499 According to what is established in the standard, this value cannot exceed 1e-8 A/cm2 (28 ECSS-E-ST20-06C page 28). Thus we demonstrated that the material is fit for purpose in space, as it easily meets  the requirements of the standard.   Mechanical, Electrical and Thermal Interfaces 

Before describing the final design and its features, we would like to explain all the interfaces found on the  device as we believe it is important to know about them in order to understand the characteristics of the design.  This project is characterised by the number of factors that must be taken into account during the design and dimensioning tasks. The wish to make a system with such strict requirements and objectives, one which is also totally modular and independent from the structure itself, means that there are numerous conditioning factors caused by local conflicts between the various elements in the assembly. We have decided to call these conflicts “interfaces”, of which there are three kinds:   Mechanical Interfaces. These are all the relationships, contacts, and dependences of the  distinct parts in the device that are mechanical in nature.  o The most obvious ones are those generated between the deployment device and the  shielding onto which it is installed, and that between the shielding and the frame. The latter is the simplest and consists of 4 countersunk M3 drill holes, whereas the former is the most complex of all the faces of the Xatcobeo, the reasons for which are given below:   Attachment of the sub-chassis. There are 4 holes through which the bolts  should pass to attach the sub-chassis to the shielding. These are M2 pass through holes.    Antenna connection. One of the most conflictive points on the assembly and  easily the one that took up the most design, verification and redesign time during the whole project.   o At this point is the mechanical interface between the sub-chassis and the shielding,  formed by 4 holes through which a part of the polymeric piece can pass towards the inside of the satellite.  o There is a further mechanical interface between the connection cable and the holding  bolt for the antenna, which had to be taken into account so that the traction from bolt tightening did not break the conection wire.   o Between the connection cable and the insulation protruding from the sub-chassis.  This protruding piece is designed to fit the coaxial's inner insulation and thus eliminate mechanical stresses on the conection wire.  o Between the cable's coaxial mesh and the joint between sub-chassis and shielding.  This interface gave the integration problems described later.  o Finally, there is a less noticeable interface made up by the sub-chassis and its parts  that protrude towards the internal face of the satellite and the structure frame.   There are other mechanical interfaces that do not directly involve the  deployment device but which take place in the shielding, such as the microHDMI connection and the RBF bolt.  o The following mechanical interface is made up of the antennas and the shielding and  that generated in the joint attachment of the antenna and polymeric enveloping film.   It is formed by the antenna itself, the bolt that enables attachment and the  sub-chassis, with the antenna connection wire in the middle.  o The interface between the polymeric film and the antennas. These can be divide into  two, as follows:   Whilst the antennas are folded