Fibre composite component, winglet and aircraft with a fibre composite component
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-001/14
B64C-003/18
B64C-001/06
B64C-001/12
출원번호
US-0054875
(2013-10-16)
등록번호
US-9957032
(2018-05-01)
우선권정보
DE-10 2011 017 460 (2011-04-20)
발명자
/ 주소
Kremer, Tobias
출원인 / 주소
AIRBUS OPERATIONS GMBH
대리인 / 주소
Lorenz & Kopf, LLP
인용정보
피인용 횟수 :
0인용 특허 :
2
초록▼
A fiber composite component made of a fiber composite material comprises at least one first surface section, at least one second surface section and at least one transition region. The first surface section and the second surface section are arranged at an angle to each other and incorporate the tra
A fiber composite component made of a fiber composite material comprises at least one first surface section, at least one second surface section and at least one transition region. The first surface section and the second surface section are arranged at an angle to each other and incorporate the transition region. The transition region comprises at least one first curvature section and at least one second curvature section whose mean curvatures differ from each other, which curvature sections connect to each other in a tangentially continuous manner. The first surface section connects to the transition region, and the transition region connects to the second surface section in each case in a tangentially continuous manner. In one example, the radius of curvature of the first curvature section is smaller than that of the second curvature section.
대표청구항▼
1. A fiber composite component made of a fiber composite material, comprising: at least one first surface section;at least one second surface section; andat least one transition region that includes a first curvature section having a first constant radius of curvature and a second curvature section
1. A fiber composite component made of a fiber composite material, comprising: at least one first surface section;at least one second surface section; andat least one transition region that includes a first curvature section having a first constant radius of curvature and a second curvature section having a second constant radius of curvature, wherein the radii of curvature differ from each other, which are curved in the same direction and which connect to each other in a tangentially continuous manner,wherein the at least one first surface section and the at least one second surface section are arranged at an angle to each other and enclose the at least one transition region, and the at least one first surface section connects to the at least one transition region, and the at least one transition region connects to the second surface section in each case in a tangentially continuous manner;wherein the fiber composite component is a fiber composite stiffening component; andwherein the thickness of the transition region is substantially constant. 2. The fiber composite component of claim 1, wherein the at least one transition region comprises two first curvature sections that incorporate a second curvature section and the two first curvature sections are connected to the at least one first surface section or the at least one second surface section in a tangentially continuous manner, andwherein the mean curvature of the second curvature section is less than the mean curvature of the first curvature sections. 3. The fiber composite component of claim 1, wherein the first curvature section comprises a radius of curvature that largely corresponds to the minimum radius of curvature of the fibers used in the fiber composite material. 4. The fiber composite component of claim 1, wherein the second curvature section is located at a predetermined location of the fiber composite component. 5. The fiber composite component of claim 4, wherein the radius of curvature of the second curvature section is selected in such a manner that at a predetermined laminate thickness of the fiber composite component, the unfolding stress does not exceed a predetermined unfolding stress. 6. The fiber composite component of claim 1, wherein the radius of curvature of the second curvature section is at least twice as large as the radius of curvature of the first curvature sections. 7. The fiber composite component of claim 1, wherein the radius of curvature of the second curvature section is at least five times as large as the radius of curvature of the first curvature sections. 8. The fiber composite component of claim 1, wherein the radius of curvature of the second curvature section is at least ten times as large as the radius of curvature of the first curvature sections. 9. The fiber composite component of claim 1, wherein the fiber composite component is an angle piece with at least one fastening means on a first surface section and at least one fastening means on a second surface section. 10. The fiber composite component of claim 1, wherein the fiber composite component is a window frame for a vehicle. 11. The fiber composite component of claim 1, wherein the fiber composite component is a stiffening component for a vehicle body. 12. A winglet, comprising: a shell; anda stiffening component as a fiber composite component, the fiber composite component including:a first surface section;a second surface section; anda transition region that includes a first curvature section having a first constant radius of curvature and a second curvature section having a second constant radius of curvature,the thickness of the transition region being substantially constant,wherein the radii of curvature differ from each other, which are curved in the same direction and which connect to each other in a tangentially continuous manner,wherein the first surface section and the second surface section are arranged at an angle to each other and enclose the transition region, and the first surface section connects to the transition region, and the transition region connects to the second surface section in each case in a tangentially continuous manner. 13. An aircraft, comprising: a fiber composite stiffening component including: a first surface section;a second surface section;a transition region that includes a first curvature section having a first constant radius of curvature and a second curvature section having a second constant radius of curvature, wherein the radii of curvature differ from each other, which are curved in the same direction and which connect to each other in a tangentially continuous manner,wherein the thickness of the transition region is substantially constant, andwherein the first surface section and the second surface section are arranged at an angle to each other and enclose the transition region, the first surface section connects to the transition region, and the transition region connects to the second surface section in each case in a tangentially continuous manner, and the first radius of curvature section largely corresponds to the minimum radius of curvature of the fibers used in the fiber composite material. 14. The aircraft of claim 13, comprising a winglet, the winglet including a shell and a stiffening component, wherein the fiber composite component is the stiffening component. 15. The aircraft of claim 13, wherein the radius of curvature of the second curvature section is at least twice as large as the radius of curvature of the first curvature section. 16. The aircraft of claim 13, wherein the radius of curvature of the second curvature section is at least five times as large as the radius of curvature of the first curvature section. 17. The aircraft of claim 13, wherein the radius of curvature of the second curvature section is at least ten times as large as the radius of curvature of the first curvature section. 18. The aircraft of claim 13, wherein the fiber composite component is an angle piece with at least one fastening means on a first surface section and at least one fastening means on a second surface section. 19. The aircraft of claim 13, wherein the fiber composite component is a window frame for the aircraft. 20. The aircraft of claim 13, wherein the fiber composite component is a stiffening component for a fuselage of the aircraft.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (2)
Abbott, Ric, Methods of manufacturing separable structures.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.