Cooperative Guidance Law for High-Speed and High-Maneuverability Air Targets

Download

index.pdf

Date

2023-2-01

Author

Cevher, Firat Yilmaz
Leblebicioğlu, Mehmet Kemal

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

175
views

130
downloads

In this paper, a novel cooperative and predictive guidance law is proposed to intercept high-speed and high-maneuverability targets with inferior interceptors. The purpose of guidance is cooperatively covering the most-probable locations where the target may be in the future. To fulfill this purpose, predicted target states in the form of a probability density function were obtained using limited target information, i.e., noisy position data for one case and maneuverability limits for the second case, at first. Next, the likelihood of the reachable set of interceptors was computed over the predicted target state. Then, to increase the probability of interception in a finite time, the interceptors' trajectories were adjusted collaboratively depending on the likelihood values. An extensive Monte Carlo study, with practically applicable simulation parameters, was used to demonstrate the effectiveness of the proposed methods against targets in challenging maneuvering modes.

Subject Keywords

cooperative guidance, multiple missiles, maneuvering target, inferior interceptor, probability of interception, IMPACT-TIME, MULTIPLE MISSILES, PREDICTIVE GUIDANCE, MANEUVERING TARGETS, STRATEGY, DESIGN, STATIONARY, ATTACK

URI

https://hdl.handle.net/11511/102748

Journal

AEROSPACE

DOI

https://doi.org/10.3390/aerospace10020155

Collections

Department of Electrical and Electronics Engineering, Article

Suggestions

OpenMETU
Core

Feedback motion planning of a novel fully actuated unmanned surface vehicle via sequential composition of random elliptical funnels Özdemir, Oğuz; Ankaralı, Mustafa Mert; Department of Electrical and Electronics Engineering (2022-12-27) This thesis proposes and analyzes a motion planning and control schema for unmanned surface vehicles that fuses sampling-based approaches’ probabilistic completeness with closed-loop approaches’ robustness. The Proposed schema is based on the sequential composition of elliptical funnels, and it consists of two stages: tree generation and motion control. For validation of the approach, we carried out experiments using both simulation and physical setup besides the mathematical analysis. In order to have a co...
Nonlinear Dynamic Inversion Autopilot Design for an Air Defense System with Aerodynamic and Thrust Vector Control Bıyıklı, Rabiya; Yavrucuk, İlkay; Tekin, Raziye; Department of Aerospace Engineering (2022-2) The study proposes complete attitude and acceleration autopilots in all three channels of a highly agile air defense missile by utilizing a subcategory of nonlinear feedback linearization methods Nonlinear Dynamic Inversion (NDI). The autopilot design includes cross-coupling effects enabling bank-to-turn (BTT) maneuvers and a rarely touched topic of control in the boost phase with hybrid control which consists of both aerodynamic fin control and thrust vector control. This piece of work suggests solut...
COOPERATIVE GUIDANCE METHOD WITH FORMATION CONTROL FOR A GUIDED MUNITION SWARM Ayhan, Furkan Zeki; Turgut, Ali Emre; Veysel, Gazi; Department of Mechanical Engineering (2023-1) A cooperative guidance method for a guided munition swarm that contains informed and naïve members is presented in this study. These guided munitions create a swarm with the help of communication between them. The communication of the members is established using RF Datalink, which can transfer a decided set of data between the transmitter and receiver. Since the seeker systems are one of the most expensive parts of a guided munition, using RF Datalink and cooperative guidance methods with formation control...
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...
Capturability of Combined Augmented Proportional Navigation against a Pull-Up Maneuvering Target Nugroho, Larasmoyo; Kutay, Ali Türker (2015-12-05) This article paper proposes a variation of the augmented proportional navigation law, called combined augmented proportional navigation which is studied to intercept a non-maneuvering target. This law is constructed from two predecessor laws, augmented proportional navigation (APN) known for its superiority performance against such target and coupled with combined proportional navigation (CPN) which has capability to compute head angle more than 90 degrees by solving the appearance of singularity in navigat...

Citation Formats

F. Y. Cevher and M. K. Leblebicioğlu, “Cooperative Guidance Law for High-Speed and High-Maneuverability Air Targets,” AEROSPACE, vol. 10, no. 2, pp. 0–0, 2023, Accessed: 00, 2023. [Online]. Available: https://hdl.handle.net/11511/102748.