Astrium Gmbh

Daimlerchrysler Aerospace Ag

Joerg Bolz

Ernst Hornung

Andreas Rittweger

Walter D Vogel

Huba Ory

Ulrich Rieck

Wolff-Dieter Ebeling

Peter Borgwardt

Wolfgang Fischer

Markus Quadt

A thermal protection system suitable as a heat shield for a space vehicle includes a flexible insulation mat that is adhesively bonded onto the outer skin of the space vehicle, a cover layer made of at least one ply of a ceramic fiber composite material secured onto the insulation mat, and a coating of an inorganic material applied onto an outer surface of the ceramic cover layer. The cover layer is secured to the insulation mat by adhesive bonding, stitching with ceramic threads or the like, or by a snap fastener button connection. The ceramic fiber composite materials of the cover layer include inorganic fibers which are preferably oxides, carbides or mixtures thereof embedded in a matrix of the same compositional components, whereby the components can be selected appropriately depending on the requirements of the particular application. The overall thermal protection system remains flexible, lightweight, and highly effective for thermal shielding, so that it may be used not only on the relatively cooler portions of the space vehicle, but also on the most highly thermally loaded areas such as the nose and the leading edges of wings and the like.

Thermal protection system especially for space vehicles

An apparatus for launching and dispensing multiple satellites into orbit includes a central structure and a plurality of satellites releasably bundled around the central structure to form a cohesive, single payload mounted on an upper stage of a launcher rocket. The central structure includes a central tube and an adapter shell that fits onto the upper stage of the rocket. Each satellite has the shape of a partial cylinder segment of which an outer wall is a cylindrical segment shell. The satellites are bundled and secured together around the central structure by tension bands, whereby the cylindrical segment shells form a load-bearing complete outer cylindrical shell that surrounds the central tube. This structure provides sufficient stiffness and strength to withstand the loads that arise during launch, while having a reduced mass. The satellites themselves, rather than the central structure, bear the loads during launch. This allows the central structure to be of relatively lightweight construction.

Apparatus for launching and deploying multiple satellites

Growing community of inventors

Bremen, Germany

Joerg Bolz