Modelling and Simulation of an Anti-Tank Guided Missile

Soliman, Mohamed Abdallah; Ouda, Ahmed Nasr

doi:10.17577/ijertv7is090051

Cited by 3 publications

(10 citation statements)

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“…The ideal system model satisfies the requirements to the closed-loop dynamics is chosen as M = and W u (s) = 0.4s+0. 9 5.9s+5 . The performance weighting functions are chosen so as to ensure an acceptable tradeoff between the nominal performance and robust performance of the closed-loop system with control action which satisfies the constraint imposed.…”

Section: Pitch Plane Performance Requirementsmentioning

confidence: 99%

“…An alternative approach to the loop shaping is the H ∞ mixed-sensitivity loop shaping, where the performance and stability specifications, Eqs. (8,9) are combined into a single infinity norm specification of the form…”

Section: Controller Performance Evaluationmentioning

confidence: 99%

“…35, which reveals that there exist some singular values > 1 and that the H ∞ norm of the closed loop system is • Redesign the robust controller using the following performance weighting functions W p (s) = 0.1s+5 27.2522s+0.015 and W u (s) = 0.4s+0. 9 5.9s+5 at the same operating point which results in a controller of 10th order. The frequency response of the structured singular value for the case of robust stability analysis is considered, where µmax = 0.47705, from the frequency response of the nominal performance it is seen that the obtained peak value of γ is 1.001 and less than 1 in the high frequency range which shows that the nominal performance has achieved.…”

Section: Pitch Plane Performance Requirementsmentioning

confidence: 99%

“…The system uncertainties included thrust variation due to different causes, variation in aerodynamic coefficients and parameters, wind velocity in different directions and different trim conditions. To overcome different sources of uncertainty, robust control is used to design the autopilot such that the system is stable with the ability to overcome un-modelled dynamics, to reject the disturbances and minimize the effects of measurement noises overall the missile flight envelope as discussed by (Ouda, hassan, Islam and Abdallah) [6][7][8][9]. The performance specifications include overshoot, speed of response, steady state error, and system stability in addition to flight paths with different engagement scenarios.…”

Section: Introductionmentioning

confidence: 99%

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Scalar H∞ autopilot synthesis for control systems and evaluation via HIL simulation

Ouda

2019

SN Appl. Sci.

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The improvement in calculation capabilities conciliate the design and performing of advanced robust control. Among the critical applications are the anti-tank missiles systems. The present work is concerned with enhancing the performance of an antitank guided missile system via robust synthesis of autopilot and guidance systems. This paper is concerned to the derivation of the missile airframe transfer functions. The obtained transfer functions are expanded with formulation for the system uncertainty to be considered during the robust design. The next objective for this paper is to design an autopilot using robust technique with complete justification against related work putting into consideration the overall requirements of flight tactics characteristics. The proposed design is implemented within the simulation model. The obtained results explain the capability of the designed controller to maintain the stability of the system in the presence of un-modeled dynamics. These autopilots proved its robustness to thrust uncertainties within 30% degradation, and about ± 30% of nominal aerodynamic coefficients. It is limited to wind speed of about 20 m/s in both directions. It proved its capability of less sensitivity to measurement noise and reject disturbance of 50% within 0.09 s and 95% within 0.22 s. Then, the actuator hardware is implemented within the simulation via interfacing cards using the designed robust autopilot in presence of the prescribed uncertainty. The results show the accuracy via using the hardware-in-the loop simulation. The obtained results revealing that the developed autopilot has the capability to stabilize the system in presence of noise and disturbance. Keywords Command guidance systems • CLOS • Robust control • H ∞ • Uncertainties List of symbols Symbols X 1 , Y 1 , and Z 1 Vectors components along the board reference axes X g , Yg, and Z g Vectors components along the ground reference axes X, Y, and Z Vectors components along the velocity reference axes δ jp and δ jy Thrust jetivator angles in pitch and yaw planes F TX 1 , F TY1 and F TZ 1 Thrust forces along the board reference axes F AX , F AY and F AZ Drag, lateral, and lift forces along the velocity axes S Characteristic area q Dynamic pressure given by q = 0.5ρ (Vm) 2 (kg/m/s 2) ρ Air density (kg/m 3) V M Missile velocity C x , C y , and C z Dimension-less aerodynamic coefficients g Vector of gravity acceleration M Mach number and given by M = V m /V a V a Sound velocity at missile position

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Section: Pitch Plane Performance Requirementsmentioning

confidence: 99%

Section: Controller Performance Evaluationmentioning

confidence: 99%

Section: Pitch Plane Performance Requirementsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Scalar H∞ autopilot synthesis for control systems and evaluation via HIL simulation

Ouda

2019

SN Appl. Sci.

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“…The intended missile system uses the command line of sight (CLOS) guidance method to hit its target even this target is moving or stationary [10]. The operator has to keep the sight reticle on the target center and as a result, missile spatial position is measured and sensed via the sight or night detectors located in the ground station, the miss angle between the actual missile position and the virtual line of sight is calculated in missile guidance unit (MGU) and consequently it generates the steering commands sent to the missile via the command wire [1].…”

Section: Introductionmentioning

confidence: 99%

Linearization of Anti-Tank Guided Missile

Mohamed¹,

Ouda²,

Abdelaty³

et al. 2019

ACIS

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Anti-tank surface to surface guided missile systems are considered to be one of the most powerful weapons in the modern war. Due to their effectiveness against either fortifications or tanks in addition to their relative low weight, they are deployed in the field easily. One of the most challenges the engineers face while designing a guided missile is the autopilot design. The autopilot loop or the inner loop of the missile should steer the missile during its spatial flight till hitting the target even it is moving or stationary. A higher maneuver target was hit by the missile, the more reliable autopilot you design. On designing a mature autopilot, a promising mathematical model of the missile should be in hand and mathematical linearized model should be derived. This paper presents a mathematical representation of an anti-tank guided missile the mathematical linearized model as well so that the design of the missile autopilot is presented in the future work.

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Synthesis of Suboptimal Guidance Law for Anti-Tank Guided Missile with Terminal Impact Angle Constraint Based on the SDRE Technique

Tran

Nguyen

et al. 2023

AAES

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In this paper, the homing-phase guidance law is proposed against a stationary target in the planar engagement scenario. In this problem, two technical criteria that the guidance law must achieve are: first, zero terminal miss distance, and second, satisfying the desired impact angle constraint at the final time. This guidance law is synthesized as a nonlinear optimal control problem with an infinite-time horizon and is solved using the state-dependent Riccati equation (SDRE) method. To obtain a guidance law with a finite-time horizon, a state weighting matrix based on the time-to-go is utilized in the SDRE control scheme. The synthesized guidance law is applied to a new generation anti-tank guided missile class, with specific thrust and drag parameters. Nonlinear simulations are conducted to demonstrate the fundamental properties, applicability, and effectiveness of the proposed guidance law.

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Modelling and Simulation of an Anti-Tank Guided Missile

Cited by 3 publications

References 1 publication

Scalar H∞ autopilot synthesis for control systems and evaluation via HIL simulation

Scalar H∞ autopilot synthesis for control systems and evaluation via HIL simulation

Linearization of Anti-Tank Guided Missile

Synthesis of Suboptimal Guidance Law for Anti-Tank Guided Missile with Terminal Impact Angle Constraint Based on the SDRE Technique

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