The majority of large engine activity in Europe is hydrogen based and requires more costly pump technology, with deep cryogenic temperatures and complex sealing requirements. This activity was to demonstrate a low-cost LOX pump design, manufacture and test capability with view to enabling a LOX Kerosene 60kN engine program. These engines are more appropriate for the small launcher market than LOX/LH2.

LENA space successfully built and demonstrated a 60kN Kerosene pump, developed internal manufacturing capabilities including specialist impeller manufacturing procedures. LENA have designed a technology development roadmap for the pump technology targeting the next critical steps towards flight qualification.

Current chemical propulsion systems rely on the hypergolic reaction of dangerous, corrosive and toxic chemicals. The selection of these chemicals was driven by a range of needs including performance, storability and reliability. They have also driven up the sub-system design justification cost. Current ''green'' propulsion options can offer some mitigation of these issues however most alternatives are not benign chemicals and continue to have safety and cost concerns. Electrolysis (ECLSS heritage) technology in Europe is at a high TRL.

Iodine as a propellant is considered a valid alternative to xenon for electric propulsion application, in particular on Hall effect thrusters. Several advantages when using iodine as opposed to xenon can be enumerated. Iodine and xenon atomic mass and first ionization energy are very close and thruster performances, in terms of thrust density, thrust efficiency and specific impulse, have proved to be almost the same. Iodine is solid at ambient temperature and pressure, with a density about four times the density of xenon stored at 200 bar of pressure and ambient temperature.

The Synergetic Air-Breathing Rocket Engine (SABRE) has the potential to allow the development of space launch systems which provide a step change in reusability, reliability and cost-per-kg to orbit. Whilst ground based development of SABRE core engine and rocket elements is progressing, flight testing of the SABRE nacelle elements is seen as most appropriate approach to raising their TRL to allow acceptable risk flight testing of an entire SABRE propulsion unit.

HC Engine Vacuum Igniter

The electric solar wind sail (E-sail) propulsion system, because it does not run out of propellant, can enable multi-target missions that can flyby or rendezvous with a larger number of asteroids or other celestial objects.