Three-Axes Missile Autopilot Design: From Linear to Nonlinear Control Strategies

Devaud, Emmanuel; Harcaut, Jean-Philippe; Siguerdidjane, Houria

doi:10.2514/2.4676

Cited by 54 publications

(27 citation statements)

References 14 publications

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“…1,21 The aerodynamic model for most of the high-performance missiles defines the dependence of rolling moment coefficient on various variables such as aerodynamic roll angle, total angle of attack, Mach number, angle of attack, side-slip angle, and control surface deflection. To this end, the generic model for roll dynamics can be written as 3,22,23 …”

Section: Roll Autopilot Design Problem Mathematical Modelmentioning

confidence: 99%

Performance investigation of extended-state-observer-based roll autopilot design

Sirisha

Das

Talole

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this work, performance analysis of the recently appeared extended-state-observer (ESO)-based roll autopilot design is carried out. Firstly, considering a more realistic roll dynamics, performance comparison of the ESO-based design with several classical roll autopilot structures is carried out and the related results are presented. Next, the better performing designs are implemented and validated through a high fidelity nonlinear 6-DOF environment for a typical tactical missile in a realistic engagement scenario. Lastly, performance of the ESO-based design is investigated using Monte Carlo simulations under several subsystem parameter uncertainties. The results show that the ESO-based design offers satisfactory performance in controlling roll angle and its rate in the presence of significant disturbances, parameter uncertainties and crosscoupling effects and thus offers a viable approach towards design of roll autopilot for high performance tactical missiles.

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Section: Roll Autopilot Design Problem Mathematical Modelmentioning

confidence: 99%

Performance investigation of extended-state-observer-based roll autopilot design

Sirisha

Das

Talole

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Assuming a rigid body, constant mass, and inertia, the standard body axis six-degree-of-freedom equations of motion [3,13,14] are written as …”

Section: Missile Dynamicsmentioning

confidence: 99%

Nonlinear autopilot design for endoatmospheric interceptors with dual control systems

Shao

Zhou

2008

2008 2nd International Symposium on Systems and Control in Aerospace and Astronautics

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acceleration a z is ofa non-minimum phase [3]. By analyzing its phase portrait, the zero dynamics of a tail-controlled missile has been proved to be unstable if the missile's divert acceleration is selected as an output [8,9]. The unstable zero dynamics can also be proved by using the Lyapunov second method [10]. It is well known that a nonlinear control system with an unstable zero dynamics is called a nonlinear non-minimum phase system. Consequently, the non-minimum phase has become an obstacle for applying the feedback linearization technique to the missile's autopilot design. Some approximate linearization methods [8-10] have been applied to overcome the non-minimum phenomenon. It is known that choosing the angle of attack as an output can avoid the non-minimum phase problem, but it indicates that the acceleration guidance command must be transformed into an angle of attack command and such a transformation must cause some error.For a missile with dual control systems, since the reaction thrust can also be involved in the measurement of accelerometers, the autopilot design may be more complicated. It is relatively easy to design an autopilot for the dual controlled missiles based on a classical small deviation linearized model [4,5,11,12] or on choosing the angle of attack as an output in the nonlinear system [6]. However, we should try to analyze the exact nonlinear model of dual controlled missiles, especially its internal dynamics while the divert acceleration is involved in outputs. If the internal dynamics are stable, then a straightforward application of the input-output linearization becomes possible. This paper is organized as follows. Section II presents the nonlinear system model of a missile with dual control systems. In section III internal dynamics of missile models with dual control systems are analyzed. In section IV an autopilot is designed on the basis of internal dynamics analysis. Simulation results are provided in section V. 'IIIAbstract-The nonlinear system model of an endoatmospheric missile whose attitude is controlled by tail fins and reaction jets is presented. By choosing the divert accelerations and rotational rates as output variables, internal dynamics of the nonlinear system are derived and are proved to be bounded under a bounded input. The blending principle of the reaction jets and tail fins is addressed to ensure the normal acceleration is mainly maintained by angle of attack or sideslip angle. An autopilot is designed by using the feedback linearization technique. Results of numerical simulation of an autopilot design example show the effectiveness of the proposed blending principle and the autopilot design.

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“…This section gives a brief overview of multi-objective output-feedback synthesis via the LMI approach described in (Chilali and Gahinet, 1996;Gahinet and Apkarian, 1994). For the missile autopilot design problem, the control objectives include H ∞ and H 2 performance.…”

Section: Multi-objective Controlmentioning

confidence: 99%

“…However, the performance of singleaxis autopilot design approaches are limited within some flight boundaries because aerodynamic coupling effects and their parameter dependencies in large angle-of-attack aerodynamics could not be considered. In this context, the design of a three-axis missile autopilot has been studied using linear and nonlinear control approaches (Choi et al, 2008;Devaud et al, 2001;Kim et al, 2008). These methods are based on gain scheduling techniques by local linearization, and demonstrate some improvements from a practical point of view.…”

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confidence: 99%

Three-Axis Autopilot Design for a High Angle-Of-Attack Missile Using Mixed H₂/H_∞Control

Won¹,

Tahk²,

Kim³

2010

International Journal of Aeronautical and Space Sciences

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The increased demand for high maneuverability of modern missiles requires excellent autopilot performance over a large flight envelope. The main difficulty in missile autopilot design is the influence of high angle-of-attack aerodynamic phenomena on stability characteristics (Hemsch, 1992). As a missile executes a high angle-of-attack maneuver, the forebody vortices can become asymmetric and give rise to significant lateral-forces and yawing moments. Classically, missile autopilots are designed using gain scheduling approaches in roll, pitch, and yaw channels (Blakelock, 1991;Shamma and Athans, 1992;Shamma and Cloutier, 1993;White et al., 2007). However, the performance of singleaxis autopilot design approaches are limited within some flight boundaries because aerodynamic coupling effects and their parameter dependencies in large angle-of-attack aerodynamics could not be considered. In this context, the design of a three-axis missile autopilot has been studied using linear and nonlinear control approaches (Choi et al., 2008;Devaud et al., 2001;Kim et al., 2008). These methods are based on gain scheduling techniques by local linearization, and demonstrate some improvements from a practical point of view.In this paper, a three-axis missile autopilot design with a multi-objective output-feedback control theory is presented. Because high angle-of-attack aerodynamics is highly nonlinear and estimates of the aerodynamic coefficients are very imprecise, a mix of H∞ and H2 criteria is employed to guarantee the performance of the three-axis missile autopilot. This control methodology, which uses linear matrix inequality (LMI) techniques, was motivated by the work in (Schere et al., 1997). This paper is organized as follows. In Section 2, we give an overview of multi-objective output-feedback control theory. Section 3 describes our formulation of the missile control problem. Section 4 describes strategies and numerical simulation results for the designed autopilot. Our conclusions are provided in Section 5. AbstractWe report on the design of a three-axis missile autopilot using multi-objective control synthesis via linear matrix inequality techniques. This autopilot design guarantees H 2 /H ∞ performance criteria for a set of finite linear models. These models are linearized at different aerodynamic roll angle conditions over the flight envelope to capture uncertainties that occur in the high-angle-of-attack regime. Simulation results are presented for different aerodynamic roll angle variations and show that the performance of the controller is very satisfactory.

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Three-Axes Missile Autopilot Design: From Linear to Nonlinear Control Strategies

Cited by 54 publications

References 14 publications

Performance investigation of extended-state-observer-based roll autopilot design

Performance investigation of extended-state-observer-based roll autopilot design

Nonlinear autopilot design for endoatmospheric interceptors with dual control systems

Three-Axis Autopilot Design for a High Angle-Of-Attack Missile Using Mixed H₂/H_∞Control

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Three-Axes Missile Autopilot Design: From Linear to Nonlinear Control Strategies

Cited by 54 publications

References 14 publications

Performance investigation of extended-state-observer-based roll autopilot design

Performance investigation of extended-state-observer-based roll autopilot design

Nonlinear autopilot design for endoatmospheric interceptors with dual control systems

Three-Axis Autopilot Design for a High Angle-Of-Attack Missile Using Mixed H2/H∞Control

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Three-Axis Autopilot Design for a High Angle-Of-Attack Missile Using Mixed H₂/H_∞Control