Publication Date: 28-JUN-18

Program ref.: Technology Developme
Tender Type: C
Tender Status: INTENDED
Price Range: 200-500 KEURO
Budget Ref.: E/0901-01 - Technology Developme
Proc. Prop.: NO
Establishment: ESTEC
Responsible: Ford, Mark
Products: Orbital Transportation & Re-entry Systems / Structures / Tanks / Propellant Tanks Launchers / Structures / Stage structures / Intestages, skirts, thrust frame, ¿ Launchers / Structures / Propellant tanks Launchers / Structures / Tanks
Techology Domains: Structures / Structural Design and Verification Methods and Tools / S/C Design and Design Tools Propulsion / Chemical Propulsion Technologies / Liquid Propulsion Systems
Industrial Policy Measure: N/A - Not apply

Spacecraft typically employ discrete tanks which support only the propellant mass and internal pressure loads and which are robust to the generated mechanical environment. For spacecraft this has always been sufficient but for lander missions, especially lunar landing with it associated large delta V requirements and significant gravity losses, the resulting propulsion system is very large and the structure necessary to support it is also significant (typically this can be over 60% of the spacecraft mass). Launch vehiclesalso achieve better mass fractions by employing structural tanking. Structural tanking is also seen on upper stage designs in both low and medium pressure configurations. Simplifying greatly, landing missions can be considered as the reverse of launcher missions.Improving the dry mass to wet mass ratio would bring huge benefits and structural tanking has huge potential in this regard. Therefore the activity is foreseen as a predominantly design and analysis based. Starting with a defined large lunar lander concept at mission level, different designs for the lander based around down-selected structural tanking concepts . Lander performance shall be evaluated based on and idealized parameterised engines. The engines will provide requirements and constraints on the tanking design including but not limited to internal tank pressure, expulsion rate, and propellant compatibility. A materials selection and trade-offwill be madeto the various applications. The trade-off criteria will be based on common structural considerations and materials consideration including but not limited to fracture control fatigue. For the most promising down selected candidates the mechanical thermal and propulsion elements of the resulting configuration will be examined in detail considering but not necessarily limited to Optimum pressure levels and Management of load introduction to pressure vessels.

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