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公开(公告)号：US11512668B2
公开(公告)日：2022-11-29
申请号：US17106089
申请日：2020-11-28
Applicant: Raytheon Company
Inventor： Frederick B. Koehler , Jacob A. Pinello-Benavides , Curtis S. Copeland , Isaiah M. McNeil , Paul Kadlec , Lauren E. Brunacini , Mark T. Langhenry
Abstract: A rocket motor has an electrically operated propellant initiator for a propellant grain that includes an electrode arrangement configured to concentrate an electric field at an ignition electrode for igniting an electrically operated propellant. The rocket motor includes a combustion chamber containing at least one propellant grain and an electrically operated propellant initiator operatively coupled to the propellant grain to initiate combustion of the propellant grain. The electrically operated propellant initiator includes the electrically operated propellant and at least one pair of electrodes configured to ignite the electrically operated propellant. The pair of electrodes includes a ground plane electrode and an ignition electrode. When an electrical input is applied to the electrically operated propellant initiator, the electric field is concentrated at the ignition electrode to ignite the electrically operated propellant at the location where the ignition electrode is arranged.
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公开(公告)号：US20210062764A1
公开(公告)日：2021-03-04
申请号：US16545474
申请日：2019-08-20
Applicant: Raytheon Company
Inventor： Louis J. Gullo , Mark T. Langhenry , Thomas R. Berger
Abstract: An effector health monitor system is configured for coupling with an energetic component. The effector health monitor system includes a characteristic sensor suite including at least first and second characteristic sensors. The first characteristic sensor is proximate to the energetic component and configured to measure a failure characteristic of the energetic component. The second characteristic sensor is configured to measure at least one environmental characteristic proximate to the energetic component. A communication hub is coupled with the first and second characteristic sensors, and is configured to communicate the measured failure and environmental characteristics outside of an effector body. A failure identification module compares the measured failure characteristic with a failure threshold and identifies a failure event. A failure model generation module logs the at least one measured environmental characteristic preceding the identified failure event with the identified failure event and generates a failure model including updating the failure model.
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公开(公告)号：US20200024210A1
公开(公告)日：2020-01-23
申请号：US16226741
申请日：2018-12-20
Applicant: Raytheon Company
Inventor： Matthew H. Summers , Jeremy C. Danforth , David G. Garrett , Mark T. Langhenry
Abstract: A system is used for additively manufacturing propellant elements, such as for rocket motors, includes partially curing a propellant mixture before extruding or otherwise dispensing the material, such that the extruded propellant material is deposited on the element in a partially-cured state. The curing process for the partially-cured extruded material may be completed shortly after the material is put into place, for example by the material being heated at or above its cure temperature, such that it finishes curing before it fully cools. The propellant material may be prepared by first mixing together, a fuel, an oxidizer, and a binder, such as in an acoustic mixer. After that mixing a curative may be added to the mixture. The propellant mixture may then be directed to an extruder (or other dispenser), in which the mixture is heated to or above a cure temperature prior to the deposition, and then deposited.
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公开(公告)号：US20170284339A1
公开(公告)日：2017-10-05
申请号：US15091245
申请日：2016-04-05
Applicant: Raytheon Company
Inventor： Frederick B. Koehler , Jeremy C. Danforth , Ward D. Lyman , Mark T. Langhenry , Matt H. Summers , Paul E. Pontius , Brian M. Pape , Jared D. Stallings , James K. Villarreal , Thomas Villarreal
IPC: F02K9/28
Abstract: A thruster includes multiple segments of electrically-operated propellant, electrodes for igniting one or a few of the electrically-operated propellant segments at a time, and a propellant feeder for moving further propellant segments into engagement with the electrodes. The segments may be configured to provide equal increments of thrust, or different amounts of thrust. The segments may each include an electrically-operated propellant material surrounded by a sealing material, so as to keep the propellant material away from moisture and other contaminants (and/or the vacuum of space) before each individual segment is to be used. The thruster may be included in any of a variety of flight vehicles, for example in a small satellite such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.
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公开(公告)号：US20170097213A1
公开(公告)日：2017-04-06
申请号：US14875741
申请日：2015-10-06
Applicant: Raytheon Company
Inventor： James Kendall Villarreal , Mark T. Langhenry , Matt H. Summers , Daniel V. Macinnis
IPC: F42B3/04
Abstract: A gas generation system for generating gases, such as for use as or as part of a rocket motor in propelling a projectile, includes two or more propellant charges and electrically operated propellant initiators operatively coupled to respective of the propellant charges, to initiate combustion in the propellant charges, wherein the propellant charges are operatively isolated from one another such that the propellant charges can be individually initiated and are not ignited due to gases generated from other of the propellant charges being combusted.
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Patent Agency Ranking
公开(公告)号：US20160355447A1
公开(公告)日：2016-12-08
申请号：US14729429
申请日：2015-06-03
Applicant: Raytheon Company
Inventor： Jeremy C. Danforth , Mark T. Langhenry , Matt H. Summers , Teresa Perdue
CPC classification number: C06B45/10 , B33Y10/00 , B33Y80/00 , C06B21/0033 , F02K9/12 , F05D2230/31
Abstract: A combustible element includes regions of fuel material interspersed with regions of oxidizer material. The element may be made by additive manufacturing processes, such as three-dimensional printing, with the fuel material regions and the oxidizer material regions placed in appropriate locations in layer of the combustible element. For example, different extruders may be used to extrude and deposit portions of a fuel filament and an oxidizer filament at different locations in each layer of the combustible element. The combustible element may define a combustion chamber within the element, where combustion occurs when the combustible element is ignited. The fuel material and the oxidizer material may be selected, and their relative amounts may be controlled, such that desired relative amounts of fuel and oxidizer are present for combustion with desired characteristics, such as combustion rate.
Abstract translation: 可燃元件包括散布有氧化剂材料区域的燃料材料区域。 该元件可以通过添加剂制造工艺（例如三维印刷）制成，其中燃料材料区域和氧化剂材料区域放置在可燃元件的层中的适当位置。 例如，可以使用不同的挤出机来挤出和沉积燃料丝和氧化剂丝的部分在可燃元件的每层中的不同位置。 可燃元件可以在元件内限定燃烧室，其中当可燃元件被点燃时发生燃烧。 可以选择燃料材料和氧化剂材料，并且可以控制它们的相对量，使得燃烧所需的相对量的燃料和氧化剂存在于具有所需特性如燃烧速率的燃烧中。
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公开(公告)号：US11208362B2
公开(公告)日：2021-12-28
申请号：US16226741
申请日：2018-12-20
Applicant: Raytheon Company
Inventor： Matthew H. Summers , Jeremy C. Danforth , David G. Garrett , Mark T. Langhenry
IPC: B29C64/165 , B33Y30/00 , B33Y40/00 , B29B7/00 , C06B21/00 , B33Y10/00 , B33Y70/00 , B33Y80/00 , B29K23/00 , B29K505/00 , B29L31/20 , B29L31/30
Abstract: A system is used for additively manufacturing propellant elements, such as for rocket motors, includes partially curing a propellant mixture before extruding or otherwise dispensing the material, such that the extruded propellant material is deposited on the element in a partially-cured state. The curing process for the partially-cured extruded material may be completed shortly after the material is put into place, for example by the material being heated at or above its cure temperature, such that it finishes curing before it fully cools. The propellant material may be prepared by first mixing together, a fuel, an oxidizer, and a binder, such as in an acoustic mixer. After that mixing a curative may be added to the mixture. The propellant mixture may then be directed to an extruder (or other dispenser), in which the mixture is heated to or above a cure temperature prior to the deposition, and then deposited.
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公开(公告)号：US11174048B2
公开(公告)日：2021-11-16
申请号：US16266520
申请日：2019-02-04
Applicant: Raytheon Company
Inventor： Frederick B. Koehler , Jeremy C. Danforth , Ward D. Lyman , Mark T. Langhenry , Matt H. Summers , Paul E. Pontius , Brian M. Pape , Jared D. Stallings , James K. Villarreal , Thomas Villarreal
IPC: B64G1/40 , F02K9/24 , F02K9/95 , B33Y80/00 , B64G1/26 , F02K9/80 , B64G1/10 , F02K99/00 , F02K9/94 , B33Y70/00
Abstract: A satellite has thrusters that are integral parts of its frame. The frame defines cavities therein where thrusters are located. The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant. The frame may be additively manufactured, and the propellant and/or the electrodes may also be additively manufactured, with the frame and the propellant and/or the electrodes also being manufactured in a single process. In addition the thrusters may have nozzle portions through which combustion gases exit the thrusters. The thrusters may be located at corners and/or along edges of the frame, and may be used to accomplish any of a variety of maneuvers for the satellite. The satellite may be a small satellite, such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.
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公开(公告)号：US10808649B2
公开(公告)日：2020-10-20
申请号：US15240932
申请日：2016-08-18
Applicant: Raytheon Company
Inventor： James K. Villarreal , Jeremy C. Danforth , Matt H. Summers , Daniel K. Johnson , Mark T. Langhenry
Abstract: Microwave energy is used to ignite and control the ignition of electrically operated propellant to produce high-pressure gas. The propellant includes conductive particles that act as a free source of electrons. Incoming microwave energy accumulates electric charge in an attenuation zone, which is discharged in the form of dielectric breakdowns to create local randomly oriented currents. The propellant also includes polar molecules. The polar molecules in the attenuation zone absorb microwave energy causing the molecules to rapidly vibrate thereby increasing the temperature of the propellant. The increase in temperature and the local current densities together establish an ignition condition to ignite and sustain ignition of an ignition surface of the attenuation zone as the zone regresses without igniting the remaining bulk of the propellant.
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公开(公告)号：US20200024003A1
公开(公告)日：2020-01-23
申请号：US16266520
申请日：2019-02-04
Applicant: Raytheon Company
Inventor： Frederick B. Koehler , Jeremy C. Danforth , Ward D. Lyman , Mark T. Langhenry , Matt H. Summers , Paul E. Pontius , Brian M. Pape , Jared D. Stallings , James K. Villarreal , Thomas Villarreal
Abstract: A satellite has thrusters that are integral parts of its frame. The frame defines cavities therein where thrusters are located. The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant. The frame may be additively manufactured, and the propellant and/or the electrodes may also be additively manufactured, with the frame and the propellant and/or the electrodes also being manufactured in a single process. In addition the thrusters may have nozzle portions through which combustion gases exit the thrusters. The thrusters may be located at corners and/or along edges of the frame, and may be used to accomplish any of a variety of maneuvers for the satellite. The satellite may be a small satellite, such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.
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