Bounded gain-scheduled LQR satellite control using a tilted wheel

Inumoh, Lawrence O.; Horri, Nadjim; Forshaw, Jason; Pechev, Alexandre

doi:10.1109/taes.2014.120778

Cited by 11 publications

(16 citation statements)

References 12 publications

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“…For years, various guidance laws have been utilized with different control concepts. Currently, most popular terminal guidance laws defined by Locke involve line-of-sight (LOS) guidance [6], [7], LOS rate guidance [8], [9], commandto-line-of-sight (CLOS) guidance [10], [11], and other advanced guidances such as proportional navigation guidance (PNG) [12]- [14], command to optimal interception point (COIP) guidance [15], augmented proportional navigation guidance (APNG) [16], optimal guidance law [17]- [19], linear quadratic Gaussian (LQG) theory [20], [21], sliding mode theory [22], H ∞ robust theory, impact angle control [23]- [25] and fuzzy logic control theory [26]- [28], etc. For the above conventional guidance strategy designs, it assumed the information of target and missile can be obtained perfectly by the seeker of missile for guidance control design, namely it neglect the effect of measurement noise in seeker.…”

Section: Introdutctionmentioning

confidence: 99%

Robust Stochastic Observer-Based Attack-Tolerant Missile Guidance Control Design Under Malicious Actuator and Sensor Attacks

2021

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In this study, the robust H ∞ stochastic observer-based attack-tolerant guidance control strategy is designed for the nonlinear stochastic missile guidance control system under the external disturbance and measurement noise as well as actuator attack signal and sensor attack signal. To simplify the attack signal estimation, a novel nonsingular smoothed dynamic model is introduced to efficiently describe the actuator and sensor attack signals. Consequently, the state/attack signal estimation can be easily achieved by using conventional Luenberger observer. Next, to attenuate the effect of external disturbance, measurement noise and approximation errors of attack signal on the missile guidance control system, the robust H ∞ attack-tolerant guidance control performance is considered and the design condition is derived in terms of nonlinear Hamilton-Jacobi inequality (HJI) constrained problem. Since HJI can not be easily solved analytically or numerically, the Takagi-Sugeno (T-S) fuzzy modelling method is utilized to facilitate the robust H ∞ attack-tolerant guidance control strategy design. Thereafter, the H ∞ observer-based attacktolerant control design problem is transformed into linear matrix inequalities problem (LMIP) which can be solved very efficiently by using the convex optimization techniques. Simulation example, with the comparison between the proposed method and conventional robust missile guidance strategy, is given to illustrate the design procedures and validate the performance of the proposed method.

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Section: Introdutctionmentioning

confidence: 99%

Robust Stochastic Observer-Based Attack-Tolerant Missile Guidance Control Design Under Malicious Actuator and Sensor Attacks

2021

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“…Amongst different actuators, the reaction wheels are acknowledged for their proven performance, relative simplicity, fast response and high pointing control accuracy. Regardless of the actuators type, various control approaches have been proposed for satellite attitude stability and tracking problem including optimal approach [10,11], adaptive control [12,13], robust control [14,15], Lyapunov-based methods [9,16,17], observer-based approaches [18,19], fuzzy control [20,21], and sliding mode control [22][23][24]. Among all mentioned methods, the sliding mode control (SMC) approach is acknowledged for its ability to cope with the uncertainties and disturbances in the nonlinear systems.…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Two‐Layer Terminal Sliding Mode Attitude Control of Satellites Equipped with Reaction Wheels

Bayat

Javaheri

2018

Asian Journal of Control

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This paper addresses the global stability and robust attitude tracking problem of a near polar orbit satellite subject to unknown disturbances and uncertainties. It is assumed that the satellite is fully actuated by a set of reaction wheels (RW) as control actuators because of their relative simplicity, versatility and high accuracy. The terminal sliding mode control (TSMC) approach is utilized in a two-level architecture to achieve control objectives. In the lower layer a detumbling-like controller is designed which guarantees the finite-time detumbling and tracking of the desired angular velocities and based on this result a robust attitude tracking controller is designed in the upper layer to achieve 3-axis attitude tracking in the presence of unknown disturbances and bounded uncertainties. Robust stability and tracking properties of designed controllers are proved using the Lyapunov theory. Finally, a set of numerical simulation results are provided to illustrate the effectiveness and performance of the proposed control method.

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“…On the other side, linear quadratic regulator (LQR) is one of the well-known and powerful methods in the design of optimal controllers which ensures a satisfactory robustness 9 and has shown good capabilities in a wide variety of applications. 10–14 Besides guaranteed Gain Margin (GM) and Phase Margin (PM), LQR also provides the designer the ability to manage the amount of error and control effort via state and control weighting matrices available in the cost function. 15 These two matrices in fact govern the feedback gain matrix and the designer can tune them to modify the system eigenstructure.…”

Section: Introductionmentioning

confidence: 99%

Pitch and flight path controller design for F-16 aircraft using combination of LQR and EA techniques

Mortazavi

Naghash

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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In a linear regulator problem with a quadratic cost function, there are two weighting matrices which determine the feedback gain matrix, and thereby the closed loop eigenvalues and eigenvectors of the system. To find the weighting matrices leading to a desired eigenstructure, trial and error is a common approach. In spite of its simplicity, trial and error is too time-consuming and does not guarantee achieving expected results. In this regard, this paper presents a step-by-step algorithm for calculation of state and control weighting matrices in such a way that the pre-specified eigenstructure is generated with acceptable accuracy. Accordingly, once the designer chooses preferred eigenvalues and eigenvectors, the feedback gain matrix will be available uniquely. In design procedure, tracking of flight path and pitch attitude commands for an F-16 aircraft will be provided. To achieve this aim completely, the feedforward gain matrix necessary for getting a zero steady state error is calculated based on the mathematical model of the aircraft as well as the pseudoinverse matrix concept. Various simulations demonstrate that the resulted controller has good performance, gives the desired eigenstructure satisfactorily and also shows the expected robustness of a linear quadratic regulator.

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Bounded gain-scheduled LQR satellite control using a tilted wheel

Cited by 11 publications

References 12 publications

Robust Stochastic Observer-Based Attack-Tolerant Missile Guidance Control Design Under Malicious Actuator and Sensor Attacks

Robust Stochastic Observer-Based Attack-Tolerant Missile Guidance Control Design Under Malicious Actuator and Sensor Attacks

Two‐Layer Terminal Sliding Mode Attitude Control of Satellites Equipped with Reaction Wheels

Pitch and flight path controller design for F-16 aircraft using combination of LQR and EA techniques

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