Abstract
This paper develops a novel autopilot design method for blended missiles with aerodynamic control surfaces and lateral jets. Firstly, the nonlinear model of blended missiles is reduced into a piecewise affine (PWA) model according to the aerodynamics properties. Secondly, based on the equivalence between the PWA model and mixed logical dynamical (MLD) model, the MLD model of blended missiles is proposed taking into account the on-off constraints of lateral pulse jets. Thirdly, a hybrid model predictive control (MPC) method is employed to design autopilot. Finally, simulation results under different conditions are presented to show the effectiveness of the proposed method, which demonstrate that control allocation between aerodynamic control surfaces and lateral jets is realized by adjusting the weighting matrix in an index function.
Highlights
The emergence of highly maneuverable targets has brought new challenges to guidance technology
To deal with the discrete property of the lateral jet forces, some logical variables are introduced for model predictive control (MPC) controller design, which increases the number of subregions inevitably
An autopilot design method for a missile with aerodynamic control surfaces and lateral jets is presented in this paper
Summary
The emergence of highly maneuverable targets has brought new challenges to guidance technology. As an important property of advanced missiles, multiple actuators are often employed to enhance maneuverability as well as interception probability Both aerodynamic surfaces and reaction jets are employed in the control system of PAC-3. For the autopilot design of blended missiles (such as PAC-3), two aspects of control input constraints should be taken into account: the saturation constraint on aerodynamic surfaces and the finite set constraint on reaction jets. They are not simultaneously considered in the aforementioned work.
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