Composite material, flying body and composite material manufacturing method
AssigneeMitsubishi Heavy Industries, Ltd.
InventorKosuke Nishikawa
Life of this patent
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Abstract
A composite material manufacturing method includes: laminating a first sheet (210) including a first slurry (214) and a third sheet (230) including a third slurry (234); and heating the first sheet (210) and the third sheet (230) that are laminated to a temperature of transforming to ceramics by pyrolysis to form an intermediate body (300). The manufacturing method further includes impregnating the intermediate body (300) with a slurry and heating at a temperature lower than a temperature of transforming to ceramics by pyrolysis.
Claims15
A composite material manufacturing method including:
- laminating a first sheet including a first slurry and a second sheet including a second slurry;
- heating the first sheet and the second sheet that are laminated to a first temperature at which the first slurry and the second slurry transform to ceramics by pyrolysis to form an intermediate body;
- and
- impregnating the intermediate body with a third slurry and heating the impregnated intermediate body at a second temperature, the second temperature being lower than a third temperature at which the third slurry transforms to ceramics by pyrolysis,
- wherein a first composition of the first slurry is different from a second composition of the second slurry, and
- wherein the first slurry includes a ceramic precursor, the second slurry includes a ceramic precursor, and the third slurry includes a ceramic precursor.
A flying body comprising a composite material at a part where aerodynamic heating is applied, the composite material comprising:
- a first layer that includes a first matrix;
- and
- a second layer that includes a second matrix and is provided below the first layer,
- wherein the first layer includes a precursor of the first matrix, and
- wherein the first matrix includes Ultra High Temperature Ceramics (UHTC) particles that have a melting point or a decomposition temperature greater than or equal to 2750° C., a composition of the second matrix is different from a composition of the first matrix, and the first matrix includes more UHTC particles than the second matrix.
Dependencies are inferred from the claim text.