Ravikumar, L and Philip, NK and Padhi, R and Bhat, MS (2016) Autonomous Terminal Maneuver of Spacecrafts for Rendezvous using Model Predictive Control. In: 2nd Indian Control Conference (ICC), JAN 04-06, 2016, Indian Inst Technol, Hyderabad, INDIA, pp. 72-78.
Ind_Con_Con_72_2016.pdf - Published Version
Restricted to Registered users only
Download (451Kb) | Request a copy
Model Predictive Control (MPC) based relative motion control is developed for rendezvous of a follower spacecraft with a leader spacecraft Debris Avoidance Maneuver operates in rendezvous phase and Line of Sight Maneuvers during terminal phase In this approach, the optimal control sequence is generated over finite horizon by considering the measurement of the state in every guidance step for different rendezvous phases. Various equality and inequality constraints are included These constraints are thrust magnitude limit, chaser spacecraft positioning with in Line-of-Sight (LOS) while approaching the target spacecraft, and chaser spacecraft terminal velocity limit for soft -docking with target spacecraft. In addition debris avoidance constraints are also considered along the rendezvous path. The robustness of this control has been verified using nonlinear dynamics with J2 perturbation model. Pulse Width and Pulse Frequency modulator (PWPFM) are used to generate the impulse velocity change by on/off thrusters as actuators. The MPC Controller is validated on nonlinear and elliptical orbit model by simulations.
|Item Type:||Conference Proceedings|
|Additional Information:||Copy right for this article belongs to the IEEE, 345 E 47TH ST, NEW YORK, NY 10017 USA|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||22 Oct 2016 09:32|
|Last Modified:||22 Oct 2016 09:32|
Actions (login required)