Slew Maneuver Control of Flexible Spacecraft

Date

2019-07-04

Author

ALTINIŞIK, SÜLEYMAN
Tekinalp, Ozan

Metadata

Show full item record

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

Item Usage Stats

143
views

0
downloads

Nonlinear slew maneuver algorithms for flexible spacecraft are developed. Theattitude trackingalgorithm that uses quaternion parametrizationand follows the prescribed time dependent attitude trajectory incorporating the derivative of the desired attitudeis employed. Nonlinear tracking feedback control algorithms that includes piezoelectric actuators and modal sensors are also developed. Through simulations, the effectiveness of the tracking attitude control algorithm is demonstrated. Also demonstrated is the effectiveness of the tracking controller utilizing piezoelectric actuators modal sensors in damping out vibration energy.

URI

https://hdl.handle.net/11511/58049

DOI

https://doi.org/10.13009/eucass2019-935

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Numerical investigations of lateral jets for missile aerodynamics Ağsarlıoğlu, Ekin; Albayrak, Kahraman; Department of Mechanical Engineering (2011) In this thesis, effects of sonic lateral jets on aerodynamics of missiles and missilelike geometries are investigated numerically by commercial Computational Fluid Dynamics (CFD) software FLUENT. The study consists of two parts. In the first part, two generic missile-like geometries with lateral jets, of which experimental data are available in literature, are analyzed by the software for validation studies. As the result of this study, experimental data and CFD results are in good agreement with each other...
Mathematical Modeling of the NOTAR Antitorque System for Flight Simulation Yavrucuk, İlkay; Uzol, Oğuz (2013-04-01) In this paper, a mathematical model of a helicopter NO TAil Rotor (NOTAR) antitorque system is developed for real-time flight simulations. The model consists of the circulation control tail boom, direct jet thruster, and the vertical stabilizers. The airflow inside the tail boom is modeled by dividing the flow into aerodynamic control volumes. The model features a bladeelement-type approach for modeling the mass flow through the axial fan blades as well as aerodynamic mass and momentum conservation calculat...
Numerical simulation of lateral jets in supersonic crossflow of missiles using computational fluid dynamics Dağlı, Efe Can; Aksel, M. Haluk.; Department of Mechanical Engineering (2019) In this thesis, numerical simulation method for modelling lateral jet in supersonic crossflow is presented. Lateral jet control provides high maneuverability to the missile at difficult flow conditions. Besides, jet in a crossflow case has a highly complicated flow domain which should be examined using numerical or experimental methods. In this study, numerical methods are used. The thesis consists of two main sections. In the first section, a validation study is conducted for numerical simulation method us...
Numerical Simulation of a Flapping Micro Aerial Vehicle Through Wing Deformation Capture Tay, W. B.; de Baar, J. H. S.; Perçin, Mustafa; Deng, S.; van Oudheusden, B. W. (American Institute of Aeronautics and Astronautics (AIAA), 2018-8) Three-dimensional numerical simulations of a four-wing flapping micro aerial vehicle (FMAV) with actual experimentally captured wing membrane kinematics have been performed using an immersed boundary method Navier-Stokes finite volume solver. To successfully simulate the clap and fling motion involving the wing intersection, the numerical solver has been specifically modified to use a newly improved interpolation template searching algorithm to prevent divergence. Reasonable agreement was found between the ...
Radar cross section analysis by shooting and bouncing rays method Çakır, Mustafa Kağan; Tokdemir, Turgut; Department of Engineering Sciences (2015) In this study, a MATLAB code incorporating `Shooting and Bouncing Rays (SBR) Method` is developed for calculating Radar Cross Section (RCS) of complex shapes. The code can calculate ray paths, magnetic current sheets, incident and scattered electric fields and RCS in horizontal, vertical and cross polarizations. While reflection effects are calculated by SBR algorithm, diffraction effects due to edges and corners are handled by `Equivalent Edge Currents (EEC’s)`. Wave frequency, aspect angle and number of r...

Citation Formats

S. ALTINIŞIK and O. Tekinalp, “Slew Maneuver Control of Flexible Spacecraft,” 2019, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/58049.