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根据一些典型的前苏联设计方案的结构外形,对几种导弹设计方案的气动特性进行了考核。包括具有前控制面或后控制面的固定翼导弹、具有固定后稳定面的翼控制导弹。这些方案的任务包括空对空、地对地、空对地和地对空攻击。分析与实验结果表明,通过合理的选形、部件布局及当地流场的考察。这些方案通常能提供好的稳定性、高的控制效率和低的控制铰链力矩。此外,在一些巡航型任务的情况下,可利用受力面积准则作为一种提高气动力效率的有效方法。通常,解决关键问题的设计准则是针对要完成的特殊任务研究特殊的结构。
According to the structure of some typical Soviet designs, the aerodynamic characteristics of several missile designs were evaluated. Including fixed-wing missiles with front or rear control surfaces and wing-control missiles with fixed rear stabilizers. The missions of these programs include air-to-air, Earth-to-Earth, air-ground and Earth-to-air attacks. Analysis and experimental results show that, through reasonable shape selection, component layout and inspection of local flow field. These solutions generally provide good stability, high control efficiency, and low control hinge torque. In addition, in some cruise missions, force-area criteria can be used as an effective way to improve aerodynamic efficiency. In general, the design criteria for solving a critical problem are to study a particular structure for the particular task to be accomplished.