Running MSc thesis subjects

Study on the Effect of Assisted Launch on Launch Vehicle Performance
My thesis tries to quantify the maximal payload increase and/or delta-V budget decrease for varying launch assists with different initial parameters. These parameters are: initial velocity, attitude and position. This is should be done by optimizing both trajectory parameters as well as launch vehicle design parameters.  
Student: Jan Vandamme
Thesis advisor: Erwin Mooij
Start/End: November 2011/July 2012 

Design of a Combinatorial Tool for Preliminary Space Mission Analysis
The main goal is to solve the discrete aspect of the 2nd Global Trajectory Optimization Competition (GTOC2), namely developing a computationally fast method to identify the most promising solution out of millions of possible combinations. The method will rely on high-thrust approximations and combinatorial optimization concepts. 
Student: Thomas André Leite Pinto Secretin 
Thesis advisor: Ron Noomen
Start/End: September 2011/July 2012  

Validating and improving the Precise Orbit Determination of Cryosat-2
The validation and improvement of the POD of Cryosat-2 is done by looking at three aspects of the process. A new data format for the SLR measurements is implemented. The Doris station coordinates are validated and a different solar radiation pressure model for the satellite is constructed. 
Student: Bart Root
Thesis advisor: Ernst Schrama
Start/End: May 2011/March 2012 

Low-Thrust Trajectory Optimization - A comparison of different (global) optimization techniques, with a focus on constraint handling/satisfaction
Student: Emil Heeren
Thesis advisor: Ron Noomen
Start/End: December 2011/August 2012

Filtering Techniques for Orbital Debris Conjunction Analysis
Verified implementation of a complete orbital debris conjunction analysis system, including the improved design of multiple versions of filters and sieves, which were tested in terms of performance, for a more efficient and reliable process. The system is based on an all-vs-all analysis of the objects of the Two-Line Element (TLE) database of the Space Surveillance Network (SSN), of which the ephemerides are determined with the Simplified General/Deep-space Perturbations 4 (SGP4/SDP4) propagator.   
Student: Jonantan Leloux
Thesis advisor: Ron Noomen
Start/End: January 2011/February 2012 

A parametric study of space debris impact footprints
An analysis of the effect of model uncertainties on the footprint location and size of re-entering space debris. One of the main goals is to improve prediction capability for future large-body re-entries. 
Student: Alexander Ronse
Thesis advisor: Erwin Mooij
Start/End: December 2011/June 2012 

Autonomous Navigation for Nano-satellites during Earth-Moon Transfer
Navigation is one of the critical technologies for putting OLFAR, a swarm of nano-satellites forming a radio-telescope around the Moon, in space. To reduce cost and complexity, an autonomous system is required to determine the position the nano-satellites both during the transfer and in orbit around the Moon.  
Student: Frederik Belien
Thesis advisor: Erwin Mooij
Start/End: December 2011/June 2012

Optimization of Multiple Gravity-Assisted Space Trajectories Including Deep Space Maneuvers
I will be building and testing various optimization techniques to find a reliable, robust and efficient optimization technique that can solve general (interplanetary) space trajectories. I will focus on impulsive trajectories, with a maximum of 1 DSM (deep space maneuver) in each leg and benchmark my results against online published results.  
Student: Paul Musegaas
Thesis advisor: Ron Noomen
Start/End: February 2012/December 2012  

Trajectory optimization of a hypersonic research vehicle
The topic of my thesis is the optimization of the launch and descent trajectory of a hypersonic research vehicle. This is part of the feasibility study for the research vehicle concept Hypresearch.  
Student: Willem Martens
Thesis advisor: Erwin Mooij
Start/End: October 2011/June 2012

Analytical low-thrust trajectory design
Student: David Gondelach
Thesis advisor: Ron Noomen
Start/End: September 2011/May 2012

Numerical Optimization of a Low-Thrust Mission to the Solar Poles
The goal is to design and optimize the transfer trajectory for an interplanetary satellite to the solar poles utilizing numerical techniques for modeling the continuous low-thrust propulsion force. Furthemore, this trajectory will be compared with an equivalent traditional patched connics transfer trajectory to quantify an improvement with current trajectories.
Student: Simon Billemont
Thesis advisor: Ron Noomen
Start/End: November 2011/2012