Lyapunov based nonlinear impact angle guidance law for stationary targets

Download

index.pdf

Date

2015

Author

Ateş, Hakkı Ulaş

Metadata

Show full item record

Item Usage Stats

123
views

117
downloads

In modern guidance law designs, not only capturing but also considering a terminal impact angle while intercepting a target has become an increasingly important neccessity in modern guided systems. For several applications such as missiles systems, space explorations or aircraft docking, approaching the target with a specific impact angle is vital requirement for efficiency of the system. To achieve this requirement, a novel Lyapunov based nonlinear impact angle control guidance law for stationary targets is investigated in this work. In the proposed guidance law, nonlinear line-of-sight dynamics of the engagement geometry and kinematics between target and pursuer is studied and state equations for the line-of-sight angle and its rate are derived. The line-of-sight angle which converges the final flight path angle of the pursuer at the final rendezvous is aimed to be controlled to satisfy impact angle constraints. The nonlinear time-variant dynamics between target and pursuer is investigated.Then, to control robustly and stably, a first order sliding manifold to force the nonlinear dynamical system to exponential stability and reduce the order of the complex system is introduced. Moreover, Robust Control Lyapunov Function candidate is also investigated to control the dynamical system in order to head towards the desired sliding manifold. The neccesary acceleration commands to head towards the target with specified terminal impact angle is carried out by deriving control input of the nonlinear system to have asymptotical stability. Finally, the results of the proposed guidance law is expressed. Moreover, capturability analysis and capture conditions of the guidance law , robustness and disturbance rejection of the system is investigated. Furthermore, the response of the guidance law to some aspects which can be encountered in practical application is discussed.

Subject Keywords

Robust control., Automatic control., Sliding mode control., Guided missiles.

URI

http://etd.lib.metu.edu.tr/upload/12618468/index.pdf
https://hdl.handle.net/11511/24413

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

High angle attack maneuvering and stabilization control of aircraft Ateşoğlu, Özgür; Özgören, Mustafa Kemal; Department of Mechanical Engineering (2007) In this study, the implementation of modern control techniques, that can be used both for the stable recovery of the aircraft from the undesired high angle of attack flight state (stall) and the agile maneuvering of the aircraft in various air combat or defense missions, are performed. In order to accomplish this task, the thrust vectoring control (TVC) actuation is blended with the conventional aerodynamic controls. The controller design is based on the nonlinear dynamic inversion (NDI) control methodologi...
Design and control of nose actuation kit for position correction of spin stabilized munitions under wind effect Eroğlu, Mesut; Kutay, Ali Türker; Department of Aerospace Engineering (2016) Unguided munitions have been replaced with guided munitions over the century. There are two main reasons for this change; to increase damage to target with fewer munitions and reduce collateral damage due to deflection of munitions. Moreover, there are two options, building new guided munitions and modification of unguided munitions to convert dummy munitions to smart ones. Modifying unguided munitions to have guided munitions instead of building a completely new one is preferable due to economic reasons. T...
Robust flight and landing autopilot / Durmaz, Ozan; Leblebicioğlu, Mehmet Kemal; Department of Electrical and Electronics Engineering (2015) In this thesis, a mathematical model of a small unmanned aircraft is implemented where the static and dynamic stability derivative coefficients are found by Digital DATCOM software. Several control methods are applied such as PID control, LQT, SMC. Two types of Sliding mode controllers are designed using different sliding surfaces. Linearized aircraft models which are trimmed at two different airspeeds are used to design controllers. A guidance block is implemented to guide aircraft with waypoints. Differen...
Comparison of image matching algorithms on satellite images taken in different seasons Yıldırım, İrem; Demirtaş, Fatih; Gülmez, Baran; Leloğlu, Uğur Murat; Yaman, Mustafa; Güneyi, Eylem Tuğçe (null; 2019-04-27) Image matching, which aims to find the corresponding points in different images, is an important process which is used in various vision-based applications in military, industrial, remote sensing and security systems. Some applications require accurate matching across images taken at different times of the year to be reliable and reusable. Although many detection and description methods are used for image matching, it is important to correctly determine the most robust method for such changes. In this paper...
Missile guidance with impact angle constraint Çilek, Barkan; Kutay, Ali Türker; Department of Aerospace Engineering (2014) Missile flight control systems are the brains of missiles. One key element of a missile FCS is the guidance module. It basically generates the necessary command inputs to the autopilot.Guidance algorithm selection depends on the purpose of the corresponding missile type. In this thesis, missile guidance design problem with impact angle constraint is studied which is the main concern of anti-tank and anti-ship missiles. Different algorithms existing in the literature have been investigated using various anal...

Citation Formats

H. U. Ateş, “Lyapunov based nonlinear impact angle guidance law for stationary targets,” M.S. - Master of Science, Middle East Technical University, 2015.