-
公开(公告)号：US20140096510A1
公开(公告)日：2014-04-10
申请号：US13647599
申请日：2012-10-09
Applicant: RAYTHEON COMPANY
Inventor： Daniel Chasman , Stephen D. Haight , James K. Villarreal
CPC classification number: F02K9/30 , F02K9/97 , F02K9/972 , Y10T29/49346
Abstract: An apparatus includes a slotted multi-nozzle grid with a plate having multiple elongated slotlettes through the plate. Each of at least some of the slotlettes has a convergent input, a divergent output, and a narrower throat portion separating the convergent input and the divergent output. At least some of the slotlettes are arranged in multiple rows. The plate further includes multiple cooling channels through the plate. At least some of the cooling channels are located between the rows of slotlettes. Each cooling channel is configured to transport coolant through the plate in order to cool the plate, such as to cool the plate as hot combustion gases pass through the plate. Each of at least some of the rows may include at least two slotlettes, and two adjacent slotlettes in one row may be separated by a structural ligament (which may have a tear-drop cross-sectional shape).
Abstract translation: 一种装置包括带槽的多喷嘴格栅，其具有穿过该板的具有多个细长槽的板。 至少一些小缝隙中的每一个具有收敛输入，发散输出和分离收敛输入和发散输出的较窄喉部。 至少一些小行星排列成多行。 板还包括穿过板的多个冷却通道。 至少一些冷却通道位于行槽之间。 每个冷却通道被构造成运输冷却剂通过板以便冷却板，例如当热燃气通过板时冷却板。 至少一些行中的每一行可以包括至少两个开槽元件，并且一行中的两个相邻的开槽元件可以被结构韧带（其可能具有泪滴横截面形状）分开。
-
公开(公告)号：US10220966B2
公开(公告)日：2019-03-05
申请号：US15091008
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
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.
-
公开(公告)号：US10220809B2
公开(公告)日：2019-03-05
申请号：US15214996
申请日：2016-07-20
Applicant: Raytheon Company
Inventor： Richard D. Loehr , James K. Villarreal
IPC: B60R21/264 , F42B3/04 , B60R21/00 , F42B3/14 , F42B3/12 , F42C19/08 , F42C19/12 , C06B33/06 , C06D5/06 , C06C9/00
Abstract: The rate of combustion of an electrically operated propellant having a self-sustaining threshold of at least 1,000 psi is controlled to produce chamber pressures that are sufficient to produce a desired pressure profile in the airbag to accommodate a range of human factors and crash conditions yet never exceeding the self-sustaining threshold. The combustion of the propellant is extinguished to control the total pressure impulse delivered to the airbag. Propellants formed with an ionic perchlorate-based oxidizer have demonstrated thresholds in excess of 1,500 psi and higher.
-
14.发明申请公开(公告)号：US20180273193A1
公开(公告)日：2018-09-27
申请号：US15469026
申请日：2017-03-24
Applicant: Raytheon Company
Inventor： Matt H. Summers , Frederick B. Koehler , James K. Villarreal , Mark T. Langhenry
CPC classification number: B64D27/023 , B64C2201/046 , B64C2201/167 , B64D31/02 , B64G1/403 , B64G1/404 , C06B33/06 , C06D5/06 , F02K9/08 , F02K9/94 , F02K9/95 , F02K9/97 , F05D2220/80 , F05D2240/35
Abstract: Electrically operated propellant thrust assist supplements an airplane's takeoff, landing or inflight maneuvers. Unlike conventional SRM propellants, the burn rate of the electrically operated propellant can be varied via an electrical input and even extinguished by interrupting the electrical to control a secondary thrust profile (e.g., amplitude, transition rates) to fulfill the needs of a given takeoff, inflight or landing maneuver and provide a smooth transition in and out of the maneuver. Multiple pairs of fixed thrusters (opposite sides of the fuselage), a single pair of gimbaled thrusters or a hybrid of fixed and gimbaled thrusters may be configured to provide all such maneuvers. Flight control inputs are passed back and forth through an interface to enable the thrust assist.
-
公开(公告)号：US20180058377A1
公开(公告)日：2018-03-01
申请号：US15247194
申请日：2016-08-25
Applicant: Raytheon Company
Inventor： James K. Villarreal , Thomas W. Villarreal , Frederick B. Koehler , Mark T. Langhenry , Matt H. Summers
Abstract: An actuator produces a displacement that maintains positive contact between an electrically operated propellant and a pair of electrodes to ignite and sustain combustion of an ignition surface. The electrodes are suitably configured such that current lines between the electrodes follow equipotential surfaces through the propellant. The displacement drives a contour of the ignition surface to substantially match an equipotential surface corresponding to a maximum and uniform current density J at a minimum gap between the electrodes to ignite and combust the entire ignition surface. The flat, angled or curved contact areas of the electrodes are suitably symmetric about a plane.
-
Patent Agency Ranking
公开(公告)号：US20180051657A1
公开(公告)日：2018-02-22
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
CPC classification number: F02K9/95 , C06B23/00 , C06B27/00 , C06B29/00 , C06B45/10 , F02K9/08 , F02K9/94
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.
-
17.发明申请ELECTRICALLY OPERATED PROPELLANTS WITH ELEVATED SELF-SUSTAINING THRESHOLD PRESSURES 审中-公开电动自动运行的推进器，带有高度自动保压的压力公开(公告)号：US20160325708A1
公开(公告)日：2016-11-10
申请号：US15214996
申请日：2016-07-20
Applicant: Raytheon Company
Inventor： Richard D. Loehr , James K. Villarreal
IPC: B60R21/264
CPC classification number: B60R21/2644 , B60R21/00 , B60R21/264 , C06B33/06 , C06C9/00 , C06D5/06 , F42B3/04 , F42B3/128 , F42B3/14 , F42C19/0823 , F42C19/12
Abstract: The rate of combustion of an electrically operated propellant having a self-sustaining threshold of at least 1,000 psi is controlled to produce chamber pressures that are sufficient to produce a desired pressure profile in the airbag to accommodate a range of human factors and crash conditions yet never exceeding the self-sustaining threshold. The combustion of the propellant is extinguished to control the total pressure impulse delivered to the airbag. Propellants formed with an ionic perchlorate-based oxidizer have demonstrated thresholds in excess of 1,500 psi and higher.
Abstract translation: 控制具有至少1,000psi的自持阈值的电动推进剂的燃烧速率以产生足以在气囊中产生期望压力分布的腔室压力以适应一系列人为因素和碰撞状况，但从未 超过自我维持的门槛。 推进剂的燃烧熄灭，以控制输送到气囊的总压力脉冲。 用离子高氯酸盐基氧化剂形成的推进剂已经证实超过1500psi或更高的阈值。
-
公开(公告)号：US20150343988A1
公开(公告)日：2015-12-03
申请号：US14289513
申请日：2014-05-28
Applicant: Raytheon Company
Inventor： James K. Villarreal , Thomas M. Deppert , Mark T. Langhenry , Matt H. Summers
IPC: B60R21/264
CPC classification number: B60R21/2644 , B60R21/00 , C06B33/06 , C06C9/00 , C06D5/06 , F42B3/04 , F42B3/128 , F42B3/14 , F42C19/0823 , F42C19/12
Abstract: The rate of combustion of an electrically operated propellant having self-sustaining threshold of at least 1,000 psi is controlled to produce chamber pressures that are sufficient to produce a desired pressure profile in the airbag to accommodate a range of human factors and crash conditions yet never exceeding the self-sustaining threshold. The combustion of the propellant is extinguished to control the total pressure impulse delivered to the airbag. Propellants formed with an ionic perchlorate-based oxidizer have demonstrated thresholds in excess of 1,500 psi and higher.
Abstract translation: 控制具有至少1,000psi的自持阈值的电动推进剂的燃烧速率以产生足以在气囊中产生所需压力分布的腔室压力，以适应一系列人为因素和碰撞条件，但从未超过 自我维持的门槛。 推进剂的燃烧熄灭，以控制输送到气囊的总压力脉冲。 用离子高氯酸盐基氧化剂形成的推进剂已经证实超过1500psi或更高的阈值。
-
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.
-
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.
-
-
-
-
-
-
-
-
-
Search Results
23
records
(took 0.016 seconds)
