• Development of metallic panel attachments should be enhanced, and more-operable attachment mechanisms for the shuttle-improved TPS should be investigated to ensure easy replacement. The metallic and ceramic-matrix composite standoff panels should be tested in arc jets to demonstrate that there is no overheating at the attachment points.

• Methods for waterproofing need to be pursued vigorously if reasonable ground-processing times are to be achieved.

• Permissible rates of heat leakage into LH₂ and LOX propellants should be established for normal and subcooled propellants.

1. Rockwell International Corporation. 1995. Space Shuttle Orbiter Thermal Protection System Processing Assessment: Final Report. Space Systems Division, Report SSD95D0250. Downey, California: Rockwell International Corporation.

2. Strauss, Eric L. 1989. Definition of TPS Concepts for the Advanced Launch System. Report ALS-424. Denver, Colorado: Martin Marietta Astronautics.

3. National Research Council. 1995. Orbital Debris: A Technical Assessment. Committee on Space Debris, Aeronautics and Space Engineering Board. Washington, D.C.: National Academy Press.