Academic

ADCS Architecture

Attitude Determination and Control of 12U CubeSat using reaction wheel and cold-gas thrusters

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

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Launch site, trajectory and payload splash site

Conceptual Design and Performance Estimation of Sounding Rocket

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

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Trajectory

Design of Interplanetary transfer using Gravity assist

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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Attitude Determination and Control of 12U CubeSat using reaction wheel and cold-gas thrusters

Conceptual Design and Performance Estimation of Sounding Rocket

Design of Interplanetary transfer using Gravity assist

Selected courses where my research interest lies and getting hands-on experiences.

Orbital Mechanics

Attitude Dynamics and Control of Spacecraft

Space Mission Design and Analysis

Telecommunication systems

Space Propulsion and Launch systems

Spacecraft Navigation

Space Flight stability and control

Spacecraft design

Propulsion

Control Engineering