Speaker
Description
Due to the multiplication of private actors in the space adventure, France has adopted in 2008 the French Space Operation Act (FSOA), which establish a national regime of authorization and supervision for space activities. Then, the Technical Regulations has clearly addressed the concepts of safety and sustainability of space activities, including the safety of people and property. Within this framework, CNES, the French Space Agency, is in charge of ensuring compliance with the Technical Regulations associated with the FSOA.
To be able to predict the debris survivability of a space vehicle and its associated fragments during their atmospheric re-entry, and assess the prospective risk on the ground, CNES develops its own spacecraft-oriented tool named PAMPERO [1]. One of its objectives is to provide a fine expertise of the whole fragmentation process.
To ensure the safety use of space, PAMPERO also enables the analysis of new solutions in the design of vehicles and their components, allowing reducing as much as possible the potential risks on the ground. In this context, in [2, 3] PAMPERO highlights that the most influencing parameters on the spacecraft's demise are the predictions of the heat load and the fragmentation process. Following these issues, in a recent paper [4], PAMPERO analyses the impact of different technologies applied to the re-entry of TARANIS satellite.
In order to extend this previous work, a promising technology that can be seen as a Design for Demise solution is introduced here, this is the topology optimization approach. This technology, coupled to additive manufacturing, is usually adopted for reducing the mass, with equivalent mechanical or thermal performances [5, 6].
The goal of this presentation is to highlight how the resulting freeform of this approach, can allow better demisability compared to classical shape.
To deal with this goal, atmospheric re-entry simulations are performed on a specific case study. The improvement of design, in terms of ground risk, is assessed using numerical simulations performed with Pampero.
[1] Van Hauwaert, P, et Al., Pampero v3, a spacecraft-oriented reentry analysis code, 2nd International Conference on Flight Vehicles, Aerothermodynamics and Re-entry Missions & Engineering (FAR), 19 - 23 June 2022. Heilbronn, Germany.
[2] J. Dumon & al. REBUILD AND DATA EXPLOITATION OF THE AVUM RE-ENTRY EVENT FOR BREAK-UP MODEL DEVELOPMENT. The 2nd International Conference on Flight Vehicles, Aerothermodynamics and Re-entry Missions Engineering (FAR), 19-23 June 2022, Heilbronn, Germany
[3] M.Spel & al. DEMISABILITY STUDY OF INDUSTRIAL TEST CASES WITH THE SPACECRAFT-ORIENTED CODE PAMPERO, 8th European Conference on Space Debris ESA/ESOC, Darmstadt, Germany ( Virtual Conference), 20 - 23 April 2021
[4] H. Pasquier & al. DESIGN FOR DEMISE AND DESIGN FOR CONTAINMENT TECHNOLOGIES FOR THE REDUCTION OF THE DEBRIS CASUALTY AREA: IMPLEMENTATION ON A MICROSATELLITE AND GAIN EVALUATION WITH DEBRISK AND PAMPERO SOFTWARES, 17th ECSSMET, Toulouse, France 28-30 March 2023.
[5] SJI Walker, F Romei, J Becedas Rodríguez, F Dalla Vedova, J Beck. An Overview of the Application of 3D Printed Spacecraft Structures within the ReDSHIFT Project. INTERNATIONAL ASTRONAUTICAL CONGRESS: IAC PROCEEDINGS, 1-10
[6] Meng, L.; Zhang, W.; Quan, D.; Shi, G.; Tang, L.; Hou, Y.; Breitkopf, P.; Zhu, J.; Gao, T. From Topology Optimization Design to Additive Manufacturing: Today’s Success and Tomorrow’s Roadmap. Arch. Comput. Methods Eng. 2020, 27, 805–830.
