固体发动机纤维缠绕壳体设计准则判别式

A Discriminant of Design Criterion for Solid Motor Filament-Wound Case

给出了固体火箭发动机纤维缠绕复合材料壳体设计准则判别式．依据这一准则，当用于制造壳体的纤维材料特征值〔σb〕／Ef≥ε#时，则该材料按刚度准则设计固体火箭发动机壳壁厚度，否则，按强度准则设计壳体厚度．以有机纤维和碳纤维为增强材料，给出两例分别按强度和刚度准则设计的实例。通过另两例强度相近但刚度不同的设计实例的比较，文中提出在设计固体火箭发动机壳体时，应合理选用纤维〔σb〕／Ef的最佳值，并建议发展纤维材料时，应注重强度与刚度的协调。

A discriminant of the design criterion for solid rocket motor filament-wound Composite case is presented. According to the discriminant, when the characteristic data [σb]/Ef of the fiber material for the case is greatcr than or equal to ε#,which is depended on winding angle α, technological parameters (k, ks) and allowable strain ([ε]c) etc, then the thickness desinn for solid rocket motor case made from the materlal is on the basis of stiffness criterion. Otherwise, i. e. when [σb]/Ef<ε#, that is on the basis of strength criterion. Two examples of cases made from organic or carbon fiber comppsite desisned respectively according two the stiffness or strength criterion arc calculated.Through comparing other two examples which are mede from fibers with same strength and different stiffness, the paper suggests that a rational value of [σb]/Ef of the fiber should be considered when the fiber is selected for the case material, and development of the fiber should pay attention to maxe its strength and stiffuess in proportion.