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A linkage mechanism for controlling an aircraft landing gear hatch door includes a primary torsion tube having a first portion located inside a landing gear hatch and a second portion outside the landing gear hatch. A first drive apparatus transfer the driving force of a landing gear support column

A linkage mechanism for controlling an aircraft landing gear hatch door includes a primary torsion tube having a first portion located inside a landing gear hatch and a second portion outside the landing gear hatch. A first drive apparatus transfer the driving force of a landing gear support column to the primary torsion tube. A secondary torsion tube has an inner end portion located inside the hatch and an outer end portion located outside the hatch. A second drive apparatus is located outside the landing gear hatch and connects the primary torsion tube and the secondary torsion tube outside the hatch. Two third drive apparatuses are connected between the inner end portion of the secondary torsion tube and one of the hatch doors.

대표청구항 ▼

1. A linkage mechanism for driving an aircraft landing gear bay door, the linkage mechanism being suitable for connecting with bay doors that control access to the inside of a landing gear bay and with a landing gear and converting a back-and-forth movement of the landing gear between a retracted po

1. A linkage mechanism for driving an aircraft landing gear bay door, the linkage mechanism being suitable for connecting with bay doors that control access to the inside of a landing gear bay and with a landing gear and converting a back-and-forth movement of the landing gear between a retracted position inside of the landing gear bay and a released position outside of the landing gear bay, respectively into a back-and-forth movement of the bay doors between a closed position and an open position, the linkage mechanism comprising: a primary torsion tube comprising a first portion located inside the landing gear bay and a second portion outside the landing gear bay;a first drive apparatus connected between the first portion and a landing gear strut so as to transfer the driving force of the strut to the primary torsion tube;a secondary torsion tube comprising an inner end portion located inside the landing gear bay and an outer end portion outside the landing gear bay;a secondary drive apparatus connecting the outer end portion and the second portion for transmitting a torque of the primary torsion tube to the secondary torsion tube; andtwo third drive apparatuses respectively connected between the inner end portion of the secondary torsion tube and one of the bay doors so as to enable the bay doors to be driven by the secondary torsion tube for accomplishing the opening and closing movement. 2. The linkage mechanism for driving an aircraft landing gear bay door according to claim 1, wherein the first drive apparatus comprises: a primary inner crank having opposed ends with one of the opposed ends securely connected to the first portion of the primary torsion tube; anda first rod having two ends, one end of the first rod being pivotally connected between the other end of the primary inner crank and the other end of the first rod being pivotally connected to the strut. 3. The linkage mechanism for driving an aircraft landing gear bay door according to claim 2, wherein the first rod is a L-shaped rod. 4. The linkage mechanism for driving an aircraft landing gear bay door according to claim 3, wherein the L-shaped rod comprises a body portion and a moving portion removably connected with each other. 5. The linkage mechanism for driving an aircraft landing gear bay door according to claim 4, wherein the body portion has a sliding hole and a first rack structure, and the moving portion has a screw hole and a second rack structure, the sliding hole being configured in such a way that a screw passing through the screw hole may slide along the sliding hole so as to adjust a connecting position of the body portion and the moving portion, and in the connecting position, the first rack structure being engaged with the second rack structure, and the body portion and the moving portion being securely tightened by the screw passing through the screw hole and the sliding hole. 6. The linkage mechanism for driving an aircraft landing gear bay door according to claim 5, wherein the inner end portion of the secondary torsion tube is supported on two side walls of the landing gear bay by a ball bearing device, and the first portion and the second portion of the primary torsion tube are respectively supported on one side wall of the landing gear bay and an aircraft supporting structure outside of the side wall by a ball bearing device. 7. The linkage mechanism for driving an aircraft landing gear bay door according to claim 4 wherein the inner end portion of the secondary torsion tube is supported on two side walls of the landing gear bay by a ball bearing device, and the first portion and the second portion of the primary torsion tube are respectively supported on one side wall of the landing gear bay and an aircraft supporting structure outside of the side wall by a ball bearing device. 8. The linkage mechanism for driving an aircraft landing gear bay door according to claim 3, wherein the inner end portion of the secondary torsion tube is supported on two side walls of the landing gear bay by a ball bearing device, and the first portion and the second portion of the primary torsion tube are respectively supported on one side wall of the landing gear bay and an aircraft supporting structure outside of the side wall by a ball bearing device. 9. The linkage mechanism for driving an aircraft landing gear bay door according to claim 2, wherein the primary inner crank and the first portion of the primary torsion tube are connected with each other through a bolt by virtue of their respective lug structures. 10. The linkage mechanism for driving an aircraft landing gear bay door according to claim 9, wherein the inner end portion of the secondary torsion tube is supported on two side walls of the landing gear bay by a ball bearing device, and the first portion and the second portion of the primary torsion tube are respectively supported on one side wall of the landing gear bay and an aircraft supporting structure outside of the side wall by a ball bearing device. 11. The linkage mechanism for driving an aircraft landing gear bay door according to claim 2, wherein the inner end portion of the secondary torsion tube is supported on two side walls of the landing gear bay by a ball bearing device, and the first portion and the second portion of the primary torsion tube are respectively supported on one side wall of the landing gear bay and an aircraft supporting structure outside of the side wall by a ball bearing device. 12. The linkage mechanism for driving an aircraft landing gear bay door according to claim 1, wherein the secondary drive apparatus comprises: a primary outer crank having two ends, one end securely connected to the second portion of the primary torsion tube;a secondary outer crank having two ends, one end securely connected to the outer end portion of the secondary torsion tube; andan intermediate rod having two ends, one end of the intermediate rod being pivotally connected two the other end of the primary outer crank and the other end of the intermediate rod being pivotally connected to the other end of the secondary outer crank. 13. The linkage mechanism for driving an aircraft landing gear bay door according to claim 12, wherein the inner end portion of the secondary torsion tube is supported on two side walls of the landing gear bay by a ball bearing device, and the first portion and the second portion of the primary torsion tube are respectively supported on one side wall of the landing gear bay and an aircraft supporting structure outside of the side wall by a ball bearing device. 14. The linkage mechanism for driving an aircraft landing gear bay door according to claim 1, wherein each third drive apparatus comprises: a secondary inner crank having one end securely connected to the inner end portion of the secondary torsion tube; anda bay door rod having two ends, one end of the bay door rod being pivotally connected two the other end of the secondary inner crank and the other end of the bay door rod being pivotally connected to one of the bay doors. 15. The linkage mechanism for driving an aircraft landing gear bay door according to claim 14, wherein the secondary inner crank and the inner end portion of the secondary torsion tube are connected with each other through a bolt by virtue of their respective lug structures. 16. The linkage mechanism for driving an aircraft landing gear bay door according to claim 15, wherein the inner end portion of the secondary torsion tube is supported on two side walls of the landing gear bay by a ball bearing device, and the first portion and the second portion of the primary torsion tube are respectively supported on one side wall of the landing gear bay and an aircraft supporting structure outside of the side wall by a ball bearing device. 17. The linkage mechanism for driving an aircraft landing gear bay door according to claim 14, wherein the inner end portion of the secondary torsion tube is supported on two side walls of the landing gear bay by a ball bearing device, and the first portion and the second portion of the primary torsion tube are respectively supported on one side wall of the landing gear bay and an aircraft supporting structure outside of the side wall by a ball bearing device. 18. The linkage mechanism for driving an aircraft landing gear bay door according to claim 1, wherein the inner end portion of the secondary torsion tube is supported on two side walls of the landing gear bay by a ball bearing device, and the first portion and the second portion of the primary torsion tube are respectively supported on one side wall of the landing gear bay and an aircraft supporting structure outside of the side wall by a ball bearing device.