| タイトル | Techno-economic requirements for composite aircraft components |
| 本文（外部サイト） | http://hdl.handle.net/2060/19940012391 |
| 著者（英） | Palmer, Ray |
| 著者所属（英） | Douglas Aircraft Co., Inc. |
| 発行日 | 1993-08-01 |
| 言語 | eng |
| 内容記述 | The primary reason for use of composites is to save structural weight. A well designed composite aircraft structure will usually save 25-30 percent of a well designed metal structure. The weight savings then translates into improved performance of the aircraft in measures of greater payload, increased flying range or improved efficiency - less use of fuel. Composite materials offer technical advantages. Key technical advantages that composites offer are high stiffness, tailored strength capability, fatigue resistance, and corrosion resistance. Low thermal expansion properties produce dimensionally stable structures over a wide range of temperature. Specialty resin 'char' forming characteristics in a fire environment offer potential fire barrier application and safer aircraft. The materials and processes of composite fabrication offer the potential for lower cost structures in the near future. The application of composite materials to aircraft are discussed. |
| NASA分類 | COMPOSITE MATERIALS |
| レポートNO | 94N16864 |
| 権利 | No Copyright |
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