Wing and blade structure using pultruded composites
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B32B-003/26
B29C-070/86
B29C-070/54
B29C-070/68
B64C-003/18
B32B-005/02
B32B-005/12
B32B-005/26
B29C-070/52
B29L-031/30
출원번호
US-0372119
(2012-02-13)
등록번호
US-9550332
(2017-01-24)
발명자
/ 주소
Karem, Abe
출원인 / 주소
Karem, Abe
대리인 / 주소
Fish & Tsang LLP
인용정보
피인용 횟수 :
0인용 특허 :
12
초록▼
Tapered layers of pre-cured composite material are integrated into a tapered, highly stressed laminate structure in order to provide improved compressive strength. The pre-cured composite material can advantageously be cured under tension as pultruded material, to further augment compressive strengt
Tapered layers of pre-cured composite material are integrated into a tapered, highly stressed laminate structure in order to provide improved compressive strength. The pre-cured composite material can advantageously be cured under tension as pultruded material, to further augment compressive strength. The thickness of composite layers can be tapered on their termination edges by mechanically abrading, chemical abrading, or other methods. Especially preferred embodiments include aircraft structural components such as wings, wing spars, wing skins, fuselage skins, rotor blades, propellers, and propeller blades. Preferred laminates can be constructed to have at least 6, 10, 30, 50, or 100 layers of material, and can have a maximum thickness of at least 0.15, 0.25, 0.5, 1.0, or 5.0 inches.
대표청구항▼
1. A composite laminate having: first and second layers;a laminate thickness tapering at least 60% from a maximum thickness to an edge of the laminate;the first layer comprising pultruded composite fibers, and having a length, a width and a thickness, wherein the length is greater than the width, an
1. A composite laminate having: first and second layers;a laminate thickness tapering at least 60% from a maximum thickness to an edge of the laminate;the first layer comprising pultruded composite fibers, and having a length, a width and a thickness, wherein the length is greater than the width, and the width is greater than the thickness; andwherein the thickness of the first layer reduces by at least 10% along the length of the first layer. 2. The laminate of claim 1, wherein the second layer comprises pultruded fibers. 3. The laminate of claim 2, wherein the fibers are graphite fibers. 4. The laminate of claim 1, wherein the thickness of the first layer is at least 10/1000 inch. 5. The laminate of claim 1, wherein the pultruded composite fibers are oriented in a first direction, and the pultruded fibers in the second layer are oriented at least 10° away from the first direction. 6. The laminate of claim 1, wherein the first layer tapers at a 10:1 or shallower slope. 7. The laminate of claim 2, further comprising a third layer of biased pre-preg tape. 8. The laminate of claim 1, comprising the first layer having a max compressive stress before failure at any point along the laminate that is at least 70% of a max tensile stress before failure of the first layer. 9. An improved aircraft, the improvement comprising a wing structure comprising the laminate of claim 1.
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이 특허에 인용된 특허 (12)
Tingley Daniel A. (3310 SW. Willamette Ave. Corvallis OR 97333), Aligned fiber reinforcement panel for structural wood members.
Koeneman James (Mesa AZ) Hansen Thomas (Phoenix AZ) Yapp Ron (Phoenix AZ) Weinstein Allan M. (Paradise Valley AZ) Johnson Roger (Phoenix AZ), Beam construction and method.
Rogers Charles W. (Arlington TX) Crane David A. (Fort Worth TX) Rai Habib G. (Bedford TX), Continuous process of making unidirectional graphite fiber reinforced pultruded rods having minimal fiber waviness.
Wiler Donna M. (Akron OH) DeTrano Mario N. (Massillon OH) Bohm Georg G. A. (Akron OH), Method and apparatus for ablative processing of elastomeric products.
Lambing Cynthia L. T. (Apollo PA) Barbus John J. (Monroeville PA) Miller Donald C. (Ford City PA), Method for pultruding fiber-reinforced thermoplastic stock.
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