Energy absorbing structure for aircraft
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0636056
(2006-12-08)
|
등록번호 |
US-8376275
(2013-02-19)
|
발명자
/ 주소 |
- Bolukbasi, Akif O.
- Baxter, Thomas R.
- Nguyen, Tuan A.
- Rassaian, Mostafa
- Davis, Kevin R.
- Koch, William J.
- Firth, Lee C.
|
출원인 / 주소 |
|
인용정보 |
피인용 횟수 :
8 인용 특허 :
10 |
초록
▼
Energy absorbing structure disposed beneath the cargo area of an aircraft provides maximum energy absorption and structural strength using carbon fiber reinforced epoxy composites. The energy absorbing structure uses laminated stanchions having ply drop-offs to produce stable, progressive crushing o
Energy absorbing structure disposed beneath the cargo area of an aircraft provides maximum energy absorption and structural strength using carbon fiber reinforced epoxy composites. The energy absorbing structure uses laminated stanchions having ply drop-offs to produce stable, progressive crushing of the stanchions during a wheels-up crash landing. Integrally formed flanges on the stanchions allow direct mounting of the stanchions on the structural members of the aircraft, without the need for specialized fittings.
대표청구항
▼
1. An aircraft, comprising: a fuselage having a fuselage frame;a floor including floor beams within the fuselage and longitudinal beams extending transverse to the floor beams; and,an energy absorbing structure between the floor and the fuselage for absorbing energy in the event the fuselage is impa
1. An aircraft, comprising: a fuselage having a fuselage frame;a floor including floor beams within the fuselage and longitudinal beams extending transverse to the floor beams; and,an energy absorbing structure between the floor and the fuselage for absorbing energy in the event the fuselage is impacted, the energy absorbing structure including a plurality of energy absorbing stanchions extending between the floor beams and the fuselage, each of said energy absorbing stanchions having a first end attached to both a floor beam and a longitudinal beam, and a second end attached to the fuselage frame, and having a cross-section comprising a first pair of spaced apart flanges, each of the flanges having a taper narrowing substantially continuously from the first end to the second end of the stanchion, and having a compressive strength that progressively decreases along substantially an entire length of the stanchion between the floor beam and the fuselage frame,the stanchions being axially oriented at differing angles relative to the longitudinal axes of the floor beams. 2. The aircraft of claim 1, wherein the fuselage includes a curved frame. 3. The aircraft of claim 1, further comprising first and second fittings for attaching each of the stanchions to said floor beam and to said longitudinal beam, each of the fittings including first and second spaced apart flanges for reinforcing the fitting, and a third flange engaging the longitudinal beams. 4. The aircraft of claim 1, wherein each of said stanchions has a cross-section that is C-shaped. 5. The aircraft of claim 1, further comprising first and second fittings directly connected to each of said stanchions, said floor beam and said longitudinal beam. 6. The aircraft of claim 1, wherein each of the stanchions contains laminated plies of reinforced composite material, the plies having varying lengths forming reduced ply steps along the length of the stanchion from the second to the first end. 7. The aircraft of claim 6, wherein the composite material includes an epoxy and a carbon fiber reinforcement. 8. The aircraft of claim 1 wherein each of the stanchions includes: a second pair of flanges respectively connected to the first pair of flanges adjacent the first end of the stanchion. 9. The aircraft of claim 8, wherein the first and second pairs of flanges are integral with each other. 10. The aircraft of claim 8, wherein the second pair of flanges are attached to the longitudinal beams. 11. An energy absorbing floor structure for an aircraft, comprising: a floor;at least one floor beam for supporting the floor;at least one support element extending transverse to the floor beam;a fuselage frame;a plurality of energy absorbing structural members extending between the floor beam and the fuselage frame, each of said energy absorbing structural members attached to both at least one floor beam and at least one support element, each of the structural members having a first set of spaced apart flanges extending from a first end of the member to a second end of the member, each of said members comprising a C-shaped cross-section, said first set of spaced apart flanges having a taper narrowing substantially continuously from the first end to the second end of the member, and a second set of flanges on one end of said structural member engaging the floor beam and said support element; and,means for attaching the each of the structural members to the fuselage frame, the floor beam and the support element. 12. The energy absorbing floor structure of claim 11, wherein: each of the structural members is formed from laminated plies of a composite material and includes ply drop-offs along is length. 13. The energy absorbing floor structure of claim 11, wherein the first set of flanges extends generally perpendicular to the second set of flanges. 14. The energy absorbing floor structure of claim 11, wherein each of the structural members is formed from composite material and the first and second flanges are formed integral with each other. 15. The energy absorbing floor structure of claim 14, wherein the fastening means includes: a first set of fasteners extending through each of the structural members into the floor beam, anda second set of fasteners extending through the second set of flanges into the support element.
이 특허에 인용된 특허 (10)
-
Cole, Barry A, Concrete mounted safety stanchion and apparatus and methods for mounting to concrete.
-
Cronkhite James D. (Hurst TX) Berry Victor L. (Bedford TX) Smith Michael R. (Bedford TX), Crashworthy composite aircraft structure with integral fuel tank.
-
Munsen Victor A. (Seattle WA) Ruane John P. (Auburn WA), Discretely stiffened composite panel.
-
Cronkhite James D. (Hurst TX) Haas Thomas J. (Grand Prairie TX) Mort Raymond W. (Hurst TX), Energy absorbing composite aircraft structure.
-
Thayer, Christopher M., Energy absorbing composite tube.
-
Hayashi, Tohru, Impact resistant structure for the helicopter and energy absorber used for the same.
-
Beuck Guenter (Bremen DEX) Mueller Hans-Juergen (Bremen DEX) Schliwa Ralf (Bremen DEX), Multi-deck passenger aircraft having impact energy absorbing structures.
-
Kulesha Richard L. (Mesa AZ) Jones Michael D. (Mesa AZ) Schmitt Thomas E. (Mesa AZ), Self-stabilized stepped crashworthy stiffeners.
-
Horst Bansemir DE, Subfloor structure of an aircraft airframe.
-
Bolukbasi, Akif O.; Sen, Joyanto Kumar, Variable density stitched-composite structural elements for energy absorption.
이 특허를 인용한 특허 (8)
-
Fitzsimmons, David, Aircraft floor support strut with design failure point.
-
Guering, Bernard; Saint-Marc, Laurent, Aircraft having a simplified general section.
-
Valembois, Guy, Composite L-shaped fitting and method and mould for the production thereof.
-
Vail, III, William Banning; Skerl, Tomislav, Methods and apparatus for monitoring and fixing holes in composite aircraft.
-
Vail, III, William Banning, Methods and apparatus to prevent failures of fiber-reinforced composite materials under compressive stresses caused by fluids and gases invading microfractures in the materials.
-
Charles, Jordan D., Methods of making and structures containing stiffeners having transition portions.
-
Wittmaak, Jr., John R.; Hannan, Philip J.; Lucas, Maxx S.; Tiwari, Chandrashekhar, Skin impact snubber.
-
Charles, Jordan D., Structures containing stiffeners having transition portions.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.