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飞机直接力控制这一主动控制技术应用于火力/飞行综合控制,可有效地提高火控精度,延长接火时间,提高命中概率。但欲进一步提高攻击区的姿态跟踪精度已受到自然飞机惯性动力学的限制。本文提出飞机中性稳定机身瞄准这一新型模态,其途径是使用后缘襟副翼的对称偏转,对迎角小扰动变化进行气动解耦,从而构成飞机中性稳定,使飞机动力学由惯性振荡型转变为非周期型,有效地加速了飞机在攻击区的姿态跟踪动志过程,抑制了动态误差,明显地提高了抑制阵风干扰能力,并实现了姿态控制过程中航迹基本不变的机身瞄准模态控制要求。对诸如上述火力/飞行系统设计者所寻求的性能,本文将以YF-16飞机为背景,在理论设计基础上进行必要的仿真验证。
The direct control of aircraft force, which is an active control technology used in fire / flight control, can effectively improve the accuracy of fire control, extend the access time and increase the probability of hit. But to further improve the attitude of the attack area tracking accuracy has been limited by the natural aircraft inertial dynamics. This paper proposes that the aircraft’s neutral and stable fuselage aim at this new mode by aerodynamically decoupling the small disturbance of the angle of attack using the symmetrical deflection of the trailing edge ailerons so as to make the aircraft neutral and stable and make the aircraft dynamics The inertial oscillation mode is changed into a non-periodic type, which accelerates the attitude tracking of the aircraft in the attack zone effectively, restrain the dynamic error, obviously improve the ability to restrain the gust disturbance, and achieve the same trajectory during the attitude control The body is aimed at modal control requirements. For the performance sought by designers such as the above firepower / flight system, this paper will carry out the necessary simulation verification on the basis of theoretical design with YF-16 as the background.