Abstract
This paper presents a comparison of three lateral acceleration autopilots for a surface-to-surface missile: three-loop conventional acceleration autopilot, and gamma-dot and three-loop acceleration autopilot based upon the inverse-dynamic control. The surface-to-surface missile motion is described by nonlinear differential equations whose parameters change rapidly over a very wide range due to variable velocity and altitude. The requirement for the accurate controlling of the missile in such an environment represents a challenge for the autopilot designer. The brief review of the calculation of the autopilot gains is given using the concept of the 'point' stability for the linear time-varying system with 'frozen' dynamic coefficients. The method of the inverse-dynamic control is presented in the next section for two types of the autopilots: gamma-dot and acceleration autopilot. Both of them require the design of the estimators for the variables used as inputs to the control law. Finally, six-degree-of-freedom simulation results of the missile response to the demanded command on the typical ballistic trajectory are presented. The comparison of three autopilots considers the steady state errors and the sensitivity of the response to the highly variable environment. It was shown that the inverse-dynamic control can be very effective in the controlling of the surface-to-surface missile.
Highlights
The aim of this paper is to present the main results of the comparison of different autopilot designs for a surface-to-surface missile (SSM)
Three types of lateral acceleration autopilots for a surface-to-surface missile were analyzed: three-loop conventional acceleration autopilot, and gamma-dot and three-loop acceleration autopilot based upon the application of the inverse-dynamic control
After the calculation of the autopilot gains for the full envelope of the missile flight, the additional adjustment of the gains should be done to compensate for the time varying dynamics of the SSM
Summary
The aim of this paper is to present the main results of the comparison of different autopilot designs for a surface-to-surface missile (SSM). The purpose of the autopilot is to control the modified SSM during the whole flight, i.e., at low-, medium- and high altitude flight conditions This is a difficult problem because the aerodynamic controls are very sensitive to the high variation of the air density, Mach number, angle of attack, and other missile dynamic properties needed for the autopilot design. Tedious process of generating numerous aerodynamic transfer functions is required After this step, the “frozen-point” stability is done to develop autopilot gains for the purpose of gain scheduling. The “frozen-point” stability is done to develop autopilot gains for the purpose of gain scheduling This method of the autopilot design was described in many references such as Refs.
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