Robust Missile Autopilot Design Using Two Time-Scale Separation

Panchal, Bhavnesh; Subramanian, K.; Talole, S. E.

doi:10.1109/taes.2018.2796654

Cited by 23 publications

(8 citation statements)

References 39 publications

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“…, δ e is deflection angle. According to equation (11), the augmented Bellman equation for acceleration tracking control can also be written as follows…”

Section: Derivation Of Data-driven Acceleration Tracking Control For ...mentioning

confidence: 99%

“…Over the past few decades, there has been a lot of research on model-based flight control. Such as, gain scheduling control, 3,4 optimal and inverse optimal control, 1,[5][6][7] adaptive control techniques, 2,8 robust control [9][10][11] and sliding mode control, [12][13][14][15][16] and so on. However, these controller designs is based on the benchmark dynamic model of UAVs, new uncertainties induced by aerodynamic damage will seriously affect flight control performance.…”

Section: Introductionmentioning

confidence: 99%

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Data-driven fault-tolerant control for unmanned aerial vehicles without using identification model

Zheng

Lin

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Unmanned aerial vehicle (UAV)’s fault-control problem was studied in this paper, and data-driven fault-tolerant control scheme was developed for acceleration tracking control of UAV in order to cope with the uncertainties induced by aerodynamic damage. A linear UAV dynamic model was given with reasonable assumptions, and the acceleration tracking control for UAV was converted to solving an infinite-horizon optimal control problem. The augmented algebraic Riccati equation (ARE) is derived, and its solution stability is proved based on Lyapunov theory. The data-driven control algorithm is further derived for online solving of the augmented ARE with only using flight data. The proposed algorithm is based on experience replay of flight data rather than model knowledge, so it greatly reduces the effect of uncertainties induced by aerodynamic damage on the flight control system for UAVs. Finally, the effectiveness of developed algorithm is verified through the numerical simulations under different uncertainties induced by aerodynamic damage.

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“…, δ e is deflection angle. According to equation (11), the augmented Bellman equation for acceleration tracking control can also be written as follows…”

Section: Derivation Of Data-driven Acceleration Tracking Control For ...mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Data-driven fault-tolerant control for unmanned aerial vehicles without using identification model

Zheng

Lin

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…To verify and demonstrate the advanced designed servo algorithm, a Monte Carlo simulation was carried out [ 34 , 35 ]. Through the Monte Carlo simulation, the effect of the improved servo algorithm is clearly shown through target-miss distance.…”

Section: Simulation and Analysismentioning

confidence: 99%

Backstepping Sliding Mode Control for Radar Seeker Servo System Considering Guidance and Control System

Wang

Lei

et al. 2018

Sensors

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This paper investigates the design of a missile seeker servo system combined with a guidance and control system. Firstly, a complete model containing a missile seeker servo system, missile guidance system, and missile control system (SGCS) was creatively proposed. Secondly, a designed high-order tracking differentiator (HTD) was used to estimate states of systems in real time, which guarantees the feasibility of the designed algorithm. To guarantee tracking precision and robustness, backstepping sliding-mode control was adopted. Aiming at the main problem of projectile motion disturbance, an adaptive radial basis function neural network (RBFNN) was proposed to compensate for disturbance. Adaptive RBFNN especially achieves online adjustment of residual error, which promotes estimation precision and eliminates the “chattering phenomenon”. The boundedness of all signals, including estimation error of high-order tracking differentiator, was especially proved via the Lyapunov stability theory, which is more rigorous. Finally, in considered scenarios, line of sight angle (LOSA)-tracking simulations were carried out to verify the tracking performance, and a Monte Carlo miss-distance simulation is presented to validate the effectiveness of the proposed method.

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“…Thus, any uncertainty not considered in the model can cause loss of performance or even instability in more extreme cases [10]. In addition, the necessary precise predictions of the aerodynamic coefficients over a wide range of flight conditions demand costly and timely wind-tunnel assays [11].…”

Section: Introductionmentioning

confidence: 99%

Robust missile autopilot design based on dynamic surface control

Zhou

Wei

Xia

et al. 2023

J. of Syst. Eng. Electron.

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Since the dynamical system and control system of the missile are typically nonlinear, an effective acceleration tracking autopilot is designed using the dynamic surface control (DSC) technique in order to make the missile control system more robust despite the uncertainty of the dynamical parameters and the presence of disturbances. Firstly, the nonlinear mathematical model of the tail-controlled missile is decomposed into slow acceleration dynamics and fast pitch rate dynamics based on the naturally existing time scale separation. Secondly, the controller based on DSC is designed after obtaining the linear dynamics characteristics of the slow and fast subsystems. An extended state observer is used to detect the uncertainty of the system state variables and aerodynamic parameters to achieve the compensation of the control law. The closed-loop stability of the controller is derived and rigorously analyzed. Finally, the effectiveness and robustness of the design is verified by Monte Carlo simulation considering different initial conditions and parameter uptake. Simulation results illustrate that the missile autopilot based DSC controller achieves better performance and robustness than the other two well-known autopilots. The method proposed in this paper is applied to the design of a missile autopilot, and the results show that the acceleration tracking autopilot based on the DSC controller can ensure accurate tracking of the required commands and has better performance.

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Robust Missile Autopilot Design Using Two Time-Scale Separation

Cited by 23 publications

References 39 publications

Data-driven fault-tolerant control for unmanned aerial vehicles without using identification model

Data-driven fault-tolerant control for unmanned aerial vehicles without using identification model

Backstepping Sliding Mode Control for Radar Seeker Servo System Considering Guidance and Control System

Robust missile autopilot design based on dynamic surface control

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