The Response Characteristics of Controlled Angular Motion of the Two-dimensional Correction Spin-stabilized Projectile with Canard Configuration

To address the angle of attack response of spin-stabilized projectiles with canard configuration under time-varying roll angle commands, a state-space model of the projectile is established based on the small angle of attack assumption, and the impulse response matrix is solved. In the time domain, a general analytical model for the angle of attack response is constructed using the convolution theorem, and in the frequency domain, the potential resonance mechanism induced by periodic command inputs is analyzed. To clarify the influence of canard structural parameters, aerodynamic parameters, and control parameters on the angle of attack, a parameterized analytical solution for the amplitude of the angle of attack is derived. The results show that the established general analytical model can accurately calculate the angle of attack response under time-varying, fixed and periodic roll angle commands. Increasing the deflection angle of the canard, the distance from the action point of control force to the projectile’s center of mass, and the derivative of lift coefficient will all lead to an increase in the amplitude of the angle of attack. During flight, the frequent changes in the roll angle should be avoided as far as possible, and the amplitude of the angle of attack should be limited to ensure the flight stability. In addition, when the roll angle command changes continuously, it is necessary to prevent its change frequency from approaching the inherent frequency of the projectile to avoid a sharp increase in the amplitude of the angle of attack. The simulated results verify the correctness of the theory, and this research supplements the studies on the angular motion characteristics of spin-stabilized projectiles with canard configuration.