This paper presents the activities that led to the assembly and verification of the ALMASat-1 microsatellite separation system carried out at the Microsatellite Laboratory of the University of Bologna, Forlì Campus. ALMASat-1 adapter and separation system was designed according to the requirements imposed by the European launch vehicle VEGA, general mission requirements and additional specific requirements related to ALMASat-1 microsatellite geometry and inertial properties. The analysis of these requirements drove the whole design process. The general architecture selected for the interface is the classical cylindrical canister adapter with a 2-clamps constraining system. This solution, common for micro- and nano- satellites, has a wide flight heritage, is typically simple and affordable and could be easily implemented for a wide range of launch vehicles. The sizing of the whole mechanism was carried out by means of theoretical calculations while advanced dynamics simulations based on MATLAB and Nastran code were performed to deeply investigate the transient phenomena characterizing the separation dynamics in the very first tens of milliseconds. Along with numerical simulations, experimental tests have been performed by means of a separation test-bed, specifically designed to reproduce the correct dynamics of both the separation system and the spacecraft. As part of this experimental activity, the spacecraft angular velocities arising from potential non-symmetric actions of the four DV springs or clamps asynchronous actuation were estimated. This evaluation is extremely important in order to avoid damages to the satellite, other payloads and LV upper stage due to possible collisions. Finally, the structural and topological optimization process performed on the ALMASat-1 Adapter and Separation System will be presented, focusing on the reduction of the system overall mass which, in turns, determines the launch costs and represents one of the most critical aspects in microsatellite missions.
A. Corbelli, D. Bruzzi, P. Tortora (2009). Design, Assembly and Verification of the ALMASat-1 Separation System. MILANO : AIDAA.
Design, Assembly and Verification of the ALMASat-1 Separation System
TORTORA, PAOLO
2009
Abstract
This paper presents the activities that led to the assembly and verification of the ALMASat-1 microsatellite separation system carried out at the Microsatellite Laboratory of the University of Bologna, Forlì Campus. ALMASat-1 adapter and separation system was designed according to the requirements imposed by the European launch vehicle VEGA, general mission requirements and additional specific requirements related to ALMASat-1 microsatellite geometry and inertial properties. The analysis of these requirements drove the whole design process. The general architecture selected for the interface is the classical cylindrical canister adapter with a 2-clamps constraining system. This solution, common for micro- and nano- satellites, has a wide flight heritage, is typically simple and affordable and could be easily implemented for a wide range of launch vehicles. The sizing of the whole mechanism was carried out by means of theoretical calculations while advanced dynamics simulations based on MATLAB and Nastran code were performed to deeply investigate the transient phenomena characterizing the separation dynamics in the very first tens of milliseconds. Along with numerical simulations, experimental tests have been performed by means of a separation test-bed, specifically designed to reproduce the correct dynamics of both the separation system and the spacecraft. As part of this experimental activity, the spacecraft angular velocities arising from potential non-symmetric actions of the four DV springs or clamps asynchronous actuation were estimated. This evaluation is extremely important in order to avoid damages to the satellite, other payloads and LV upper stage due to possible collisions. Finally, the structural and topological optimization process performed on the ALMASat-1 Adapter and Separation System will be presented, focusing on the reduction of the system overall mass which, in turns, determines the launch costs and represents one of the most critical aspects in microsatellite missions.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
