Patent number 8539753 is assigned to
The following quote was obtained by the news editors from the background information supplied by the inventors: "This disclosure relates to propulsion systems, and more particularly to a hybrid propulsion system.
"Liquid systems and solid systems are the two basic types of rocket propulsion systems that are most widely used in the rocket industry. In a solid propellant system, solid rocket fuel and an oxidizer are mixed together and allowed to cure inside a rocket case to form a solid propellant material, which is then ignited in the rocket case. Upon ignition, pressure forms within the rocket case and gases are released through a nozzle to produce thrust. In a solid propellant system, the solid propellant burns uninterrupted until all the propellant is exhausted, which can be undesirable in certain circumstances.
"In a liquid system, a liquid oxidizer is fed into a combustion chamber in combination with a liquid fuel. The oxidizer and liquid fuel are mixed in the combustion chamber, where they react to produce gases under high temperature and high pressure. The gases exhaust through a nozzle from the combustion chamber to thereby produce thrust. Although widely used, there are certain drawbacks associated with liquid propulsion systems.
"Another type of rocket propulsion system is the hybrid system. A hybrid system combines aspects of both liquid systems and solid systems in that one propellant is stored as a solid and another propellant is stored as a liquid. In a typical system, the solid material is used as the fuel and the liquid material is used as the oxidizer. A variety of materials can be used as the solid fuel, including Plexiglas (polymethyl methacrylate (PMMA)), high density polyethylene (HDPE), hydroxyl terminated polybutadiene (HTPB), etc. Nitrous Oxide is a commonly used as the oxidizer, although other oxidizers can be used."
In addition to the background information obtained for this patent, VerticalNews journalists also obtained the inventor's summary information for this patent: "There is currently a need for improved hybrid rocket systems. Disclosed is an improved hybrid rocket system. In one aspect, there is disclosed a hybrid rocket motor comprising a supply of oxidizer, a first solid fuel element positioned around the supply of oxidizer, a second solid fuel element positioned concentrically around the first solid fuel element, and a combustion port positioned between the first and second solid fuel elements. The oxidizer interacts with the first and second solid fuel elements within the combustion port to produce a combustion product. A nozzle is in communication with the combustion port for combustion discharge of the combustion product.
"In another aspect, there is disclosed a hybrid rocket motor, comprising a oxidizer tank containing an oxidizer, a main casing surrounding the oxidizer tank, and at least one injector adapted to inject oxidizer from the oxidizer tank into the main casing. The main casing includes a first, annular solid fuel grain; a second, annular solid fuel grain positioned concentrically around the first, annular solid fuel grain; a combustion port positioned between the first and second annular solid fuel grains wherein the oxidizer interacts with the first and second solid fuel elements within the combustion port to produce a combustion product; and a nozzle in communication with the combustion port for combustion discharge of the combustion product.
"The details of one or more embodiments are set forth in the accompanying drawings and the description below. Other features, objects, and advantages will be apparent from the description and drawings, and from the claims."
URL and more information on this patent, see: Macklin, Frank. Hybrid Rocket Motor with Annular, Concentric Solid Fuel Elements. U.S. Patent Number 8539753, filed
Keywords for this news article include: Aerospace and Defense Companies.
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