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公开(公告)号：US11879416B1
公开(公告)日：2024-01-23
申请号：US17930741
申请日：2022-09-09
申请人： Raytheon Company
CPC分类号： F02K9/90 , F02K9/80 , F42B10/64 , F42B10/66 , F42B10/665
摘要： A method of thrust vectoring a missile utilizing jet tabs is presented. Jet tabs are used to create lateral control moments on a missile by rotating tabs into the rocket exhaust plume and changing the thrust deflection angle. The method includes simultaneously rolling the missile during the thrust vector maneuver in order to reduce the maximum tab exposure to the rocket plume. The method enables aggressive pitchover maneuvers while reducing the risk of tab failure due to excessive exposure.
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公开(公告)号：US20230182928A1
公开(公告)日：2023-06-15
申请号：US17991671
申请日：2022-11-21
申请人： Maxar Space LLC
发明人： Giovanni Lenguito
摘要： A satellite propellant tank includes a tank body and a dome attached to the tank body to enclose an interior volume for propellant storage. One or more cavities are formed in the dome. One or more propellant control components are located in the one or more cavities formed in the dome.
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公开(公告)号：US11286887B2
公开(公告)日：2022-03-29
申请号：US14695082
申请日：2015-04-24
摘要： A turbine pump assembly has a turbine, a centrifugal pump, a passive electrical speed control system, and a pneumatic circuit breaker. The pneumatic circuit breaker has a plurality of elements that are configured to move to a position blocking an outlet duct of the turbine when a flow velocity exceeds a predetermined threshold. A rocket thrust vector control system is also disclosed.
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4.发明授权公开(公告)号：US11084605B2
公开(公告)日：2021-08-10
申请号：US15423909
申请日：2017-02-03
发明人： Jürgen Ramsel , Pedro Caldas-Pinto , Karl Wieland Naumann , Helmut Niedermaier , Tobias Meyer , Albert Thumann , Susanne Risse
IPC分类号： B64G1/26 , F02K9/88 , B64G1/40 , F42B10/66 , F02K9/94 , F02K9/52 , F02K9/68 , F02K9/72 , F02K9/80 , F41H11/00 , F41H11/02 , B64G1/00 , F42B10/00
摘要： Apparatus for trajectory control and/or position control of a missile (99), comprising a controllable gas generator (109, 200) with a fuel flow control valve (124, 213), an injector head (112, 202), a combustion chamber (111) and at least one outflow nozzle (103, 204) or at least one throttle.
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公开(公告)号：US10590888B2
公开(公告)日：2020-03-17
申请号：US15268737
申请日：2016-09-19
申请人： Airbus DS GmbH
发明人： Manuel Frey , Thomas Aichner , Philip Martin
摘要： A thrust nozzle, in particular thrust nozzle for a rocket engine, with a convergent wall section, a throat section and a divergent wall section. The divergent wall section has a first region adjacent to the throat section, the wall contour of which region corresponds to a truncated ideal nozzle, and the divergent wall section has a second region facing away from the throat section, which region has a wall contour deviating from the first region.
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公开(公告)号：US10386165B1
公开(公告)日：2019-08-20
申请号：US15462776
申请日：2017-03-17
发明人： Michael Levin , Jacob R. Boettcher , John Cromie , Douglas Discher , Yu Gyone Hwee , Nathan Larry Johnson , Robert Kinser , Leo Laux
摘要： A method and concept for employing a T-sin-alpha kill vehicle with energy flexibility is disclosed. The energy flexibility method applies divert pulses at multiple phases of the kill vehicle flight time and allows for range extension to increase the kill vehicle coverage of targets outside the normal reach, reaction to target updates, removal of navigation error, and homing divert to intercept the target. Each of these capabilities is essential to the successful intercept of exo-atmospheric ballistic targets in their midcourse phase of flight. A flight vehicle includes a main body, a number of attitude control mechanisms, a control unit, a divert system, a sensor unit, and an attitude control system. The divert system provides acceleration of the flight vehicle in a desired direction. The sensor unit tracks a target along a line of sight (LOS) of the sensor unit. The attitude control system maintains an orientation of the main body.
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公开(公告)号：US10385805B2
公开(公告)日：2019-08-20
申请号：US15725238
申请日：2017-10-04
申请人： ROLLS-ROYCE plc
发明人： Jack F Colebrooke
摘要： A variable geometry exhaust nozzle arrangement includes a plurality of hingable exhaust petals defining a perimeter of an exhaust duct and an annular ring slidably engagable against a radially outer surface of each petal. The annular ring is coupled to a plurality of circumferentially spaced actuator arrangements, each including first and second circumferentially spaced parallel actuator arms pivotably coupled to the annular ring at a first end and to a slide arrangement at a second end. Each slide arrangement is mounted for linear sliding movement relative to the annular ring, such that sliding movement of each slide arrangement causes pivoting of the first and second actuator arms to thereby translate the annular ring in one or both of a longitudinal direction and a lateral direction.
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公开(公告)号：US10220966B2
公开(公告)日：2019-03-05
申请号：US15091008
申请日：2016-04-05
申请人： Raytheon Company
发明人： 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
摘要： 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：US10167732B2
公开(公告)日：2019-01-01
申请号：US14695079
申请日：2015-04-24
IPC分类号： F02K9/00 , F01D21/02 , F01D17/20 , F02K9/48 , F02K9/56 , F02K9/80 , F02K9/84 , F01D5/02 , F01D9/02 , F01D15/08 , F01D15/10 , F04D17/08 , F04D27/02
摘要： A turbine pump assembly has a turbine, a centrifugal pump, and a passive electrical speed control system. The turbine has a peak efficiency at a first speed that is lower than a second speed at which the centrifugal pump is operating at a peak power requirement. A rocket thrust vector control system is also disclosed.
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公开(公告)号：US09919792B2
公开(公告)日：2018-03-20
申请号：US14322752
申请日：2014-07-02
发明人： Kevin L Zondervan , Jerome K Fuller
摘要： Attitude and/or attitude rate of a vehicle may be controlled using jet paddles and/or movable masses. Thrust direction generally may also be controlled using jet paddles. The jet paddles may be moved into and/or sufficiently close to the exhaust flow, and out of the exhaust flow, to change the thrust direction. Movable masses may also be used in addition to, or in lieu of, jet paddles. Movement of the movable masses alters a center-of-mass of the vehicle, generating torque that changes vehicle attitude.
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