SPLASH (Self-DePloyable FLexible AeroSHell for de-Orbiting and Space Re-entry) is a 12U CubeSat with di-mensions of 226.3x226.3x366 mm and a mass of 24 kg. The satellite is a technology demonstrator carried out incollaboration between the University of Brasilia and CIRA, which aims to perform atmospheric re-entry from a LEOorbit, making it possible to use it as a safe device for returning scientific payloads or data from LEO orbits. The open-ing mechanism is built in a similar way to an umbrella, and consists of 8 arms, each supported by a beam, which isconnected to a sliding ring. During re-entry, the main stresses are generated by dynamic pressure. An approximateestimate of the pressure acting on the shield can be obtained by considering that the satellite re-enters the Earth follow-ing a vertical direction and maintains a constant attitude, without any type of rotation. A static analysis was carriedout using the finite element method with line elements and solid elements. The values obtained were compared withthe analytical model. The proposed initial geometry was first analyzed, followed by a parametric analysis to find theoptimum value for positioning the supports. After defining the supports, an optimum value for the cross-section wasalso defined through parametric optimization. Next, a topological optimization was carried out to find places whereit was possible to reduce the mechanism’s mass. The results obtained show that the design is capable of withstandingthe re-entry loads and that by combining parametric optimization with topological optimization it is possible to find anoptimal geometry model, with significant mass reduction and while maintaining the mechanical properties.
Deployment Mechanism Design for Atmospheric Reentry Protection Systems / Alves, Pedro; Nascimento Dias Barcelos Júnior, Manuel; Silvac, William; Vendittozzi, Cristian; Andrianov, Artem; Fernanda de Sousa Pimentel, Maria; Malta, Gustavo; Dimino, Ignazio. - 2024:(2024). (Intervento presentato al convegno International Astronautical Congress, IAC24 Responsible Space for Sustainability tenutosi a Milan, Italy).
Deployment Mechanism Design for Atmospheric Reentry Protection Systems
Cristian Vendittozzi;
2024
Abstract
SPLASH (Self-DePloyable FLexible AeroSHell for de-Orbiting and Space Re-entry) is a 12U CubeSat with di-mensions of 226.3x226.3x366 mm and a mass of 24 kg. The satellite is a technology demonstrator carried out incollaboration between the University of Brasilia and CIRA, which aims to perform atmospheric re-entry from a LEOorbit, making it possible to use it as a safe device for returning scientific payloads or data from LEO orbits. The open-ing mechanism is built in a similar way to an umbrella, and consists of 8 arms, each supported by a beam, which isconnected to a sliding ring. During re-entry, the main stresses are generated by dynamic pressure. An approximateestimate of the pressure acting on the shield can be obtained by considering that the satellite re-enters the Earth follow-ing a vertical direction and maintains a constant attitude, without any type of rotation. A static analysis was carriedout using the finite element method with line elements and solid elements. The values obtained were compared withthe analytical model. The proposed initial geometry was first analyzed, followed by a parametric analysis to find theoptimum value for positioning the supports. After defining the supports, an optimum value for the cross-section wasalso defined through parametric optimization. Next, a topological optimization was carried out to find places whereit was possible to reduce the mechanism’s mass. The results obtained show that the design is capable of withstandingthe re-entry loads and that by combining parametric optimization with topological optimization it is possible to find anoptimal geometry model, with significant mass reduction and while maintaining the mechanical properties.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.