AIRCRAFT

Abstract

The invention relates to an aircraft having a supporting structure (12) and a shell (10) that can be filled with a gas and which is tensioned by the supporting structure (12). According to the invention, said supporting structure (12) comprises a plurality of rod or tube-shaped sections (24-30) which define a circular, oval or polygonal main clamping plane for the shell (10).

Claims

1: An aircraft having a supporting structure and an envelope that is tensioned by the supporting structure and can be filled with a gas, wherein the supporting structure comprises a plurality of rod or tube portions which define a circular, oval or polygonal main tension plane for the envelope.

2: The aircraft according to claim 1, wherein the end parts of the rod or tube portions are detachably fitted together in pairs by means of a plurality of sleeve elements comprising at least two sleeve parts.

3: The aircraft according to claim 2, wherein at least one portion of the sleeve elements that are opposite one another in a main tension plane comprises at least one additional sleeve part for receiving end parts of at least one additional rod or tube portion, the additional rod or tube portion arching over the main tension plane for the stabilization thereof.

4: The aircraft according to claim 3, wherein at least two intersecting rod or tube portions are provided for stabilizing the main tension plane, a frame part being arranged in the intersecting region of these rod or tube portions, which frame part comprises openings for the rod or tube portions.

5: The aircraft according to claim 4, wherein a blower is arranged on the frame part, which blower applies compressed air to the interior of the envelope.

6: The aircraft according to claim 4, wherein downward projecting supporting legs for the aircraft are arranged on the frame part.

7: The aircraft according to claim 4, wherein functional components, e.g. control electronics for operating the aircraft, transmitting and/or receiving modules for optical or electromagnetic communication, a camera module or the like, are arranged on the frame part.

8: The aircraft according to claim 2, wherein a portion of the sleeve elements comprises an additional sleeve part for incorporating an axis of rotation of a wing element that can be adjusted about the axis of rotation and protrudes from the outer periphery of the sleeve.

9: The aircraft according to claim 2, wherein the sleeve parts of the sleeve elements are oversized with respect to the end parts of the rod or tube parts.

10: The aircraft according to claim 2, wherein the sleeve parts of the sleeve elements are each overlapped by a securing sleeve arranged on the rod or tube portion.

11: The aircraft according to claim 1, wherein the rod or tube portions comprise a carbon fiber material.

12: The aircraft according to claim 1, wherein the envelope is made of an air-impermeable, tear-resistant synthetic fabric material, for example spinnaker material.

13: The aircraft according to claim 1, wherein the envelope comprises two envelope halves that can be interconnected by means of at least one zipper, which halves are securely interconnected at a short connection region and can be folded apart in a shell-like manner when the at least one zipper is opened.

14: The aircraft according to claim 13, wherein two zippers that can be actuated in the same or opposite direction are provided, between which zippers, when closed, a tunnel is formed for receiving the rod or tube portions of the supporting structure defining the main tension plane of the envelope.

15: The aircraft according to claim 1, wherein a communication antenna is incorporated into the material of the envelope or is deposited or rolled thereon.

16: The aircraft according to claim 1, wherein a hot wire is arranged on the envelope and a gas cell arranged in the envelope for a lighter-than-air gas, in order to be able to melt said envelope and cell along an appropriate length if required in order to relieve pressure.

17: The aircraft according to claim 1, wherein the envelope comprises fastening elements on the inside, for example hook-and-loop fastener parts, for fastening a gas cell for a lighter-than-air gas that is arranged inside the envelope and comprises complementary fastening elements.

18: The aircraft according to claim 1, wherein the supporting structure comprises connection elements between an upper and a lower region of the envelope that can be deformed and/or longitudinally adjusted, by means of which a modifiable aerodynamic outer contour of the envelope can be produced.

19: The supporting structure for an aircraft according to claim 1, comprising a plurality of rod or tube portions, which can be interconnected by means of sleeve elements, for tensioning an envelope of the aircraft.

20: The supporting structure according to claim 19, wherein the end parts of the rod or tube portions are detachably fitted together in pairs by means of a plurality of sleeve elements comprising at least two sleeve parts.

21: The supporting structure according to claim 19, wherein at least one portion of the sleeve elements mutually opposing in a main tension plane comprises at least one additional sleeve part for receiving end parts of at least one additional rod or tube portion, the additional rod or tube portion arching over the main tension plane for the stabilization thereof.

22: The supporting structure according to claim 21, wherein at least two intersecting rod or tube portions are provided for stabilizing the main tension plane, a frame part being arranged in the intersecting region of said rod or tube portions, which frame part comprises openings for the rod or tube elements.

23: The supporting structure according to claim 22, wherein a blower is arranged on the frame part, which blower applies compressed air to the interior of the envelope.

24: The supporting structure according to claim 22, wherein downward projecting supporting legs for the aircraft are arranged on the frame part.

25: The supporting structure according to claim 22, wherein functional components, e.g. control electronics for operating the aircraft, transmitting and/or receiving modules for optical or electromagnetic communication, a camera module or the like, are arranged on the frame part.

26: The supporting structure according to claim 19, wherein a portion of the sleeve elements comprises an additional sleeve part for incorporating an axis of rotation of a wing element that can be adjusted about the axis of rotation and protrudes from the outer periphery of the sleeve.

27: The supporting structure according to claim 19, wherein the sleeve parts of the sleeve elements are oversized with respect to the end parts of the rod or tube parts.

28: The supporting structure according to claim 19, wherein the sleeve parts of the sleeve elements are each overlapped by a securing sleeve arranged on the rod or tube portion.

29: The supporting structure according to claim 19, wherein the rod or tube portions comprise a carbon fiber material.

30: A use of the aircraft according to claim 1, wherein a plurality of aircraft are coupled to one another, forming an assembly.

31: The use according to claim 30, wherein the plurality of aircraft are coupled to one another by ropes, cables or a planar solar element.

32: A use of the aircraft according to claim 1, wherein the aircraft is anchored to the ground by ropes or cables, in order to monitor a limited region by means of optical and/or electromagnetic devices arranged on the aircraft.

Description

[0042] The invention will be explained in more detail in the following with reference to an embodiment that is shown schematically in the drawings. In the drawings:

[0043] FIG. 1 is a view of an aircraft having an envelope, wings and drives;

[0044] FIG. 2 shows a supporting structure arranged in the envelope of the aircraft according to FIG. 1;

[0045] FIG. 3 is a detailed view of a sleeve element of the supporting structure according to FIG. 2;

[0046] FIG. 4 is a detailed view of an additional sleeve element of the supporting structure according to FIG. 2;

[0047] FIG. 5 shows a securing sleeve for the supporting structure according to FIG. 2;

[0048] FIG. 6 shows a frame part of the supporting structure according to FIG. 2; and

[0049] FIG. 7 shows a payload carrier for fastening to the frame part according to FIG. 6.

[0050] The aircraft shown in FIG. 1 comprises an envelope 10, in which a supporting structure 12 according to FIG. 2 is arranged. Two wings 14, 16 are arranged on the supporting structure 12 so as to be mutually opposing, which wings support propeller drives 18, 20 at the ends thereof, which propeller drives are pivotable about the wing longitudinal axis together with or independently from the wings 14, 16. A payload that can be displaced along a rail 22 that is arranged below the envelope 10 is arranged on the rail 22.

[0051] The supporting structure 12 shown in FIG. 2 comprises a plurality of tube or rod portions 24-30, which define a main tension plane for the envelope 10. The tube or rod portions 24-30 are each inserted, by the two end regions thereof, into sleeve elements 32 and 34, respectively, which are shown in detail in FIGS. 3 and 4. The axes of rotation of the wings 14, 16 and/or of the propeller drives 18, 20 are indicated by the dashed lines 36, 38, which extend through sleeve parts of the sleeve elements 34. The ring formed by the rod or tube portions 24-30 is subjected to bending and torsional forces and is therefore stabilized by additional rod or tube portions 40, 42, the end parts of which engage with additional sleeve parts of the sleeve elements 32, 34. A frame part 44 (FIG. 6) is arranged in the intersecting region of the rod or tube portions, which frame part comprises openings for the rod or tube portions 40, 42, so that said portions are fixed in position. Furthermore, a blower (not shown in more detail) is arranged on the frame part 44, by means of which blower the interior of the envelope 10 is inflated.

[0052] The sleeve element 32 shown in various views in FIG. 3 is designed as a tee and comprises a first sleeve part 46, into which end regions of the rod or tube portions 24, 26 and 28, 30 are inserted, and a second sleeve part 48, into which an end part of the stabilizing rod or tube portion 40 is inserted. In order to secure the end parts of the rod or tube portions 24, 26 and 28, 30 and/or 40 against sliding out of the sleeve parts 46 or 48, securing sleeves 50, 52 are provided which are arranged on the rod or tube portions 24, 26 and 28, 30 and/or 40 and on the outer side of the sleeve part 46, 48 in a force-locking manner, whereas the rod or tube portions 24, 26 and 28, 30 and/or 40 are arranged in the respective sleeve parts 46, 48 with some backlash, in order to reduce the risk of breakage under changing loads.

[0053] The sleeve element 34 shown in various views in FIG. 4 comprises, like the sleeve element 32, sleeve parts 54 and 56 for receiving the end parts of the rod or tube portions 24-30 and 42, which are also provided with securing sleeves (not shown in more detail here). The sleeve element 34 also comprises a sleeve part 58 through which the support shafts of the wings 14, 16 extend.

[0054] FIG. 5 is a view and a section through the securing sleeve 50, 52.

[0055] FIG. 6 shows various views of the frame part 44. Openings 60, 62 for the rod or tube portion 42 and openings 64, 66 for the rod or tube portion 40 are provided in the walls of the frame part 44. A plurality of holes 68 penetrating the walls of the frame part 44 are used to fasten the blower (not shown in more detail) and possible additional components, such as electronic control devices or the like.

[0056] A payload carrier body 70 shown in various views in FIG. 7 is also arranged on the frame part 44. The payload carrier body 70 also comprises two tabs 72, 74 having holes 76, 78 through which one of the rod or tube portions 40, 42 passes, for example. Payloads of various kinds, such as cameras, radio transmitters and/or receivers and the like, can be fastened to a ground plate 80 of the payload carrier body 70.