Bi-objective missile rescheduling for a naval task group with dynamic disruptions

Silav, Ahmet
Karasakal, Orhan
Karasakal, Esra
This paper considers the rescheduling of surface-to-air missiles (SAMs) for a naval task group (TG), where a set of SAMs have already been scheduled to intercept a set of anti-ship missiles (ASMs). In missile defense, the initial engagement schedule is developed according to the initial state of the defensive and attacking units. However, unforeseen events may arise during the engagement, creating a dynamic environment to be handled, and making the initial schedule infeasible or inefficient. In this study, the initial engagement schedule of a TG is assumed to be disrupted by the occurrence of a destroyed ASM, the breakdown of a SAM system, or an incoming new target ASM. To produce an updated schedule, a new biobjective mathematical model is formulated that maximizes the no-leaker probability value for the TG and minimizes the total deviation from the initial schedule. With the problem shown to be NP-hard, some special cases are presented that can be solved in polynomial time. We solve small size problems by the augmented epsilon-constraint method and propose heuristic procedures to generate a set of nondominated solutions for larger problems. The results are presented for different size problems and the total effectiveness of the model is evaluated.


Köse, Bala İlkim; Karasakal, Esra; Karasakal, Orhan; Department of Industrial Engineering (2022-5-10)
The purpose of this thesis is to analyze the air defense effectiveness of a naval task group (TG) under different coordination levels. Event Graphs methodology, and component-based discrete-event simulation modeling techniques are used. The simulation model is built using Simkit, an open-source java package, which enables the use of component-based modeling. TG is analyzed under different coordination policies consisting of no-coordination, partial coordination, and full coordination within TG, then these c...
Varying mass missile dynamics, guidance & control
Günbatar, Yakup; Leblebicioğlu, Mehmet Kemal; Department of Electrical and Electronics Engineering (2007)
The focus of this study is to be able to control the air-to-surface missile throughout the entire flight, with emphasis on the propulsion phase to increase the impact range of the missile. A major difficulty in controlling the missile during the propulsion phase is the important change in mass of the missile. This results in sliding the center of gravity (cg) point and changing inertias. Moreover, aerodynamic coefficients and stability derivatives are not assumed to be constant at predetermined ranges; conv...
End-to-end networks for detection and tracking of micro unmanned aerial vehicles
Aker, Cemal; Kalkan, Sinan; Department of Computer Engineering (2018)
As the number of micro unmanned aerial vehicles (mUAV) increases, several threats arise. Hence, there is a need for a system that can detect and track them. In this thesis, an object detection model based on convolutional neural networks for mUAV detection, and a novel end-to-end object tracking architecture are proposed. To solve the scarce data problem for training the detection network, an algorithm for creating an extensive artificial dataset by combining background-subtracted real images is proposed. I...
Composite impact vector control based on Apollo descent guidance
ERER, Koray S.; TEKIN, Raziye; Özgören, Mustafa Kemal (2022-01-01)
© 2021 Chinese Society of Aeronautics and AstronauticsA new three-dimensional missile guidance law to control the impact vector against a stationary target is proposed. The composite guidance law has two well-known components: Apollo descent guidance and trajectory shaping guidance. These respectively linear and planar guidance laws are combined to achieve a specified impact direction. The main idea is to define an impact plane and to steer the missile onto this plane using Apollo descent guidance while con...
Missile autopilot design by projective control theory
Doruk, Reşat Özgür; Kocaoğlan, Erol; Department of Electrical and Electronics Engineering (2003)
In this thesis, autopilots are developed for missiles with moderate dynamics and stationary targets. The aim is to use the designs in real applications. Since the real missile model is nonlinear, a linearization process is required to get use of systematic linear controller design techniques. In the scope of this thesis, the linear quadratic full state feedback approach is applied for developing missile autopilots. However, the limitations of measurement systems on the missiles restrict the availability of ...
Citation Formats
A. Silav, O. Karasakal, and E. Karasakal, “Bi-objective missile rescheduling for a naval task group with dynamic disruptions,” NAVAL RESEARCH LOGISTICS, pp. 596–615, 2019, Accessed: 00, 2020. [Online]. Available: