LANDING GEAR DEPARTMENT

1. WP1 Review of System Requirements WP6 Management, Dissemination and Exploitation 1.1 Atmosphere modelling 6.2 Dissemination & Exploitation 1.2 Trajectories 1.3 Aerodynamics & ATD 1.4 Vehicle Design WP2 Ground Facilities Improvement WP3 Key Technologies for High Speed Entry WP4 Ablation- Flight Mechanics Coupling assessment WP5 Gas-Surface Interactions Modelling Concept: Ballistic, passive return of a soil sample from another planetary body in a Sample-Return Capsule, entering and aero-braking through the Earth’s atmosphere at high velocity. 2.1: Analysis of Current Ground Facilities 3.1: Choice of TPS + Joints 4.1 Tools coupling 5.1: Review of surface roughness and blowing influence 6.1 Management 2.2: Shock tube technology 3.2: Flow tests 4.2 Ablation coupling assessment 5.2: Ground Experiment Preparation 2.3: Ballistic Range Technology 3.3: Breadboard manufacturing 4.3 Engineering modelling Correction by CFD 5.3: CFD Modelling 2.4: Plasma Generator Technology 3.4: Crushable Structure 5.4: Synthesis of WP 2.5: Synthesis LANDING GEAR DEPARTMENT NCSR Demokritos, Greece Institute of Aviation, Poland Centro Italiano Ricerche Aerospaziali, Italy Office National d’Etudes et de Recherches Aérospatiales, France Lomonosov Moscow State University, Russia ASTRIUM-ST SAS, Coordinator, France CFS Engineering, Switzerland KYBERTEC, Czech Rep. Von Karman Institute for Fluid Dynamics, Belgium CNRS/EM2C, France • Challenges: • The main challenges faced by a ballistic, Sample-Return Vehicle are: • Ensure the entry phase of the ballistic trajectory and sustain the thermal and aerodynamical loads encountered during the entry until impact. • Protect the payload from heat and mechanical loads throughout the re-entry until impact on the ground • Comply with the planetary requirements, typically ensure sample container integrity until impact and guarantee sealing conditions at any time of the mission and under any circumstances. Radiation-Shapes-Thermal Protection Investigations for High Speed Earth Re-entry FP7/SPACE/241992 1/9/2011 – 30/10/2011 Total Budget: 2.3M€ CONCEPT OF A SAMPLE-RETURN VEHICLE FOR BALLISTIC EARTH RE-ENTRY • Objective: • “To increase Europe’s knowledge in high speed re-entry vehicle technology to allow for planetary exploration missions in the coming decades” • The specific Objectives are: • To better understand phenomena during high speed re-entry enabling more precise Capsule sizing and reduced margins. • To identify the ground facility needs for simulation • To master heat shield manufacturing techniques and demonstrate heat shield capabilities • To master damping at ground impact and flight mechanics and thus ensure a safe return of the samples Lid structure Lid TPS Rear Energy absorbing material AFT TPS IF Carrier Internal insulation Filling Foam The PARTNERS: FS Structure Internal structure FS TPS Front Energy absorbing material Sample Canister Main characteristics of a ballistic Earth re-entry. Effective max. total heat flux is about 11.6MW/m2, max. velocity 12.3km/sec (47.5Mach), total heat energy about 250MJ/m2. The Work Plan http://www.rastas-spear.eu/ FP7/SPACE: Activity 9.2.1 Strengthening of Space foundations / Research to support space science and exploration - SPA.2009.2.1.01 The research leading to these results has received funding from the European Union Seventh Framework Programme (FP7/2007-2013) under grant agreement n 241992