Analytical study of a modified LOS guidance

Jalali-Naini, Seyed Hamid

doi:10.2514/6.2001-4045

Cited by 4 publications

(5 citation statements)

References 7 publications

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“…Assume that the trajectories lie on the switching surface s(x,t) = 0, then the derivative ) t , x ( s  must be zero in order that the trajectories remain there and eventually tracking errors would be driven to zero. Thus, the general control structure that satisfies the stability condition of sliding motion, (12), can be given as…”

Section: Sliding Mode Controlmentioning

confidence: 99%

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Guidance Law Design Using Intelligent Non-Linear Controller

Elhalwagy

2009

International Conference on Aerospace Sciences and Aviation Tec

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A sliding mode control algorithm combined with a fuzzy control scheme is developed for the trajectory control of a command guidance system. The acceleration command input is obtained. The proposed controller is used to compensate for the influence of unmodeled dynamics and to alleviate chattering. Simulation results show that the proposed controller gives good system performance in the face of system parameters variation and external disturbances. Moreover, the simulation results show the effectiveness of the proposed missile guidance law against different engagement scenarios.

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Section: Sliding Mode Controlmentioning

confidence: 99%

“…With the phenomenal growth of highly manoeuvrable targets, research on improved guidance laws is continuing [1][2][3][4][5][6]. In recent years, many authors have addressed the importance of the command-to-line-of-sight (CLOS) guidance law due to the recent advances in beam-pointing technology [7][8][9][10][11][12].…”

Section: Introductionmentioning

confidence: 99%

Guidance Law Design Using Intelligent Non-Linear Controller

Elhalwagy

2009

International Conference on Aerospace Sciences and Aviation Tec

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“…Since Λ Λ is stable, such P always exists. Using Equations (17) and (19) and considering ⏐ e ⏐ ≥ δ, we will have:…”

Section: Thereforementioning

confidence: 99%

“…Moreover, as the range of target increases, it will be a challenge to compromise between miss distance and control effort. To reduce the acceleration demands for high speed targets, there is a well-known modification on CLOS guidance, called the lead angle method (4,5,19,20) . In this method, missile is guided toward a virtual target located with a lead angle with respect to the real target.…”

Section: Introductionmentioning

confidence: 99%

An optimal-fuzzy two-phase CLOS guidance law design using ant colony optimisation

Nobahari

Pourtakdoust

2007

Aeronaut. j.

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The well-known ant colony optimisation (ACO) meta-heuristic is applied to optimise the parameters of a new fuzzy command to line-of-sight (CLOS) guidance law. The new guidance scheme includes two phases, a midcourse and a terminal phase. In the first phase, a lead strategy is utilised which reduces the acceleration demands. A proportional derivative (PD) fuzzy sliding mode controller is used as the main tracking controller of the first phase. Moreover, a supervisory controller is coupled with the main tracking controller to guarantee the missile flight within the beam. In the terminal phase, a pure CLOS guidance law without lead angle is utilised. For this phase, a new hybrid fuzzy proportional-integral-derivative (PID) fuzzy sliding mode controller is proposed as a high precision tracking controller. The parameters of the proposed controllers for the first and the second phases are optimised using ACO. In this regard, the recently developed continuous ant colony system (CACS) algorithm is extended to multi-objective optimisation problems and utilised to optimise the parameters of the pre-constructed fuzzy controllers. The performance of the resulting guidance law is evaluated at different engagement scenarios and compared with the well-known feedback linearisation method. The comparison is also made in the presence of measurement noise.

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“…To reduce the acceleration commands, there is a wellknown modification to CLOS guidance, called the Lead Angle method (Blackelock, 1991;Shneydor, 1998;Jalali-Naini, 2001;Jalali-Naini, 2004). In this method, missile is guided toward a virtual target, located with a lead angle with respect to the real target.…”

Section: Introductionmentioning

confidence: 99%

Design of a supervisory controller for CLOS guidance with lead angle

Nobahari

Alasty

Pourtakdoust

2006

Aircraft Engineering and Aerospace Technology

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Purpose -The purpose of this paper is to propose a supervisory command-to-line-of-sight guidance law with lead angle which keeps the missile flight within the tracking beam. Design/methodology/approach -A nonlinear supervisory controller is designed and coupled with the main sliding mode controller in the form of an additional control signal. The supervisory control signal is activated when the beam angle constraint goes to be violated. Initially a supervisory controller is designed using nonlinear control theory. Subsequently the main tracking controller is designed using sliding mode approach which forces the missile to fly along the desired line-of-sight. The stability of the supervisory controller coupled with the main controller is proved in the Lyapunov sense.Findings -There exists a major drawback with the lead angle method of guidance, which is a high probability of flying out of the beam. The proposed supervisory controller has successfully overcome this deficiency. Thus, a better performance has been achieved. Practical implications -The proposed guidance scheme can be applied to tactical surface to air missiles. Additionally the idea of supervisory controller can be applied to any similar control problem where there are some constrains over the states of the system. Originality/value -The idea of supervisory controller has not been applied to the problem of command-to-line-of-sight guidance law. This paper utilizes and extends the idea of supervisory controller design to cases when a special state is to be supervised while considering the effect of external disturbances.

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Analytical study of a modified LOS guidance

Cited by 4 publications

References 7 publications

Guidance Law Design Using Intelligent Non-Linear Controller

Guidance Law Design Using Intelligent Non-Linear Controller

An optimal-fuzzy two-phase CLOS guidance law design using ant colony optimisation

Design of a supervisory controller for CLOS guidance with lead angle

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