Patents by Inventor Yen-Sen CHEN
Yen-Sen CHEN 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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Patent number: 11846254Abstract: An integrated propulsion system for hybrid rockets includes an oxidizer tank, a rocket engine, a pressurization device, a pressurization device and an oxidizer pipe and valve unit. The rocket engine is disposed within the oxidizer tank partially and located on a first side of the oxidizer tank. The pressurization device is disposed, at least in part, within the oxidizer tank, is located on a second side of the oxidizer tank opposite to the first side of the oxidizer tank, and is configured to regulate an overall pressure level within the oxidizer tank. The oxidizer pipe and valve unit is connected to the oxidizer tank and the rocket engine, and is configured to control feeding of an oxidizer from the oxidizer tank into the rocket engine.Type: GrantFiled: March 4, 2023Date of Patent: December 19, 2023Assignee: AT SPACE PTY LTDInventor: Yen-Sen Chen
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Publication number: 20230204004Abstract: An integrated propulsion system for hybrid rockets includes an oxidizer tank, a rocket engine, a pressurization device, a pressurization device and an oxidizer pipe and valve unit. The rocket engine is disposed within the oxidizer tank partially and located on a first side of the oxidizer tank. The pressurization device is disposed, at least in part, within the oxidizer tank, is located on a second side of the oxidizer tank opposite to the first side of the oxidizer tank, and is configured to regulate an overall pressure level within the oxidizer tank. The oxidizer pipe and valve unit is connected to the oxidizer tank and the rocket engine, and is configured to control feeding of an oxidizer from the oxidizer tank into the rocket engine.Type: ApplicationFiled: March 4, 2023Publication date: June 29, 2023Inventor: Yen-Sen CHEN
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Publication number: 20230150676Abstract: A drogue parachute system for a spacecraft includes a first parachute that is inflatable, at least one inflating device that is connected to the first parachute and can inflate the first parachute, a first set of connection lines, an extension device, a second set of connection lines, a second parachute and a third set of connection lines. Each connection line of the first set of connection lines includes two opposite ends respectively connected to the first parachute and the spacecraft. Each connection line of the second set of connection lines includes two opposite ends respectively connected to the extension device and the first parachute. Each connection line of the third set of connection lines includes two opposite ends respectively connected to the second parachute and the extension device. The first parachute fully deployed is reverse umbrella-shaped with respect to the spacecraft.Type: ApplicationFiled: January 14, 2023Publication date: May 18, 2023Inventor: Yen-Sen CHEN
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Patent number: 11598288Abstract: A motor and fuel-powered hybrid system of a rocket thruster is disclosed, which mainly provides power through a motor and a fluid fuel injector. In particular, at the beginning stage of the rocket lift-off, the motor drives the compressor to provide power to send the rocket into air. When the speed and height of the rocket gradually increase, the fuel is ignited to give power to keep propelling the rocket, thereby reducing the fluid fuel that needs to be carried on the rocket, increasing the rocket's loading space and enhancing the carrying capacity.Type: GrantFiled: February 22, 2022Date of Patent: March 7, 2023Assignee: Taiwan Innovative Space, Inc.Inventor: Yen-Sen Chen
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Publication number: 20230012171Abstract: A propellant injector is adapted to be installed to a hybrid rocket engine and includes an injector casing, a tube and a plurality of blades. The tube is arranged along a center axis of the propellant injector in an inner space of the injector casing. The plurality of blades is disposed to and evenly distributed over an outer surface of the tube, and is configured to cause vortices toward a combustion chamber of the hybrid rocket engine when being driven to rotate.Type: ApplicationFiled: July 6, 2021Publication date: January 12, 2023Inventor: Yen-Sen CHEN
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Publication number: 20220411080Abstract: A drogue parachute system for a spacecraft includes a first parachute, a first set of connection lines, an extension device, a second set of connection lines, a second parachute and a third set of connection lines. Each connection line of the first set of connection lines includes two opposite ends respectively connected to the first parachute and the spacecraft. Each connection line of the second set of connection lines includes two opposite ends respectively connected to the extension device and the first parachute. Each connection line of the third set of connection lines includes two opposite ends respectively connected to the second parachute and the extension device.Type: ApplicationFiled: June 23, 2021Publication date: December 29, 2022Inventor: Yen-Sen CHEN
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Publication number: 20220397079Abstract: An integrated propulsion system for hybrid rockets includes an oxidizer tank, a rocket engine, a pressurization device, a pressurization device and an oxidizer pipe and valve unit. The rocket engine is disposed within the oxidizer tank partially and located on a first side of the oxidizer tank. The pressurization device is disposed, at least in part, within the oxidizer tank, is located on a second side of the oxidizer tank opposite to the first side of the oxidizer tank, and is configured to regulate an overall pressure level within the oxidizer tank. The oxidizer pipe and valve unit is connected to the oxidizer tank and the rocket engine, and is configured to control feeding of an oxidizer from the oxidizer tank into the rocket engine.Type: ApplicationFiled: June 10, 2021Publication date: December 15, 2022Inventor: Yen-Sen CHEN
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Patent number: 11518547Abstract: A booster system for a launch vehicle includes a plurality of core boosters and a plurality of patchy boosters. The plurality of core boosters and the plurality of patchy boosters are arranged in an inner space of a rocket casing of the launch vehicle, and the plurality of patchy boosters is separatable from the launch vehicle.Type: GrantFiled: June 18, 2021Date of Patent: December 6, 2022Assignee: AT SPACE PTY LTDInventor: Yen-Sen Chen
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Publication number: 20220341374Abstract: A motor and fuel-powered hybrid system of a rocket thruster is disclosed, which mainly provides power through a motor and a fluid fuel injector. In particular, at the beginning stage of the rocket lift-off, the motor drives the compressor to provide power to send the rocket into air. When the speed and height of the rocket gradually increase, the fuel is ignited to give power to keep propelling the rocket, thereby reducing the fluid fuel that needs to be carried on the rocket, increasing the rocket's loading space and enhancing the carrying capacity.Type: ApplicationFiled: February 22, 2022Publication date: October 27, 2022Inventor: YEN-SEN CHEN
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Patent number: 11391245Abstract: A motor has an oxidizer injector, the oxidizer injector is mainly suitable for using in a combustion chamber, the oxidizer injector has a body having a first runner assembly and a second runner assembly arranged along an axis, the first runner assembly injects oxidizer into the combustion chamber to form a forward swirl, and the second runner assembly injects oxidizer into the combustion chamber to form a reverse swirl, the axial torsion generated by the forward swirl and the axial torsion generated by the reverse swirl counteract each other, so as to solve the problem of axial torsion imbalance in the combustion chamber.Type: GrantFiled: March 12, 2019Date of Patent: July 19, 2022Assignee: TAIWAN INNOVATIVE SPACE, INC.Inventor: Yen-Sen Chen
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Publication number: 20220090561Abstract: A motor and fuel-powered hybrid system of a rocket thruster is disclosed, which mainly provides power through a motor and a fluid fuel injector. In particular, at the beginning stage of the rocket lift-off, the motor drives the compressor to provide power to send the rocket into air. When the speed and height of the rocket gradually increase, the fuel is ignited to give power to keep propelling the rocket, thereby reducing the fluid fuel that needs to be carried on the rocket, increasing the rocket's loading space and enhancing the carrying capacity.Type: ApplicationFiled: September 22, 2020Publication date: March 24, 2022Inventor: Yen-Sen CHEN
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Patent number: 11060483Abstract: A rocket engine with an improved solid fuel segment mainly comprises a combustion chamber, a solid fuel segment installed in the combustion chamber, and an oxidizer injector installed at one end of the combustion chamber. The solid fuel segment surrounds and forms a trajectory to allow the oxidizer injector to inject oxidizer into the trajectory, in particular, on the solid fuel segment is formed with a plurality of protrusions, between the each two protrusions are defined a recess, a flame holding hot-gas region is formed between the protrusion and the recess, so as to produce eddy current in the flame holding hot-gas region when the propellant mixture is burned inside the trajectory, such that the whole solid fuel segment can produce even regression rate and high combustion efficiency.Type: GrantFiled: March 12, 2019Date of Patent: July 13, 2021Assignee: Taiwan Innovative Space, Inc.Inventor: Yen-Sen Chen
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Publication number: 20200291897Abstract: An oxidizer injector for motor, which is mainly suitable for using in a combustion chamber, the oxidizer injector mainly comprises a body having a first runner assembly and a second runner assembly arranged along an axis, the first runner assembly injects oxidizer into the combustion chamber to form a forward swirl, and the second runner assembly injects oxidizer into the combustion chamber to form a reverse swirl, the axial torsion generated by the forward swirl and the axial torsion generated by the reverse swirl counteract each other, so as to solve the problem of axial torsion imbalance in the combustion chamber.Type: ApplicationFiled: March 12, 2019Publication date: September 17, 2020Inventor: Yen-Sen CHEN
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Publication number: 20200291899Abstract: A rocket engine with an improved solid fuel segment mainly comprises a combustion chamber, a solid fuel segment installed in the combustion chamber, and an oxidizer injector installed at one end of the combustion chamber. The solid fuel segment surrounds and forms a trajectory to allow the oxidizer injector to inject oxidizer into the trajectory, in particular, on the solid fuel segment is formed with a plurality of protrusions, between the each two protrusions are defined a recess, a flame holding hot-gas region is formed between the protrusion and the recess, so as to produce eddy current in the flame holding hot-gas region when the propellant mixture is burned inside the trajectory, such that the whole solid fuel segment can produce even regression rate and high combustion efficiency.Type: ApplicationFiled: March 12, 2019Publication date: September 17, 2020Inventor: Yen-Sen CHEN
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Patent number: 9458796Abstract: The present invention discloses a dual-vortical-flow hybrid rocket engine, including a main body and a nozzle communicating with an end of the main body. The main body includes a plurality of disk-like combustion chambers arranged longitudinally, and a central combustion chamber formed along the axial portion and communicating the disk-like combustion chambers. Each of the disk-like combustion chambers is provided with a plurality of oxidizer injection nozzles at its inner circumference surface. Inside the disk-like combustion chambers, the oxidizer is injected in nearly the tangent directions of the circumference, and the injection directions are opposite for the neighboring disk-like combustion chambers, which creates vortical flows with opposite rotating directions so as to increase the total residence time of the combustion reactions of the oxidizer and the solid-state fuel in the disk-like combustion chambers of the present invention.Type: GrantFiled: November 4, 2013Date of Patent: October 4, 2016Assignees: National Applied Research Laboratories, National Chiao Tung UniversityInventors: Yen-Sen Chen, Men-Zen Wu, Jong-Shinn Wu, Alfred Lai, Jhe-Wei Lin, Tzu-Hao Chou
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Publication number: 20140352276Abstract: The present invention discloses a dual-vortical-flow hybrid rocket engine, including a main body and a nozzle communicating with an end of the main body. The main body includes a plurality of disk-like combustion chambers arranged longitudinally, and a central combustion chamber formed along the axial portion and communicating the disk-like combustion chambers. Each of the disk-like combustion chambers is provided with a plurality of oxidizer injection nozzles at its inner circumference surface. Inside the disk-like combustion chambers, the oxidizer is injected in nearly the tangent directions of the circumference, and the injection directions are opposite for the neighboring disk-like combustion chambers, which creates vortical flows with opposite rotating directions so as to increase the total residence time of the combustion reactions of the oxidizer and the solid-state fuel in the disk-like combustion chambers of the present invention.Type: ApplicationFiled: November 4, 2013Publication date: December 4, 2014Applicants: National Chiao Tung University, National Applied Research LaboratoriesInventors: Yen-Sen Chen, Men-Zen Wu, Jong-Shinn Wu, Alfred Lai, Jhe-Wei Lin, Tzu-Hao Chou
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Patent number: 8776526Abstract: 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.Type: GrantFiled: February 1, 2011Date of Patent: July 15, 2014Assignee: National Applied Research LaboratoriesInventors: Yen-Sen Chen, Jong-Shinn Wu, Tzu-Hao Chou
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Publication number: 20110203256Abstract: 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.Type: ApplicationFiled: February 1, 2011Publication date: August 25, 2011Inventors: Yen-Sen CHEN, Jong-Shinn Wu, Tzu-Hao Chou