High energy solid propellant

Abstract

The present invention provides a high energy solid propellant containing an oxidizer, binder and fuel, wherein the fuel and / or the propellant as a whole is encapsulated or microencapsulated so as prevent premature reaction while still maintaining the energetic properties thereof. The oxidizer is preferably ammonium perchlorate, ammonium nitrate or ammonium dinitramide. The binder is preferably polymeric hydrocarbons or polymers. The fuel is preferably lithium hexahydridoborane or lithium hexahydridoalane.

Description

FIELD OF THE INVENTION [0001] The present invention provides a solid propellant for use in rocket engines. In particular, the present invention provides a high energy solid propellant comprised of an oxidizer, fuel and binder, wherein the fuel is encapsulated or microencapsulated. This encapsulation or microencapsulation allows for use of a highly energetic fuel component, while avoiding uncontrollable reactivity, and provides a propellant having an exceptionally high specific impulse. BACKGROUND OF THE INVENTION [0002] A solid propellant is conventionally comprised of an oxidizer, fuel and a binder. Generally, in a solid propellant comprised of 72% oxidizer, 16% fuel and 12% binder, an Isp of around 272 seconds is common. Conventionally, solid propellant binders, such as PBAN (polybutadiene acrylonitrile copolymer) have been used, as well as HTPB (hydroxyl-terminated polybutadiene). [0003] A significant problem with conventional solid propellants is the phenomena of two-phase flow....

AI Technical Summary

Benefits of technology

[0010] In a second embodiment, a high energy solid propellant according to the first embodiment above is provided, wherein the binder is PDCPD (polydicyclopentadiene), polyethylene, polystyrene, or low molecular weight polyethylene.

[0011] In a third embodiment, a high energy solid propellant according to the first embodiment above is provided, wherein the fuel is comprised of lithium hexahydridoborane and aluminum, or LHA (lithium hexahydridoalane) and aluminum.

[0012] In a fourth embodiment, a high energy solid propellant according to the second embodiment above is provided, wherein fuel is comprised of lithium hexahydridoborane and aluminum, or LHA (lithium hexahyd

Problems solved by technology

A significant problem with conventional solid propellants is the phenomena of two-phase flow.

However, the kinetics of the rocket combustion process can lead to liquid, unreacted aluminum emerging from the nozzle with a commensurate decrease in thrust.

Again, the energy gain is lost by the subsequent “after-burning”.