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公开(公告)号：US12098110B2
公开(公告)日：2024-09-24
申请号：US15762761
申请日：2016-11-15
发明人： Daniel Doll , Scott K. Dawley
摘要： A solid rocket propellant includes a hydroxyl-terminated polybudadiene (HTPB) binder system having a high molecular weight diol that is greater than thirty carbon atoms (>C30) and less than fifty carbon atoms (
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公开(公告)号：US12031506B2
公开(公告)日：2024-07-09
申请号：US17770156
申请日：2019-12-10
发明人： Larry Coady
IPC分类号： F02K9/58
CPC分类号： F02K9/58 , F05D2260/42 , F05D2270/301 , F05D2270/52
摘要： 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：US20230294846A1
公开(公告)日：2023-09-21
申请号：US18014404
申请日：2020-07-10
发明人： Brian A. Koch
摘要： A spacecraft propulsion system including a first thruster system including a first power processing unit connected to a first thruster string via a crossover switching unit and connected to a second thruster string via the crossover switching unit. A second thruster system including a second power processing unit connected to the second thruster string via the crossover switching unit and to the first thruster string via the crossover switching unit. A controller is connected to each of the first power processing unit, the second power processing unit, and the crossover switching unit.
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公开(公告)号：US20230265955A1
公开(公告)日：2023-08-24
申请号：US17920456
申请日：2020-04-24
发明人： David Meyer , Mario Padilla , Gary Grenon
CPC分类号： F16L37/148 , F16K15/033 , F16K27/0227
摘要： A valve device (20) includes male and female housings (22, 24) that together define a fluid through-passage (28). The male and female housings have, respectively, exterior and interior annular channels (22a, 24a). The male housing is receivable into the female housing such that the exterior and interior annular channels together define a toroidal tube. First and second valve elements (30,32) are disposed, respectively, in the male and female housings. Ball locks (36) are receivable into the toroidal tube and axially lock the male and female housings together. A lock (40) engageable when the first and second valve elements are in functional alignment and which when engaged rotationally locks the male and female housings.
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公开(公告)号：US11312814B2
公开(公告)日：2022-04-26
申请号：US15762745
申请日：2016-09-30
发明人： Daniel Doll , Scott Dawley
IPC分类号： C08G18/62 , C08G18/10 , C06B45/10 , C08L83/08 , C08G18/61 , C08G18/38 , C08G18/48 , C06B23/00 , C08G18/77 , F02K9/08 , F02K9/97
摘要： A solid rocket propellant includes a binder that has hydroxyl-terminated polybudadiene (HTPB) with a curative that is selected from isocyanate-terminated polyether, isocyanate-terminated polysiloxane, or combinations thereof.
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公开(公告)号：US11236703B2
公开(公告)日：2022-02-01
申请号：US15580051
申请日：2015-06-30
发明人： Matthew Dawson , Gerald Brewster
摘要： A catalytic thruster includes a reaction chamber that extends between first and second opposed chamber ends. The first chamber end includes a thermal standoff cup. There is a catalyst bed in the reaction chamber, and a feed tube extends into the reaction chamber through the thermal standoff cup.
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公开(公告)号：US20210164453A1
公开(公告)日：2021-06-03
申请号：US16771026
申请日：2017-12-19
发明人： Justin Pucci
IPC分类号： F03H1/00
摘要： A Hall thruster includes an annular discharge region and an annular cathode concentric to the annular discharge region.
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公开(公告)号：US10954892B2
公开(公告)日：2021-03-23
申请号：US16302159
申请日：2017-06-15
摘要： A liquid propellant rocket engine includes a combustion chamber that has a throat and a nozzle aft of the throat. The nozzle has a first nozzle section adjacent the throat and a second nozzle section aft of the first nozzle section. The first nozzle section includes active cooling features and the second nozzle section excludes any active cooling features. The first nozzle section is operative via at least the active cooling features to form a condensate that passively cools the second nozzle section.
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公开(公告)号：US10934026B2
公开(公告)日：2021-03-02
申请号：US15762176
申请日：2015-10-19
发明人： Ronald Corey
摘要： A propulsion system includes at least one group of electric thrusters that are spatially distributed in a multi-axis system. A controller is in communication with each of the electric thrusters. The controller is configured to differentially throttle the thrusts of the electric thrusters with respect to propulsion force about two axes of the multi-axis system.
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公开(公告)号：US10859068B2
公开(公告)日：2020-12-08
申请号：US15305176
申请日：2014-06-02
摘要： A circuit (400, 700, 800) comprising: a first power source (402) supplying first current to a load (470) during a first Period of Time (“PoT”); a second power source (416) supplying a second current to the load during a second POT; a Unidirectional Current Valve (“UCV”) in series with the first power source; a current detector (420, 702, 802) in series with the UCV (422); and a switch (424) in parallel with a series combination of the current detector and UCV to bypass the UCV during the second PoT. The current detector determines whether the second period of time has commenced and whether the switch has closed.
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