ESA Open Invitation to Tender AO9890
Open Date: 13/09/2019
Closing Date: 25/10/2019 13:00:00

Status: ISSUED
Reference Nr.: 19.1QQ.02
Prog. Ref.: Technology Developme
Budget Ref.: E/0901-01 – Technology Developme
Special Prov.: BE+DK+FR+DE+IT+NL+ES+SE+CH+GB+IE+AT+NO+FI+PT+GR+LU+CZ+RO+PL+EE+HU
Tender Type: C
Price Range: 200-500 KEURO
Products: Satellites & Probes / System Engineering Software / Dependability, Safety and Quality tools / RAMS, FMECA, … / Ground Segment / Mission Operations / Operations Execution / Configuration management, FOP tools, On-board resource checker, …
Technology Domains: Quality, Dependability and Safety / System Dependability and Safety / Dependability and Safety Methods & Tools
Establishment: ESTEC
Directorate: Directorate of Tech, Eng. & Quality
Department: Product Assurance and Safety Department
Division: Quality, Dependability and PA Support Di
Contract Officer: Reinsoo, Anna
Industrial Policy Measure: N/A – Not apply
Last Update Date: 13/09/2019
Update Reason: Tender issue

Objectives of the activity: Reliability of End of Life operations is becoming a driver requirement for the design of future satellites, with an absolute value of reliability starting to be specified by international and national regulations and guidelines. Currently the lifetimeestimates for initiating the End-of-Life operations or to decide for mission extensions are mainly driven by consumables. There is an urgent need for more accurate quantitative reliability-based lifetime assessments. These estimations and must be validated by test and in-orbit experience data to prevent in-orbit satellite failures allowing at the same time to maximize return oninvestment. Furthermore, it will support other operations that have a growing market application such as constellation replenishment, launch date planning, etc.The lifetime prediction model shall take into account wear out mechanisms impacted by environmental stresses (e.g. Radiation) or use conditions (e.g. Thermal and power cycles), limited resources (e.g. Propellant, power degradation over time), and the minimum configuration needed for disposal. This activity encompasses the following tasks: Model unit degradation using test-based, model-based, stochastic and data trend analyses Validation through test at unit level and reference cases with in-orbit experience data Integration in system level proof-of-concept representative of different mission classes Derive guidelines for reliability driven design, health monitoring, operational approach, etc.