus Helicopters Deutschland Gmbh (Airbus SE)
• Original Assignee: Airbus Helicopters Deutschland Gmbh (Airbus SE)
• Inventors: Behrens, Michael, Wahnfried, Markus
• Primary Examiner(s): Dinh, Tien Q
• Assistant Examiner(s): Green, Richard R
• Application Number:
  US14/711,243
• Publication Number:
  US 20150360779A1
• Time in Patent Office: 951 Days
• CPC Class Codes: B64C 1/22 Other structures integral with fuselages to facilitate loading , e.g. cargo bays, cranes
• CPC Class Codes: B64D 1/22 Taking-up articles from earth's surface
• CPC Class Codes: B64D 9/00 Equipment for handling freight; Equipment for facilitating passenger embarkation or the like emergency equipment B64D17/00, B64D19/00, B64D25/00; structures integral with fuselage to facilitate loading, fuselage floors specially adapted for freight, steps mounted on and retractable within aircraft B64C; ground installations B64F

Abstract

An external load mass rope for attachment to a cargo hook device of a rotorcraft that comprises at least one first cargo hook and at least one second cargo hook, the external load mass rope comprising at least one first rope leg and at least one second rope leg, wherein the at least one first rope leg is adapted for attachment to the at least one first cargo hook and the at least one second rope leg is adapted for attachment to the at least one second cargo hook, characterized in that at least one of the first and second rope legs comprises an associated length adjustment unit that is adapted to shorten or lengthen the at least one of the first and second rope legs in operation on the basis of associated operating parameters.

Claims

1. An external load mass rope for attachment to a cargo hook device of a rotorcraft that comprises at least one first cargo hook and at least one second cargo hook, the external load mass rope comprising at least one first rope leg and at least one second rope leg, wherein the at least one first rope leg is configured for attachment to the at least one first cargo hook and the at least one second rope leg is configured for attachment to the at least one second cargo hook, wherein at least one third rope leg is connected to the at least one first rope leg and the at least one second rope leg such that the at least one first, second and third rope legs define a Y-rope, the at least one third rope leg comprising an external load mass interface for attachment to an external load mass that is to be carried by the rotorcraft in operation, wherein the first rope leg comprises a first length adjustment unit in-line with the first rope leg and that is adapted to shorten or lengthen the first rope leg in flight operation of the rotorcraft on the basis of associated operating parameters, and wherein the second rope leg comprises a second length adjustment unit in-line with the second rope leg and that is adapted to shorten or lengthen the second rope leg in flight operation of the rotorcraft on the basis of the associated operating parameters, the first and second length adjustment units defining a length adjustment device;

wherein the external load mass is deflected in forward flight direction or backward flight direction of the rotorcraft in operation by an associated external load mass deflection angle; and

wherein the cargo hook device is configured as a double cargo hook arrangement defining a forward cargo hook attachment point and an aft cargo hook attachment point, the first rope leg of the external load mass rope being a forward leg configured for attachment to the forward cargo hook attachment point using the at least one first cargo hook and with the first length adjustment unit being adapted to shorten or lengthen the forward rope leg in flight operation, the second rope leg of the external load mass rope being an aft leg configured for attachment to the aft cargo hook attachment point using the at least one second cargo hook and with the second length adjustment unit being adapted to shorten or lengthen the aft rope leg in flight operation.

2. The external load mass rope according to claim 1, wherein the first and second length adjustment units comprise shortening and lengthening capacities that are defined as a function of a predetermined clearance between the at least one first cargo hook and the at least one second cargo hook.

3. The external load mass rope according to claim 1, wherein the first and second length adjustment units are adapted to shorten or lengthen the first and second rope legs in flight operation on the basis of the associated operating parameters for distributing a payload that is applied to the external load mass rope to the at least one first rope leg and the at least one second rope leg.

4. The external load mass rope according to claim 1, wherein the associated operating parameters comprise at least weight and dimensions of the external load mass and/or the external load mass deflection angle.

5. The external load mass rope according to claim 4, wherein the first and second length adjustment units are adapted to shorten or lengthen the first and second rope legs in flight operation depending at least on the weight and dimensions of the external load mass and/or the external load mass deflection angle for distributing a payload that is applied to the external load mass rope by the external load mass to the at least one first rope leg and the at least one second rope leg.

6. The external load mass rope according to claim 1, wherein the first length adjustment unit and/or the second length adjustment unit is defined by a rope material having predefined lengthening properties for elastic elongation.

7. The external load mass rope according to claim 6, wherein the rope material comprises polyamide.

8. The external load mass rope according to claim 1, wherein the first length adjustment unit and/or the second length adjustment unit comprises at least one spring coil damper having predefined dampening properties.

9. The external load mass rope according to claim 8, wherein the predefined dampening properties are configured to enable the length adjustment device to distribute a payload that is applied in operation to the external load mass rope to the at least one first rope leg and the at least one second rope leg such that the payload may exceed a maximum payload that is applicable to each one of the at least one first and second cargo hooks separately.

10. The external load mass rope according to claim 1, wherein the first length adjustment unit and/or the second length adjustment unit comprises at least one pulley block arrangement, wherein at least a part of the at least one first rope leg and/or the at least one second rope leg is enrolled on the at least one pulley block arrangement.

11. The external load mass rope according to claim 10, wherein at least the part of the at least one first rope leg and/or the at least one second rope leg that is enrolled on the at least one pulley block arrangement comprises a rope material having predefined lengthening properties for elastic elongation, in particular polyamide.

12. The external load mass rope according to claim 10, wherein the at least one pulley block arrangement comprises a plurality of pulleys on which the part of the at least one first rope leg and/or the at least one second rope leg is enrolled.

13. The external load mass rope according to claim 1 wherein a distal end of each of the first, second, and third rope legs are directly coupled to an interface to connect the first, second, and third legs together such that the distal ends of each of the first, second, and third rope legs are fixed relative to one another.

14. A rotorcraft comprising:

a cargo hook device connected to one of a fuselage and a landing gear and having a double cargo hook arrangement with a forward cargo hook attachment point and an aft cargo hook attachment point spaced apart from one another longitudinally;

an external load mass rope having a first rope leg, a second rope leg, and a third rope leg, a first end of each of the first, second and third rope legs coupled to one another such that the external mass rope defines a Y-rope, the first rope leg having a first length adjustment unit, in-line with the first rope leg and the second rope leg having a second length adjustment unit in-line with the second rope leg;

a forward cargo hook attaching a second end of the first rope leg of the external load mass rope to the forward cargo attachment point;

an aft cargo hook attaching a second end of the second rope leg of the external load mass rope to the aft cargo attachment point;

an external load mass interface connected to a second end of the third rope leg, the external load mass interface configured to attach an external load mass to be carried by the rotorcraft in flight operation;

wherein the first length adjustment unit is configured to shorten or lengthen the first rope leg during flight operation of the rotorcraft on the basis of associated operating parameters; and

wherein the second length adjustment unit is configured to shorten or lengthen the second rope leg during flight operation of the rotorcraft on the basis of associated operating parameters.

15. The rotorcraft of claim 14 wherein the external load mass is deflected in forward flight direction or backward flight direction of the rotorcraft in operation by an associated external load mass deflection angle;

wherein the first length adjustment unit is configured to lengthen and the second length adjustment unit is configured to shorten in response to forward flight direction of the rotorcraft; and

wherein the first length adjustment unit is configured to shorten and the second length adjustment unit is configured to lengthen in response to backward flight direction of the rotorcraft.

16. The rotorcraft of claim 14 wherein the first and second length adjustment units are configured to vary a length of the first and second rope legs, respectively, with a variation in an external load mass deflection angle of the external load relative to the rotorcraft in forward or backward flight and thereby divide and distribute a mass of the external load to the forward and aft cargo hooks.

17. The rotorcraft of claim 14 wherein each of the first and second length adjustment units comprise a spring coil damper.

18. The rotorcraft of claim 17 wherein the spring coil damper of each of the first and second length adjustment units comprises a housing containing a spring coil connected to a piston, the housing defining a first connection hook and the piston defining a second connection hook.

19. A rotorcraft comprising:

a cargo hook device connected to one of a fuselage and a landing gear and having a double cargo hook arrangement with a forward cargo hook attachment point and an aft cargo hook attachment point spaced apart from one another longitudinally;

an external load mass rope having a first rope leg, a second rope leg, and a third rope leg, a first end of each of the first, second and third rope legs coupled to one another such that the external mass rope defines a Y-rope, at least one of the first rope leg and the second rope leg having an associated length adjustment unit in-line with the associated rope leg and configured to shorten or lengthen the associated rope leg during flight operation of the rotorcraft on the basis of associated operating parameters;

a forward cargo hook attaching a second end of the first rope leg of the external load mass rope to the forward cargo attachment point;

an aft cargo hook attaching a second end of the second rope leg of the external load mass rope to the aft cargo attachment point; and

an external load mass interface connected to a second end of the third rope leg, the external load mass interface configured to attach an external load mass to be carried by the rotorcraft in flight operation.

20. The rotorcraft according to claim 19 wherein the a length of the length adjustment unit is configured to vary in response to a varying external load mass deflection angle based on a deflection of the external load mass in forward flight direction or backward flight direction of the rotorcraft, and a weight of the external load mass.