Reinforcing element for a structural profile, structural arrangement, aircraft or spacecraft, and method for producing a structural arrangement

{
  "publication_number": "US2023415404A1",
  "country": "US",
  "kind": "A1",
  "title": "Reinforcing element for a structural profile, structural arrangement, aircraft or spacecraft, and method for producing a structural arrangement",
  "abstract": "A reinforcing element for a structural profile, in particular for a round, oval or elliptical structural tube, includes a composite structure, which has a hollow-cylindrical, helically wound mesh of fiber strands which form an inner shell surface configured to receive the structural profile, wherein the fiber strands are respectively embedded in a matrix material, which has an electroactive polymer which can be stretched along a longitudinal extent of the fiber strands by application of an electrical voltage, such that the composite structure can be expanded by application of the electrical voltage to introduce the structural profile into the composite structure and can be shrunk by switching off the electrical voltage to fix the structural profile on the shell surface in the composite structure.",
  "claims": [
    "1. A reinforcing element for a structural profile, comprising: a composite structure, which has a hollow-cylindrical, helically wound mesh of fiber strands which form an inner shell surface configured to receive the structural profile, wherein the fiber strands are respectively embedded in a matrix material, which has an electroactive polymer which can be stretched along a longitudinal extent of the fiber strands by application of an electrical voltage such that the composite structure can be expanded by application of the electrical voltage in order to introduce the structural profile into the composite structure and can be shrunk by switching off the electrical voltage in order to fix the structural profile on the shell surface in the composite structure. 2. The reinforcing element as claimed in claim 1, wherein the fiber strands respectively together with the matrix material form material strips which are wound helically around the shell surface. 3. A structural arrangement, comprising: a structural profile; and a reinforcing element as claimed in claim 1 which locally surrounds the structural profile, wherein the composite structure is shrunk from an unshrunk state for the application of a tensile stress and is thereby connected to the structural profile with a force fit. 4. The structural arrangement as claimed in claim 3, wherein the structural profile comprises a round, oval or elliptical structural tube. 5. The structural arrangement as claimed in claim 3, wherein the structural profile has two longitudinal portions, wherein the reinforcing element surrounds two mutually opposite ends of the respective longitudinal portions and thus connects the two longitudinal portions to each other. 6. The structural arrangement as claimed in claim 3, wherein the reinforcing element is configured and arranged to stiffen the structural profile. 7. The structural arrangement as claimed in claim 6, wherein the reinforcing element is configured and arranged to provide local bending stiffening. 8. The structural arrangement as claimed in claim 6, wherein the reinforcing element is configured and arranged to introduce axial loads into the structural profile. 9. The structural arrangement as claimed in claim 3, wherein the reinforcing element has a receptacle which is coupled to the composite structure and is configured to transmit axial loads to the composite structure. 10. The structural arrangement as claimed in claim 3, wherein the composite structure is configured such that the mesh of fiber strands axially lengthens and radially contracts during axial tensile loading such that the force fit to the structural profile is automatically reinforced. 11. An aircraft or spacecraft with a structural arrangement as claimed in claim 3. 12. The aircraft or spacecraft as claimed in claim 11, wherein the structural profile is configured as a structural tube which is connected to a primary structure of the aircraft or spacecraft and is configured to connect at least one component to the primary structure. 13. The aircraft or spacecraft as claimed in claim 12, wherein the structural tube is arranged axially on a fuselage structure of the aircraft or spacecraft. 14. The aircraft or spacecraft as claimed in claim 12, wherein at least one of: the at least one component is connected to the structural tube via the reinforcing element, or the structural tube is connected to the primary structure via the reinforcing element. 15. The aircraft or spacecraft as claimed in claim 12, wherein the composite structure is configured for dimensionally stable transmission of conventional flight loads by the force fit, applied with the shrinking of the composite structure, to the structural tube. 16. The aircraft or spacecraft as claimed in claim 11, wherein the composite structure is configured for shape-changing transmission of axial overloads, to the structural profile by axial lengthening and radial contraction. 17. A method for producing a structural arrangement as claimed in claim 3, comprising: arranging the shrunk reinforcing element in the unshrunk state on a structural profile by application of an electrical voltage in such a manner that the inner shell surface locally surrounds the structural profile; performing tolerance compensation by displacing the reinforcing element along the structural profile into a final position; and switching off the electrical voltage to fasten the inner shell surface to the structural profile by shrinking the composite structure. 18. The method as claimed in claim 17, wherein the reinforcing element is configured to connect a component to the structural profile, wherein performing the tolerance compensation comprises coupling the component to the reinforcing element and finally positioning the component in its installation position such that the component is connected to the structural profile by shrinking the composite structure of the reinforcing element in the installation position."
  ],
  "description_excerpt": "The present invention relates to a reinforcing element for a structural profile, to a structural arrangement, in particular for an aircraft or spacecraft, with such a reinforcing element, to an aircraft or spacecraft with such a structural arrangement, and to a method for producing such a structural arrangement.\n\nIn aeronautics, tubes are used as structural profiles for local absorbents of axial loads owing to their high resistance to bending. DE 10 2008 041 230 A1 describes attaching a line to a crosspiece, which is formed by a tube, by means of holders. Furthermore, the attaching of the tube to a fuselage cell structure by means of holders is described. For this purpose, the tube has a multiplicity of transverse bores which are introduced in a bore grid and are provided for form-fitting, axial securing of the holders. The holders have transverse webs with pins which correspond to the bores and are introduced into the bores in a form-fitting manner. The document DE 10 2018 218 039 A1 describes a reinforcing element with a hollow-cylindrical, helically wound mesh of fiber strands which are respectively embedded in a thermoplastic matrix material which can be shrunk by heating in order to fasten the reinforcing element to a structural profile via an inner shell surface.\n\nAgainst this background, the present invention is based on an object of creating a reinforcing element which permits a simplified connection to a structural profile, in particular to a tube. According to the invention, a reinforcing element for a structural profile, in particular for a round, oval or elliptical structural tube, is provided.",
  "cpc": [
    "B29C 63/42",
    "B29C 53/582",
    "B29C 53/60",
    "B29C 63/0021",
    "B29C 70/08",
    "B29C 70/222",
    "B29C 70/32",
    "B29C 70/68",
    "B29C 70/88",
    "B29L 2031/3082",
    "B64C 1/06",
    "B64C 1/068",
    "B64C 2001/0072",
    "B64G 1/22",
    "F16B 7/0426",
    "F16L 3/12",
    "H10N 30/206",
    "H10N 30/852"
  ],
  "ipc": [
    "B29C 63/00",
    "B29C 63/42",
    "B64C 1/06",
    "F16B 7/04",
    "F16L 3/12"
  ],
  "assignees": [
    "AIRBUS OPERATIONS GMBH"
  ],
  "inventors": [
    "HEGENBART MATTHIAS",
    "BENTHIEN HERMANN"
  ],
  "filing_date": "2023-06-07",
  "publication_date": "2023-12-28",
  "priority_date": "2022-06-22",
  "application_number": "US-202318330842-A",
  "family_id": "82214293",
  "citations": [
    "US2009085444A1",
    "US2013069630A1",
    "US2020122815A1",
    "US7193350B1"
  ]
}