Design of Integrated Guidance and Control for a Missile using Sliding Mode Control Technique
| dc.contributor.advisor | Dereje Shiferaw (PhD) | |
| dc.contributor.author | Addisalem Hailegnaw | |
| dc.date.accessioned | 2024-09-03T08:21:35Z | |
| dc.date.available | 2024-09-03T08:21:35Z | |
| dc.date.issued | 2019-10 | |
| dc.description.abstract | Guided missiles with respect to their capability to engage high speed, highly agile targets and capability to achieve precision end-game trajectory requires extremely accurate performance of all component systems. In order to develop systems that meet the required accuracies, integrated guidance and control (IGC) systems are currently being studied. These IGC architectures infuse the guidance and con- trol systems into a single framework thereby promoting natural synergy among the missile subsystems. Compared with designing the guidance subsystem and control subsystem of missile separately, integrated guidance and control has many superior- ities, such as improving performance, reducing implementation cost and maximizing the adjustability of missile. Integrated guidance and control uses the target states relative to the missile to directly generate fin deflections that will result in target interception. In addition to achieving target interception, the integrated guidance and control has the responsibility for ensuring the internal stability of the missile dynamics. In this thesis Integrated guidance and control for a missile is developed using sliding mode control, taking a more natural guidance parameters which are predicted impact point heading errors as sliding surfaces. Mathematical model of a generic missile is derived by using the equations of motion, and missile/target engagement kinematics equations of the collision course are developed. Theoretical analysis shows the effectiveness of Integrated sliding mode guidance and control and simulations are carried out to show two dimensional and three dimensional missile target engagement scenarios using proportional navigation guidance law, and missile airframe is simulated to show the response to fin deflection so as to integrate the guidance law and control law later. | |
| dc.identifier.uri | https://etd.aau.edu.et/handle/123456789/3454 | |
| dc.language.iso | en_US | |
| dc.publisher | Addis Ababa University | |
| dc.subject | Guided Missile | |
| dc.subject | Mathematical Model of Missile | |
| dc.subject | Integrated Guidance and control | |
| dc.subject | Sliding Mode Control | |
| dc.subject | Sliding Surface | |
| dc.subject | Predicted impact point | |
| dc.subject | Heading error | |
| dc.subject | Proportional navigation | |
| dc.title | Design of Integrated Guidance and Control for a Missile using Sliding Mode Control Technique | |
| dc.type | Thesis |