29, June 2018

ESA Open Invitation to Tender AO9304
Open Date: 26/06/2018
Closing Date: 28/09/2018 13:00:00

Status: ISSUED
Reference Nr.: 18.1EP.01
Prog. Ref.: GSTP Element 1 Dev
Budget Ref.: E/0904-611 – GSTP Element 1 Dev
Special Prov.: BE+DE+CH
Tender Type: C
Price Range: > 500 KEURO
Products: Satellites & Probes / Electronics / EEE Components / Monolithic Microcircuits (including MMICs) / Satellites & Probes / Electronics / EEE Components / Hybrid circuits / Satellites & Probes / Power / Power Monitoring and Control – BB / Other
Techology Domains: Spacecraft Electrical Power / Power Conditioning and Distribution / Power Conditioning
Establishment: ESTEC
Directorate: Directorate of Tech, Eng. & Quality
Department: Electrical Engineering Department
Division: Power & Energy Conversion Division
Contract Officer: Ferreol, Audrey
Industrial Policy Measure: N/A – Not apply
Last Update Date: 26/06/2018
Update Reason: Tender issue

The activity aims at developing an IC that includes the power switch, the driver, the oscillator, a simple PWM, an Op-Amp for the control loop and a start-up circuit. It should have a built in overcurrent protection, over temperature protection and an enable pin to turn-off the switch.In this IC, the main target is not performance but having a device to simplify as much as possible the design of simple DC-DC converters for local small power supplies, auxiliary supplies, etc. The target topology is mainly a Flyback converter. If this chip was available, it will enable the possibility of simplifying many designs by making power available where is needed. Only the magnetic component, the output diode, the output filter and the feedback network will be needed to build a power supply.As a consequence, issues like having isolated power supplies for upper side drivers, start up systems, etc will not be a problem anymore. In fact, the high compactness of the IC would allow having multiple supplies in one board if needed. This would enable more complex electrical systems with a wider supply voltage range of options.The key advantage is the ability to be connected directly tothe bus voltage and start switching immediately without external circuitry. Thus, the input voltage characteristics should be compatible with the typical bus voltage levels used in European satellites: 28 V, 50 V and 100 V.The development plan shall include: Consolidation of the set of requirements Conceptual functional block design Development of all blocks to achieve radiation tolerance Design of the prototype with all functionalities Manufacturing of a prototype Test campaignThe test campaign shall include: Functional electrical tests Thermal cycles at ambient pressure TID/SEE radiation campaign to assess the validity of the design

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