Missile acceleration controller design using proportional–integral and non-linear dynamic control design method

Abstract

In this article, a method to make the normal acceleration of medium angle of attack missile to track some desired trajectories is presented. The dynamics which describe a missile acceleration are known to be non-minimum phase, which makes it difficult to use a straightforward feedback linearization technique. This article aims at showing that this problem may be overcome by employing cascaded regulations in the non-linear area. First, inner loop controller by dynamical sliding mode control (SMC) method based on asymptotic output tracking is designed for angle of attack control which has a minimum phase characteristics. Also then, the problem that is addressed here is the completion of the global loop by designing an additional outer loop proportional–integral (PI) controller and angle of attack estimator. The performance and stability of proposed method are illustrated via computer simulations.

High angle of attack command generation technique and tracking control for agile missiles

“…A lot of studies mentioned above have designed angle of attack control system, implying a transformation from desired acceleration command to equivalent angle of attack command. To this end, the relationship between missile turn rate and angle of attack was discussed in [6,11] Similarly, under the assumption that the missile body acceleration is proportional to angle of attack, a PI controller approach has been proposed in [10,12] in order to generate a desired angle of attack signal used for tracking body acceleration reference in agile turn. No matter which generation approach of angle of attack command is taken, high angle of attack flight is necessary for a missile to complete the agile turn.…”

Missile two-loop acceleration autopilot design based on 𝓛1adaptive output feedback control

“…Based on two-time 1 L adaptive state feedback augmented DI autopilot. In erver were adopted for the design of a new angle-ofheory and a PI controller, the authors in [6] designed a r loop is a sliding mode control (SMC) based angle-ofmethod considers the 'worst case' in the design procedure. In [3], the authors designed a novel dynamic inversion (DI) architecture through output redefinition (i.e., a combination of angle of attack and pitch rate as output instead of the typical acceleration), which they augmented using a neural network.…”

“…In [5], the time-delay control and nonlinear observer were adopted for the design of a new angle-of-attack autopilot. Using sliding mode control theory and a PI controller, the authors in [6] designed a two-loop acceleration autopilot, where the inner loop is a sliding mode control (SMC) based angle-of-attack tracking loop and the outer loop is the PI acceleration tracking loop. In [7], adaptive SMC theory is used to design a model-following missile pitch autopilot to reject model uncertainty and disturbance, and the well-known classical PI-type autopilot is constructed as the reference model.…”

Agile Missile Autopilot Design using Nonlinear Backstepping Control with Time-Delay Adaptation

“…Unlike the angle-of-attack control loop, a straightforward application of the backstepping method to the acceleration control is limited due to the nonminimum characteristic of the acceleration control loop. 9,10,24,25) In order to track the desired acceleration and handle the non-minimum phase system for acceleration control, a cascaded control structure, as shown in Fig. 3, is used as studied in Refs.…”

“…Furthermore, an intercept scenario, including the agile turn and the terminal homing phases, is also performed. For this purpose, the acceleration controller is also constructed based on a cascaded control structure, 24,25) the angle-of-attack controller is augmented by the outer proportional-integral (PI) controller in order to handle the non-minimum phase characteristics, and at end of the agile turn phase, the autopilot controlling the angle-of-attack is reconfigured to control the body acceleration using a simple control command blending logic.…”