Class / Patent application number | Description | Number of patent applications / Date published |
060251000 | Solid and fluid propellant | 11 |
20090139204 | Hybrid Rocket System - The present invention describes a hybrid rocket motor that includes a first solid reactant and at least one thrust nozzle and at least one moveable combustion control member within the hybrid rocket motor that restricts the contact of a first fluid reactant in the combustion chamber. In this way, it is then possible to regulate the exposure of the solid reactant to the fluid reactant and thus control thrust. | 06-04-2009 |
20090211226 | HYBRID ROCKET MOTOR WITH ANNULAR, CONCENTRIC SOLID FUEL ELEMENTS - A hybrid rocket motor includes 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. | 08-27-2009 |
20090217642 | Radial flow stereolithographic rocket motor - A hybrid rocket motor is manufactured by photopolymerizing the solid fuel grain in a stereolithography method, wherein fuel grains in a plastic matrix are deposited in layers for building a solid fuel rocket body in three dimensions for improved performance and for a compact design, the hybrid rocket motor including radial channels for defining a desired burn profile including the oxidizer to fuel burn ratio. | 09-03-2009 |
20110167793 | HYBRID ROCKET USING CATALYTIC DECOMPOSITION OF OXIDIZER - Provided is a hybrid rocket using catalytic decomposition of oxidizer, which generates thrust by injecting high temperature oxygen and steam formed by catalytic decomposing liquid oxidizer into solid fuel and thereby auto igniting and combusting the solid fuel without a separate igniter. The hybrid rocket using catalytic decomposition of an oxidizer, including: a liquid phase oxidizer ( | 07-14-2011 |
20110203256 | MOTOR - The present invention provides a motor including a combustion chamber, an oxidizer injector, a vortex generators and a nozzle. The combustion chamber can be used to dispose a solid fuel, and the oxidizer injector is used to control the flow rate of an oxidizer and to inject the oxidizer into the combustion chamber. The vortex generators is disposed on the inner wall of the combustion chamber for generating eddies to enhance the mixing of the fuel and the oxidizer. Additionally, the nozzle is connected with the combustion chamber for exhausting the gas generated by the combustion of the propellants. | 08-25-2011 |
20110314790 | HYBRID PROPULSION SYSTEM - Disclosed is a propulsion system having a structural configuration that provides easy and convenient access to the interior regions of a liquid fuel tank and a hybrid rocket motor case. In one embodiment, the propulsion system comprises: a hybrid rocket motor case and a fuel tank coupled to the hybrid motor case. The motor case is configured to hold solid rocket fuel and the fuel tank defines an internal volume configured to hold a fluid oxidizer. A bulkhead is interposed between the motor case and the fuel tank, wherein at least one access passageway extends through the bulkhead. The access passageway provides exterior access to the interior volume of the motor case or the internal volume of the storage tank while the hybrid rocket motor is coupled to the fuel tank. | 12-29-2011 |
20130305687 | Thruster and Spacecraft - A thruster designed to produce thrust by introducing a propellant to a catalyst layer from a propellant valve via a propellant introduction member and spurting out a gas resulting from decomposition of the propellant occurring on the catalyst layer, wherein the thruster comprises a chamber of an Ni alloy for holding the catalyst layer inside, the propellant introduction member is made of an Ni alloy and connects the propellant valve and the chamber, and a propellant valve flange of a Ti alloy with a plurality of columns of a Ti alloy is arranged between the chamber and the propellant valve to support the chamber by the columns. | 11-21-2013 |
20140026537 | Multiple Use Hybrid Rocket Motor - The Multiple Use Plug Hybrid (for) Nanosats (“MUPHyN”) prototype thruster is being developed to fill a niche application for NanoSat scale spacecraft propulsion. The MUPHyN thruster uses safe-handling and inexpensive nitrous oxide (N | 01-30-2014 |
20140083081 | ROCKET ENGINE SYSTEMS - The present invention relates to improved rocket engine systems. In one embodiment, an improved rocket engine system includes a propellant source, at least one power source, at least one power source motor, a rocket engine, and at least one pump. The improved rocket engine system may further include at least one of the following: at least one controller, at least one propellant valve, and a propellant pressurizing source. | 03-27-2014 |
20150322892 | Restartable Ignition Devices, Systems, and Methods Thereof - Devices, methods, and systems for providing a restartable ignition system for a hybrid rocket system. In one embodiment, an ignition device includes a housing and at least two electrodes. The housing includes a first side and a second side and defines a bore with an axis extending therethrough between the first and second sides, the bore defining an internal surface of the housing. The at least two electrodes extend through the housing to the internal surface. The at least two electrodes are configured to be spaced apart so as to provide an electrical potential field along the internal surface between the at least two electrodes. Such housing is formed with and includes multiple flat layers such that the multiple flat layers provide ridges along the internal surface. With this arrangement, the internal surface with the ridges are configured to concentrate an electrical charge upon being subjected to the electrical potential field. | 11-12-2015 |
20170234268 | HYBRID ROCKET MOTOR WITH INTEGRAL OXIDIZER TANK | 08-17-2017 |