Patents by Inventor Allen Yan
Allen Yan has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20240165634Abstract: Methods, systems, and apparatus, including computer programs encoded on computer storage media, for in-process adjustment to crushing systems.Type: ApplicationFiled: November 18, 2022Publication date: May 23, 2024Inventors: Ray Jr. Anthony Nagatani, Allen Richard Zhao, Antonio Raymond Papania-Davis, Weishi Yan, Brian Howell, Jeffrey Bush, Charles Stephen Spirakis
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Publication number: 20240169030Abstract: Methods, systems, and apparatus, including computer programs encoded on computer storage media, for characterization of aggregate particles. A method includes obtaining, from a set of low fidelity sensors, first sensor data of a first portion of particles; obtaining, from a set of high fidelity sensors, second sensor data of the first portion of particles, the second sensor data comprising a higher fidelity representation of characteristics of the first portion of particles than the first sensor data; training a characterization model using the first sensor data and the second sensor data, the training comprising: providing, as training data to the characterization model, the second sensor data; and processing the second sensor data with the characterization model to correlate the first sensor data with the second sensor data. The first sensor data can indicate shape characteristics of each particle; and the second sensor data indicates a surface area of each particle.Type: ApplicationFiled: November 18, 2022Publication date: May 23, 2024Inventors: Ray Jr. Anthony Nagatani, Allen Richard Zhao, Antonio Raymond Papania-Davis, Weishi Yan, Jeffrey Bush, Charles Stephen Spirakis, Brian Howell
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Patent number: 11680543Abstract: Various implementations of an extinguishable, solid propellant divert system for a flight vehicle are disclosed. Also disclosed are methods for using the divert system to control the flight of a flight vehicle. In one implementation, a divert system includes a hot gas generator pneumatically linked to one or more divert thrusters and an extinguishment valve. The extinguishment valve can be opened to rapidly depressurize the hot gas generator and extinguish the solid propellant burning inside. In another implementation, a method of controlling the trajectory of the flight vehicle includes repeatedly igniting and extinguishing the solid propellant in a hot gas generator and using the hot gas to provide divert thrust for the flight vehicle.Type: GrantFiled: September 14, 2021Date of Patent: June 20, 2023Assignee: Valley Tech Systems, Inc.Inventors: Russell Carlson, Dustin Barr, Allen Yan, Justin Carpenter
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Patent number: 11448165Abstract: An attitude control system for a guided missile includes a gas generator, an accumulator coupled to the gas generator, and a valve positioned between the gas generator and the accumulator. The gas generator contains propellant that burns to provide hot gas to pressurize the accumulator. The valve is opened to recharge the accumulator with hot gas and closed when it is full. A vent valve can be included to extinguish the propellant in the gas generator. The accumulator can be coupled to thrusters that use the stored hot gas to adjust the attitude of the guided missile.Type: GrantFiled: March 23, 2020Date of Patent: September 20, 2022Assignee: Valley Tech Systems, Inc.Inventors: Russell Carlson, Dustin Barr, Allen Yan
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Publication number: 20210404418Abstract: Various implementations of an extinguishable, solid propellant divert system for a flight vehicle are disclosed. Also disclosed are methods for using the divert system to control the flight of a flight vehicle. In one implementation, a divert system includes a hot gas generator pneumatically linked to one or more divert thrusters and an extinguishment valve. The extinguishment valve can be opened to rapidly depressurize the hot gas generator and extinguish the solid propellant burning inside. In another implementation, a method of controlling the trajectory of the flight vehicle includes repeatedly igniting and extinguishing the solid propellant in a hot gas generator and using the hot gas to provide divert thrust for the flight vehicle.Type: ApplicationFiled: September 14, 2021Publication date: December 30, 2021Inventors: Russell Carlson, Dustin Barr, Allen Yan, Justin Carpenter
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Patent number: 11143143Abstract: Various implementations of an extinguishable, solid propellant divert system for a flight vehicle are disclosed. Also disclosed are methods for using the divert system to control the flight of a flight vehicle. In one implementation, a divert system includes a hot gas generator pneumatically linked to one or more divert thrusters and an extinguishment valve. The extinguishment valve can be opened to rapidly depressurize the hot gas generator and extinguish the solid propellant burning inside. In another implementation, a method of controlling the trajectory of the flight vehicle includes repeatedly igniting and extinguishing the solid propellant in a hot gas generator and using the hot gas to provide divert thrust for the flight vehicle.Type: GrantFiled: May 13, 2019Date of Patent: October 12, 2021Assignee: Valley Tech Systems, Inc.Inventors: Russell Carlson, Dustin Barr, Allen Yan, Justin Carpenter
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Patent number: 10712138Abstract: A method for controlling the attitude and/or flight path of a flight vehicle includes burning propellant in a gas generator to produce hot gas, storing the hot gas in an accumulator, and releasing the hot gas in the accumulator through one or more thrusters to control the attitude and/or flight path of the flight vehicle.Type: GrantFiled: March 26, 2018Date of Patent: July 14, 2020Assignee: Valley Tech Systems, Inc.Inventors: Russell Carlson, Dustin Barr, Allen Yan
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Patent number: 10598128Abstract: An attitude control system for a guided missile includes a gas generator, an accumulator coupled to the gas generator, and a valve positioned between the gas generator and the accumulator. The gas generator contains propellant that burns to provide hot gas to pressurize the accumulator. The valve is opened to recharge the accumulator with hot gas and closed when it is full. A vent valve can be included to extinguish the propellant in the gas generator. The accumulator can be coupled to thrusters that use the stored hot gas to adjust the attitude of the guided missile.Type: GrantFiled: October 5, 2015Date of Patent: March 24, 2020Assignee: Valley Tech Systems, Inc.Inventors: Russell Carlson, Dustin Barr, Allen Yan
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Patent number: 9927217Abstract: An attitude control system for a guided missile includes a gas generator, an accumulator coupled to the gas generator, and a valve positioned between the gas generator and the accumulator. The gas generator contains propellant that burns to provide hot gas to pressurize the accumulator. The valve is opened to recharge the accumulator with hot gas and closed when it is full. A vent valve can be included to extinguish the propellant in the gas generator. The accumulator can be coupled to thrusters that use the stored hot gas to adjust the attitude of the guided missile.Type: GrantFiled: September 8, 2015Date of Patent: March 27, 2018Assignee: Valley Tech Systems, Inc.Inventors: Russell Carlson, Dustin Barr, Allen Yan
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Publication number: 20120273099Abstract: The disclosure described herein is a reduced toxicity rocket propellant comprising a liquid fuel and a liquid oxidizer that ignites spontaneously upon contact with each other. The rocket propellant includes a metal hydride catalyst. Multiple embodiments of the propellant include multiple compositions of liquid fuel.Type: ApplicationFiled: April 30, 2012Publication date: November 1, 2012Inventors: William Anderson, Erik Michael Dambach, Yair Solomon, Rohit Mahakali, Allen Yan