A high-lift system of an aircraft has at least one drive unit, at least one load station as well as one or more transmissions for transmitting the drive energy of the drive unit to the at least one load station. One or more of the transmissions are made as transmission shafts from a material contain
A high-lift system of an aircraft has at least one drive unit, at least one load station as well as one or more transmissions for transmitting the drive energy of the drive unit to the at least one load station. One or more of the transmissions are made as transmission shafts from a material containing titanium or include a material containing titanium.
대표청구항▼
1. A high-lift system of an aircraft having at least one drive unit, havingat least one load station as well as havingone or more transmissions for transmitting the drive energy of the drive unit to the at least one load station, whereinone or more of the transmissions are made as transmission shaft
1. A high-lift system of an aircraft having at least one drive unit, havingat least one load station as well as havingone or more transmissions for transmitting the drive energy of the drive unit to the at least one load station, whereinone or more of the transmissions are made as transmission shafts which comprise a material containing titanium and having a Young's modulus in the region of 100 to 120 GPa and/or a shear modulus in the range from 39 GPa to 42 Gpa, andthe transmission shaft (1) is provided with two connector elements (2, 3) on opposite ends thereof, with one connector element (2) in the shape of a flange for releasable connection and the other connector element (3) in the shape of a fork for an integrated gimbal joint (4). 2. A high-lift system in accordance with claim 1, wherein the material comprises, in addition to titanium, only or inter alia aluminum and/or vanadium as further components, with provision preferably being made that both aluminum and vanadium are present and aluminum is present in a larger mass portion than vanadium. 3. A high-lift system in accordance with claim 2, wherein aluminum is present in a range from 4.5% by weight to 7.5% by weight and preferably in a range from 5.5% by weight to 6.5% by weight. 4. A high-lift system in accordance with claim 2, wherein vanadium is present in a range from 0.5% by weight to 5.5% by weight and preferably in a range from 3.5% by weight to 4.5% by weight. 5. A high-lift system in accordance with claim 1, wherein the material is the alloy Ti 6Al 4V. 6. A high-lift system in accordance with claim 1, wherein the material has a tensile strength Rm of >1000 N/qmm and/or an elongation at break of >8%. 7. A high-lift system in accordance with claim 1, wherein the two connector elements (2, 3) each comprise a material containing titanium. 8. A high-lift system in accordance with claim 7, wherein the two connector elements (2, 3) each consists of the material. 9. A high-lift system in accordance with claim 1, wherein the two connector elements (2, 3) are welded (5) to the transmission shaft (1). 10. A high-lift system of an aircraft having at least one drive unit,at least one load station, andone or more transmissions for transmitting the drive energy of the drive unit to the at least one load station, whereinone or more of the transmissions are made as transmission shafts which comprise a material containing titanium and having a Young's modulus in the region of 100 to 120 GPa and/or a shear modulus in the range from 39 GPa to 42 GPa, andthe transmission shaft (1) is provided with two connector elements (2, 3) on opposite ends thereof, with one connector element (2) in the shape of a flange for releasable connection and the other connector element (3) having external teeth. 11. A high-lift system in accordance with claim 10, wherein the two connector elements (2, 3) each comprise a material containing titanium. 12. A high-lift system in accordance with claim 10, wherein the two connector elements (2, 3) each consists of the material. 13. A high-lift system in accordance with claim 10, wherein the two connector elements (2, 3) are welded (5) to the transmission shaft (1). 14. A high-lift system in accordance with claim 10, wherein the material comprises, in addition to titanium, only or inter alia aluminum and/or vanadium as further components, with provision preferably being made that both aluminum and vanadium are present and aluminum is present in a larger mass portion than vanadium. 15. A high-lift system in accordance with claim 14, wherein aluminum is present in a range from 4.5% by weight to 7.6% by weight and preferably in a range from 5.5% by weight to 6.5% by weight. 16. A high-lift system in accordance with claim 14, wherein vanadium is present in a range from 2.5% by weight to 5.5% by weight and preferably in a range from 3.5% by weight to 4.5% by weight. 17. A high-lift system in accordance with claim 10, wherein the material is the alloy Ti 6Al 4V. 18. A high-lift system in accordance with claim 10, wherein the material has a tensile strength Rm of >1000 N/qmm and/or an elongation at break of >8%. 19. A high-lift system of an aircraft having at least one drive unit,at least one load station, andone or more transmissions for transmitting the drive energy of the drive unit to the at least one load station, whereinone or more of the transmissions are made as transmission shafts which comprise a material containing titanium and having a Young's modulus in the region of 100 to 120 GPa and/or a shear modulus in the range from 39 GPa to 42 GPa, andthe transmission shaft (1) is provided with two connector elements (2, 3) on opposite ends thereof and both in the shape of flanges. 20. A high-lift system in accordance with claim 19, wherein the two connector elements (2, 3) each comprise a material containing titanium. 21. A high-lift system in accordance with claim 20, wherein the two connector elements (2, 3) each consists of the material. 22. A high-lift system in accordance with claim 19, wherein the two connector elements (2, 3) are welded (5) to the transmission shaft (1). 23. A high-lift system in accordance with claim 19, wherein the material comprises, in addition to titanium, only or inter alia aluminum and/or vanadium as further components, with provision preferably being made that both aluminum and vanadium are present and aluminum is present in a larger mass portion than vanadium. 24. A high-lift system in accordance with claim 23, wherein aluminum is present in a range from 4.5% by weight to 7.5% by weight and preferably in a range from 5.5% by weight to 6.5% by weight. 25. A high-lift system in accordance with claim 23, wherein vanadium is present in a range from 2.5% by weight to 5.5% by weight and preferably in a range from 3.5% by weight to 4.5% by weight. 26. A high-lift system in accordance with claim 19, wherein the material is the alloy Ti 6Al 4V. 27. A high-lift system in accordance with claim 19, wherein the material has a tensile strength Rm of >1000 N/qmm and/or an elongation at break of >8%.
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이 특허에 인용된 특허 (2)
Shaheen, Milad A.; Dreher, Robert V., Actuator for aircraft stabilizers with a failure responsive lock control mechanism.
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