WO2021108001A1 - Augmented aerospike nozzle, engine including the augmented aerospike nozzle, and vehicle including the engine - Google Patents
Augmented aerospike nozzle, engine including the augmented aerospike nozzle, and vehicle including the engine Download PDFInfo
- Publication number
- WO2021108001A1 WO2021108001A1 PCT/US2020/048178 US2020048178W WO2021108001A1 WO 2021108001 A1 WO2021108001 A1 WO 2021108001A1 US 2020048178 W US2020048178 W US 2020048178W WO 2021108001 A1 WO2021108001 A1 WO 2021108001A1
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- WO
- WIPO (PCT)
- Prior art keywords
- expansion surface
- augmented
- nozzle
- aerospike
- centerbody
- Prior art date
Links
- 230000003190 augmentative effect Effects 0.000 title claims abstract description 48
- 230000007423 decrease Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 description 7
- 235000015842 Hesperis Nutrition 0.000 description 4
- 235000012633 Iberis amara Nutrition 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/002—Launch systems
- B64G1/006—Reusable launch rockets or boosters
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
- F02K9/972—Fluid cooling arrangements for nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/128—Nozzles
- F05D2240/1281—Plug nozzles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/14—Two-dimensional elliptical
- F05D2250/141—Two-dimensional elliptical circular
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
- F05D2250/311—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being in line
Definitions
- the present disclosure generally relates to propulsion systems having exhaust nozzles.
- the present disclosure more particularly relates to an augmented aerospike nozzle, an engine including the augmented aerospike nozzle, and a vehicle including the engine.
- Aircraft-like reusability for rockets has long been the “holy grail” of rocketry due to the potential for huge cost benefits.
- the ability to recover and reuse an upper stage rocket of a multi-stage rocket system (e.g., the second stage rocket of a two-stage rocket system) remains a significant technical gap that has not yet been solved by the industry.
- Reusing the upper stage of a multi-stage rocket is challenging due to the harsh re-entry environment and the performance penalties associated with increased structural mass required for robust reuse.
- Upper stage rockets are typically constructed with the minimum structure and complexity since any mass addition to the second stage is a 1 :1 reduction in payload capacity. Reusing an upper stage rocket therefore requires significant additional functionality but with minimal mass addition.
- the prior art aerospike engine 112 includes at least one high pressure chamber 136 (e.g., a combustion chamber) and an aerospike nozzle 110.
- the aerospike nozzle 110 includes at least one initial nozzle portion 160 through which exhaust gas initially exits the high pressure chamber 136, and a secondary nozzle portion 162 downstream relative to the initial nozzle portion 160.
- the initial nozzle portion 160 includes at least one throat 124, one or more surfaces 164, 166 downstream relative to the throat 124, and an outer aft end 168 defined by the throat 124 and/or at least one of the surfaces 164, 166.
- the secondary nozzle portion 162 includes a centerbody 128 (e.g., an aerospike) defining an inner expansion surface 126.
- the typical prior art aerospike nozzle 110 includes an initial nozzle portion 160 in the form of a converging-diverging nozzle.
- the throat 124 defines a transition between an upstream converging section with opposing converging surfaces 170, 172, and a downstream diverging section with opposing diverging surfaces 164, 166.
- the diverging surfaces 164, 166 define an initial nozzle cavity 125 therebetween.
- the inner diverging surface 164 is contiguous with (e.g., at least substantially flush with) the inner expansion surface 126 defined by the centerbody 128 of the secondary nozzle portion 162.
- the outer aft end 168 of the initial nozzle portion 160 is defined by the aft end of the wall defining the outer diverging surface 166. In some instances, at least a portion of the outer diverging surface 166 is defined by a cowl, a shroud, and/or another component of the vehicle on which the aerospike engine 112 is mounted. In prior art embodiments like the one shown in FIG. 2, the initial nozzle portion 160 is sometimes referred to as a “primary nozzle.”
- an outer portion of the throat 124 defines the outer aft end 168 of the initial nozzle portion 160. That is, the diverging section of the initial nozzle portion 160 excludes the outer diverging surface 166 included in prior art aerospike nozzles like that shown in FIG. 2.
- the engine 112 has a so-called “plug cluster” configuration.
- the engine 112 includes a plurality of discrete high pressure chambers 136 spaced relative to one another and a plurality of discrete initial nozzle portions 160 spaced relative to one another.
- Each initial nozzle portion 160 is disposed relative to a corresponding high pressure chamber 136, and is configured to exhaust gas exiting the respective high pressure chamber 136.
- each high pressure chamber 136 and initial nozzle portion 160 pair is known in the art as a “thrust can.”
- the initial nozzle portion 160 of each thrust can includes a discrete throat 124 that extends annularly about an axis 174 of the initial nozzle portion 160.
- the converging surfaces 170, 172 of the throat 124 form a continuous surface that extends annularly about the axis 174
- the diverging surfaces 164, 166 of the throat 124 form a continuous surface that extends annularly about the axis 174.
- the converging surfaces 170, 172 and/or the diverging surfaces 164, 166 are axisymmetric relative to the axis 174.
- the thrust cans are circumferentially spaced about the centerline 116 of the vehicle on which the engine 112 is disposed.
- the thrust cans are spaced linearly along a plane parallel to the centerline 116 of the vehicle.
- the engine 112 includes a single high pressure chamber 136 and a single initial nozzle portion 160 with a single throat 124.
- the converging surfaces 170, 172 of the throat 124 are discrete surfaces relative to one another, and the diverging surfaces 164, 166 of the throat 124 are discrete surfaces relative to one another.
- the high pressure chamber 136 and the throat 124 each extend annularly about a centerline 116 of the vehicle on which the engine 112 is disposed.
- the high pressure chamber 136 and the throat 124 each extend linearly in respective planes parallel to the centerline 116 of the vehicle.
- the net turning angle Q can be greater than 90°.
- the exhaust gas deflects outboard of the outer aft end 168 of the initial nozzle cavity 125, resulting in lost performance for the prior art aerospike engine 112 when operated in a vacuum.
- an augmented aerospike nozzle includes a throat, a centerbody extending aft of the throat, an inner expansion surface defined by the centerbody, an outer expansion surface outboard of the inner expansion surface, and an expansion cavity defined between the inner expansion surface and the outer expansion surface.
- an engine includes a high pressure chamber and an augmented aerospike nozzle that exhausts gas generated by the high pressure chamber.
- the augmented aerospike nozzle includes a throat, a centerbody extending aft of the throat, an inner expansion surface defined by the centerbody, an outer expansion surface outboard of the inner expansion surface, and an expansion cavity defined between the inner expansion surface and the outer expansion surface.
- a vehicle includes an engine with a high pressure chamber and an augmented aerospike nozzle that exhausts gas generated by the high pressure chamber.
- the augmented aerospike nozzle includes a throat, a centerbody extending aft of the throat, an inner expansion surface defined by the centerbody, an outer expansion surface outboard of the inner expansion surface, and an expansion cavity defined between the inner expansion surface and the outer expansion surface.
- a re usable upper stage rocket of a multi-stage rocket system includes an engine configured for in-space propulsion and atmospheric landing propulsion.
- the inner expansion surface and the outer expansion surface are configured such that the expansion cavity has a width that continuously increases in the aft direction;
- the outer expansion surface extends as far aft as the inner expansion surface
- the outer expansion surface extends further aft than the inner expansion surface
- the inner expansion surface extends further aft than the outer expansion surface
- the expansion cavity extends annularly about the centerbody, and is concentrically aligned with the centerbody about a centerline of the nozzle;
- the augmented aerospike nozzle is a linear aerospike nozzle
- the throat is included in an initial nozzle portion of the augmented aerospike nozzle, and the outer expansion surface extends in an aft direction from an outer aft end of the initial nozzle portion;
- the vehicle is an upper stage rocket
- the centerbody is a truncated toroidal aerospike having a centerbody base that partially defines the aft end of the vehicle;
- the engine is recessed into a base surface of the vehicle
- the outer expansion surface is integrally connected to the vehicle, and the augmented aerospike nozzle includes a seal that allows the centerbody to gimbal while allowing the outer expansion surface to remain fixed with respect to the vehicle;
- FIG. 1 schematically illustrates a prior art aerospike engine.
- FIG. 2 schematically illustrates a portion of the prior art aerospike engine of FIG. 1.
- FIG. 3 schematically illustrates a portion of another prior art aerospike engine.
- FIG. 4 is a perspective view of a vehicle including an engine with an augmented aerospike nozzle.
- FIG. 5 is a schematic sectional view of a portion of the vehicle of FIG. 4 during vacuum operation (left of centerline) and atmospheric operation (right of centerline).
- FIG. 6 is a sectional perspective view of the aft portion of the vehicle of FIG. 4.
- FIG. 7 schematically illustrates a portion of the augmented aerospike engine of FIG. 4.
- FIG. 8 schematically illustrates a portion of another augmented aerospike engine.
- the present disclosure describes an augmented aerospike nozzle 10, an engine 12 including the augmented aerospike nozzle 10, and a vehicle 14 including the engine 12.
- the vehicle 14 is a rocket (e.g., a multi stage rocket, a single-stage-to-orbit (SSTO) rocket, an upper stage rocket, a booster rocket, etc.), a missile, a spacecraft, an aircraft, or another vehicle designed for travel (e.g., flight) up to at least supersonic speeds (e.g., supersonic speeds, hypersonic speeds, re-entry speeds, etc.) in atmospheric, sub-orbital, orbital, and/or outer space environments.
- the vehicle 14 is a second stage rocket of a two-stage rocket (not shown).
- the vehicle 14 (hereinafter the “second stage rocket 14”) extends along a centerline 16 between a forward end 18 and an opposing aft end 20 thereof.
- the second stage rocket 14 includes a payload 22 toward the forward end 18, and the engine 12 toward the aft end 20.
- the augmented aerospike nozzle 10 includes at least one initial nozzle portion 60 through which exhaust gas initially exits at least one high pressure chamber 36, and a secondary nozzle portion 62 downstream relative to the initial nozzle portion 60.
- the initial nozzle portion 60 includes at least one throat 24, one or more surfaces 64, 66 extending downstream relative to the throat 24, and an outer aft end 68 defined by the throat 24 and/or at least one of the surfaces 64, 66.
- the secondary nozzle portion 62 includes a centerbody 28 (e.g., an aerospike) defining an inner expansion surface 26.
- the secondary nozzle portion 62 also includes an outer expansion surface 30 outboard of the inner expansion surface 26, and an expansion cavity 32 defined between the inner expansion surface 26 and the outer expansion surface 30.
- the initial nozzle portion 60 of the nozzle 10 is in the form of a converging-diverging nozzle and/or a primary nozzle.
- the throat 24 defines a transition between an upstream converging section with opposing converging surfaces 70, 72, and a downstream diverging section with opposing diverging surfaces 64, 66.
- the diverging surfaces 64, 66 define an initial nozzle cavity 25 therebetween.
- the inner diverging surface 64 is contiguous with (e.g., at least substantially flush with) the inner expansion surface 126 defined by the centerbody 128 of the secondary nozzle portion 62.
- the outer expansion surface 30 is connected (e.g., connected directly, connected indirectly via a seal, etc.) and extends in the aft direction from the outer aft end 68 of the initial nozzle portion 60, which is defined by the aft end of the outer diverging surface 66.
- An inflection point is defined where the outer diverging surface 66 of the initial nozzle portion 60 meets the outer expansion surface 30 of the secondary nozzle portion 62.
- the initial nozzle portion 60 is configured such that an outer portion of the throat 24 defines the outer aft end 68 of the initial nozzle portion 60. That is, the initial nozzle portion 60 excludes the outer diverging surface 66 included in nozzles like that shown in FIG. 7.
- the outer expansion surface 30 is connected (e.g., connected directly, connected indirectly via a seal, etc.) and extends in the aft direction from the outer aft end 68 of the initial nozzle portion 60.
- the centerbody 28 that defines the inner expansion surface 26 of the augmented aerospike nozzle 10 is an aerospike (e.g., toroidal aerospike, linear aerospike) or another type of plug nozzle.
- the contour of the inner expansion surface 26 will depend on the particular application, and can be selected and/or optimized using methods by Angelino (1964) and/or other methods known in the art.
- the centerbody 28 is a truncated toroidal aerospike having a centerbody base 34 that partially defines the aft end 20 of the second stage rocket 14.
- the radius n of a forward portion of the centerbody 28 is greater than the radius G2 of an aft portion of the centerbody 28.
- a dimension of the centerbody 28 (e.g., the radius) continuously decreases in the aft direction.
- the inner and outer expansion surfaces 26, 30 of the secondary nozzle portion 62 of the augmented aerospike nozzle 10 are configured such that the expansion cavity 32 defined therebetween has a width (e.g., a dimension in the direction perpendicular to the centerline 16) that increases (e.g., continuously increases) in the aft direction.
- the contour of the outer expansion surface 30 will depend on the particular application, and can be selected and/or optimized using methods by Angelino (1964) and/or other methods known in the art. That is, known methods for selecting and/or optimizing the contour of the inner expansion surface 26 can be applied when selecting and/or optimizing the contour of the outer expansion surface 30.
- the outer expansion surface 30 extends as far aft as the inner expansion surface 26. In other embodiments not shown in the drawings, the outer expansion surface 30 extends further aft than the inner expansion surface 26, or the inner expansion surface 26 extends further aft than the outer expansion surface 30. In the illustrated embodiments, the expansion cavity 32 extends annularly about the centerbody 28, and is concentrically aligned with the centerbody 28 about the centerline 16 of the second stage rocket 14.
- the engine 12 includes the high pressure chamber 36 (e.g., a combustion chamber) and the augmented aerospike nozzle 10.
- the high pressure chamber 36 generates gas that is exhausted through the augmented aerospike nozzle 10.
- the high pressure chamber 36 is in the form of an annular ring, a segmented ring, individual thrust chambers, or any other configuration providing supersonic flow to the inner expansion surface 26 and the outer expansion surface 30.
- the engine 12 includes a single high pressure chamber 36 and a single initial nozzle portion 60 with a single throat 24.
- the nozzle 10 is in the form of a toroidal aerospike.
- the high pressure chamber 36 and the throat 24 each extend annularly about the centerline 16 of the second stage rocket 14 (see FIGS. 4-6).
- the converging surfaces 70, 72 of the throat 24 are discrete surfaces relative to one another.
- the diverging surfaces 64, 66 of the throat 24 are also discrete surfaces relative to one another.
- the engine 12 has a so-called “plug cluster” configuration similar to that of the prior art embodiment illustrated in FIGS. 1 and 2, for example.
- the engine 12 includes a plurality of discrete high pressure chambers 36 spaced relative to one another, and a plurality of discrete initial nozzle portions 60 spaced relative to one another.
- Each initial nozzle portion 60 is disposed relative to a corresponding high pressure chamber 36, and is configured to exhaust gas exiting the respective high pressure chamber 36.
- Each high pressure chamber 36 and initial nozzle portion 60 pair forms a so-called “thrust can.”
- the initial nozzle portion 60 of each thrust can includes a discrete throat 24 that extends annularly about an axis of the respective initial nozzle portion 60.
- the converging surfaces 70, 72 of the throat 24 form a continuous surface that extends annularly about the axis of the respective initial nozzle portion 60.
- the converging surfaces 70, 72 and/or the diverging surfaces 64, 66 are axisymmetric relative to the axis 74.
- the thrust cans are circumferentially spaced about the centerline 16 of the second stage rocket 14.
- the thrust cans are spaced linearly along a plane parallel to the centerline 16 of the second stage rocket 14 .
- the engine 12 is recessed into the base surface 38 of the second stage rocket 14 to protect portions of the engine 12 from a highly-loaded environment, such as during re-entry into the atmosphere.
- the outer expansion surface 30 of the augmented aerospike nozzle 10 which is absent in prior art aerospike nozzles, captures the flow of exhaust gas and turns it in the axial direction, generating additional thrust.
- the expansion area 40 would be a function of throat radial location 42, and further increases in expansion area 40 would require increases in throat radial location 42 resulting in very small dimensions of the throat 24 for a fixed thrust.
- the outer expansion surface 30 is integrally connected to the second stage rocket 14 via beams 39, 41 extending radially between the augmented aerospike nozzle 10 and the sidewall 43 of the second stage rocket 14.
- the beams 39, 41 also support the thrust takeout structure 78 on which the engine 10 is mounted via a gimbal 80 and a plurality of struts 82.
- the nozzle 10 includes a seal 44 (e.g., hot gas seal formed by metal bellows) that allows the centerbody 28 to gimbal while allowing the outer expansion surface 30 to remain fixed with respect to the second stage rocket 14.
- the seal 44 extends between forward end of the outer expansion surface 30 and the outer aft end 68 of the initial nozzle portion 60. In other embodiments not shown in the drawings, the seal 44 is positioned in another location (e.g., where the aft end of the outer expansion surface 30 abuts the base surface 38 of the second stage rocket 14) to permit gimballing of the entire augmented aerospike nozzle 10 (including the outer expansion surface) relative to the sidewall 43 of the second stage rocket 14.
- the engine 12 with the augmented aerospike nozzle 10 therefore provides many advantages over prior art nozzles, and does so with a form factor that is substantially shorter than other prior art nozzles.
- the approximate doubling of the nozzle expansion area ratio increases the nozzle vacuum efficiency and raises the engine specific impulse by ten or more seconds, providing in-space performance commensurate with industry-leading upper stage engines.
- the recessing of the nozzle 10 into the second stage rocket 14 improves ground clearance and reduces local heating effects.
- the remainder of the vehicle base 20 may be actively cooled using the heat shielding system disclosed in the commonly-assigned U.S. Provisional Patent Application No. 62/942,886, filed December 3, 2019, the contents of which are hereby incorporated by reference in their entirety.
- the vehicle base 20 can therefore provide a robust barrier that protects the second stage rocket 14 from surface ejecta generated when landing on unprepared planetary surfaces. These features enable the second stage rocket 14 to perform a base-first atmospheric re-entry trajectory with low-throttle terminal descent burns, and to make a soft vertical landing, with a single propulsion engine.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Engines (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
Description
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Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AU2020394317A AU2020394317A1 (en) | 2019-11-27 | 2020-08-27 | Augmented aerospike nozzle, engine including the augmented aerospike nozzle, and vehicle including the engine |
EP20893636.9A EP4042006A4 (en) | 2019-11-27 | 2020-08-27 | Augmented aerospike nozzle, engine including the augmented aerospike nozzle, and vehicle including the engine |
US17/754,787 US20240083597A1 (en) | 2019-11-27 | 2020-08-27 | Augmented Aerospike Nozzle, Engine Including the Augmented Aerospike Nozzle, and Vehicle Including the Engine |
JP2022524569A JP2023512860A (en) | 2019-11-27 | 2020-08-27 | Augmented aerospike nozzle, engine including augmented aerospike nozzle, and vehicle including engine |
CN202080076058.8A CN114930000A (en) | 2019-11-27 | 2020-08-27 | Enhanced aerodynamic tip nozzle, engine including enhanced aerodynamic tip nozzle, and vehicle including engine |
US17/407,472 US20210381469A1 (en) | 2019-11-27 | 2021-08-20 | Augmented Aerospike Nozzle, Engine Including the Augmented Aerospike Nozzle, and Vehicle Including the Engine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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US201962941386P | 2019-11-27 | 2019-11-27 | |
US62/941,386 | 2019-11-27 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US17/407,472 Continuation US20210381469A1 (en) | 2019-11-27 | 2021-08-20 | Augmented Aerospike Nozzle, Engine Including the Augmented Aerospike Nozzle, and Vehicle Including the Engine |
Publications (1)
Publication Number | Publication Date |
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WO2021108001A1 true WO2021108001A1 (en) | 2021-06-03 |
Family
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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PCT/US2020/048178 WO2021108001A1 (en) | 2019-11-27 | 2020-08-27 | Augmented aerospike nozzle, engine including the augmented aerospike nozzle, and vehicle including the engine |
Country Status (6)
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US (2) | US20240083597A1 (en) |
EP (1) | EP4042006A4 (en) |
JP (1) | JP2023512860A (en) |
CN (1) | CN114930000A (en) |
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Publication number | Priority date | Publication date | Assignee | Title |
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US11933249B2 (en) * | 2021-12-30 | 2024-03-19 | Blue Origin, Llc | Reusable upper stage rocket with aerospike engine |
CN114776462A (en) * | 2022-04-14 | 2022-07-22 | 中国航发沈阳发动机研究所 | Throat-adjustable unilateral expansion spray pipe |
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2020
- 2020-08-27 US US17/754,787 patent/US20240083597A1/en active Pending
- 2020-08-27 WO PCT/US2020/048178 patent/WO2021108001A1/en active Application Filing
- 2020-08-27 JP JP2022524569A patent/JP2023512860A/en active Pending
- 2020-08-27 CN CN202080076058.8A patent/CN114930000A/en active Pending
- 2020-08-27 EP EP20893636.9A patent/EP4042006A4/en active Pending
- 2020-08-27 AU AU2020394317A patent/AU2020394317A1/en active Pending
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2021
- 2021-08-20 US US17/407,472 patent/US20210381469A1/en active Pending
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US5463866A (en) * | 1993-12-30 | 1995-11-07 | The Boeing Company | Supersonic jet engine installation and method with sound suppressing nozzle |
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AU2020394317A1 (en) | 2022-05-26 |
CN114930000A (en) | 2022-08-19 |
US20240083597A1 (en) | 2024-03-14 |
EP4042006A1 (en) | 2022-08-17 |
EP4042006A4 (en) | 2023-10-18 |
US20210381469A1 (en) | 2021-12-09 |
JP2023512860A (en) | 2023-03-30 |
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