SAFE SPACECRAFT RENDEZVOUS WITH CONSTRAINED MODEL PREDICTIVE CONTROL

Date

2019-01-01

Author

BÜYÜKKOÇAK, ALİ TEVFİK
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

172
views

0
downloads

Rendezvous and docking problem of a pair of low Earth orbit spacecraft is addressed. Equations for the nonlinear orbital relative motion of spacecraft are derived and a simulation code for this motion is developed. For the control algorithm, linearized Hill-Clohessy-Wiltshire (HCW) equations are used in chaser target spacecraft configuration. All authority is given to the chaser spacecraft, and the target is kept passive. The HCW equations are linearized assuming a circular orbit. Model Predictive Control (MPC) strategy is applied with safety constraints including debris avoidance and Line of Sight constraint. This includes the avoidance of a relatively moving debris with an unbounded motion. Simulation results are given and discussed. A parametric study is also performed to obtain the proper prediction horizon as well as weighting matrices to be used in the simulations.

URI

https://hdl.handle.net/11511/53612

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Safe Spacecraft Rendezvous with Constraint Model Predictive Control Tekinalp, Ozan (2018-08-23) Rendezvous and docking problem of a pair of low Earth orbit spacecraft is addressed. Equations for the nonlinear orbital relative motion of spacecraft are derived and a simulation code for this motion is developed. For the control algorithm, linearized Hill-Clohessy-Wiltshire (HCW) equations are used in chasertarget spacecraft configuration. All authority is given to the chaser spacecraft, and the target is kept passive. The HCW equations are linearized assuming a circular orbit. Model Predictive Control (M...
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...
Choice of Pole Number of Two-Rotor Axial-Flux PM Motor for Control Moment Gyroscope Özlü Ertan, Hatice Gülçin (2011-09-10) Modern low earth orbit satellites use control moment gyroscopes (CMG) for maneuvering. GMC's generally use a brushless DC motor to run an inertial wheel at about 10000 rpm. In this paper axial-flux BLDC motor is considered for this task with a view to design a low volume, low weight CMC. Various axial-flux (AF) motor topologies are possible. However, two-rotor AF topology is found to be more advantageous. The specifications of an existing CMG design, based on a commercial BLDC motor are taken as reference. ...
Long term and safe relative orbit design for heterogeneous spacecraft clusters Yaglioglu, Burak; Tekinalp, Ozan (2021-06-01) The problem of obtaining long term relative orbit configurations for spacecraft clusters with realistic operational considerations such as safety, station keeping and inter-spacecraft distances is addressed. Two different approaches are developed for station keeping and safety objectives. In the first approach, relative orbit configurations, or relative TLEs, are found minimizing deviations from reference mean orbit which would maximize the station-keeping objective. In second one, relative configurations a...
An interactive program for GPS-based dynamic orbit determination of small satellites Karslıoğlu, Mahmut Onur (Elsevier BV, 2005-04-01) This work introduces a near real-time dynamic orbit determination program for small satellites. A quality check of orbit data on ground is important for satellites with GPS positioning that is only available at discrete time epochs because of the limited power-supply onboard, so that space-borne GPS receivers are switched on/off intermittently, or because of possible malfunctioning of GPS receivers. The method of parameter estimation with space-borne GPS position fixes as observations is based on an extende...

Citation Formats

A. T. BÜYÜKKOÇAK and O. Tekinalp, “SAFE SPACECRAFT RENDEZVOUS WITH CONSTRAINED MODEL PREDICTIVE CONTROL,” 2019, vol. 167, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/53612.