The invention relates to the technical field of tolerance control methods, and discloses an aerodynamic outer edge tolerance control method for a laminar flow wing aircraft, which specifically comprises the following steps of: S100, partitioning a whole aircraft according to the sensitivity of aerodynamic characteristics of all parts and all areas of the whole aircraft to the surface quality of anaerodynamic outer edge; S200, arranging and covering pneumatic outer edge tolerance project ranges related to all aircrafts, and selecting pneumatic outer edge surface related tolerances from the pneumatic outer edge tolerance project ranges; and S300, according to different pneumatic partition ranges, putting differentiated grading tolerance requirements for tolerance related to the pneumatic outer edge surface. The defects of an existing pneumatic outer edge tolerance control method are overcome, the requirement for the surface quality of the pneumatic outer edge of the aircraft is met, andmeanwhile cost increase is restrained.
本发明涉及公差控制方法的技术领域,公开了一种层流机翼飞行器气动外缘公差控制方法,具体包括:步骤S100:根据全机各部件、各区域的气动特性对气动外缘表面质量的敏感程度,对全机进行分区;步骤S200:整理覆盖所有飞行器涉及到的气动外缘公差项目范围,从中挑选出与气动外缘表面相关公差;步骤S300:根据不同气动分区范围,对与气动外缘表面相关公差提出差异化分级公差要求。本发明弥补现有气动外缘公差控制方法的不足,既保证了飞行器气动外缘表面质量要求,同时抑制了成本增加。
Aerodynamic outer edge tolerance control method for laminar flow wing aircraft
一种层流机翼飞行器气动外缘公差控制方法
2020-08-07
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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