DESIGN RULES & PRODUCT ASSURANCE PROCESSES FOR FUTURE TELECOMMUNICATION SATELLITES INCLUDING MEGACONSTELLATIONS (ARTES FPE 1B.117)

Status

ISSUED

EMITS REFERENCE

Program

ARTES 1 VI

Price Range

200-500 KEURO

Description

Until recently, the telecommunication-satellite manufacturing satellite sector has been building its reputation on the paradigm of technical and industrial excellence, privileging performances, quality and reliability over cost at delivery. Newcomers competing directly with European US incumbents on the geostationary satellite market and new players developing new approaches on the LEO market segment create significant cost pressures on the European Canadian industry. There is thus a need for equipment suppliers, prime designers integrators that are market competitive, and for customers to accept solutions which meet their requirements, but leaving to the industry the flexibility to select the most appropriate approach for the design and production of their products to achieve the optimal competitiveness.

Rather than applying Design-not-to-fail scheme where significant margins have to be applied from material selections up to system margin level, a more commercially competitive approach would be to seek adaption of the system to be fault-tolerant, and to define a qualification processes and production processes guaranteeing the optimal product costs and quality reproducibility.

The objective of the activity will thus be to define the design rules, development, qualification and production processes that will permit to optimize the cost of production of telecommunication satellites. The expected outcomes will be guidelines to be disseminated to the European Canadian telecommunication satellite industry.

The following work logic is defined:

(A)Two reference mission definition scenarios will be defined

  1. A geostationary telecommunication satellite, involving both Ku and Cmissions
  2. A constellation of small satellites including 300 satellites, each with a launch mass of 300 kg, assuming a DC payloadpower of 2 kW for a life time ranging from 5 to 10 year in LEO

(B) Design rules of satellites will be assessed against the specificarchitectures of the satellites to optimize the cost and production time of these units taking into account operational requirements (e.g. de-orbiting)

(C) Part Selection, Procurement, Qualification, Validation Processes and Production processes will be defined

(D) A set of guidelines will be proposed for implementation by the European Canadian industry.

The team will be including representatives of the satellite industry (Prime, equipment suppliers for payload and platform units) as well as experts/consultants from non-space sectors that will contribute integrating their experience to the space industry.

Tender Specifics