Apparatus for closing a locker, which can be lowered, of a baggage compartment
An apparatus for closing a locker, which can be lowered, of a baggage compartment, in particular of an overhead baggage compartment in an aircraft, wherein the locker is connected in an actuating element ( 5 ) which is held on a frame ( 1 ) such that it can rotate or pivot, and is connected to a gas compression spring ( 18 ) in order to assist a closing movement of the locker. In order to allow a completely automatic closing movement, the invention proposes that an electromechanical hybrid drive is provided in order to drive the actuating element ( 5 ) and, in addition to the mechanical component of the gas compression spring ( 18 ), has an electrical drive apparatus ( 12 ) as an electrical component.
1. An apparatus for closing a lowerable locker of a baggage compartment in an aircraft, comprising:
an actuating element, to which the locker is connected, the actuating element being held on a frame such that the actuating element is capable of rotating or pivoting,
a drive disc connected to the actuating element, the drive disc comprising a toothed crown,
a gas compression spring, to which the locker is connected to assist a closing movement of the locker, and
an electrical drive apparatus for driving the actuating element, and
a linear movement element of the gas compression spring, the linear movement element comprising a toothed rod, the toothed rod being configured to engage the toothed crown of the drive disc.
2. The apparatus according to claim 1 , wherein a restoring force produced by the gas compression spring corresponds to 0.3 to 0.7 times of a permissible load weight of the locker.
3. The apparatus according to claim 1 , wherein the electrical drive apparatus is connected to an electrical energy store to supply electrical power.
4. The apparatus according to claim 3 , wherein the electrical energy store is formed from a plurality of capacitors.
5. The apparatus according to claim 1 , wherein the electrical drive apparatus comprises an electric motor which comprises a gearbox.
6. The apparatus according to claim 1 , wherein the actuating element comprises a winding disc for winding up and unwinding at least one cable.
7. The apparatus according to claim 5 , wherein the electrical drive apparatus comprises a drive shaft, wherein the drive shaft is connected via a bevel tooth system to the drive disc.
8. The apparatus according to claim 1 , further comprising a control device for controlling the electrical drive apparatus, the control device comprising a load sensor for measurement of a load held in the locker.
9. The apparatus according to claim 8 , wherein the control device comprises a manually operable switching device for selectively opening and closing the locker.
10. The apparatus according to claim 9 , wherein the switching device is fitted to the locker.
11. The apparatus according to claim 3 , wherein, if a predetermined limit load held in the locker is exceeded, the electric motor takes electrical power from the electrical energy store.
12. An aircraft having at least one overhead baggage compartment, whose locker is connected to an apparatus according to claim 1 , which apparatus is fitted to a frame structure element.
13. The apparatus according to claim 2 , wherein the restoring force corresponds to 0.4 to 0.6 times of a permissible load weight of the locker.
14. The apparatus according to claim 5 , wherein the gearbox comprises an epicyclic gearbox.
15. An apparatus for closing a lowerable locker of a baggage compartment in an aircraft, comprising:
an actuating element, to which the locker is connected, the actuating element being held on a frame such that the actuating element is capable of rotating or pivoting,
a drive disc connected to the actuating element,
a gas compression spring, to which the locker is connected to assist a closing movement of the locker, and
an electrical drive apparatus for driving the actuating element, the electrical drive apparatus comprising a drive shaft, wherein the drive shaft is connected via a bevel tooth system to the drive disc.
16. The apparatus according to claim 15 , wherein a restoring force produced by the gas compression spring corresponds to 0.3 to 0.7 times of a permissible load weight of the locker.
17. The apparatus according to claim 16 , wherein the restoring force corresponds to 0.4 to 0.6 times of a permissible load weight of the locker.
18. The apparatus according to claim 15 , wherein the electrical drive apparatus is connected to an electrical energy store to supply electrical power.
19. The apparatus according to claim 17 , wherein the electrical energy store is formed from a plurality of capacitors.
20. The apparatus according to claim 19 , wherein, if a predetermined limit load held in the locker is exceeded, the electric motor takes electrical power from the electrical energy store.
21. The apparatus according to claim 15 , wherein the electrical drive apparatus comprises an electric motor which comprises a gearbox.
22. The apparatus according to claim 21 , wherein the gearbox comprises an epicyclic gearbox.
23. The apparatus according to claim 15 , wherein the actuating element comprises a winding disc for winding up and unwinding at least one cable.
24. The apparatus according to claim 15 , wherein the gas compression spring comprises a linear movement element which comprises a toothed rod, and wherein the drive disc comprises a toothed crown, the toothed rod and the toothed crown being configured to engage each other.
25. The apparatus according to claim 15 , further comprising a control device for controlling the electrical drive apparatus, the control device comprising a load sensor for measurement of a load held in the locker.
26. The apparatus according to claim 23 , wherein the control device comprises a manually operable switching device for selectively opening and closing the locker.
27. The apparatus according to claim 24 , wherein the switching device is fitted to the locker.
28. An aircraft having at least one overhead baggage compartment, whose locker is connected to an apparatus according to claim 15 , which apparatus is fitted to a frame structure element.