Academic Projects
High thrust transfer trajectory
Potential hazardous asteroids (PHA) are asteroids which have relatively high probability of impacting the Earth compared to that in Kuiper belts. PHA are class of asteroids
which stay near the Earth orbit, thus they are also called Near earth asteroids(NEA). Many mitigation strategies have been conceptualized in the past to deflect asteroid from
impacting the Earth. Deflection techniques such as Kinematic impactor and nuclear detonation techniques essentially deals with instantaneous energy impartation to the asteroid as a way to deflect it. Whereas, techniques such as Gravity traction and Space tug uses the mutual gravity field and tugging force respectively for deflection, thus requiring a large amount of time. In this study, gravity traction technique’s feasibility is analyzed in the context of real mission scenario. The mission is named Asteroid Redirection with Gravity tractoring and Observation or ARGO for short. This work will delineate the comprehensive feasibility study carried out by the ARGO mission team
on gravity traction deflection technique. I
ADCS Architecture
The attitude determination and control subsystem are the module which is responsible for maintaining, monitoring and controlling the satellite attitude against the environmental disturbances torques, which affect the satellite orientation and leads to angular destabilization of the satellite while it is in orbit. Under the guidance of Prof. Biggs James ADCS project is developed.
As seen the architecture, Sun sensor and Earth Horizon sensors were designed to obtain the full attitude. The maximum thrust from the 8 cold gas thrusters is considered for real control which is developed as per the Schmidt trigger logic in the Detumbling situation. Pyramidal configuration is chosen with 4 Reaction wheels, so that no actuator is aligned with the principal axis of inertia of the spacecraft during Slew maneuvering and Tracking phase.
Keywords: ADCS, Control, Kalman filters, Lyapunov stability
Tools: MATLAB & Simulink
Launch site, trajectory and payload splash site
The objective of this project is to perform the conceptual design and the performance estimation of a sounding rocket launched from a sea platform, with an apogee altitude of at least 100 km and carrying a payload of 150 kg. The rocket must be
own entirely in the Mediterranean area and the payload must be recovered. We must grant that the
rocket flies for a certain period under microgravity conditions, so that the scientific experiments contained in the payload can be carried out. This report contains propulsion system, mass budget, aerodynamics, trajectory, launch site, recovery methodology and uncertainties analysis to build a sounding rocket able to complete the mission with the given requirements. House of Quality investigation and Pareto analysis have been performed to define the critical parameters and requirements we have to consider for the project.
Keywords: House of Quality, Pareto Rule, Microgravity, Project Management
Tools: MATLAB & Simulink, LaTeX, MS Excel
Trajectory
The analysed planets are Mercury, Venus and Earth for the departure, fly-by and arrival, respectively. The
range of the considered window is from January 2019 to 2045. The reason not to examine a wider amount
of time relies upon the inner positions of these planets with respect to the solar system. Hence, their short
revolution periods lead their relative positions to repeat after less time than that required by the outer
planets.
The problem is modelled according to the patched conics method while the main assumptions are:
- no external perturbations
- instantaneous fly-by
- no corrective manoeuvres allowed
Keywords: Lambert problem, DeltaV minimization
Tools: MATLAB & Simulink, LaTeX
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