Patent ID: 9694916
Date: 2017-07-04
CPC Classifications: B64D,B64G

Claim:
1. A payload delivery system to deliver a passive payload, of radioactive waste, from the Earth's surface by propelling said payload in excess of the Earth's escape velocity to allow capture by the Sun's gravitational force, said payload delivery system comprising: A. one or more rocket systems, wherein each of said one or more rocket systems is a two-stage rocket system, wherein said first stage includes a rocket main propulsive engine and propellant; and B. said two-stage rocket system including a decomposition device; C. a final stage of said two-stage rocket system, wherein said final stage includes both a pneumatic cannon and a hybrid rocket main propulsive engine, said hybrid engine including a solid propellant fuel and a single liquid propellant of hydrogen peroxide; D. wherein said single liquid propellant of hydrogen peroxide is a source both for propellant for said final stage and also oxidizer for said single hybrid rocket main propulsive engine; wherein further said single liquid propellant is utilized to generate ullage pressurant as energy for all required pump and control thruster operation of said final stage; and ullage pressurant is a sole source for pressurizing said single liquid propellant; E. wherein said decomposition device decomposes said single liquid propellant to generate ullage pressurant during operation of said single hybrid rocket main propulsive engine; and F. a aircraft operable to fly, wherein said aircraft: includes at least one air-breathing engine for propulsion, and is operable to carry said one or more rocket systems; and G. said payload delivery system comprising further limitations wherein: