Placing all closed loop poles of missile attitude control systems in the sliding mode via the root locus technique

Huang, Ying; Way, H.K.

doi:10.1016/s0019-0578(01)00003-9

Cited by 13 publications

(6 citation statements)

References 9 publications

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“…The problem of interest in the present case is to generate a second-order sliding mode on a chosen sliding surface s(t). In the literature, some different sliding functions were used in the derivation of sliding mode controllers such as integral operation sliding surface [30,40], SMC + I [10], integral sliding surface [41][42][43][44], PID surface with two independent gain parameters [45]. The PID sliding surface with constant coefficients can be introduced as: (19) where k p , k i and k d are the independent positive constants denoting proportional, integral and derivative gains, respectively, k p , k i , k d ∈ + , β is also a positive constant, β ∈ + , that contributes in the damping of s(t), determining the rate of decay for s(t) (after the sliding mode is enforced).…”

Section: Second-order Sliding Mode Controlmentioning

confidence: 99%

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Second-order sliding mode control with experimental application

Eker

2010

ISA Transactions

188

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Section: Second-order Sliding Mode Controlmentioning

confidence: 99%

“…The parameters in Eq. (41) are calculated from the measured plant output to be K = 0.822, T d = 0.009 s, and T = 0.1418 s. Using the approximate plant model, the nominal parameters are calculated as A n = 118.1663, B n = 783.5762 and C n = 644.0997, where A n = (…”

Section: Experimental Set-up and Preliminariesmentioning

confidence: 99%

Second-order sliding mode control with experimental application

Eker

2010

ISA Transactions

188

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“…The linearized model of canard-configured missile [6] is described by the following state-space model in (1).…”

Section: A Missile Model In Canard Configurationmentioning

confidence: 99%

“…having an open loop zero in the right-half s-plane. The system under study, being both controllable and observable [6], the task is now to design an efficient control scheme to track a step-input angle of attack command with stochastic observer based state-feedback control by varying the control inputs that directly affects the canard's deflection. Control of canard missile has been previously studied using sliding mode [6] and LQG [7] controller.…”

Section: Introductionmentioning

confidence: 99%

Missile attitude control via a hybrid LQG-LTR-LQI control scheme with optimum weight selection

Das

Halder

2014

2014 First International Conference on Automation, Control, Energy and Systems (ACES)

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Abstract-This paper proposes a new strategy for missile attitude control using a hybridization of Linear Quadratic Gaussian (LQG), Loop Transfer Recovery (LTR), and Linear Quadratic Integral (LQI) control techniques. The LQG control design is carried out in two steps i.e. firstly applying Kalman filter for state estimation in noisy environment and then using the estimated states for an optimal state feedback control via Linear Quadratic Regulator (LQR). As further steps of performance improvement of the missile attitude control system, the LTR and LQI schemes are applied to increase the stability margins and guarantee set-point tracking performance respectively, while also preserving the optimality of the LQG. The weighting matrix (Q) and weighting factor (R) of LQG and the LTR fictitious noise coefficient (q) are tuned using Nelder-Mead Simplex optimization technique to make the closed-loop system act faster. Simulations are given to illustrate the validity of the proposed technique.

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“…The performed literature survey indicates that designs of autopilots primarily involve application of established control theories such as classical (Devaud et al, 2000), robust (Buschek, 2003;Biannica and Apkariana, 1999;McLain and Beard, 1999;Bennani et al, 1998;Rodriguez and Cloutier, 1994;Lin and Lee, 1984), adaptive (Kim et al, 2004;Han and Balakrishnan, 2002;Lin and Wang, 1998), gain-scheduling Leith et al, 2001;Shamma and Cloutier, 1993), sliding mode (Huang and Way, 2001;Shkolnikov et al, 2000), quantitative feedback theory (Benshabat and Chait, 1993), predictive control (Chen et al, 2003;Lu, 1994), genetic approach (Lin and Lai, 2001;Crawford et al, 1999) or a combination of a set of these techniques (Donha et al, 1998;Schumacher and Khargonekar, 1998;Reichert, 1992). Of course, as performance requirements for aerospace vehicles increase, more complicated control algorithms may be required.…”

Section: Introductionmentioning

confidence: 99%

Simple autopilot design procedure based on a factorization approach

Nassirharand

Alizadeh²

2006

Aircraft Engineering and Aerospace Technology

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Purpose -The purpose of this paper is to apply a factorization-based control system design procedure to design of auto-pilot systems. Design/methodology/approach -The design approach is based on a previously developed factorization-based control system design procedure. The design approach requires a stable coprime factorization of the plant, a set of stable coprime factors that are solutions to the Bezout identity, the linear model of a desired response, and the desired frequency range of interest. When all this information is provided, the developed automated software outputs a candidate auto-pilot whose performance should be verified. Findings -For a specific class of aerospace vehicles, it is found that the described factorization-based auto-pilot design procedure may replace the presently complicated auto-pilot design procedures. The final design is simpler than other techniques that are based on classical, robust, adaptive, QFT, gain scheduling, or interpolation techniques, and the total required man hours for the design loop is less than the mentioned alternative approaches. Research limitations/implications -There are two basic limitations -time variations of plant parameters must not be very large as is the case with the agile aerospace vehicles, and specification of the desired closed-loop system behavior is not systematic. Practical implications -The major outcome of this research is that complicated autopilots of a class of aerospace vehicles may be replaced by simpler systems with competitive performance. Originality/value -This is the first paper in the area of autopilot design that is based on the application of a simple factorization-based design procedure.

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Placing all closed loop poles of missile attitude control systems in the sliding mode via the root locus technique

Cited by 13 publications

References 9 publications

Second-order sliding mode control with experimental application

Second-order sliding mode control with experimental application

Missile attitude control via a hybrid LQG-LTR-LQI control scheme with optimum weight selection

Simple autopilot design procedure based on a factorization approach

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