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公开(公告)号：EP3374723A1
公开(公告)日：2018-09-19
申请号：EP16732212.2
申请日：2016-06-21
Applicant: Raytheon Company
Inventor： VILLARREAL, James Kendall , LANGHENRY, Mark T. , DANFORTH, Jeremy C.
Abstract: A motor assembly is provided for use with projectiles, such as munitions, having relatively low length to diameter ratios. The motor assembly has an aerospike nozzle and a casing disposed about the aerospike nozzle, where interior aerospike volume contains propellant and where walls of both the cowl of the casing and of the aerospike nozzle jointly define a combustion chamber.
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公开(公告)号：EP3359796A1
公开(公告)日：2018-08-15
申请号：EP16734122.1
申请日：2016-06-22
Applicant: Raytheon Company
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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公开(公告)号：EP3850206A1
公开(公告)日：2021-07-21
申请号：EP19769681.8
申请日：2019-09-03
Applicant: Raytheon Company
Inventor： SUMMERS, Matt H. , CASE, David M. , RAYMOND, John J. , FOWLER, Gray , LANGHENRY, Mark T.
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公开(公告)号：EP3440332A1
公开(公告)日：2019-02-13
申请号：EP16788851.0
申请日：2016-10-11
Applicant: Raytheon Company
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Patent Agency Ranking
公开(公告)号：EP3778404A1
公开(公告)日：2021-02-17
申请号：EP20176085.7
申请日：2016-10-11
Applicant: Raytheon Company
Inventor： KOEHLER, Frederick B. , DANFORTH, Jeremy C. , LYMAN, Ward D. , LANGHENRY, Mark T. , SUMMERS, Matt H. , PONTIUS, Paul E. , PAPE, Brian M. , STALLINGS, Jared D. , VILLARREAL, James K. , VILLARREAL, Thomas
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：EP3374723B1
公开(公告)日：2019-12-11
申请号：EP16732212.2
申请日：2016-06-21
Applicant: Raytheon Company
Inventor： VILLARREAL, James Kendall , LANGHENRY, Mark T. , DANFORTH, Jeremy C.
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公开(公告)号：EP3433567A1
公开(公告)日：2019-01-30
申请号：EP17800960.1
申请日：2017-06-09
Applicant: Raytheon Company
Inventor： SUMMERS, Matt H. , VILLARREAL, James K. , LANGHENRY, Mark T. , DANFORTH, Jeremy C. , WALTER, John W.
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19.发明公开ELECTRICALLY CONTROLLED VARIABLE FORCE DEPLOYMENT AIRBAG AND INFLATION 审中-公开安卡拉ENTFALTUNG MIT ELEKTRISCH GESTEUERTER，KRAFTVERÄNDERLICHERAUSLÖSUNG
公开(公告)号：EP3148847A2
公开(公告)日：2017-04-05
申请号：EP15724924.4
申请日：2015-05-15
Applicant: Raytheon Company
Inventor： VILLARREAL, James K. , DEPPERT, Thomas M. , LANGHENRY, Mark T. , SUMMERS, Matt H.
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 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明超过1500psi和更高的阈值。
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