The Spacecraft Mass Dummy (S-MD) is designed to be used for AIT (Assembly, Integration and Testing) activities within the frame of the Galileo G2 Satellites Batch 1 program.
The SDM is intended to represent the spacecraft mass and interface conditions during integration and testing operations, ensuring proper simulation of load and Centre of Gravity (CoG) requirements.
Structure and Interfaces
The SDM is constituted by a steel frame equipped with S/C interface brackets on the upper and lower sides of the structure.
The Interfaces (IFs) are realized by means of brackets bolted to the frame. In addition, Saver IFs, reproducing the S/C Saver IFs, are foreseen for the SDM in order to ensure accurate interface representativity.
Along the beams composing the frame, different holes are foreseen to allow installation of movable masses in various positions.
Configurations
The SDM is reconfigurable in two different configurations:
- SWL Configuration – composed of the frame, movable masses and IFs;
- PROOF Configuration – obtained by connecting square tubes to the frame by means of bolts.
This reconfigurability allows the SMD to simulate both Safe Working Load and Proof Load conditions as required by the test campaign.
Load Mass and Centre of Gravity
The SDM is designed to envelop the following loads:
- MSWL = 2300 kg @ h = 1376.4 mm, CoG out-of-plane in S/C coordinate system
- MPROOF = 4600 kg @ h = 1376.4 mm, CoG out-of-plane in S/C coordinate system
Several movable masses are foreseen in the design in order to reach the requested CoG position, ensuring accurate mass distribution and compliance with spacecraft requirements.
