Abstract: The present invention comprises a distributed system for providing warm, high pressure gas that is lighter weight, lower cost, and more reliable than comparable currant art pressurization systems. The invention employs Tridyne or another non-explosive but combustible pressurant mix flowing through a plurality of catalytic devices to provide heated pressurant to both the needed rocket system applications as well as to the plurality of pressurant storage bottles, thereby decreasing the mass of the unused pressurant at the end of mission.

Abstract: A Fluid Injection System for rocket engines is disclosed, which comprises methods and apparatus for combining a ring-type rocket injector body and face into a single cast part, eliminating all subassemblies, their associated fabrication and integration costs, and thereby significantly lowering injector costs while increasing injector quality and reliability. The injectors may be used in rocket engines and auxiliary propulsion devices such as gas generators for a variety of applications including rockets, missiles, space launch vehicles, space vehicles, and Lunar, asteroid, and Mars lander vehicles.

Abstract: An Aerospace Manufacturing System is disclosed, which comprises methods and apparatus for reducing the manufacturing costs in an aerospace product. In one embodiment, this method is accomplished by designing the aerospace product to use non-aerospace industry components and by maximizing the use of said plurality of readily commercially available, non-aerospace industry components. These commercially available, non-aerospace components are sometimes referred to by the term “commercial off the shelf” or “COTS” products.

Abstract: Methods and apparatus for providing a Two-Stage Ignition System are disclosed. In one embodiment of the invention, a pilot stage (16) is employed to ignite a plurality of propellants (12, 14) and to create a pilot flame (22). The plurality of propellants (12, 14) are ignited in the main combustion stage (24) using the pilot flame (22), and a flow of an elevated temperature combustion product (30) is produced.