Patents Assigned to SpaceDev, Inc.
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Patent number: 8539753Abstract: 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.Type: GrantFiled: June 18, 2007Date of Patent: September 24, 2013Assignee: SpaceDev, Inc.Inventor: Frank Macklin
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Patent number: 8140198Abstract: A method is adapted for slewing a body from an initial state to merge with a desired state profile. In an embodiment, the method includes the steps of (a) obtaining data indicative of a time profile of desired future states for the body; (b) searching sequentially through the time profile of desired future states; (c) calculating several slews for the body from the initial state to each of the desired future states; (d) determining the earliest future state to which the body can actually slew; (e) choosing the minimum-energy slew to that state; and (f) causing the body to perform that chosen slew.Type: GrantFiled: November 2, 2007Date of Patent: March 20, 2012Assignee: Spacedev, Inc.Inventor: Jesse D. Koenig
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Patent number: 8099945Abstract: 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.Type: GrantFiled: March 16, 2009Date of Patent: January 24, 2012Assignee: Spacedev, Inc.Inventors: Frank Macklin, Chris Grainger
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Patent number: 7966809Abstract: A hybrid rocket motor is formed from a single piece of material, such as, for example, by extrusion or injection molding. The rocket motor includes various components, such as casing, structure, oxidizer tank, combustion chamber, fuel, port and nozzle that are all formed from a single piece of material. The material can be, for example, a material that can be used as solid rocket fuel.Type: GrantFiled: January 30, 2007Date of Patent: June 28, 2011Assignee: Spacedev, Inc.Inventor: Jim Benson
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Patent number: 7795566Abstract: Systems and methods for are adapted for automatic implementation of exclusion zone avoidance for target-tracking vehicles, such as spacecraft. The systems and methods are configured to monitor pointing commands (commanded attitude and angular rates) generated for target tracking, and modify these commands as necessary to avoid pointing a boresight into an exclusion zone.Type: GrantFiled: March 27, 2008Date of Patent: September 14, 2010Assignee: SpaceDev, Inc.Inventor: Jesse D. Koenig
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Patent number: 7503165Abstract: 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.Type: GrantFiled: February 1, 2005Date of Patent: March 17, 2009Assignee: SpaceDev, Inc.Inventors: Frank MacKlin, Chris Grainger
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Patent number: 7404288Abstract: 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. The system operates with a high oxidizer-to-fuel ratio and a high bulk density propellant combination that has a near uniform specific impulse over a large oxidizer-to-fuel ratio range. The system has an increased propellant mass fraction and reduced propellant residuals. This improves the performance of the hybrid propulsion system.Type: GrantFiled: October 28, 2005Date of Patent: July 29, 2008Assignee: SpaceDev, Inc.Inventors: Marti Sarigul-Klijn, Nesrin Sarigul-Klijn, Jim Benson, Grant Williams, Frank Macklin
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Patent number: 7069717Abstract: Disclosed is a propulsion system for a spacecraft. The propulsion system includes a supply of oxidizer and at least one nozzle. A conduit fluidly couples the supply of oxidizer and the nozzle. The conduit provides a pathway for oxidizer to flow in a downstream direction from the supply of oxidizer toward and into the nozzle. A pressure regulator is coupled to the conduit and is interposed between the supply of oxidizer and the nozzle, wherein the pressure regulator regulates the pressure of oxidizer flowing through the conduit and downstream of the pressure regulator to a pressure at or below the pressure required to maintain the oxidizer in a gas state to ensure that the any oxidizer flowing through the conduit is in a gas state prior to entering the nozzle. The conduit supplies oxidizer from the supply of oxidizer to a hybrid rocket motor.Type: GrantFiled: April 15, 2004Date of Patent: July 4, 2006Assignee: SpaceDev, Inc.Inventors: Chris Grainger, Frank Macklin