Dual mode chemical rocket engine and dual mode propulsion system comprising the rocket engine
AssigneeEcaps AB
InventorsGöran Bergman, Kjell Anflo
Life of this patent
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Abstract
The invention relates generally to dual mode bipropellant chemical rocket propulsion systems to be used in aerospace applications for 1) orbit raising, orbit maneuvers and maintenance, attitude control and deorbiting of spacecraft, and/or 2) propellant settling, attitude and roll control of missiles, launchers and space planes. The present invention also relates to a dual mode chemical rocket engine for use in such systems. The engine uses low-hazardous storable liquid propellants and can be operated either in monopropellant mode or in bipropellant mode. The monopropellants used are a low-hazard liquid fuel-rich monopropellant, and a low-hazard liquid oxidizer-rich monopropellant, respectively.
Claims5
A dual mode chemical rocket engine comprising:
- one or more first primary reaction chambers (130) for a liquid fuel-rich monopropellant and comprising a catalyst bed for the fuel-rich monopropellant,
- one or more second primary reaction chambers (140) in parallel arrangement to said one or more first primary reaction chambers (130) for an oxidizer-rich monopropellant and comprising a catalyst for the oxidizer-rich monopropellant;
- and
- a secondary reaction chamber (150) connected to said first and second primary reaction chambers (130, 140), and having a passageway for injection (125) therein of a second oxidizer-rich monopropellant;
- wherein said fuel-rich monopropellant is Ammonium DiNitramide (ADN) based or Hydroxyl Ammonium Nitrate (HAN) based.
Dependencies are inferred from the claim text.