IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0410865
(2009-03-25)
|
등록번호 |
US-8322655
(2012-12-04)
|
발명자
/ 주소 |
- Kismarton, Max
- Kutzmann, Aaron J.
- Lutke, Kevin
|
출원인 / 주소 |
|
대리인 / 주소 |
Hope Baldauff Hartman, LLC
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
31 |
초록
▼
Apparatus and methods provide for an aircraft empennage that utilizes two torque tube members to create opposing sides of the empennage. The torque tube members are connected using a bridging member that is attached at opposing ends to the top portions of the torque tube members. The torque tube mem
Apparatus and methods provide for an aircraft empennage that utilizes two torque tube members to create opposing sides of the empennage. The torque tube members are connected using a bridging member that is attached at opposing ends to the top portions of the torque tube members. The torque tube members and bridging member provide structural support for access cut-outs within the aircraft skin between the torque tube members for access to a payload space within. The torque tube members may include any number of walls, any of which may provide a pressure barrier to the payload space.
대표청구항
▼
1. A twin-boom empennage, comprising: a pair of torque tube members, each torque tube member attached to and extending rearward from a fuselage portion of an aircraft and comprising at least one wall configured to enclose a space extending a length of the torque tube; anda bridging member connecting
1. A twin-boom empennage, comprising: a pair of torque tube members, each torque tube member attached to and extending rearward from a fuselage portion of an aircraft and comprising at least one wall configured to enclose a space extending a length of the torque tube; anda bridging member connecting a top portion of each of the pair of torque tube members, that the pair of torque tube members and the bridging member providing opposing lateral barriers and an upper barrier around a payload space disposed between the pair of torque tube members such that the opposing lateral barriers and the upper barrier provide structural support for an access cut-out to the payload space between the pair of the torque tube members; whereineach of the pair of torque tube members comprises a trapezoidal cross-sectional shape, and wherein each of the pair of torque tube members is configured such that a longest side of the trapezoidal cross-sectional shape is positioned adjacent to the payload space and an opposing shortest side of the trapezoidal cross-sectional shape is positioned adjacent to a side of the aircraft. 2. The twin-boom empennage of claim 1, wherein the at least one wall of each torque tube member comprises an internal barrier adjacent to the payload space and at least one external barrier, and wherein the internal barrier of each torque tube member is configured as a pressure barrier to the payload space such that an air pressure within the space extending the length of each torque tube member may vary from an air pressure of the payload space. 3. The twin-boom empennage of claim 1, wherein the at least one wall of each torque tube member comprises an internal barrier adjacent to the payload space and at least one external barrier, and wherein the at least one external barrier of each torque tube member is configured as a pressure barrier such that the an air pressure within the space extending the length of each torque tube member is substantially equivalent to an air pressure of the payload space. 4. The twin-boom empennage of claim 1, further comprising a plurality of stiffening members disposed within each of the pair of torque tube members. 5. The twin-boom empennage of claim 1, wherein the access cut-out is sized according to a cross-sectional width and height of the payload space to maximize access to the payload space for loading and unloading of cargo. 6. The twin-boom empennage of claim 5, further comprising a payload door movably connected to the access cut-out. 7. The twin-boom empennage of claim 1, further comprising a payload floor spanning between a bottom portion of each of the pair of torque tube members such that the payload floor, the bridging member, and the at least one wall of each of the pair of torque tube members comprise bottom, top, and opposing lateral pressure barriers for pressurizing the payload space. 8. The twin-boom empennage of claim 1, wherein the bridging member comprises a frame member connected to the top portion of each of the pair of torque tube members such that the frame member penetrates each of the pair of torque tube members at opposing ends of the frame member and is secured within each of the pair of torque tube members. 9. The twin-boom empennage of claim 1, wherein the at least one wall of each of the pair of torque tube members comprises an outer wall facing a side of the aircraft, the outer wall comprising a flat surface suitable for mounting aircraft components. 10. An aircraft fuselage, comprising: a main fuselage portion connected to an aircraft wing;a first torque tube member attached to the main fuselage portion of an aircraft and extending away from the main fuselage portion such that the first torque tube member creates a first empennage side;a second torque tube member attached to the main fuselage portion of the aircraft and extending away from the main fuselage portion such that the second torque tube member creates a second empennage side;a bridging component connecting a top portion of the first torque tube member to a top portion of the second torque tube member such that the first torque tube member, the second torque tube member, and the bridging component define a load bearing empennage; andan aircraft skin covering the load bearing empennage comprising an access cut-out at a location between the first torque tube member and the second torque tube member that provides access to a payload space within the load bearing empennage; whereineach of the first and second torque tube members comprises a trapezoidal cross-sectional shape, and wherein each of the first and second torque tube members is configured such that a longest side of the trapezoidal cross-sectional shape is positioned adjacent to the payload space and an opposing shortest side of the trapezoidal cross-sectional shape is positioned adjacent to a side of the aircraft. 11. The aircraft fuselage of claim 10, wherein each of the first torque tube member and the second torque tube member comprises an inner wall adjacent to the payload space and at least one outer wall, and wherein each inner wall is configured as a pressure barrier to the payload space. 12. The aircraft fuselage of claim 10, wherein each of the first torque tube member and the second torque tube member comprises an inner wall adjacent to the payload space and at least one outer wall, and wherein each of the at least outer walls is configured as a pressure barrier to the payload space. 13. The aircraft fuselage of claim 10, further comprising a payload floor spanning between a bottom portion of each of the first and second torque tube members such that the payload floor, the bridging component, and at least one wall of each of the first and second torque tube members comprise bottom, top, and opposing lateral pressure barriers for pressurizing the payload space. 14. The aircraft fuselage of claim 10, wherein the bridging component is connected to the top portion of each of the first and second torque tube members such that the bridging component penetrates each of the first and second torque tube members at opposing ends of the bridging component and is secured within each of the first and second torque tube members. 15. A method for providing an aircraft empennage, the method comprising: attaching a first torque tube member having a trapezoidal cross-sectional shape to a first side of a main fuselage portion of an aircraft such that the first torque tube member extends away from the main fuselage portion to create a first empennage side;attaching a second torque tube member having a trapezoidal cross-sectional shape to a second side of the main fuselage portion of the aircraft such that the second torque tube member extends away from the main fuselage portion to create a second empennage side;splicing a first end of a bridging component into a top portion of the first torque tube member;splicing an opposing second end of the bridging component into a top portion of the second torque tube member such that the first torque tube member, the second torque tube member, and the bridging component define a load bearing empennage;attaching a bottom portion of the first torque tube member and a bottom portion of the second torque tube member to a payload floor such that the load bearing empennage and the payload floor define a perimeter of a payload space and such that a longest side of the trapezoidal cross-sectional shape of the first torque tube member and of the second torque tube member is positioned adjacent to the payload space and an opposing shortest side of the trapezoidal cross-sectional shape of the first torque tube member and of the second torque tube member is positioned adjacent to a side of the aircraft;covering an outer surface of the load bearing empennage and payload floor with an aircraft skin; andproviding an access cut-out in the aircraft skin between the first torque tube member and the second torque tube member to provide access to the payload space. 16. The method of claim 15, further comprising configuring each of the first torque tube member and the second torque tube member such that an outer wall of the torque tube member comprises a pressure barrier between an interior air pressure within the payload space and an exterior air pressure and such that an inner wall of the torque tube member comprises a physical barrier to payload within the payload space and is open to the interior air pressure on opposing sides of the inner wall. 17. The method of claim 15, further comprising configuring each of the first torque tube member and the second torque tube member such that an inner wall of the torque tube member comprises a physical barrier to payload within the payload space and comprises a pressure barrier between an interior air pressure within the payload space and an exterior air pressure within the torque tube member. 18. The method of claim 15, further comprising configuring each of the first torque tube member and the second torque tube member with a trapezoidal cross-sectional shape such that a longest side of the trapezoidal cross-sectional shape is positioned adjacent to the payload space and an opposing shortest side of the trapezoidal cross-sectional shape is positioned adjacent to a side of the aircraft.
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