ESA Intended Invitation To Tender


AO Number: 1-9565
Program ref.: GSTP Element 1 Dev
Tender Type: C
Tender Status: ISSUED
Price Range: > 500 KEURO
Budget Ref.: E/0904-611 - GSTP Element 1 Dev
Proc. Prop.: YIPC
Special Prov.: NO+FI
Establishment: ESTEC
Directorate: Directorate of Tech, Eng. & Quality
Department: Electrical Department
Division: Data Syst & Microelectronics Division
Contract Officer: Casini, Gian Lorenzo
Products: Satellites & Probes / On-board Data Management / On Board Data Management / Remote Terminal Units
Technology Domains: Onboard Data Systems / Onboard Data Management / Onboard Networks and Control/Monitoring
Industrial Policy Measure: N/A - Not apply
Publication Date: 17-SEP-18

This activity shall develop a Payload Interface Data Handling Unit (PIDHU) for SWE hosted payloads which shall provide power supplies at various voltages required by space weather/environment instruments limiting the mass required for individual instrument voltage transformers. The PIDHU shall receive data streams from instruments through various protocols including UART (RS-422/485), SpaceWire, MIL-STD-1553 and CAN Bus and provide data though a single data interface adaptable to hosting spacecraft requirements. As an option, the PIDHU will include on-board data processing and storage capabilities to reduce the data bandwidth required and therefore increasing the volume of useable, processed data to be downlinked. As a further option, the system will include an interface to a dedicated transmitter allowing for independent downlink of data to a SSA or other ground stations. The design phase shall also consider the desired compatibility with a SmallSat mission which is currently under study. The mass, volume and power requirement of such an PIDHU will depend strongly on the number of instruments to be supported, the ratio of the power conversion needed and the amount of on-board processing capability required. The baseline PIDHU to support more than 5 instruments and convert power from a 28 V (TBC) supply shall have a mass less than 2 kg and a volume envelope of less than 200 x 200 x 200 mm, which can be traded versus recurrent costs versus a modular building blocks approach. The power required by the instruments will be further investigated during the design phase of the study. A proto-flight model of the PIDHU shall be built to conform to the requirements of an identified flight opportunity to test a selection of space weather/environment instruments presently under development. This proto-flight model shall undergo standard space environment tests and end-to-end qualification tests with the instruments identified as part of the payload.