Modern Missile Guidance

Yanushevsky, Rafael

doi:10.1201/9781351202954

Cited by 31 publications

(19 citation statements)

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“…Augmented Proportional Navigation(APN) Guidance Scenario. Augmented proportional navigation based on the assuming of target's maneuvering acceleration is constant, and an additional square term 0.5a T t go 2 to the zero-effort miss(ZEM) is converted into a basic variables the proportional guidance law [21] . In augmented proportional navigation(APN) guidance, the acceleration is:…”

Section: Simulation and Discussionmentioning

confidence: 99%

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Research on the Omnidirectional Interception Guidance Law for High Speed Maneuvering Targets

Bai¹,

Hu²,

Duan³

et al. 2016

Proceedings of the 2016 7th International Conference on Mechatronics, Control and Materials (ICMCM 2016)

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Aiming to intercept high-speed maneuvering targets, nonlinear model was established and relative dynamic equations between the interceptor and the target were analyzed. An omni-directional true proportional navigation (OTPN) guidance law was developed. In high-speed target interception, OTPN guidance law has a wide capture region and can automatically shift interception mode. Formulary analysis proved that target maneuver has no effect on the expression form of OTPN guidance law. Without any additional conditions, OTPN guidance law can meet the requirement to intercepting high-speed maneuvering targets. Numerical simulation results showed that OTPN guidance law can effectively intercept high-speed maneuvering targets and its capture region is influenced by targets' maneuver ability and initial LOS angle. The parameters of OTPN, such as capture region, ballistic characteristics, and overload variation and control efforts, show that OTPN are superior to traditional guidance schemes.

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Section: Simulation and Discussionmentioning

confidence: 99%

“…The interceptor's acceleration perpendicular to the LOS, in Equation 20 (21) Substitute Equation (21)into Equation 18:…”

Section: Figure 2 Relative Motion Between Interceptor and Targetmentioning

confidence: 99%

Research on the Omnidirectional Interception Guidance Law for High Speed Maneuvering Targets

Bai¹,

Hu²,

Duan³

et al. 2016

Proceedings of the 2016 7th International Conference on Mechatronics, Control and Materials (ICMCM 2016)

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show abstract

“…The system under consideration is a homing system based on a proportional navigation method in which control signals are dependent on parameters of the line of sight (Siouris, 2004;Yanushevsky, 2007; Zarchan, 2012)…”

Section: Homing Loop Modelmentioning

confidence: 99%

“…This situation is particularly disadvantageous during the terminal guidance phase, as it requires a very rapid reaction on the part of the missile, involving significant rotations of its airframe. This disturbs working conditions of the seeker, increasing dynamic errors of the coordinate determination system (Grycewicz et al, 1984;Siouris, 2004;Yanushevsky, 2007;Gapiński and Krzysztofik, 2014). These errors are incorporated into the missile control commands, leading to increased miss distances and, thus, to reduced effectiveness of fire against the target.…”

Section: Introductionmentioning

confidence: 99%

Dual-control missile guidance: a simulation study

Bużantowicz

Pietrasieński

2018

jtam

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Theoretical considerations and a simulation study concerning description and analysis of new autopilot structures and issues relating to conversion of guidance commands into deflections of a complex system of control surfaces aimed at minimizing the miss distance value are presented in this paper. Due to nonlinear and nonstationary nature of the phenomena associated with the guidance process, a significant role is assigned to simulation studies. A comparative analysis has been made of the guidance processes of three models of a dual-control missile, which differ in terms of formulae implemented in the control command converters.

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“…Uwzględniono zmienność charakterystyk masowo-bezwładnościowych rakiety powstałą wskutek spalania paliwa i przemieszczania się It was assumed that the object is a body of unrestricted movement in the space. The changes of mass-inertial characteristics caused by propellant burning process and shifting the centre of środka ciężkości [1], [8]. Wzięto również pod uwagę zaburzenia powstałe przy uruchamianiu silnika rakietowego jak również niektóre zjawiska aerodynamiki nieustalonej.…”

Section: Fig 3 Simlified Model Of a Missile Used In Numerical Simulunclassified

Missile Vertical Launch System With Reaction Control Jets

Głębocki

Jacewicz

2018

PTU

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The paper deals with a concept of a missile vertical launch system using reaction control jets. The purpose of the study was a detailed investigation of a method optimizing fuel consumption in the first phase of the missile flight to increase the range and optimize the flight path. In the designed system the missile is ejected vertically and turned to the desired position by using corrective engines before the sustainer motor is started. The dynamics and controllability of the missile at low velocities were studied. The physical and mathematical model of the object has been described, taking into account the nonlinearities connected with the dynamics of the rocket itself, the disturbances caused by firing the rocket engine as well as some effects the unsteady aerodynamics. A method identifying the aerodynamic characteristics of the missile and an algorithm controlling the correction engines is presented. A prepared mathematical model of the missile was used to create a simulating environment. The results of numerical simulations in the form of graphs and tables are presented.

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Modern Missile Guidance

Cited by 31 publications

References 0 publications

Research on the Omnidirectional Interception Guidance Law for High Speed Maneuvering Targets

Research on the Omnidirectional Interception Guidance Law for High Speed Maneuvering Targets

Dual-control missile guidance: a simulation study

Missile Vertical Launch System With Reaction Control Jets

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