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公开(公告)号：US20230073547A1
公开(公告)日：2023-03-09
申请号：US17466245
申请日：2021-09-03
Applicant: Raytheon Company
Inventor： Jacob Pinello-Benavides , John Meschberger , Stephen Moore , Edward Little, III
Abstract: A propulsion system includes multiple solid rocket motors that are activated by a single initiator. The rocket motors act in parallel, providing thrust in a single direction. The initiator activates an ignition charge that is in or operatively coupled to a plenum that transports hot gasses from the ignition charge to the rockets to be ignited. The plenum may be an annular plenum, which may be located in an annular manifold. The plenum may be an unchoked plenum, allowing flow of hot gasses without choking. The plenum may be lined with an insulator material. A cover may be used to cover the plenum, and also to receive the rocket motors. The rocket motors may be solid-fuel rocket motors. The individual rocket motors may have separate ignition booster charges coupled to the plenum, which are ignited by the ignition charge and which in turn ignite the propellant grains.
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公开(公告)号：US11732677B2
公开(公告)日：2023-08-22
申请号：US17181162
申请日：2021-02-22
Applicant: Raytheon Company
Inventor： Ryan Starkey , Dario N. Altamirano , John Meschberger
CPC classification number: F02K9/97 , B64G1/403 , F02K9/08 , F02K9/32 , F02K9/34 , F02K9/763 , F02K9/88
Abstract: A rocket booster has an annular shape, with a casing defining an annular space therewithin, and a solid rocket fuel in the annular spacing. The rocket booster also includes one or more nozzle pieces, mechanically coupled to the casing, that define one or more nozzles at the aft side of the rocket booster. The rocket booster may be mechanically coupled to an object protruding from the back of a fuselage of a flight vehicle, such as a missile. For example, the rocket booster may be placed around an aft turbojet nozzle of the flight vehicle. This allows the rocket booster to be used in situations where primary propulsion must be running both before and after (and perhaps during) the firing of the rocket booster.
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公开(公告)号：US11846252B2
公开(公告)日：2023-12-19
申请号：US17466113
申请日：2021-09-03
Applicant: Raytheon Company
Inventor： Edward Little, III , Bryce Chanes , Jacob Pinello-Benavides , John Meschberger
Abstract: A power generation system includes a manifold having multiple plenums, capable of receiving multiple solid rocket motors. Initiators are coupled to the manifold, and are operatively coupled to respective of the plenums, to selectively fire different groups of the rocket motors coupled to respective of the plenums. The rocket motors act in parallel, to provide thrust in a single direction. The initiators may activate ignition charges that are in the plenums. The plenums may be annular plenums, which may be located in an annular manifold. The plenums may be lined with an insulator material. A cover may be used to cover the plenums, and also to receive the rocket motors. The rocket motors may be solid-fuel rocket motors, with propellant grains and nozzles. The individual rocket motors may have separate ignition booster charges coupled to the plenum, which are ignited by the ignition charge.
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Patent Agency Ranking
公开(公告)号：US11643997B2
公开(公告)日：2023-05-09
申请号：US17466248
申请日：2021-09-03
Applicant: Raytheon Company
Inventor： Jacob Pinello-Benavides , John Meschberger , Stephen Moore , Edward Little, III
Abstract: A propulsion system includes multiple solid rocket motors that are activated by a single initiator. The rocket motors act in parallel, providing thrust in a single direction. The initiator activates an ignition charge that is in or operatively coupled to a non-annular plenum that transports hot gasses from the ignition charge to the rockets to be ignited. The plenum may be an unchoked plenum, allowing flow of hot gasses without choking. The plenum may be lined with an insulator material. A cover may be used to cover the plenum, and also to receive the rocket motors. The rocket motors may be solid-fuel rocket motors, with propellant grains and nozzles. The individual rocket motors may have separate ignition booster charges coupled to the plenum, which are ignited by the ignition charge and which in turn ignite the propellant grains.
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公开(公告)号：US11852104B2
公开(公告)日：2023-12-26
申请号：US17466245
申请日：2021-09-03
Applicant: Raytheon Company
Inventor： Jacob Pinello-Benavides , John Meschberger , Stephen Moore , Edward Little, III
Abstract: A propulsion system includes multiple solid rocket motors that are activated by a single initiator. The rocket motors act in parallel, providing thrust in a single direction. The initiator activates an ignition charge that is in or operatively coupled to a plenum that transports hot gasses from the ignition charge to the rockets to be ignited. The plenum may be an annular plenum, which may be located in an annular manifold. The plenum may be an unchoked plenum, allowing flow of hot gasses without choking. The plenum may be lined with an insulator material. A cover may be used to cover the plenum, and also to receive the rocket motors. The rocket motors may be solid-fuel rocket motors. The individual rocket motors may have separate ignition booster charges coupled to the plenum, which are ignited by the ignition charge and which in turn ignite the propellant grains.
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公开(公告)号：US20220268240A1
公开(公告)日：2022-08-25
申请号：US17181162
申请日：2021-02-22
Applicant: Raytheon Company
Inventor： Ryan Starkey , Dario N. Altamirano , John Meschberger
Abstract: A rocket booster has an annular shape, with a casing defining an annular space therewithin, and a solid rocket fuel in the annular spacing. The rocket booster also includes one or more nozzle pieces, mechanically coupled to the casing, that define one or more nozzles at the aft side of the rocket booster. The rocket booster may be mechanically coupled to an object protruding from the back of a fuselage of a flight vehicle, such as a missile. For example, the rocket booster may be placed around an aft turbojet nozzle of the flight vehicle. This allows the rocket booster to be used in situations where primary propulsion must be running both before and after (and perhaps during) the firing of the rocket booster.
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公开(公告)号：US20230072320A1
公开(公告)日：2023-03-09
申请号：US17466113
申请日：2021-09-03
Applicant: Raytheon Company
Inventor： Edward Little, III , Bryce Chanes , Jacob Pinello-Benavides , John Meschberger
Abstract: A power generation system includes a manifold having multiple plenums, capable of receiving multiple solid rocket motors. Initiators are coupled to the manifold, and are operatively coupled to respective of the plenums, to selectively fire different groups of the rocket motors coupled to respective of the plenums. The rocket motors act in parallel, to provide thrust in a single direction. The initiators may activate ignition charges that are in the plenums. The plenums may be annular plenums, which may be located in an annular manifold. The plenums may be lined with an insulator material. A cover may be used to cover the plenums, and also to receive the rocket motors. The rocket motors may be solid-fuel rocket motors, with propellant grains and nozzles. The individual rocket motors may have separate ignition booster charges coupled to the plenum, which are ignited by the ignition charge.
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公开(公告)号：US20230071915A1
公开(公告)日：2023-03-09
申请号：US17466248
申请日：2021-09-03
Applicant: Raytheon Company
Inventor： Jacob Pinello-Benavides , John Meschberger , Stephen Moore , Edward Little, III
IPC: F02K9/76
Abstract: A propulsion system includes multiple solid rocket motors that are activated by a single initiator. The rocket motors act in parallel, providing thrust in a single direction. The initiator activates an ignition charge that is in or operatively coupled to a non-annular plenum that transports hot gasses from the ignition charge to the rockets to be ignited. The plenum may be an unchoked plenum, allowing flow of hot gasses without choking. The plenum may be lined with an insulator material. A cover may be used to cover the plenum, and also to receive the rocket motors. The rocket motors may be solid-fuel rocket motors, with propellant grains and nozzles. The individual rocket motors may have separate ignition booster charges coupled to the plenum, which are ignited by the ignition charge and which in turn ignite the propellant grains.
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