Nonlinear tracking attitude control of spacecraft on time dependent trajectories

Date

2015-08-13

Author

Tekinalp, Ozan
Atas, Omer

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

180
views

0
downloads

The spacecraft attitude control is carried out using the to-go quatemion. A derivative of the to-go quaternion is derived where the desired attitude is a time dependent function. Based on this new attitude formulation, a proper state dependent coefficient matrix expression is obtained. Then the nonlinear tracking attitude control is realized using the state dependent Riccati equation method. The simulation results are given and discussed.

Subject Keywords

Spacecraft attitude, Riccati equation method

URI

https://hdl.handle.net/11511/53221

Conference Name

AAS/AIAA Astrodynamics Specialist Conference

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Study on an Advanced Attitude Determination Algorithm for the ERG Spacecraft Söken, Halil Ersin; Asamura, Kazushi; Nakamura, Yosuke; Takashima, Takeshi (null; 2017-06-07) AXA’s Arase Spacecraft, which is formerly known as Exploration of Energization and Radiation in Geospace (ERG), was launched on 20 December 2016. The spacecraft is spin-stabilized. Its mission is exploring how relativistic electrons in the radiation belts are generated during space storms. Two on-ground attitude determination algorithms are considered for the mission: a conventional simple algorithm that inherits from old missions and an advanced algorithm that is newly designed. This paper discusses the de...
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...
Attitude control of an earth orbiting solar sail satellite to progressively change the selected orbital element Ataş, Ömer; Tekinalp, Ozan; Department of Aerospace Engineering (2014) Solar sailing is currently under investigation for space propulsion. Radiation pressure from the Sun is utilized to propel the spacecraft. This thesis examines locally optimal steering law to progressively change the selected orbital elements, without considering others, of an Earth centered Keplerian orbit of a cube satellite with solar sail. The proper attitude maneuver mechanization is proposed to harvest highest solar radiation force in the desired direction for such Earth orbiting satellites. The satel...
Spinning Spacecraft Attitude Filtering with Spin Parameters: Performance Evaluation with Real Data Söken, Halil Ersin; Van Der Ha, Jozef C. (null; 2017-06-07) Three-axis attitude estimation for spinning spacecraft is recently of considerable practical interest. In this scope, sequential filtering algorithms are also being studied recently. In this study, we extend our recent research for a nonlinear filtering algorithm for spinning spacecraft attitude estimation. In the filter the attitude of the spacecraft is represented using a set of spin parameters. These parameters consist of the spin-axis orientation unit vector in the inertial frame and the spin phase angl...
Autonomous spacecraft rendezvous and docking on safe trajectories Büyükkoçak, Ali Tevfik; Tekinalp, Ozan; Department of Aerospace Engineering (2018) In this thesis, rendezvous and docking operation of a pair of low earth orbit spacecraft is addressed. Two different sets of equations for the nonlinear orbital relative motion of spacecraft are derived and simulation codes for this motion are developed. First, Hill-Clohessy-Wiltshire (HCW) equations are used in chaser-target spacecraft configuration with Model Predictive Control (MPC) algorithm including some safety considerations such as debris avoidance, direction of approach constraint and slow impact r...

Citation Formats

O. Tekinalp and O. Atas, “Nonlinear tracking attitude control of spacecraft on time dependent trajectories,” Vail, CO, 2015, vol. 156, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/53221.