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公开(公告)号：US20240228066A9
公开(公告)日：2024-07-11
申请号：US18491511
申请日：2023-10-20
Applicant: Purdue Research Foundation
Inventor： Alexey Shashurin , Timothee Louis Pourpoint
IPC: B64G1/40
CPC classification number: B64G1/413 , B64G1/4026
Abstract: A dual mode engine for propelling a spacecraft, including a combustion chamber having a flange end, an open nozzle end, and an enclosed chamber portion extending therebetween, a propellant tank in fluidic communication with the combustion chamber, an electronic controller, a power source operationally connected to the electronic controller, and a fluid flow motivator operationally connected to the electronic controller and connected in fluidic communication with the propellant tank. The engine further includes a chemical propulsion portion further including a propellant inlet port operationally connected to the combustion chamber and disposed adjacent the flange end, an ignition trigger electrode positioned in the combustion chamber adjacent the propellant inlet port and operationally connected to the electronic controller and operationally connected to the power source, wherein the propellant inlet port is fluidically connected to the propellant tank. The engine also includes an electric propulsion portion, further including at least two spaced electrodes for ionizing the propellant positioned in the combustion chamber adjacent the nozzle end, a plurality of attitude control thrusters operationally connected to the electronic controller and in fluidic communication with the propellant tank, and a plurality of respective valves, each respective valve fluidically connected between a respective attitude control thruster and the propellant tank, wherein the propellant inlet port is fluidically connected to the propellant tank.
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公开(公告)号：US20210199590A1
公开(公告)日：2021-07-01
申请号：US17085856
申请日：2020-10-30
Applicant: Purdue Research Foundation
Inventor： Alexey Shashurin , Xingxing Wang
Abstract: Methods and systems capable of measuring gas temperatures utilizing plasma discharges. Such a method performs a measurement of a temperature of a gas by generating a probing nanosecond plasma pulse in the gas, and then using an optical emission spectroscopy technique to measure the temperature of the gas by processing a light emission signal excited by the probing nanosecond plasma pulse.
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Patent Agency Ranking
公开(公告)号：US20240132232A1
公开(公告)日：2024-04-25
申请号：US18491511
申请日：2023-10-19
Applicant: Purdue Research Foundation
Inventor： Alexey Shashurin , Timothee Louis Pourpoint
IPC: B64G1/40
CPC classification number: B64G1/413 , B64G1/4026
Abstract: A dual mode engine for propelling a spacecraft, including a combustion chamber having a flange end, an open nozzle end, and an enclosed chamber portion extending therebetween, a propellant tank in fluidic communication with the combustion chamber, an electronic controller, a power source operationally connected to the electronic controller, and a fluid flow motivator operationally connected to the electronic controller and connected in fluidic communication with the propellant tank. The engine further includes a chemical propulsion portion further including a propellant inlet port operationally connected to the combustion chamber and disposed adjacent the flange end, an ignition trigger electrode positioned in the combustion chamber adjacent the propellant inlet port and operationally connected to the electronic controller and operationally connected to the power source, wherein the propellant inlet port is fluidically connected to the propellant tank. The engine also includes an electric propulsion portion, further including at least two spaced electrodes for ionizing the propellant positioned in the combustion chamber adjacent the nozzle end, a plurality of attitude control thrusters operationally connected to the electronic controller and in fluidic communication with the propellant tank, and a plurality of respective valves, each respective valve fluidically connected between a respective attitude control thruster and the propellant tank, wherein the propellant inlet port is fluidically connected to the propellant tank.
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公开(公告)号：US11946871B2
公开(公告)日：2024-04-02
申请号：US17085856
申请日：2020-10-30
Applicant: Purdue Research Foundation
Inventor： Alexey Shashurin , Xingxing Wang
CPC classification number: G01N21/67 , G01N21/1702 , G01N2021/1704
Abstract: Methods and systems capable of measuring gas temperatures utilizing plasma discharges. Such a method performs a measurement of a temperature of a gas by generating a probing nanosecond plasma pulse in the gas, and then using an optical emission spectroscopy technique to measure the temperature of the gas by processing a light emission signal excited by the probing nanosecond plasma pulse.
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公开(公告)号：US11193964B2
公开(公告)日：2021-12-07
申请号：US16431370
申请日：2019-06-04
Applicant: Purdue Research Foundation
Inventor： Abhijeet Dhiman , Vikas Tomar , Animesh Sharma , Alexey Shashurin , Sergey O Macheret
Abstract: A method of determining stress within a composite structure is provided which includes coupling a sensor to a composite structure under load having embedded therein a plurality of particles, wherein the particles at room temperature are paraelectric or ferroelectric, transmitting an electromagnetic radiation to the sensor, thereby generating an electromagnetic field into the composite structure, sweeping frequency from a first frequency to a second frequency in a pulsed manner, receiving reflected power from the composite structure, determining the resonance frequency of the sensor, and translating the resonance frequency of the sensor to stress within the composite structure.
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公开(公告)号：US20190078559A1
公开(公告)日：2019-03-14
申请号：US16128658
申请日：2018-09-12
Applicant: Purdue Research Foundation
Inventor： Alexey Shashurin , Omar Gabriel Dary , Yunping Zhang
Abstract: An ignitor subsystem for use in an electric propulsion system is disclosed. The igniter subsystem includes an igniter, which includes a first electrically conducting electrode, a second electrically conducting electrode, and an electrically insulating layer sandwiched between the first and the second electrically conducting electrodes, and a voltage pulse generator electrically coupled to the first and the second electrically conducting electrodes and is adapted to generate a plurality of pulses each with sufficient voltage to cause a breakdown of the electrically insulating layer, thus causing an avalanche of electrons from one of the first and the second electrically conducting electrodes to the other, the voltage pulse generator is further adapted to limit energy transferred to the igniter in each of the plurality of pulses so as to minimize damage to the igniter.
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公开(公告)号：US20180117196A1
公开(公告)日：2018-05-03
申请号：US15729971
申请日：2017-10-11
Applicant: Purdue Research Foundation
Inventor： Alexey Shashurin , Xingxing Wang
IPC: A61L2/14 , A61L2/26 , A23B7/144 , A23L3/3409
CPC classification number: A61L2/14 , A23B7/144 , A23L3/3409 , A23V2002/00 , A61L2/26 , A61L2202/11 , A61L2202/24
Abstract: A plasma generating system capable of generating a cold plasma. The plasma generating includes two electrodes, a DC voltage source capable of applying a constant DC voltage between the two electrodes, an insulator located in proximity of the two electrodes, and a gas filling a gap between the two electrodes, wherein cold plasma in the form of series of repetitive streamer breakdowns of the gas is generated, in response to the constant DC voltage applied between the two electrodes. A method of producing and storing a sterilizing gas. The method includes providing a flow of a gas into a chamber, generating cold plasma through repetitive streamer breakdowns of the gas in response to an applied DC voltage, resulting in the gas becoming a sterilizing gas. A method of sterilizing an object. The method includes exposing an object to be sterilized to the sterilizing gas for a period of time.
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