Rotorcraft fuselage structure incorporating a load-bearing middle floor interposed between a cabin space and an equipment space
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-001/22
B64D-047/00
B64C-001/18
B64D-011/06
B64C-001/06
B64C-027/04
출원번호
US-0529572
(2014-10-31)
등록번호
US-9617013
(2017-04-11)
우선권정보
FR-13 02560 (2013-11-05)
발명자
/ 주소
Mairou, Joseph
Nicola, Jean
출원인 / 주소
Airbus Helicopters
대리인 / 주소
Brooks Kushman P.C.
인용정보
피인용 횟수 :
0인용 특허 :
9
초록▼
A fuselage structure for a rotorcraft (1), the structure comprising load-bearing members including middle frames (9a, 9b) carrying a top floor (12a) and a middle floor (12b). The middle floor (12b) internally partitions the fuselage into two compartments (6, 7), including a cabin-forming top compart
A fuselage structure for a rotorcraft (1), the structure comprising load-bearing members including middle frames (9a, 9b) carrying a top floor (12a) and a middle floor (12b). The middle floor (12b) internally partitions the fuselage into two compartments (6, 7), including a cabin-forming top compartment (6) and a bottom compartment (7) having an open bottom (23) leading to the outside via the bottom face of the fuselage. The middle floor (12b) provides a loading plane in the top compartment (6) having a false-floor (27) made up of interchangeable slabs (28) fitted out in a variety of ways. The middle floor (12b) also forms an anchor member from which equipment (16, 17) for suspending can be suspended, which equipment is accessible from outside the fuselage through said open bottom (23).
대표청구항▼
1. A fuselage structure for a rotorcraft extending longitudinally from the front to the rear of the rotorcraft and made up of load-bearing stiffener members and a load-bearing covering, the stiffener members comprising load-bearing transverse frames locally defining a transverse profile of the fusel
1. A fuselage structure for a rotorcraft extending longitudinally from the front to the rear of the rotorcraft and made up of load-bearing stiffener members and a load-bearing covering, the stiffener members comprising load-bearing transverse frames locally defining a transverse profile of the fuselage structure, and load-bearing longitudinal stiffeners, the fuselage structure having a middle segment longitudinally interposed between a cockpit and a tail boom carrying an anti-torque device, a load-bearing top floor being securely engaged with at least two of the frames, referred to as middle frames and incorporated in the middle segment of the fuselage structure, the top floor providing a top wall of the fuselage and constituting a member for installing at least a substantially vertical axis main rotor of the rotorcraft on the fuselage structure, the fuselage structure being fitted with partitioning structures defining a plurality of compartments in the inside volume of the fuselage, including at least one top compartment having a cabin space function, and at least one bottom compartment having an equipment space function, the top compartment and the bottom compartment being separated from each other by a middle floor arranged vertically between the top compartment and the bottom compartment, the fuselage structure having the top floor overlying the middle floor at least in part, the middle floor providing via its top face a loading plane in the top compartment, wherein the middle floor is secured with at least the middle frames by forming a load-bearing floor, the bottom compartment being free of the covering on a bottom face of the fuselage structure, the middle floor being made up of reinforced panels carried by stiffener members forming load-bearing cross-members and load-bearing longerons of the fuselage structure, the reinforced panels being secured to the load-bearing cross-members and load-being longerons, the fuselage structure having a bottom face that is open to the outside by providing an open bottom for the bottom compartment leading to the outside of the fuselage structure. 2. A rotorcraft fuselage structure according to claim 1, wherein the middle floor provides via its bottom face a suspension anchor member for at least one equipment to be suspended by being accessible from outside the fuselage structure through the open bottom. 3. A rotorcraft fuselage structure according to claim 2, wherein the middle floor is provided via its bottom face forming the ceiling of the bottom compartment with suspension support means for supporting the equipment that is to be suspended, which equipment is selected from at least one any one of the following: at least one fuel tank;slinging equipment dedicated to transporting heavy loads; andwinching equipment dedicated to engaging light loads on board in the bottom compartment. 4. A rotorcraft fuselage structure according to claim 1, wherein the bottom compartment is defined between the middle floor and a lateral skirt arranged in a substructure of the fuselage structure to extend the covering, the skirt defining the open bottom at the margins of free edges of the skirt arranged at its bottom face that is open to the outside of the fuselage structure. 5. A rotorcraft fuselage structure according to claim 1, wherein the top face of the middle floor forms a plane for fastening a false-floor made up of interchangeable slabs selected from a set of slabs respectively pre-fitted with fastener members that are specific to particular pieces of equipment of the rotorcraft, the top compartment being suitable for being arranged to match a variety of flight missions of the rotorcraft by selective replacement of the slabs. 6. A rotorcraft fuselage structure according to claim 5, wherein the slabs are individually pre-fitted with the fastener members for fastening pieces of equipment of the rotorcraft selected from at least any one of the following pieces of equipment: at least one seat;at least one freight attachment member;at least one cord for supporting personnel in suspension;at least one console including at least one computer instrument and at least one information display screen;at least one outlet for connection to an electrical power supply network on board the rotorcraft; andat least one outlet for connection to an information communications network of the rotorcraft. 7. A rotorcraft fuselage structure according to claim 5, wherein a passage is provided for long elements between the top face of the middle floor and the false-floor. 8. A rotorcraft fuselage structure according to claim 1, wherein the open bottom is provided with a removable shutter wall, the removable shutter wall providing, by removal, an access to the bottom compartment from outside of the rotorcraft on ground and providing in flight, by its installation on the fuselage structure, a closing element of bottom compartment. 9. A rotorcraft fuselage structure according to claim 8, wherein the removable shutter wall is formed by a nacelle forming part of winching equipment carried in suspension from the bottom face of the middle floor. 10. A rotorcraft fuselage structure according to claim 1, wherein the load-bearing cross-members are secured with at least the middle frames via the load-bearing longerons interconnecting the cross-members. 11. A rotorcraft fuselage structure according to claim 10, wherein the panels are laminated panels arranged as reinforced honeycomb panels. 12. A rotorcraft fuselage structure according to claim 10, wherein the panels have their edges received in channels formed at least by the cross-members if not also by the longerons. 13. A rotorcraft fuselage structure according to claim 1, wherein the middle floor constitutes a shield providing protection against intrusion into the top compartment of elements external to the top compartment. 14. A rotorcraft including a fuselage structure according to claim 1. 15. A fuselage structure for a rotorcraft comprising: first and second load-bearing transverse end frames, each transverse end frame locally defining a transverse profile of the fuselage structure, the first transverse frame positioned at a first longitudinal end of the structure, and the second transverse frame positioned at a second opposed longitudinal end of the structure;first and second load-bearing transverse middle frames longitudinally spaced apart from one another and positioned between the first and second transverse end frames in a middle segment of the structure longitudinally positioned between a cockpit and a tail boom carrying an anti-torque device, each transverse middle frame locally defining the transverse profile of the fuselage structure;first and second load-bearing longitudinal stiffeners securing the first and second transverse end frames and the first and second transverse middle frames to one another;a load-bearing top floor extending between and secured to the first and second transverse middle frames, the top floor providing a top wall of the fuselage structure, the top floor having a substantially vertical axis main rotor of the rotorcraft installed thereon;first and second load-being longerons secured to and interconnecting the first and second transverse middle frames, the first and second longerons extending longitudinally;a plurality of load-bearing cross-members extending transversely between and secured to the first and second longerons;a load-bearing middle floor formed by reinforced panels secured to and supported by the load-bearing cross-members and the load-bearing longerons, the middle floor partitioning and separating the middle segment of the fuselage structure into a top cabin space compartment and a bottom equipment space compartment, a top face of the middle floor providing a loading plane for the top compartment, the top floor overlying the middle floor to define the top compartment extending therebetween; anda load-bearing covering forming walls for the fuselage and connected to the first and second transverse end frames, the first and second transverse middle frames, and the plurality of longitudinal stiffeners;wherein a bottom face of the fuselage structure is free of the covering such that the bottom compartment is open to the outside of the fuselage structure via an open bottom of the bottom compartment. 16. The fuselage structure of claim 15 wherein the first and second longitudinal stiffeners each extend from the first transverse end frame to the second transverse end frame, the first and second longitudinal stiffeners defining a longitudinal profile of the fuselage structure. 17. The fuselage structure of claim 15 wherein the covering forms a skirt, the skirt cooperating with the middle floor to define the bottom compartment, a free edge of the skirt defining the open bottom of the bottom compartment. 18. The fuselage structure of claim 17 further comprising reinforcement members connected to the skirt and positioned adjacent to the free edge of the skirt and about the open bottom of the bottom compartment. 19. The fuselage structure of claim 15 further comprising a suspension anchor member connected to a bottom face of the middle floor, the suspension anchor member supporting at least one of a fuel tank, slinging equipment, and winching equipment to be accessible via the open bottom. 20. The fuselage structure of claim 15 wherein the middle floor extends from the first transverse end frame to the second transverse end frame to at least partially define the cockpit and the top compartment; and wherein the fuselage structure further comprises a first and second undercarriage for the rotorcraft, the first and second undercarriage anchored to the bottom face of the middle floor.
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이 특허에 인용된 특허 (9)
Barre, Marie Ange; De Villele, Didier; Duperou, Thierry; Godenzi, Christian; Tesson, Mathieu; Vedel, Anne Laure, Aircraft fuselage section.
Sanderson Paul H. (2019 Cripple Creek Lewisville TX 75067), Apparatus and methods for mounting a weaponry support plank on the cabin area floor of a helicopter.
Cronkhite James D. (Hurst TX) Berry Victor L. (Bedford TX) Smith Michael R. (Bedford TX), Crashworthy composite aircraft structure with integral fuel tank.
Wittko Joseph N. (Old Westbury NY) Harding David G. (Brookhaven PA) Schneider John J. (Media PA) Gonsalves Joseph E. (Springfield PA), Hammock supported fuel tank.
Furs Stanley (East Haven CT) Grom Glen (Fairfield CT) Miller Paul W. (Milford CT) Wang David E. (Newton CT) Berardi Arthur F. (Seymour CT), Method for removing a fuel cell.
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