Robust Flight Control Tuning for Highly Agile Missiles

Theodoulis, Spilios; Proff, Michael

doi:10.2514/6.2021-1568

Cited by 3 publications

(3 citation statements)

References 31 publications

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“…I n the last decades, the Linear Parameter Varying (LPV) framework has attracted increasing interest in the modeling and the control of a wide range of aerospace applications. Initial studies presented the LPV modeling approach as a perfect match for the well-established gain-scheduling controller design technique, leading to relevant contributions both in terms of missile [1][2][3][4][5], and aircraft [6][7][8] applications. Important studies have also focused on the investigation of guided projectiles, intending to improve the accuracy and the range capability of artillery operations.…”

Section: Introductionmentioning

confidence: 99%

Linear Parameter Varying Pitch Autopilot Design for a Class of Long Range Guided Projectiles

Vinco

Theodoulis

Sename

et al. 2023

AIAA SCITECH 2023 Forum

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Promising results on LPV design have been recently proposed, concerning the modeling and control of missiles, rockets, and aircraft. However, very few investigations have been focused on the development of guided projectile applications. This paper presents a pure linear parameter varying (LPV) modeling and control design approach intended to improve the range capability of a new class of Long Range Guided Projectiles (LRGP). The investigated concept consists of an asymmetric 155 mm fin-stabilized projectile equipped with a reduced amount of control actuators and characterized by a predominant unstable behavior across the analyzed flight envelope. The main advantages of the LPV design in terms of guaranteed robustness and stability are compared to standard gain-scheduling-based linear time-invariant (LTI) control strategies. A nonlinear simulation scenario is performed in order to assess the reliability of a pure LPV autopilot design, based on the polytopic formulation, across the entire flight envelope, over a local modal control design related to a specific set of flight conditions.

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Section: Introductionmentioning

confidence: 99%

Linear Parameter Varying Pitch Autopilot Design for a Class of Long Range Guided Projectiles

Vinco

Theodoulis

Sename

et al. 2023

AIAA SCITECH 2023 Forum

Self Cite

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“…Various practical systems have dynamics that exhibit non-minimum phase characteristics, from process control [2] (e.g., thermal processes where time delays are approximated by non-minimum phase zero system dynamics), to aerospace systems (e.g., altitude of an aircraft, tail-controlled missile) [3], to maritime systems (e.g., pitch control of underwater vehicles) [4], to mechanical systems (e.g., pole balancing type systems) and ground vehicle applications (e.g., nulling control of tilting rail vehicles) [5].…”

Section: Introductionmentioning

confidence: 99%

Simple Internal Model-Based Robust Control Design for a Non-Minimum Phase Unmanned Aerial Vehicle

Zolotas

2023

Machines

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Robust control has been successful in enabling flight stability and performance for UAVs. This paper presents a simple explainable robust control design for UAV platforms with non-minimum phase (NMP) zero characteristics in their model. The paper contributes to economic (simple) robust control design by addressing the NMP model’s characteristics via Internal Model Control (IMC) and its impact on the UAV pitch response performance. The proposed design is compared with a Parallel Feedback Control Design (PFCD) scheme for the same vehicle platform, for fair comparison. Simulation results illustrate the achievement of the proposed control designs for the UAV platform; only the pitch control is addressed. A by-product of this work is the interpretation of different ways of manipulating the non-minimum phase plant model, so-called ‘modelling for control’, to enable the simple controller design. The work in this paper underpins the simplicity and robustness of the IMC technique for the NMP UAV platform, which further supports the explainability of the control structure relative to performance.

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“…However, missiles face interference from various uncertainties during the attitude control process. If the anti-interference performance is not good, it will seriously affect the missile's command tracking accuracy [1][2][3][4][5][6]. Therefore, the designed controller must ensure the performance and stability robustness of the system under strong uncertainty.…”

Section: Introductionmentioning

confidence: 99%

Attitude Autopilot Design Based on Fuzzy Linear Active Disturbance Rejection Control

Han

Shi

2022

Aerospace

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In view of the multi-source uncertainty disturbance problem during flight control, the attitude autopilot based on fuzzy linear active disturbance rejection control (F-LADRC) was proposed. A second-order linear active disturbance rejection controller was designed to stabilize the attitude angle of the missiles, and the frequency domain characteristics were analyzed. Firstly, it was proved that the linear expansion state observer (LESO) is convergent and can achieve the indifference estimation of the system state variables and total disturbance. Then, it was proved that the linear active disturbance rejection control (LADRC) possesses disturbance rejection characteristics, and the influence of the bandwidth parameter on the disturbance rejection performance of the system was analyzed. The fuzzy control was used to adjust the parameter adaptively. Finally, the tracking, robustness, and anti-disturbance of the F-LADRC attitude autopilot were verified by performing simulations.

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Robust Flight Control Tuning for Highly Agile Missiles

Cited by 3 publications

References 31 publications

Linear Parameter Varying Pitch Autopilot Design for a Class of Long Range Guided Projectiles

Linear Parameter Varying Pitch Autopilot Design for a Class of Long Range Guided Projectiles

Simple Internal Model-Based Robust Control Design for a Non-Minimum Phase Unmanned Aerial Vehicle

Attitude Autopilot Design Based on Fuzzy Linear Active Disturbance Rejection Control

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