为提高导弹的气动力特性,设计导弹的气动外形时可能出现气动中心位于重心之前的现象。本文应用状态空间分析法,研究气动中心超前的对偶问题,据此获得导弹无恢复力矩时关于飞行状态的完全可控和可测的条件。在状态反馈下,使用极点配置法导出了气动中心超前的极限值,即放宽静稳定性的准则。列举了计算结果。 In order to improve the aerodynamic characteristics of the missile, it may happen that the aerodynamic center is located before the center of gravity when designing the aerodynamic shape of the missile. In this paper, state space analysis is applied to study the duality problem of advanced aerodynamic center. Based on this, the completely controllable and measurable conditions of flight state are obtained when the missile has no restoring moment. Under the state feedback, the pole placement method is used to derive the aerodynamic center leading limit, which is the criterion to relax the static stability. Cited the calculation results.