Dual-control missile guidance: a simulation study

Bużantowicz, Witold; Pietrasieński, Paweł

doi:10.15632/jtam-pl.56.3.727

Cited by 8 publications

(5 citation statements)

References 14 publications

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“…When guiding a missile towards a target, it is desirable that ω ≈θ (2.1) namely, that the angular rate ω of the airframe be approximately equal to the angular rateθ of the missile velocity vector, and not depend on the dynamics of the missile itself (Bużantowicz and Pietrasieński, 2018;Grycewicz et al, 1984). Hence, a solution is sought which minimizes the value of the quantity index given in the form of the functional…”

Section: Formulation Of the Problemmentioning

confidence: 99%

A sliding mode controller design for a missile autopilot system

Bużantowicz

2020

Journal of Theoretical and Applied Mechanics

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A description is given of an application of the sliding mode control (SMC) for stabilizing the static and dynamic characteristics of an anti-aircraft missile. The solution provides effective separation of the control process from the dynamics of the missile airframe. In the equivalent part of the stabilization system, a linear-quadratic regulator (LQR) is considered, and an analytical method of selecting the weighting elements of the gain matrix is proposed. This eliminates the need for an iterative solution of the Riccati equation. A nonlinear switching component is introduced into the control signal to provide smoothness of the system response. In simulation tests, the proposed solution was evaluated against selected quantity indices. The paper ends with observations and conclusions.

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Section: Formulation Of the Problemmentioning

confidence: 99%

A sliding mode controller design for a missile autopilot system

Bużantowicz

2020

Journal of Theoretical and Applied Mechanics

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“…The accurate angle measurement of the detected object has a significant impact on the accuracy of its tracking [38][39][40][41][42]. In order to correctly determine the angular position of the detected object, it should be determined the law of airspace scanning by the optoelectronic system.…”

Section: Vector Filtration Of Control Signals By Means Of the Extended Kalman Filtermentioning

confidence: 99%

Control of Optoelectronic Scanning and Tracking Seeker by Means the LQR Modified Method with the Input Signal Estimated Using of the Extended Kalman Filter

Gapiński¹,

Koruba

2021

Energies

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The paper presents the concept of controlling the designed optoelectronic scanning and tracking seeker. The above device is intended for the so-called passive guidance of short-range anti-aircraft missiles to various types of air maneuvering targets. In the presented control method, the modified linear-quadratic regulator (LQR) and the estimation of input signals using the extended Kalman filter (EKF) were used. The LQR regulation utilizes linearization of the mathematical model of the above-mentioned seeker by means of the so-called Jacobians. What is more, in order to improve the stability of the seeker control, vector selection of signals received by the optoelectronic system was used, which also utilized EKF. The results of the research are presented in a graphical form. Numerical simulations were carried out on the basis of the author’s own program developed in the programming language C++.

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“…For simulation purposes, the aerial target is modeled as a mass point [6,41,45,[53][54][55] whose motion in space is described by the vector of parameters…”

Section: Conflicts Of Interest: I Declare No Conflict Of Interestmentioning

confidence: 99%

Tuning of a Linear-Quadratic Stabilization System for an Anti-Aircraft Missile

Bużantowicz

2021

Aerospace

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A description is given of an application of a linear-quadratic regulator (LQR) for stabilizing the characteristics of an anti-aircraft missile, and an analytical method of selecting the weighting elements of the gain matrix in feedback loop is proposed. A novel method of LQR tuning via a single parameter ς was proposed and tested. The article supplements and develops the topics addressed in the author’s previous work. Its added value includes the observation that the solutions obtained are symmetric pairs, and that the tuning parameter ς proposed for the designed linear-quadratic regulator enables the selection of suitable parameters for the airframe stabilizing loop for the majority of the analytical solutions of the considered Riccati equation.

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Dual-control missile guidance: a simulation study

Cited by 8 publications

References 14 publications

A sliding mode controller design for a missile autopilot system

A sliding mode controller design for a missile autopilot system

Control of Optoelectronic Scanning and Tracking Seeker by Means the LQR Modified Method with the Input Signal Estimated Using of the Extended Kalman Filter

Tuning of a Linear-Quadratic Stabilization System for an Anti-Aircraft Missile

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