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公开(公告)号：US12030274B2
公开(公告)日：2024-07-09
申请号：US17782772
申请日：2020-02-20
Applicant: AEROJET ROCKETDYNE, INC.
Inventor： Russell A. Ellis , Jeffrey D. Haynes
CPC classification number: B32B1/08 , B32B5/10 , B32B5/12 , B32B9/007 , B32B2250/20 , B32B2262/105 , B32B2262/106 , B32B2262/12 , B32B2305/08 , B32B2305/18 , B32B2313/04 , B32B2315/02 , B32B2605/08
Abstract: An article includes a completed fabric structure that has multiple plies of fiber reinforced fabric. A first portion of the fabric structure has a three-directional fiber reinforced configuration and, exclusive of the first portion, a second portion of the fabric structure having a two-directional fiber reinforced configuration. In the three-directional fiber reinforced configuration there are multiple plies that are bound together via a matrix and a plurality of fibers normal through the multiple plies. In the two-directional fiber reinforced configuration the multiple plies are bound to one another via the matrix and not fibers normal through the multiple plies.
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公开(公告)号：US11635045B2
公开(公告)日：2023-04-25
申请号：US16316685
申请日：2017-06-29
Applicant: Aerojet Rocketdyne, Inc.
Inventor： Douglas S. Parker , Daniel P. Cap , Frederick E. Dodd
IPC: F02K9/52
Abstract: An injector element for a liquid propellant rocket engine includes an oxidizer conduit, a central cavity that is fluidly coupled with the oxidizer conduit downstream of the oxidizer conduit, a first annulus that at least partially surrounds the oxidizer conduit and is fluidly coupled with an ignition fluid supply downstream of the ignition fluid supply, and a second annulus that at least partially surrounds the oxidizer conduit and is fluidly coupled with a fuel supply downstream of the fuel supply. The second annulus is fluidly coupled between the first annulus and the central cavity.
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公开(公告)号：US20220389885A1
公开(公告)日：2022-12-08
申请号：US17770156
申请日：2019-12-10
Applicant: Aerojet Rocketdyne, Inc.
Inventor： Larry Coady
IPC: F02K9/58
Abstract: A liquid fuel rocket engine according to one example includes a combustor, a liquid fuel repository connected to the combustor via a fuel line and a first valve, an oxidizer repository connected to the combustor via an oxidizer line and a second valve, a valve controller configured to output a valve control current to the first valve, the valve controller storing instructions for determining at least one actual minimum impulse bit of a valve based on a current profile and a voltage profile of a single operation of the first valve, and to adjust valve controls to account for the at least one actual minimum impulse bit.
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公开(公告)号：US20220024836A1
公开(公告)日：2022-01-27
申请号：US17311411
申请日：2019-01-24
Applicant: AEROJET ROCKETDYNE, INC.
Inventor： Robert K. Masse
IPC: C06B47/08
Abstract: The hydrazine-containing composition is a liquid mixture that includes from 5 mol % to 95 mol % of unprotonated hydrazine selected from hydrazine, monomoethylhydrazine, dimethylhydrazine, ethylhydrazine, and combinations thereof, and from 5 mol % to 90 mol % of at least one oxygen-containing solute or solvent selected from acetals, acetyls, alcoxyamines having two or more carbon atoms, aldehydes, amides, amides and particularly carboxamides, aminoalcohols, carbazides, semicarbazides, carbon-containing nitrate salts comprising cations with logarithmic dissociation constants less than 9.2, hydroxyalkyl nitro compounds, hydroxyalkylhydrazines, carbonates, carboxylic acids and anhydrides of carboxylic acids, esters, ethers, ketals, ketones, mono- and poly-alcohols in 31% or greater mass fraction, nitrate esters, nitrosamines, sugars, and combinations thereof. The unprotonated hydrazine has a first vapor pressure and the oxygen-containing solvent has a second vapor pressure that is less than the first vapor pressure.
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公开(公告)号：US11162988B2
公开(公告)日：2021-11-02
申请号：US16768472
申请日：2017-12-04
Applicant: Aerojet Rocketdyne, Inc.
Inventor： Bryce L. Hesterman
Abstract: An impedance measurement circuit includes a signal injector having a voltage input and a voltage output, a controllable switch, and a voltage drop device connected in parallel with the controllable switch between the voltage input and the voltage output. The voltage output is connected to a load. A voltage sensor is configured to measure a voltage across the load. A current sensor is configured to measure a current draw of the load. A computing device is configured to determine an impedance of the load at a frequency based on the measured voltage and the measured current. The computing device controls the switch based on the frequency.
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Patent Agency Ranking
公开(公告)号：US20210003138A1
公开(公告)日：2021-01-07
申请号：US16767820
申请日：2018-10-12
Applicant: Aerojet Rocketdyne, Inc.
Abstract: A pump includes an axial inducer. The axial inducer includes a housing that has an internal surface that defines an axial fluid passage. A rotor is disposed about a central axis in the fluid passage. The rotor includes at least one blade that defines at least one blade tip. The internal surface of the housing defines a plurality of grooves adjacent the at least one blade tip. The grooves are elongated in a circumferential direction.
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公开(公告)号：US10570069B2
公开(公告)日：2020-02-25
申请号：US14794758
申请日：2015-07-08
Applicant: Aerojet Rocketdyne, Inc.
Inventor： Scott K. Dawley , Mark Peyser Friedlander
Abstract: An end-burning grain of a solid rocket motor or other gas-generating device is supplemented with one or more sticks of high-burn-rate propellant embedded in a matrix of a relatively low-burn-rate propellant. The sticks increase the burning surface area as the grain burns by forming conical indentations in the surface.
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公开(公告)号：US20190153980A1
公开(公告)日：2019-05-23
申请号：US16316685
申请日：2017-06-29
Applicant: Aerojet Rocketdyne, Inc.
Inventor： Douglas S. Parker , Daniel P. Cap , Frederick E. Dodd
IPC: F02K9/52
Abstract: An injector element for a liquid propellant rocket engine includes an oxidizer conduit, a central cavity that is fluidly coupled with the oxidizer conduit downstream of the oxidizer conduit, a first annulus that at least partially surrounds the oxidizer conduit and is fluidly coupled with an ignition fluid supply downstream of the ignition fluid supply, and a second annulus that at least partially surrounds the oxidizer conduit and is fluidly coupled with a fuel supply downstream of the fuel supply. The second annulus is fluidly coupled between the first annulus and the central cavity.
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公开(公告)号：US20190153955A1
公开(公告)日：2019-05-23
申请号：US16316703
申请日：2017-07-26
Applicant: Aerojet Rocketdyne, Inc.
Inventor： Neil H. Orr
Abstract: A liquid propellant rocket engine includes a pump that is disposed along a central axis. The pump includes a purge system, a collection annulus in fluid communication with the purge system, and a drain. The collection annulus has an outer diameter wall, an inner diameter wall, and an end wall. The end wall defines an annular channel that has a channel depth that varies circumferentially. The drain opens to the collection annulus. At the drain, the annular channel has a lowest point at which the channel depth is maximum depth.
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公开(公告)号：US20180223770A1
公开(公告)日：2018-08-09
申请号：US15506480
申请日：2015-09-10
Applicant: Aerojet Rocketdyne, Inc.
Inventor： Michael Douglas Lynch
IPC: F02K9/14 , F02K9/24 , B33Y80/00 , B33Y10/00 , B29C64/165
CPC classification number: F02K9/14 , B29C64/106 , B29C64/165 , B29K2027/06 , B29L2009/00 , B29L2031/3097 , B33Y10/00 , B33Y70/00 , B33Y80/00 , F02K9/24
Abstract: A rocket motor includes a nozzle and a solid propellant section in communication with the nozzle. The solid propellant section includes a first energetic grain layer that has a top surface and a bottom surface, and a second energetic grain layer that has a top surface and a bottom surface. The second layer is located on top of the first layer. The bottom surface of the second energetic grain layer partially abuts the top surface of the first energetic grain layer, and the bottom surface of the second energetic grain layer and the top surface of the first energetic grain layer define a micro-void therebetween.
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