Aircraft rotational joint with a slip-ring device for electrical energy transmission

Abstract

An aircraft rotational joint comprises a slip-ring device arranged for electrical energy transmission through the rotational joint. The slip-ring device comprises a first member attached to a first part of the rotational joint. The first member has a plurality of arcuate metallic ring segments and all these ring segments are isolated from each other and are spaced apart from each other. Further, the slip-ring device comprises a second member which is rotatable relative to the first member about a common rotational axis. The second member is attached to a second part of the joint and has a plurality of contact elements, each of which are arranged for electrically connecting one, preferably only one, of the ring segments.

Claims

1. An aircraft rotational joint comprising a slip-ring device for electrical energy transmission through the aircraft rotational joint, the slip-ring device comprising: a first member attached to a first part of the rotational joint, the first member comprising a plurality of arcuate conductive ring segments, wherein the ring segments are electrically isolated from each other, a second member attached to a second part of the aircraft rotational joint, the second member comprising a plurality of contact elements, wherein each of the contact elements is in electrical contact with one of the ring segments, wherein the first member and the second member are rotatable relative to each other about a common rotational axis which is also the rotational axis of the aircraft rotational joint, wherein each of the ring segments extends along a different circular arc segment, wherein a center of each of the circular arc segments is arranged on the rotational axis, and wherein at least two of the ring segments extend along circular arc segments having an identical radius and an identical center.

2. The aircraft rotational joint according to claim 1, wherein three or more of the ring segments extend along circular arc segments having an identical center and an identical radius, wherein the circular arc segments are preferably evenly spaced from one another.

3. The aircraft rotational joint according to claim 1, wherein the first member comprises at least one stop element arranged between two ring segments extending along circular arc segments having an identical radius and an identical center, wherein the stop element is adapted to limit a rotation of the second member relative to the first member.

4. The aircraft rotational joint according to claim 1, wherein the first member is disc shaped or has a cylindrical outer surface extending along the common rotational axis.

5. The aircraft rotational joint according to claim 1, wherein two ring segments extending along circular arc segments having an identical radius and an identical center have different dimensions in at least one of along the common rotational axis and perpendicular to the common rotational axis.

6. The aircraft rotational joint according to claim 1, wherein two or more of the ring segments form a first segment group and two or more of the ring segments form a second segment group, wherein the ring segments of the first segment group and the second segment group are arranged in a plane extending perpendicular to the common rotational axis and wherein a ring segment of the first segment group and a ring segment of the second segment group extend along circular arc segments having the identical radius and the identical center.

7. The aircraft rotational joint according to claim 6, wherein the ring segments of the first segment group are arranged for transmitting power and the ring segments of the second segment group are arranged for transmitting data signals.

8. The aircraft rotational joint according to claim 1, wherein the first member and the second member have a recess or through-hole extending along the rotational axis.

9. The aircraft rotational joint according to claim 1, wherein the contact elements are biased towards the ring segments, wherein the contact elements are spring loaded.

10. The aircraft rotational joint according to claim 1, wherein the second member comprises at least one connecting element supporting two or more of the contact elements.

11. The aircraft rotational joint according to claim 10, wherein two or more of the connecting elements are evenly distributed about the common rotational axis.

12. The aircraft rotational joint according to claim 1, wherein the first and second members have mechanical connectors connected with parts of the rotational joint.

13. The aircraft rotational joint according to claim 1, further comprising two disc shaped first members spaced apart along the common rotational axis, wherein the second member is arranged between the first members for electrically contacting ring segments of one of the first members.

14. A wing of an aircraft comprising a main wing and a foldable wing tip device, wherein at least one aircraft rotational joint according to claim 1 connects the foldable wing tip device to the main wing.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Further advantages of the invention are apparent from the enclosed figures showing illustrative examples of the slip-ring device, wherein

[0026] FIG. 1 shows an inside of an exemplary slip-ring device of an aircraft rotational joint with ring segments arranged in groups on a disc shaped first member,

[0027] FIG. 2 shows a slip-ring device of an aircraft rotational joint with two first members according to FIG. 1 and isolated from each other,

[0028] FIG. 3 shows a wing section with an aircraft rotational joint and a built in slip-ring device with disc shaped first member,

[0029] FIG. 4 shows an enlarged section of FIG. 3,

[0030] FIG. 5 shows the wing section of FIG. 3 from a different angle,

[0031] FIG. 6 shows another exemplary slip-ring device of an aircraft rotational joint with a first member having a cylindrical outer surface,

[0032] FIG. 7 shows the slip-ring device of FIG. 6, the second member depicted transparently,

[0033] FIG. 8 shows the slip-ring device of FIG. 7 from a different angle,

[0034] FIG. 9 shows a wing section with an aircraft rotational joint and a built in slip-ring device according to FIG. 6,

[0035] FIG. 10 shows the wing section including the built in slip-ring device according to FIGS. 6 and 9 from a different angle,

[0036] FIG. 11 shows the wing section including the built in slip-ring device according to FIGS. 6 and 9 from a different angle and

[0037] FIG. 12 shows an aircraft wing comprising a foldable wing tip device.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0038] FIG. 1 schematically shows the inside of a slip-ring device 1 of an aircraft rotational joint. The rotational joint is used for movably or rotatably connecting a foldable wing tip device to a main wing of an aircraft. The slip-ring device 1 is arranged for electrical energy transmission through an aircraft rotational joint. It comprises a first member 2 attached on a first part of the rotational joint. The first member has a plurality of arcuate conductive ring segments 3. In the embodiments shown in the Figures the ring segments are metal ring segments 3. Only two of the ring segments 3 have been indicated with reference numbers to keep the drawings intelligible. The ring segments 3 are electrically isolated from each other, e.g., by arranging them spaced apart from one another. Further, the slip-ring device comprises a second member (not shown in FIG. 1) which is rotatable relative to the first member about a common rotational axis A which is also the axis of rotation of the aircraft rotational joint. The second member is attached to a second part of the rotational joint and has a plurality of contact elements (not shown in FIG. 1), each of which are in electrical contact with only one of the ring segments 3.

[0039] The ring segments 3 are arranged in four segment groups 7, 8, 14, 15 on the disc shaped first member 2. The second member (not shown) of the slip-ring device 1 has four connecting elements 10, which support the spring loaded contact elements (not shown) for electrical contact with the ring segments 3. All ring segments 3 extend along circular arc segments. The center of each of these arc segments coincides with the common rotational axis A, i.e., the arc segments and therefore the ring segments 3 are arranged on imaginary circles about the common axis of rotation or rotational axis A. Four ring segments 3a, 3b, 3c, 3d, one of the each segment group 7, 8, 14, 15, extend along circular arc segments that have an identical radius and an identical center. In other words, always four of the ring segments 3a, 3b, 3c, 3d are arranged on the same circumference about the common rotational axis A on the first member 2, particularly on an outer surface of the first member 2. Only one set of four ring segments 3a, 3b, 3c, 3d has been designated in the FIG. 1 to avoid overcomplicating FIG. 1. However, it is readily apparent for the skilled person from the drawings that multiple sets of ring segments extending along circular arc segments with an identical radius and in identical center can be designated in the FIG. 1.

[0040] In a first segment group 7 the ring segments 3 are arranged on different circumferences, i.e., they extend along circular arc segments having different radii about the common rotational axis A. However, the ring segments 3 of the first group are preferably arranged within the same sector or angular range about the common rotational axis. A ring segment 3a of the first segment group 7 extends along an arc segment having the identical radius and the identical center as a circular arc segment along which the ring segment 3b of the second segment group 8 extends.

[0041] The segments groups 7, 8, 14, 15 and their ring segments 3 are separated by stop elements 6 arranged between ring segments on the first member. Against the stop elements 6 the connecting elements can abut when the second member is rotated relative to the first member 2. Further, the stop elements 6 provide electrical isolation between the ring segments 3 of the different segment groups 7, 8, 14, 15. The stop elements 6 are optional and may, for example, be replaced by stop elements of the rotational joint.

[0042] The first and second members have a through-hole 9 for receiving a part of the rotational joint such as a shaft or a geared rotary actuator.

[0043] FIG. 2 shows a slip-ring device 1 of an aircraft rotational joint with two first members 2 according to FIG. 1 and electrically isolated from each other. In all Figures like elements are designated with like reference numerals. The slip-ring device 1 also has two second members 4 according to FIG. 1. The members 2, 4 are stacked as follows: first member 2-second member 4-second member 4-first member 2. This example offers more paths for electrical energy transmission or redundancy by parallel connection of the two first members 2, depending on the cable harnesses which are not shown in the Figures.

[0044] Alternatively but not shown, a single second member 4 could electrically contact the ring segments 3 of both first members 2 to reduce the number of parts of the slip-ring device 1.

[0045] FIG. 3 shows a wing section 31 with a rotational joint 32 and a built in slip-ring device 1 according to FIG. 1 with a disc shaped first member 2. The first member 2 is connected with the first part 22 of the rotational joint 32 and the second member 4 is connected with the second part 23 of the rotational joint 32.

[0046] FIG. 4 shows an enlarged section of FIG. 3.

[0047] FIG. 5 shows a sectional view of the wing section 31 of FIG. 3 from a different angle. The arcuate metallic ring segments 3 are arranged on a disc shaped first member 2, as already explained with respect to FIG. 1. Also, connecting means 10 of the second member 4 are arranged adjacent to the ring segments 3 and support the contact elements (not shown) of the second member 4 for electrical contact with ring segments 3. The first member 2 is connected with the stationary part 21 of the rotational joint 31 and the second member 22 is connected with the rotatable part 22 of the rotational joint 31. In FIG. 5 a shaft 33 extends through the opening 9 in the center of the slip-ring device 1.

[0048] FIGS. 6 to 11 show another exemplary slip-ring device 1 of an aircraft rotational joint. The slip-ring device 1 is arranged for electrical energy transmission through the rotational joint. It comprises a first member 2 attached to a first part of the rotational joint. The first member 2 has a plurality of arcuate metallic ring segments 3. The ring segments 3 are isolated from one another and also spaced apart from one another. Further, the slip-ring device 1 comprises a second member 4 which is rotatable relative to the first member 2 about a common rotational axis A which is also the rotational axis of the aircraft rotary joint. The second member is attached to a second part of the rotational joint and has a plurality of contact elements (not shown), each of which are arranged for electrically connecting exactly one of the ring segments 3.

[0049] The first member 2 has a cylindrical outer surface 16. The first member 2 is sectionally surrounded by the second member 4. On the cylindrical surface 16 of the first member 2, the ring segments 3 are arranged in four groups 7, 8, 14, 15 and the second member comprises four connecting elements 10 each supporting several contact elements (not shown). The slip-ring device 1 comprises a housing 12 receiving the second member 4. Wall sections 17 of the housing 12 serves to limit the rotation of the second member 4 relative to the first member 2.

[0050] FIG. 7 shows the slip-ring device 1 of FIG. 6, the housing 12 being depicted transparently. The ring segments 3 are arranged in four segment groups 7, 8, 14, 15 on the cylindrical outer surface 16 of the first member 2. The first member 2 has three arms 11 with holes for a mechanical connection with the first part 21 of the rotational joint 32. The second member 4 inside the housing 12 has four connecting elements 10 supporting contact elements (not shown). Wall sections 17 of the housing 12 serve to limit the rotation of the second member 4 relative to the first member 2.

[0051] FIG. 8 shows the slip-ring device 1 of FIG. 7 from a different angle. Bosses on the underside of the first member 2 are for electrical connection with its ring members.

[0052] FIG. 9 shows a wing section 31 with a rotational joint 32 and a built in slip-ring device 1 according to FIGS. 6 to 8. The first member 2 of the slip-ring device 1 is mechanically connected with the stationary part 21 and the second member 4 is mechanically connected with the rotational part 22 of the rotational joint 31.

[0053] FIG. 10 shows the wing section 31 of FIG. 9 including the built in slip-ring device 1 according to FIGS. 6 to 9 from a different angle.

[0054] FIG. 11 shows the wing section of FIGS. 9, 10 including the built in slip-ring device 1 according to FIGS. 6 to 9 from the underside. The first member 2 has mechanical connectors 11 for the mechanical connection with the stationary part 21.

[0055] Finally, FIG. 12 shows a wing 34 of an aircraft comprising a main wing 35 and a foldable wing tip device 36. The foldable wing tip device 36 is shown in an extended position denoted by reference numeral 37 and a retracted folded position denoted by reference numeral 38. The foldable wing tip device 36 is rotatably mounted or connected to the main wing 35 using at last one exemplary embodiment of a rotational joint 31 according to the present invention. The rotational joint 31 is not shown in FIG. 12. However, the rotational axis A of the at least one rotational joint coincides with the axis about which the foldable wing tip device 36 rotates relative to the main wing 35.

[0056] While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms comprise or comprising do not exclude other elements or steps, the terms a or one do not exclude a plural number, and the term or means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.