| 摘要 |
The present invention is related to an improved thermal insulation of an exhaust tube (6) for use in a rocket engine. The thermal insulation is provided for as a layered structure wherein respective layers comprises a composite material, and wherein dominant directions of fibres in respective adjacent layers are different with respect to each other. In addition, a flexible layer might be used to attach the thermal insulation to an inner wall of the exhaust tube (6).
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