Abstract: A tank suitable for containing cryogenic propellant includes an inner liner structure comprised of two layers forming a gap. An intermediary layer comprised of micro-particles is disposed in the gap formed between the two layers of the inner liner structure. A structural overwrap layer covers the inner liner structure in a manner that enables the inner liner structure to float within the structural overwrap layer. The inner floating liner structure can be formed by two thin interlocking (outer and inner) shell s formed in a cylindrical, end dome geometry. The inner and outer shells are both sectioned beyond the tank midpoints. The micro-particles can be comprised of PTFE. An outer structural overwrap comprised of graphite/epoxy covers the double shell liner. A pair of separately fabricated polar bosses seal against the inner of the two interlocking floating liner shells are then each bonded to the tank, fittings, and piping.

Abstract: An airborne pneumatic launch tube ejection system to described for launching an aerospace vehicle/payload into orbit. The system can be installed in a jet transport aircraft without requiring structural modifications.

Abstract: A HAN TEAN mixing gas generator pressurization system is proposed for use on pressure-fed rockets. HAN (hydroxyl ammonium nitrate) and TEAN (triethanol ammonium nitrate) are salts dissolved in water to form a single liquid propellant. Combustion of HAN TEAN results in water, carbon dioxide, and nitrogen at high temperatures and pressures. A cryogenic primary working fluid is mixed the HAN TEAN exhaust products to provide warm high-pressure gas to pressurize the rocket's main propellant tanks.