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The scope of the EAM activities is to define and to develop a competitive high thrust, high specific impulse European Apogee Motor (EAM).
|The central phase of the project reflects the development and optimization of the high performance injector and combustion chamber according to the requirements to obtain the best motor on the market. The product shall have exclusively European components to be Itar free and shall provide the versatility of all the interfaces for the use on board of existing platforms (SpaceBus, Eurostar, etc) as well as for the use on AlphaBus.|
In the last phase of the project the EAM design has to demonstrate the ability to meet all specification requirements. The suitability of the EAM design shall be assessed to proceed finally into a formal qualification program with a flight like EAM hardware. A Critical Design Review (CDR) shall be held before starting the qualification phase.
Three major technologies are the basis for the motor concept:
The EAM shall be competitive on the world market in terms of form, fit function and costs. Therefore, the dominating requirements for the development are:
The European Apogee Motor (EAM) is a high performance bi-propellant engine operating with the propellants MMH (Monomethyl Hydrazine) and MON (Mixed Oxides of Nitrogen) for use in the Chemical Propulsion System (CPS) of a large satellite platform as well as in existing propulsion systems like Alcatel's SpaceBus or Astrium's Eurostar platform or others.
|The Fuel and Oxidizer valves are mounted perpendicular to the axial direction optimized for minimum motor overall length, small dribble volume and maximum performance. The valves are mounted on the injector housing with an angle of 120º to each other to enable proper mounting of the motor to the S/C. The interface from EAM to S/C is realized by three attachment points with alignment capabilities.|
A heat shield configuration can be mounted to the injector housing, if required. The atomization is achieved through a Micro Showerhead injector delivering the appropriate droplet size for effective and stable combustion over a large EAM operation box.
All parts in contact with the propellants are manufactured from stainless steel (valves), titanium (injector) and ceramic material (chamber and nozzle). The combustion chamber and expansion nozzle must withstand the maximum temperatures of combustion and the vibration loads during launch with sufficient marg
The development logic follows ESA's SOW:
The EAM Phase 1 activities were completed by end of March 2004 resulting in the establishment the EAM requirements.