Simulation Model and Hardware-in-the-Loop Verification of the EventSat ADCS

Institut

Lehrstuhl für Spacecraft Systems (TUM-ED)

Typ

Bachelorarbeit /

Inhalt

 

Beschreibung

EventSat is a 6U CubeSat under development at the Chair of Spacecraft Systems, targeting a Sun-synchronous orbit at 450 km altitude and operating in five defined attitude modes Detumbling, Safe, Idle, Observation and Communication. Attitude determination and control is provided by CubeSpace. This implements a baseline EventSat model in D2S2, the simulation framework used at the chair, capturing the spacecraft’s physical properties, communication capabilities, power modes and ADCS modes, so that the model can serve as the common starting point that subsequent EventSat simulation studies inherit rather than re-create. The baseline is then exercised against the CubeADCS hardware in a hardware-in-the-loop (HIL) configuration and used to answer two open ADCS design questions: how reaction-wheel momentum accumulates and when saturation is reached, and how much energy storage detumbling requires.

Overall Objective: The overall objective is to implement a baseline simulation model of EventSat in D2S2, verify it against the CubeADCS flight hardware in a hardware-in-the-loop setup, and use the validated baseline to quantify reaction-wheel momentum build-up and desaturation strategy, and the energy storage required for detumbling.

On the engineering side, the objective is a reusable and parameterised EventSat baseline (mass properties, orbit, communication capabilities, power modes and the five ADCS modes) that is validated against hardware rather than assumed. On the analysis side, the objective is a momentum model of the reaction wheels under the EventSat mode profile, yielding the time to saturation per mode, a magnetorquer-based desaturation law with its duty cycle and power cost, an assessment of whether magnetorquers and wheels should be operated continuously in combination to delay saturation, and a worst-case detumbling energy budget derived from the deployer tip-off rate.

Goal type: implementation and validation, followed by an analysis component built on the validated baseline.

Success Criteria: Success is measured by four outcomes: (i) a running D2S2 EventSat baseline that reproduces all five ADCS modes and the associated power modes, with every input parameter documented in a released parameter spreadsheet; (ii) a HIL run in which the CubeADCS responds to OBC commands under simulated dynamics, together with a documented answer on whether the CubeComputer remains reachable through the OBC while the HIL loop is running; (iii) a predicted time-to-saturation and desaturation duty cycle consistent with the magnetic moment and the momentum storage capacity; and (iv) a detumbling energy figure with stated margin, traceable to the EventSat power budget.

Möglicher Beginn

October 2026

Kontakt

Vincenzo Messina
Tel.: +49 89 289 55752
vincenzo.messinatum.de

Ausschreibung