Oxidizer-rich liquid monopropellants for a dual mode chemical rocket engine

Abstract

The subject invention relates to oxidizer-rich liquid monopropellants based on ADN or HAN for a dual mode bipropellant chemical rocket engine. Such engines may be part of propulsion systems to be used in aerospace applications for 1) orbit raising, orbit manoeuvres and maintenance, attitude control and deorbiting of spacecraft, and / or 2) propellant settling, attitude and roll control of missiles, launchers and space planes.

Description

FIELD OF THE INVENTION[0001]The subject invention relates to oxidizer-rich liquid monopropellants based on ADN or HAN for a dual mode bipropellant chemical rocket engine. Such engines may be part of propulsion systems to be used in aerospace applications for 1) orbit raising, orbit manoeuvres and maintenance, attitude control and deorbiting of spacecraft, and / or 2) propellant settling, attitude and roll control of missiles, launchers and space planes.BACKGROUND OF THE INVENTION[0002]Dual mode rocket propulsion systems and dual mode rocket engines (also referred to as thrusters) are known in the art. Currently, many spacecraft use dual-mode propulsion systems, with bipropellant engines for larger thrust operations, and monopropellant engines for smaller thrust or when minimum impulse bit is important. In the art the choice of propellants which are suitable in both bipropellant and monopropellant engines are limited to a few very hazardous propellants. Such bipropellants comprise hydr...

AI Technical Summary

Benefits of technology

The invention is about a new type of oxidizer-rich liquid monopropellant that can be used in a rocket engine to produce thrust. This monopropellant can be combined with existing fuel-rich liquid monopropellants to improve their performance. The use of this new monopropellant will reduce the hazard and environmental impact of current propellants, making it a safer and more environmentally friendly option for chemical rocket engines. The new monopropellant does not require a catalyst bed for its decomposition, which makes it easier to use in existing systems. Overall, this invention provides a way to achieve comparable performance with more environmentally benign and safe propellants.

Problems solved by technology

In the art the choice of propellants which are suitable in both bipropellant and monopropellant engines are limited to a few very hazardous propellants.

Both hydrazine (fuel) and nitrogen tetroxide (oxidizer), and their derivatives are extremely hazardous for humans as they are highly toxic, carcinogenic, corrosive, etc., and they are associated with significant concerns regarding the severe impact on the environment that they can cause in the case of spillage and emissions Therefore, the handling thereof and the safety requirements are extremely demanding, time consuming and costly.

Accordingly, it is therefore desirable to provide a propellant enabling a dual mode propulsion system avoiding the use of hydrazine, nitrogen tetroxide, and derivatives thereof However, so far, no viable rocket propulsion systems, rocket engines, and corresponding alternative propellants with performance comparable to the prior art hazardous hydrazine propellants have been realized.

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