The Boeing Company

Thomas L Andrews

Lorie R Grimes-Ledesma

Leora Peltz

Michael J Robinson

Robert V Frampton

Xavier D Simon

A first part, a second part, and a seal ring are fastened together to form a pressure structure configured for a spacecraft structure of a spacecraft, wherein the first part and the second part are each formed from a single workpiece.

Mechanically fastened large pressurized vehicle structure

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

Mechanically fastened large pressurized spacecraft structure

An integrated instrumentation system includes a body comprising a thermal protection system (TPS) material (e.g., an ablatable material), one or more sensors embedded within the body, and a processor (e.g., an FPGA or the like) communicatively coupled to the plurality of sensors. The processor is configured to acquire sensor signals from the plurality of sensors and produce digital sensor data associated therewith. The sensors may include, for example, recession sensors, pressure transducers, thermocouples, and accelerometers.

Methods and apparatus for an integrated instrumentation module for a thermal protection system

An optical fiber wound onto an exterior surface of a composite structure in a two-dimensional pattern and adhered thereto to detect damage to the structure caused by impacts to or handling of the composite structure.

Fiber optic damage detection system for composite pressure vessels

An optical fiber is wound onto an exterior surface of a composite structure in a two-dimensional pattern and adhered thereto to detect damage to the structure caused by impacts to or handling of the composite structure.

Growing community of inventors

Newport Beach, CA, United States of America

Thomas L Andrews