The Boeing Company

Xavier D Simon

Victor John Barackman

Michael J Robinson

Thomas L Andrews

John K Pulley

Sandra D McKee

The thermal protection system disclosed herein is suitable for use with a spacecraft such as a reentry module or vehicle, where the spacecraft has a convex surface to be protected. An embodiment of the thermal protection system includes a plurality of heat resistant panels, each having an outer surface configured for exposure to atmosphere, an inner surface opposite the outer surface and configured for attachment to the convex surface of the spacecraft, and a joint edge defined between the outer surface and the inner surface. The joint edges of adjacent ones of the heat resistant panels are configured to mate with each other to form staggered joints that run between the peak of the convex surface and the base section of the convex surface.

Thermal protection system with staggered joints

A spacecraft pressure vessel has a tub member. A sidewall member is coupled to the tub member so that a bottom section of the sidewall member extends from an attachment intersection with the tub member and away from the tub member. The bottom section of the sidewall member receives and transfers a load through the sidewall member.

Pressure vessel having continuous sidewall

A two-part seat () providing full body support that is specific for each crew member () on an individual basis. The two-part construction for the seat () can accommodate many sizes and shapes for crewmembers () because it is reconfigurable and therefore reusable for subsequent flights. The first component of the two-part seat construction is a composite shell () that surrounds the crewmember's entire body and is generically fitted to their general size in height and weight. The second component of the two-part seat () is a cushion () that conforms exactly to the specific crewmember's entire body and gives total body support in more complex environment.

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Aliso Viejo, CA, United States of America

Xavier D Simon