Introduction

The structural elements of the space engines (satellite and probes) are subjected to strict environmental constraints. Their design as well as technologies used take into account these requirements.

Expected and forced performances

The structure is used initially as " system of rangement" for the equipment of space engine.

The principal expected performances are:

• capacity of installation necessary (surfaces of installation, not of fixing,…)
• behavior of mechanical environments during handling on the ground
• and especially during launching, the limitation of the deformations due to the elastic thermo effects.

The principal constraints related to the use in space are:

• the limitation of mass (forced by launching)

• great temperature variations seen in space
• impossibility of using certain materials (degasification, effects of radiations, the vacuum…)

Design methods

The structural design does not call upon particular techniques; the computer tools used (Grid and analyzes with the finite elements are those classically employed in the field of the resistance of materials.

Technologies

It is on the level of the technologies implemented that the space one is characterized. The first constraint of a space structure, it is its mass. One thus calls largely upon composite materials (especially containing Carbon fiber or fibers aramides. A frequently encountered difficulty is the behavior in temperature of the resins and the adhesives employed in the assembly of these material. The materials containing carbon fiber have also a great dimensional stability with the temperature variations: they largely to this end are used. One uses them in various forms: tablecloths of fabric assembled in " peaux" , bars, angles…

One also largely uses panels or tubes in technology " sandwich": a very light material (for example a lattice honeycomb aluminum) is sandwiched between two skins of aluminum or carbon fibers. This technology makes it possible to obtain compromises exceptional weights/performance. The assembly of stucturaux elements or the fixing of equipment is done with screws and bolts, by the means of inserts drowned in the mass of the panel and stuck; these inserts comprise clamp holes tapped. The sufficiently light equipment is fixed on the skins directly by rivets or joining. In addition to composite materials evoked above, the structures call upon parts out of aluminum (for its lightness) or out of titanium (low coefficient of expansion).

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