The invention discloses a composite material wing spar and a forming method thereof, the wing spar is an integrally formed integral beam, a plurality of cavities are formed in the length direction of the integral beam, and the inner wall surfaces of the cavities are web surfaces of the integral beam; the area, except the cavity, of the upper surface of the integral beam is an upper edge strip surface, and the upper edge strip surface is arranged to be an inclined surface and used for assembling an upper skin; a lower flanging for assembling a lower skin is arranged on one surface opposite to the upper edge strip surface; the web plate surface is in transition connection with the upper edge strip surface through a fillet; every two adjacent web plate surfaces are in transition connection through a fillet; and the side surface of the integral beam is in transition connection with the lower flanging through a fillet. The composite material wing spar is of an integrated wing spar structure, the number of wing spar parts is reduced, and the integrity and reliability of the wing spar structure are improved; compared with a traditional wing spar structure, the integral beam has the advantages that the number of fasteners is reduced, the weight of the wing spar is reduced, the cost is reduced, and the fuel economy and maneuverability of an aircraft are improved.
本发明公开了一种复合材料机翼翼梁及其成型方法,翼梁为一体化成型的整体梁,沿整体梁的长度方向上设置有若干空腔,空腔的内壁面为整体梁的腹板面;整体梁的上表面除空腔以外的区域为上缘条面,上缘条面设置为斜面,用于装配上蒙皮;与上缘条面相对的一面设置有用于装配下蒙皮的下翻边;腹板面与上缘条面之间通过圆角过渡连接;相邻两个腹板面之间通过圆角过渡连接;整体梁的侧面与下翻边之间通过圆角过渡连接。本发明的复合材料机翼翼梁为一体化的整体翼梁结构,减少了翼梁零部件数量,提高翼梁结构的整体性与可靠性;本发明的整体梁相较于传统的翼梁结构其紧固件的数量降低,降低了翼梁的重量,降低成本,提高飞机的燃油经济性和机动性。
Composite material wing spar and forming method thereof
一种复合材料机翼翼梁及其成型方法
2022-03-29
Patent
Elektronische Ressource
Chinesisch