Tracking control of spacecraft attitude on time dependent trajectories

A spacecraft attitude control which uses the quaternion parametrization, is proposed. The derivative of the to-go quaternion is obtained where the desired attitude is a time dependent function. Using this new attitude formulation, a Lyapunov function based feed-back control law that takes the time derivative of the desired attitude into account is proposed. The simulation results demonstrate the success of the new algorithm in tracking the desired attitude trajectory.
AIAA/AAS Astrodynamics Specialist Conference, (13 - 16 Eylül 2016)


BÜYÜKKOÇAK, ALİ TEVFİK; Tekinalp, Ozan (2019-01-01)
A spacecraft attitude and position control algorithm that uses dual quaternions for parametrization is proposed. Error dual quaternion and its derivative are obtained from the desired attitude and position information which are the trajectories of time dependent functions. This position and orientation (pose) formulation is used in a Lyapunov based nonlinear feedback control law that includes derivative of desired attitude and position. Simulation results show that desired attitude and position trajectories...
Orbit Control of an Earth Orbiting Solar Sail Satellite
Polat, Halis Can; Tekinalp, Ozan (2022-09-01)
A concept for the utilization of solar sail satellite's propellant-free thrust capability at Low earth orbit (LEO) is proposed and its orbit control strategy is analyzed. Thrust vector control of the sail's normal direction is used to harvest the solar radiation pressure for generating the necessary acceleration to change the orbital elements. The required control vector direction is determined with two approaches. The first approach is realized by approximating the Gaussian Variational Equations at the emp...
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 State Dependent Riccati Equation Based Tracking Flight Controller for an Unmanned Aircraft
Tekinalp, Ozan (2013-08-22)
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 opt...
Nonlinear guidance and control of leader-follower UAV formations
Kumbasar, Sarper; Tekinalp, Ozan; Department of Aerospace Engineering (2015)
In this thesis work, two nonlinear guidance methods are proposed to control the autonomous formation flight: State Dependent Riccati Equation method and Lyapunov function method. Leader-Follower formation scheme is chosen and a pair of fighter aircrafts are used in simulations. One of them is chosen as the leader and it carries out the commanded maneuvers. Other aircraft is the follower and it follows the leader keeping the prescribed formation structure. Both aircraft models are nonlinear. In the inner loo...
Citation Formats
O. Tekinalp, “Tracking control of spacecraft attitude on time dependent trajectories,” presented at the AIAA/AAS Astrodynamics Specialist Conference, (13 - 16 Eylül 2016), Long Beach, CA, Amerika Birleşik Devletleri, 2016, Accessed: 00, 2021. [Online]. Available: