摘要:
The purpose of the present invention is to obtain a fiber-reinforced plastic that is capable of controlling anisotropy, has excellent mechanical characteristics, has little variation, has excellent heat resistance, and has good fluidity during forming. A production method for fiber-reinforced plastic, having: a step in which a material (A) (100) including a prepreg base material is obtained, said prepreg base material having cuts therein and having a thermoplastic resin impregnated in reinforcing fibers (110) arranged in parallel in one direction; a step in which a pressurizing device is used that applies a substantially uniform pressure in a direction (X) orthogonal to the travel direction of the material (A) (100) and the material (A) (100) is caused to travel in the one direction and is pressurized while being heated to a prescribed temperature (T), an angle (.theta.) of −20-20.degree. being formed between the orthogonal direction (X) and a fiber axial direction (Y) for the reinforcing fibers (110) of the prepreg base material; and a step in which the material (A) (100) pressurized by the pressurizing device is cooled and the fiber-reinforced plastic is obtained
摘要:
A composite bearing comprising a densified portion, wherein a hole location is positioned at the approximate center of said densified portion; and a plurality of filament tendrils, wherein the plurality of filament tendrils are configured to wrap around the hole location to create a “U” shape.
摘要:
A method of making a composite board and a product made thereby are disclosed. The method includes a lining forming step, a fiber pipe rolling step, a fiber pipe mounting step, a fiber material covering step, and a board body forming step. The product includes a lining acting as a board body, a plurality of long slots formed on the lining, a fiber pipe placed in each of long slots, a foam material mounted in each of fiber pipes, and a fiber material covering an external periphery of the lining. The fiber materials and the fiber pipes are melted and combined together by heat, thereby shortening the operating time. The fiber pipe becomes a reinforcement support structure to increase a structural strength of the composite board, thereby producing a finished product with a light weight and a strong structure.
摘要:
A method of through-thickness reinforcing a laminated material is disclosed, in which a reinforcing element is coated with a thermoplastic layer. The reinforcing element is inserted into a base material, and a matrix material, such as a polymeric, is included in the base material. The combination is then cured, or heated, such that the thermoplastic layer and the matrix material diffuse into each other, thereby forming an interphase region around the reinforcing element. This interphase region helps to prevent cracks from propagating from the reinforcing element.
摘要:
An aircraft wing cover (10) comprising an integrally stiffened sandwich panel including first and second skins (11, 12) sandwiching a core layer (13), wherein at least one of the skins has a plurality of spanwise extending integral regions of increased thickness (18) accommodated by corresponding regions (19) of decreased thickness in the core. Also, a method of fabricating an aircraft wing cover, and a method of designing an aircraft wing.
摘要:
A fiber preform for producing fiber composite structures, a wall thereof including a first zone made from reinforcing fiber bundles having a first resin composition and a second zone made from at least one fiber tape comprising at least one unidirectionally directed reinforcing yarn strand having a second resin composition. The reinforcing fiber bundles in the first zone are oriented in different spatial directions to each other when viewed in a direction parallel to the extension of the thickness. Each reinforcing fiber has a length of from 3 to 50 mm, and contains the first resin composition in a concentration of from 1 to 10 wt % of the fiber weight. The wall of the fiber preform has a proportion of reinforcing fibers of more than 35 vol %, and the second zone forms a discrete region when viewed in a direction perpendicular to the thickness extension of the wall.
摘要:
A method of fabricating a composite material part such as a link. The method comprises the successive operations of applying reinforcing fiber layers (14a, 14b, 14c) that are braided around a mandrel over all or part of the length of the mandrel, the layers being superposed one on another. The method includes a step of cutting an intermediate reinforcing fiber layer (14a, 14b, 14c) after it has been applied, a step of withdrawing a cut portion prior to applying the following braided layer (14b, 14c), thereby locally building up an extra thickness of reinforcing layers on each portion of the cut layer that has remained in place, the extra thickness constituting local reinforcement of the part. Resin is subsequently injected into the various braided layers prior to the resin being polymerized in order to prepare a blank. The method applies in particular to the field of aviation.
摘要:
Portable apparatus for curing a part includes a wheeled frame having sliding part supports that move the part from a loading position to a curing position. A part clamping assembly is slidably mounted on the frame to apply clamping pressure to the part when the part is in the curing position in order to compact the part during a cure cycle. The clamping assembly includes a set of electrically heated shoes that heat the part to a cure temperature. A fan is provided to accelerate cool down the part after curing is complete. The heating and cooling operations are automatically performed by a programmed controller.
摘要:
An aircraft wing cover (10) comprising an integrally stiffened sandwich panel including first and second skins (11, 12) sandwiching a core layer (13), wherein at least one of the skins has a plurality of spanwise extending integral regions of increased thickness (18) accommodated by corresponding regions (19) of decreased thickness in the core. Also, a method of fabricating an aircraft wing cover, and a method of designing an aircraft wing.
摘要:
The present disclosure relates to a fibrous veil and methods of making the same. The fibrous veil includes a base having a plurality of fibers, each of the plurality of fibers having an average diameter ranging from about 7,000 nm to about 9,000 nm. Graphite nano-platelets are attached to at least some of the plurality of fibers without a polymeric binder.