Disclosed is a multi-spar torsion box structure comprising a plurality of spars of composite material arranged to form a multi-cell structure with two or more cells extending longitudinally along the torsion box, and upper and lower skin covers formed of composite material and joined to upper and lo
Disclosed is a multi-spar torsion box structure comprising a plurality of spars of composite material arranged to form a multi-cell structure with two or more cells extending longitudinally along the torsion box, and upper and lower skin covers formed of composite material and joined to upper and lower surfaces of the multi-cell structure, respectively. The structure further comprises at least one belt-like reinforcing element extending around the outer perimeter of the torsion box, and fixed to the upper and lower surfaces of the multi-cell structure, and transversely arranged with respect to the longitudinal direction of the torsion box. The belt-like reinforcing element is made of a metallic or a composite material. The disclosed torsion box can advantageously be used in the manufacture of aircraft lifting surfaces, such as horizontal tailplanes (HTP) or wings.
대표청구항▼
1. A multi-spar torsion box structure, comprising: a plurality of spars, including at least a front spar and a rear spar, of a composite material arranged to form a multi-cell structure with at least two cells extending in a longitudinal direction of said torsion box, said multi-cell structure havin
1. A multi-spar torsion box structure, comprising: a plurality of spars, including at least a front spar and a rear spar, of a composite material arranged to form a multi-cell structure with at least two cells extending in a longitudinal direction of said torsion box, said multi-cell structure having upper and lower surfaces,upper and lower skin covers of a composite material are joined to said upper and lower surfaces, respectively, of said multi-cell structure,wherein said multi-spar torsion box structure further includes at least one belt-like reinforcing element, said reinforcing element received in a groove and said belt-like reinforcing element is configured as a closed loop and extends completely around an outer perimeter of said torsion box, and fixed to said upper and lower surfaces of said multi-cell structure, and wherein at least a part of said belt-like reinforcing element is transversely arranged with respect to an axis (X) oriented in said longitudinal direction of said torsion box, and wherein said belt-like reinforcing element is made of a composite material, and wherein a width and a thickness of said reinforcing element is dimensioned to withstand torsional loads and to prevent deformations of said torsion box. 2. The multi-spar torsion box structure of claim 1, wherein said belt-like reinforcing element is arranged in a load introduction direction. 3. The multi-spar torsion box structure of claim 1, wherein said belt-like reinforcing element is a stack of plies of a composite material having unidirectional orientated fibers, and wherein a majority of said plies of said reinforcing element are transversely arranged with respect to said axis (X) which is oriented in said longitudinal direction of said torsion box. 4. The multi-spar torsion box structure of claim 3, wherein said belt-like reinforcing element is co-cured, co-bonded or secondarily bonded with a component of said structure. 5. The multi-spar torsion box structure of claim 1, further comprising: a leading edge fitted to said front spar of said torsion box, andwherein said belt-like reinforcing element also extends around a perimeter of said leading edge. 6. The multi-spar torsion box structure of claim 5, further comprising: a trailing edge fitted to said rear spar of said torsion box, andwherein said belt-like reinforcing element also extends around a perimeter of said trailing edge. 7. The multi-spar torsion box structure of claim 6 wherein both of said leading edge and said trailing edge respectively each comprise at least two adjacent sections arranged longitudinally in said structure, and wherein said belt-like reinforcing element is placed in a position corresponding to separation lines between adjacent leading edge and trailing edge sections. 8. The multi-spar torsion box structure of claim 7, wherein a part of said belt-like reinforcing element extends around said leading edge of said structure. 9. The multi-spar torsion box structure of claim 7, wherein a part of said belt-like reinforcing element extends around said trailing edge of said structure. 10. The multi-spar torsion box structure of claim 1, wherein at least one part of said belt-like reinforcing element is placed between said multi-cell structure and at least one of said skin covers. 11. The multi-spar torsion box structure of claim 10, wherein another part of said belt-like reinforcing element is placed between two adjacent spars of said torsion box. 12. The multi-spar torsion box structure of claim 1, wherein at least one part of said belt-like reinforcing element is placed on at least one of said skin covers. 13. The multi-spar torsion box structure of claim 1, wherein said belt-like reinforcing element is formed from two or more individual segments. 14. A horizontal tailplane for an aircraft, comprising: two symmetrically arranged multi-spar torsion box structures, each having a plurality of spars of a composite material arranged to form a multi-cell structure with at least two cells extending longitudinally along said torsion box, said multi-cell structure having both upper and lower surfaces and upper and lower skin covers of a composite material joined to said upper and lower surfaces, respectively, of said multi-cell structure, wherein each of said two symmetrically arranged multi-spar torsion box structures further include at least one belt-like reinforcing element, said reinforcing element received in a groove and said belt-like reinforcing element is configured as a closed loop and extends completely around an outer perimeter of said torsion box, and fixed to said upper and lower surfaces of said multi-cell structure, and wherein at least a part of said belt-like reinforcing element is transversely arranged with respect to an axis (X) oriented in a longitudinal direction of said torsion box, and wherein said belt-like reinforcing element is made of a composite material, and wherein a width and a thickness of said reinforcing element are dimensioned to withstand torsional loads and to prevent deformations of said torsion box.
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이 특허에 인용된 특허 (5)
Isenberg Jack M. (Bellevue WA), Apparatus and method for manufacturing laminar flow control aircraft structure.
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