Abstract
In this paper, we derive the sufficient and necessary stability conditions for rolling missiles with velocity orientation autopilot. For the mathematical derivation, linear time-invariant mathematical models are established. Structures of the velocity orientation autopilot for nonrolling and rolling missiles are introduced. In addition, the effects of the autopilot structure and parameters on stability are discussed. Furthermore, methods associated with actuator dynamics, static stability and decoupling are presented to improve the stability of rolling missiles. Numerical simulations are conducted to verify the accuracy of the discussion. It is demonstrated that the stability conditions can guide rolling missile velocity orientation autopilot design for the stabilization of the flight of rolling missiles.
Highlights
V ELOCITY orientation autopilot is a typical autopilot that can improve the damping characteristics and increase the stability and interference rejection capability of missiles
In this paper, the sufficient and necessary stability conditions for rolling missiles with velocity orientation autopilot are obtained by mathematical derivation
The analysis of the stability conditions indicates that the total deviation angle of the control system should not exceed 90°
Summary
V ELOCITY orientation autopilot is a typical autopilot that can improve the damping characteristics and increase the stability and interference rejection capability of missiles. Limited studies have pay attention on on the stability conditions of the coning motion of rolling missiles with velocity orientation autopilot which is commonly used. Motivated by the previously mentioned works, this paper proposes the stability criterion of the velocity orientation autopilot of a rolling missile. The steady-state deviation angle of the actuators in the nonrolling body coordinates of a rolling missile can be expressed as follows: γc = arccos. The inner loop is necessary to stabilize a velocity orientation autopilot regardless of whether the missile is statically stable
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