ARTES-5.1 – ESA Telecom Technology Workplan ... - Emits - ESA

Annex 2Page 232.5 Mechanical SystemRef. Activity Title Procurement Policy Budget(KEUR)4E.029(07.153.21)Objective:Description:Planned TenderIssueDevelopment of a Versatile European Eddy Current Damper Open Competitive Tender Type: C 600 Priority 2 18Estimated Duration(months)The objective is to develop, manufacture and test an Engineering Model of a European Eddy Current Damper suitable for the control and regulation of the deployment of medium sizedappendages on board small telecom platforms. The activity shall fully demonstrate the performances of the developed model in representative environment.The intended activity covers recommendations and conclusions of the harmonisation meeting on Space Mechanisms Hold Down/Separation Systems/Deployment Components held during thefirst semester 2004. The deployment of appendages like reflector antennas, radiators and solar arrays, requires regulation in order to control the dynamic of the deployment and to avoid thebuilding up of important kinetic energy. Too high kinetic energy would generate large latching shocks at the end of the deployment which would be critical for the integrity of the appendage,the platform and the AOCS. Regulation is most of the time achieved using passive damping systems which provide a constant deployment velocity. This is currently deemed as one of themost optimised/cost efficient deployment strategy. Only one space qualified damper is currently available in Europe and it is limited in performances. Most of the eddy current dampers usedon European spacecraft are from the US.The proposed activity is to develop a European Rotary Eddy Current Damper. Eddy Current Dampers are based on static magnets providing a constant and uniform magnetic field. Rotation ofa disk in the field produces a generated voltage in the disk. This voltage develops circulating currents (Eddy Currents) within the disk, which results in a restraining torque proportional tovelocity. The drag torque created is a linear function of the rotational speed of the disk. The main advantages of this reliable technology is unlimited rotation range, high temperatureoperational range, no degradation of performances versus temperature, no issues of contamination, high configurability with respect to deployment torque and velocity, and very highupgrading capabilities to achieve active damping when deemed necessary. The targeted application is the Small GEO spacecraft for which cost and mass efficiency are mandatory and ITARregulation is an issue.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.Ref. Activity Title Procurement Policy Budget(KEUR)4E.031(08.153.44)Objective:Description:Planned TenderIssueFriction Less lateral deployment hinge Open Competitive Tender Type: C 330 Priority 2 18Estimated Duration(months)To develop, manufacture and test an Engineering Model of Friction Less Deployment Hinge following promising work performed during an ESA ITI Contract. The demonstration ofperformance will be achieved through representative testing of an Engineering Model.Lateral deployment of Telecom spacecraft solar array panels is presently achieved by making use of standard in-line hinges or very low friction torque hinges that are rather complex andheavy.The innovative proposed concept, which feasibility was demonstrated in the frame of an ITI contract, will be fully demonstrated through a complete design documentation as well as the builtand test of an Engineering Model. By concept, this new generation of hinge is not prone to any wear or ageing and will then by concept simplify the solar array verification sequence as theground testing of lateral deployment will be required.NOTE: This activity has been designated as "Priority 2". Priority 2 activities will only be initiated on the explicit request of at least one delegation.