Development of a State Dependent Riccati Equation Based Tracking Flight Controller for an Unmanned Aircraft

Date

2013-08-22

Author

Tekinalp, Ozan

Metadata

Show full item record

Item Usage Stats

190
views

0
downloads

A dual loop nonlinear State Dependent Riccati Equation (SDRE) control method is developed for the flight control of an unmanned aircraft. The outer loop addresses the attitude and altitude kinematics, while the inner loop handles the translational and rotational equations of motion. The control strategy utilizes a tracking control problem. The mismatch due to the SDC factorization of the inner loop is handled with a nonlinear compensator again derived from the tracking control formulation. The quadratic optimal control problems of the inner and outer loops are solved at discrete intervals in time. A nonlinear simulation model of the UAV is used to examine the performance of the SDRE controller. Two flight scenarios are considered: a coordinated turn maneuver and a high angle of attack flight. These simulation results show the effectiveness of the proposed nonlinear controller.

Subject Keywords

Aircraft, Angle of attack indicators, Computer simulation, Controllers, Equations of motion, Optimal control systems

URI

https://hdl.handle.net/11511/71897
https://www.scopus.com/record/display.uri?eid=2-s2.0-84883703230&origin=resultslist&sort=plf-f&src=s&st1=&st2=&sid=db9dc621e4dbb2370f3f42c935ab8e3e&sot=b&sdt=b&sl=123&s=TITLE-ABS-KEY+%28Development+of+a+State+Dependent+Riccati+Equation+Based+Tracking+Flight+Controller+for+an+Unmanned+Aircraft%29&relpos=0&citeCnt=13&searchTerm=

Conference Name

AIAA Guidance, Navigation, and Control (GNC) Conference (19-22 August 2013)

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Development of state dependent factorized optimal control methods with application to spacecraft coulomb formations Gomroki, Mohammad Mehdi; Tekinalp, Ozan; Topputo, Francesco; Department of Aerospace Engineering (2017) Among spacecraft formation control techniques, Coulomb tether to control the relative distance is proposed in the literature. A Coulomb tether is similar to physical tether that uses coulomb forces to keep spacecraft at close proximity. It is indicated that a coulomb tether provides an almost a propellantless formation control. The charges loaded to the bodies, can create attractive and repulsive forces between these bodies. Since the forces are relative, coulomb forces cannot change the total linear or ang...
Development of a multigrid accelerated euler solver on adaptively refined two- and three-dimensional cartesian grids Çakmak, Mehtap; Aksel, Mehmet Haluk; Department of Mechanical Engineering (2009) Cartesian grids offer a valuable option to simulate aerodynamic flows around complex geometries such as multi-element airfoils, aircrafts, and rockets. Therefore, an adaptively-refined Cartesian grid generator and Euler solver are developed. For the mesh generation part of the algorithm, dynamic data structures are used to determine connectivity information between cells and uniform mesh is created in the domain. Marching squares and cubes algorithms are used to form interfaces of cut and split cells. Geome...
Development of a tool for prediction of the orbital parameters of earth observation satellites Altay, Alkan; Karsli, Gizem; Oezkan, Ahmet (2007-06-16) Development of a tool that predicts the orbital parameters of a satellite from an initial state vector for a specified time interval is addressed. The elements used in the algorithm are presented. The prediction performance of the algorithm is demonstrated by using the two line elements of a GPS satellite and the CHAMP scientific satellite.
Development of a rotorcraft time domain system identification software Aslandoğan, Ongun Hazar; Yavrucuk, İlkay; Gürsoy, Gönenç; Department of Aerospace Engineering (2023-1-03) A system identification software to identify stability and control derivatives for rotorcraft in hover and forward flight conditions is developed in this thesis. To demonstrate the identification procedure, a high fidelity nonlinear model of the H135 helicopter is used. Frequency sweep, 3211 and 2311 type inputs are given to the nonlinear helicopter model to generate test data. The procedure is carried out by identifying a state space model structure in time domain using output error method with Levenberg-M...
Implementation of sensorless vector control drive with current position estimation Filci, Tayfun; Ertan, Hulusi Bülent; Department of Electrical and Electronics Engineering (2016) In this thesis, an algorithm will be developed and implemented online for the estimation of rotor position from the rotor slot harmonics in stator currents. Experiments will be done on an inverter driven induction motor hardware, and the performance of the position detection algorithm will be evaluated in comparison with commercial encoder outputs.

Citation Formats

O. Tekinalp, “Development of a State Dependent Riccati Equation Based Tracking Flight Controller for an Unmanned Aircraft,” presented at the AIAA Guidance, Navigation, and Control (GNC) Conference (19-22 August 2013), Boston, MA, USA, 2013, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/71897.