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公开(公告)号：US11927152B2
公开(公告)日：2024-03-12
申请号：US18094300
申请日：2023-01-06
Applicant: Sierra Space Corporation
Inventor： Ryan C. Cavitt , Trevor P. Ormonde , Jake W. Carey , Patrick D. Satyshur , Christopher P. St. Clair , Scott M. Munson
CPC classification number: F02K9/68 , F02K9/28 , F02K9/42 , F02K9/425 , F02K9/44 , F02K9/58 , F02K9/72
Abstract: Various embodiments of a vortex thruster system is described herein that is configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system is configured to decompose a monopropellant and deliver the decomposed monopropellant into a vortex combustion chamber for generating various thrust levels. In some embodiments, the vortex thruster system includes a secondary propellant valve configured to deliver a secondary propellant into the vortex combustion chamber containing decomposed monopropellant to create a high thrust level. Related systems, methods, and articles of manufacture are also described.
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公开(公告)号：US20230265816A1
公开(公告)日：2023-08-24
申请号：US18103460
申请日：2023-01-30
Applicant: Sierra Space Corporation
Inventor： Martin Chiaverini , Patrick D. Satyshur , Christopher St. Clair
Abstract: Various embodiments of a vortex hybrid motor are described herein. In some embodiments, the vortex hybrid motor may include a combustion zone defined by a fuel core and/or motor housing. The combustion zone may include an upper zone and a central zone that each contribute to thrust created by the vortex hybrid motor. In some embodiments, an injection port configuration is described that includes a proximal injection port that may be controlled for modulating a delivery of an amount of oxidizer for adjusting an oxidizer-to-fuel ratio. In some embodiments, a fuel core configuration is described that provides radially varying gradients of fuel in order to achieve desired thrust profiles. In some embodiments, the fuel core may include a support structure and/or a proximal end of a nozzle of the vortex hybrid motor may extend into the fuel core.
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公开(公告)号：US11572851B2
公开(公告)日：2023-02-07
申请号：US16449229
申请日：2019-06-21
Applicant: Sierra Space Corporation
Inventor： Ryan C. Cavitt , Trevor P. Ormonde , Jake W. Carey , Patrick D. Satyshur , Christopher P. St. Clair , Scott M. Munson
Abstract: Various embodiments of a vortex thruster system is described herein that is configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system is configured to decompose a monopropellant and deliver the decomposed monopropellant into a vortex combustion chamber for generating various thrust levels. In some embodiments, the vortex thruster system includes a secondary propellant valve configured to deliver a secondary propellant into the vortex combustion chamber containing decomposed monopropellant to create a high thrust level. Related systems, methods, and articles of manufacture are also described.
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公开(公告)号：US12071915B2
公开(公告)日：2024-08-27
申请号：US18103460
申请日：2023-01-30
Applicant: Sierra Space Corporation
Inventor： Martin Chiaverini , Patrick D. Satyshur , Christopher St. Clair
Abstract: Various embodiments of a vortex hybrid motor are described herein. In some embodiments, the vortex hybrid motor may include a combustion zone defined by a fuel core and/or motor housing. The combustion zone may include an upper zone and a central zone that each contribute to thrust created by the vortex hybrid motor. In some embodiments, an injection port configuration is described that includes a proximal injection port that may be controlled for modulating a delivery of an amount of oxidizer for adjusting an oxidizer-to-fuel ratio. In some embodiments, a fuel core configuration is described that provides radially varying gradients of fuel in order to achieve desired thrust profiles. In some embodiments, the fuel core may include a support structure and/or a proximal end of a nozzle of the vortex hybrid motor may extend into the fuel core.
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公开(公告)号：US20230160359A1
公开(公告)日：2023-05-25
申请号：US18094300
申请日：2023-01-06
Applicant: Sierra Space Corporation
Inventor： Ryan C. Cavitt , Trevor P. Ormonde , Jake W. Carey , Patrick D. Satyshur , Christopher P. St. Clair , Scott M. Munson
CPC classification number: F02K9/68 , F02K9/28 , F02K9/72 , F02K9/42 , F02K9/44 , F02K9/425 , F02K9/58
Abstract: Various embodiments of a vortex thruster system is described herein that is configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system is configured to decompose a monopropellant and deliver the decomposed monopropellant into a vortex combustion chamber for generating various thrust levels. In some embodiments, the vortex thruster system includes a secondary propellant valve configured to deliver a secondary propellant into the vortex combustion chamber containing decomposed monopropellant to create a high thrust level. Related systems, methods, and articles of manufacture are also described.
