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All satellites must have the ability to correct for the high rotational tip-off rates after initial release from the launch vehicle. On current navigation satellites, de-tumbling is usually achieved in short duration using the onboard chemical propulsion thrusters. With future Navigation satellites looking at using all-electric propulsion satellites, these manouevres are to be performed by xenon-fed auxiliary thrusters. COTS (xenon cold gas) auxiliary thrusters are limited in the max thrust level provided and the de-tumbling duration, in the absence of chemical thrusters, is a concern.

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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.

Objective:
Demonstrate robust and repeatable vacuum ignition of LOX/Kerosene breadboard ignitor.

Achievements:

• Successful plasma ignition was demonstrated with SSI-developed subsystems and the IRS IPT lab model. The ignition test campaign was conducted from 11th -14th April 2023 at IRS, Stuttgart.

• Two PPU amplifiers were designed, simulated, built, and tested; the Class E amplifier successfully ignited the thruster.