Abstract: A method of joining a ceramic matrix composite rocket nozzle to a metal manifold is provided, wherein a silicon nitride insert is disposed inside the ceramic matrix composite rocket nozzle and the metal manifold to provide a joint therebetween. The silicon nitride insert is preferably co-processed with the ceramic matrix composite rocket nozzle such that the ceramic matrix provides a bond between the rocket nozzle and the insert. The metal manifold is then secured to the silicon nitride insert, preferably using brazing, to form a joint assembly.

Abstract: A method of joining a ceramic matrix composite rocket nozzle to a metal manifold is provided, wherein a silicon nitride insert is disposed inside the ceramic matrix composite rocket nozzle and the metal manifold to provide a joint therebetween. The silicon nitride insert is preferably co-processed with the ceramic matrix composite rocket nozzle such that the ceramic matrix provides a bond between the rocket nozzle and the insert. The metal manifold is then secured to the silicon nitride insert, preferably using brazing, to form a joint assembly.

Abstract: A woven preform for a ceramic composite has a plurality of layers and structural members. The plurality of layer are of woven yarns of fibrous material. The structural members extend between the layers. The layers and members define interlayer spaces. One or more of the layers may have a plurality of openings extending therethrough. Low density ceramic insulation made be deposited in the interlayer spaces via a slurry that enters the preform, or the preform after it has been made a part of a composite, through the openings. The carrier of the slurry exits the preform, leaving the randomly packed fibers in the interlayer spaces. The structural members may be walls that, along with the layers, define channels. The channels may be used to direct fluid through so as the composite functions as an insulator. The channels may be directed in the warp direction for achieving increased benefits.