The GIESEPP Project has been planned in 5 phases, Phase 1 Mission Scenarios, Platforms, Requirements and Gap Identification, Phase 2 Electric Propulsion System Definition, Phase 3 Electric Propulsion System Development and Cost Optimisation, Phase 4 Build, Procure, Assemble and Prepare Standardised Tests and Phase 5 Test and Analysis.
Within phase 1 candidate platforms for
• LEO
• GEO and
• Space transportation, exploration and interplanetary missions
have been defined and assessed towards implementation of the GIESEPP platform as driving design element for the candidate satellite platform. Preliminary requirements were provided and assessed from EP subsystem and component point of view. The requirement breakdown on component level and the existing technical evaluation heritage allowed the identification of technical and performance gaps of all key EP elements (PPU, thrusters, and fluid management). In addition, first assessments regarding the functionality with alternative propellants were started on single component level and on GIESEPP system level. System trade-offs were performed resulting in a preliminary GIESEPP definition for the complete EPS and the single components.
Phase 2 was dedicated to the definition of the GIESEPP system coping with the requirements of the platform prime company. After the concept review of the EPS, design assessments on platform level were performed in order to define design sensitivity parameters influencing both the GIESEPP design on one hand and the candidate platform design on the other hand. The design sensitivity parameters (technical and economical) lead to further refinement of the candidate platform requirements towards the GIESEPP system and in consequence to its components. Specifications of the components of GIESEPP were defined and design and development plans were set up.
Phase 3 started after SRR. Final mission parameters have been defined taking into account the iterated GIESEPP system on one hand and direct customer and market input on the other. The phase allowed the identification of key cost drivers. Their re-assessment towards cost optimisation was constantly analysed in terms of performance and overall economic impact. The design in particular on component level was re-assessed with regard to a serial production of GIESEPP 1L, 2L and 1G considering high volume production scenerios. For both 1L/2L and 1G/1S respective PDR meetings have been performed.
Within phase 4 a set of component engineering models in preparation of a successful EM TRR for the different coupling tests has been manufactured and pre-tested. Also different potential harness solutions have been evaluated for first functional results – with a starting focus on 1L.
In parallel a test plan for coupling and alternative propellant tests has been established as baseline for individual test procedures specific to each partner.
Phase 5 was dominated by test execution and analysis:
• ArianeGroup RIT-10 based tests on both component level and coupled on 1L/2L system level (in two distinct configurations, once as pre-test w/o PPU and including Krypton as alternative propellant, then as full coupling test with PPU)
• ArianeGroup RIT-2X based test on both component level and coupled on 1G system level
• QinetiQ T7 based tests both on component and coupled level
Project results were regularly presented and distributed e.g. at IEPC2019 or via social media channels.
