Auxiliary drive system for a helicopter

Patent metadata

Field	Value
Publication number	US-9708074-B2
Application number	US-201314416764-A
Country	US
Kind code	B2
Filing date	Jul 19, 2013
Priority date	Jul 26, 2012
Publication date	Jul 18, 2017
Grant date	Jul 18, 2017

Abstract

A drive system for a helicopter includes a main drive for driving a rotor the helicopter, a flywheel mass battery including at least one flywheel, a first transmission coupling the flywheel mass battery with the main drive such that, during operation of the main drive, output can be transferred from the main drive to the flywheel mass battery, and a second, variable transmission connecting the flywheel mass battery to the rotor of the helicopter such that a predetermined output can be transferred to the rotor through adjustment of a transmission ratio of the variable transmission.

First claim

The invention claimed is:

1. A helicopter with a drive system, comprising:
a main drive configured to drive a lift-generating rotor of the helicopter;
a flywheel mass battery comprising at least one flywheel;
a first transmission coupling the flywheel mass battery to the main drive such that, during operation of the main drive, output is transferred from the main drive to the flywheel mass battery;
a second, variable transmission connecting the flywheel mass battery to the lift-generating rotor of the helicopter such that a predetermined output is transferred to the lift-generating rotor through adjustment of a transmission ratio of the variable transmission; and
a main transmission between the main drive and the lift-generating rotor,
wherein the main transmission comprises a first input with which the main drive is coupled,
wherein the main transmission has a second input with which the flywheel mass battery is coupled via the variable transmission.

2. The helicopter with a drive system of claim 1 , wherein the variable transmission is a continuously variable transmission.

3. The helicopter with a drive system of claim 1 , wherein the variable transmission is electrically controlled.

4. The helicopter with a drive system of claim 1 , wherein the first transmission is a transmission with a fixed transmission ratio.

5. The helicopter with a drive system of claim 1 , further comprising:
a freewheel unit between the first transmission and the main drive.

6. The helicopter with a drive system of claim 1 , further comprising:
an auxiliary drive shaft via which the variable transmission is coupled with the second input of the main transmission,
wherein the auxiliary drive shaft is coupled via a freewheel unit with the main transmission.

7. The helicopter with a drive system of claim 1 , further comprising:
a drive shaft via which the main drive is coupled with the first input of the main transmission.

8. The helicopter with a drive system of claim 7 , wherein the drive shaft is coupled via a freewheel unit with the main transmission.

9. The helicopter with a drive system of claim 7 , wherein the first transmission is coupled with the drive shaft.

10. A method for operating an auxiliary drive system of a helicopter, the method comprising the steps:
determining whether a main drive of the helicopter is providing a desired output;
when the main drive is not providing the desired output, connecting of a flywheel mass battery to a lift-generating rotor of the helicopter via a variable transmission, the flywheel mass battery having been charged mechanically by the main drive during normal operation;
controlling of a transmission ratio of the variable transmission such that a desired output is transferred to the lift-generating rotor; and
separating operation of the lift-generating rotor via the main drive from operation of the lift-generating rotor via the flywheel mass battery by a first input and a second input of a main transmission, wherein the first input is coupled with the main drive and the second input is coupled via the variable transmission with the flywheel mass battery.

11. The method of claim 10 , further comprising the steps:
detecting whether the lift-generating rotor is being operated in autorotation; and
separating of the flywheel mass battery from the lift-generating rotor when it is detected that the lift-generating rotor is being operated in autorotation.

12. The method of claim 10 , further comprising the steps:
detecting whether a landing procedure is being initiated;
connecting of the flywheel mass battery to the lift-generating rotor when it is detected that a landing procedure is being initiated.

Assignees

• Airbus Defence & Space Gmbh

Inventors

• Jaenker Peter

Classifications

• B64D35/023

  of series-parallel type · CPC title

• B64C27/006 Primary

  Safety devices · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• B64C27/12

  Rotor drives · CPC title

• B64D35/02 Primary

  specially adapted for specific power plants · CPC title