ÇEŞİTLİ GÜDÜM PROBLEMLERİ İÇİN ORTAK BİR TASARIM METODU

Artan operasyonel gereksinimlerden ötürü, yörünge şekillendirmesine ilişkin çalışmalarda literatürde artış olmuştur. Füze güdümünün ilk ve temel amacı füzeyi hedefe sıfır kaçırma mesafesi ile ya da bunu en aza indirerek hedefe ulaştırmaktır. İkinci ve popüler bir gereksinim ise tanksavar füzeleri ve dik vuruş özelliğine sahip güdümlü mühimmatlar için vuruş açısının kontrolüdür. Yörünge izleme, ya da yol noktası takibi konuları da füze sistemlerinin ilgi alanında olduğu kadar otonom tüm araçlar ile insansız hava araçlarını da ilgilendiren konulardır. Bunlara ilaveten, mesafeli hedef takibi de bu tarz sistemlerde diğer bir araştırma konusudur. Bu makalede, üç problemin güdüm algoritmaları tasarımı açısından ortak bir stratejiye dayanarak çözülebileceği gösterilmektedir. Bunun için oransal seyrüsefer güdüme bir yanlılık terimi eklenerek takip açıklarının bir fonksiyonu olacak şekilde tasarım yapılırken, sabit hedef ile birlikte sanal hedef konsepti de uygulanmıştır. Önerilen güdüm kanunu varış zamanı ya da gidilecek mesafe kestirimine ihtiyaç duymaz. Tasarımın performansı, vuruş açısı, yörünge takibi ve mesafeli hedef takibi olarak üç ayrı benzetimde incelenmiştir.

Anahtar Kelimeler:

Füze Güdümü, Vuruş Açısı, yörünge izleme, sanal hedef takibi

A Common Design Framework for Various Guidance Problems

With rising interest and operation requirements, literature on the trajectory shaping guidance algorithms have increased. The primary objective of missile guidance is to have zero miss or near miss distance at the end of the flight. One of the popular secondary objectives is impact angle control, which might be preferred for anti-tank missiles or vertical impact guided munitions in order to increase the warhead effectiveness. Path following or way point tracking problems are also in the scope of missile systems as well as any autonomous vehicles or unmanned aerial vehicles. In addition to these, standoff target tracking is also another field of study for such systems. In this paper, a common framework for these three trajectory shaping problems is introduced. It is shown that they can base on a same strategy in terms of guidance algorithm design. For this purpose, a bias term to enhance proportional navigation guidance is designed. The design bases on an error signal which is a function of pursuit angles against a stationary target with the concept of virtual target. The performance of the proposed guidance law is demonstrated in simulations with no need of time-to-go or range-to-go estimation.

Keywords:

Missile Guidance, Impact Angle Control, path following, Standoff Target Tracking,

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