公开(公告)号：US10982625B2

公开(公告)日：2021-04-20

申请号：US16056293

申请日：2018-08-06

Applicant: GOODRICH CORPORATION

Inventor： Paul Parinas ,  Brian Wilson

IPC: F02K9/12 ,  F02K9/28 ,  C06B31/30 ,  C06B29/22 ,  F02K9/22

Abstract: A solid propellant rocket motor may comprise a core-burning propellant grain extending along a longitudinal axis of the solid propellant rocket motor between an exhaust end of the solid propellant rocket motor and a forward end of the solid propellant rocket motor, a first burn inhibitor layer surrounding the core-burning propellant grain, an end-burning propellant grain surrounding the first burn inhibitor layer, a second burn inhibitor layer surrounding the end-burning propellant grain, and an aperture at least partially defined by the first burn inhibitor layer. The end-burning propellant grain is ignited by the core-burning propellant grain via the aperture.

公开(公告)号：US20190249970A1

公开(公告)日：2019-08-15

申请号：US15897840

申请日：2018-02-15

Applicant: GOODRICH CORPORATION

Inventor： Brian Wilson ,  Kevin Mueller

IPC: F42C15/34 ,  F42C15/32

CPC classification number: F42C15/34 ,  B64D25/08 ,  F42C7/00 ,  F42C15/32 ,  F42C19/10 ,  F42D1/043

Abstract: The present disclosure provides a high explosive firing mechanism. The high explosive firing mechanism may comprise a housing comprising a firing pin tube having a primer inlet. The high explosive firing mechanism may further comprise a firing pin disposed within the firing pin tube, the firing pin comprising a nub. The nub may partially extend into the primer inlet.

公开(公告)号：US20240149502A1

公开(公告)日：2024-05-09

申请号：US18545882

申请日：2023-12-19

Applicant: GOODRICH CORPORATION

Inventor： Brian Wilson ,  Jean C Rodriguez

IPC: B29C39/26 ,  B29C33/44 ,  B29C39/36 ,  F02K9/24

CPC classification number: B29C39/26 ,  B29C33/448 ,  B29C39/36 ,  F02K9/24 ,  B29K2901/12

Abstract: Systems and methods for casting solid propellants include a mandrel for forming geometric features in a perforation of a propellant grain. In various embodiments, the mandrel includes a frangible portion that is removed from the propellant grain after the propellant grain has cured around the mandrel. A second portion of the mandrel may be left behind in the propellant grain. The mandrel may include a support structured disposed in the through hole of the mandrel. The support structure may include a plurality of longitudinal channels for directed exhaust gasses through the mandrel upon ignition of the propellant grain.

公开(公告)号：US11608183B2

公开(公告)日：2023-03-21

申请号：US17201886

申请日：2021-03-15

Applicant: GOODRICH CORPORATION

Inventor： Brian Wilson ,  Jatin H. Solanki

IPC: B64D25/10

Abstract: A control system for an ejection system may comprise an ejection seat, a canopy jettison system, a sensor, a controller, and a tangible, non-transitory memory configured to communicate with the controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising receiving an eject command, polling the sensor for a sensor data, receiving the sensor data, passing the sensor data to a time delay logic, determining via the time delay logic a time delay based on the sensor data, and actuating the ejection seat based on the time delay.

公开(公告)号：US20200040849A1

公开(公告)日：2020-02-06

申请号：US16056293

申请日：2018-08-06

Applicant: GOODRICH CORPORATION

Inventor： Paul Parinas ,  Brian Wilson

IPC: F02K9/12 ,  F02K9/28 ,  F02K9/22 ,  C06B31/30 ,  C06B29/22

Abstract: A solid propellant rocket motor may comprise a core-burning propellant grain extending along a longitudinal axis of the solid propellant rocket motor between an exhaust end of the solid propellant rocket motor and a forward end of the solid propellant rocket motor, a first burn inhibitor layer surrounding the core-burning propellant grain, an end-burning propellant grain surrounding the first burn inhibitor layer, a second burn inhibitor layer surrounding the end-burning propellant grain, and an aperture at least partially defined by the first burn inhibitor layer. The end-burning propellant grain is ignited by the core-burning propellant grain via the aperture.

公开(公告)号：US20200003533A1

公开(公告)日：2020-01-02

申请号：US16024207

申请日：2018-06-29

Applicant: GOODRICH CORPORATION

Inventor： Brian Wilson ,  German Ramirez

IPC: F42B33/06 ,  F42B1/028

Abstract: A variable stand-off distance explosive cord assembly for a casing is disclosed. In various embodiments, the assembly includes an explosive cord configured for positioning at a stand-off distance from the casing and a thermally responsive material configured to vary the stand-off distance from a first distance to a second distance.

公开(公告)号：US20210323684A1

公开(公告)日：2021-10-21

申请号：US17201886

申请日：2021-03-15

Applicant: GOODRICH CORPORATION

Inventor： Brian Wilson ,  Jatin H. Solanki

IPC: B64D25/10

Abstract: A control system for an ejection system may comprise an ejection seat, a canopy jettison system, a sensor, a controller, and a tangible, non-transitory memory configured to communicate with the controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising receiving an eject command, polling the sensor for a sensor data, receiving the sensor data, passing the sensor data to a time delay logic, determining via the time delay logic a time delay based on the sensor data, and actuating the ejection seat based on the time delay.

公开(公告)号：US10801822B2

公开(公告)日：2020-10-13

申请号：US16024207

申请日：2018-06-29

Applicant: GOODRICH CORPORATION

Inventor： Brian Wilson ,  German Ramirez

IPC: F42B33/06 ,  F42B1/028

Abstract: A variable stand-off distance explosive cord assembly for a casing is disclosed. In various embodiments, the assembly includes an explosive cord configured for positioning at a stand-off distance from the casing and a thermally responsive material configured to vary the stand-off distance from a first distance to a second distance.

公开(公告)号：US11884408B2

公开(公告)日：2024-01-30

申请号：US17539479

申请日：2021-12-01

Applicant: GOODRICH CORPORATION

Inventor： Brian Wilson ,  Kaylyn Beseler

IPC: B64D25/10 ,  F02K9/34 ,  F02K9/12 ,  F02K9/18 ,  F02K9/28 ,  F02K9/26

CPC classification number: B64D25/10 ,  F02K9/12 ,  F02K9/18 ,  F02K9/26 ,  F02K9/28 ,  F02K9/346

Abstract: A solid propellant propulsion motor may comprise: a forward propellant grain extending along a longitudinal axis of a motor case between a forward end of the motor case and a first burn inhibitor layer in the motor case; the first burn inhibitor layer disposed axially adjacent to the forward propellant grain; an aft propellant grain disposed axially adjacent to the first burn inhibitor layer; a second burn inhibitor layer disposed axially adjacent to an aft end of the aft propellant grain; and an ablative material layer disposed on a radially inner surface of the aft propellant grain.

公开(公告)号：US11512645B2

公开(公告)日：2022-11-29

申请号：US16811673

申请日：2020-03-06

Applicant: GOODRICH CORPORATION

Inventor： Brian Wilson ,  Kevin Mueller

IPC: F15B15/19 ,  F02C7/272 ,  F02K9/95 ,  F42B3/04 ,  F02C7/32

Abstract: A solid-propellant gas generator assembly may comprise a bulkhead having an orifice disposed in a housing. The bulkhead may be disposed between a first end and a second end of the housing. The bulkhead and the first end may define a propellant cavity. The bulkhead and the second end may define a pressure chamber. A fast burning solid-propellant may be disposed in the propellant cavity. The solid-propellant gas generator assembly may be configured to replace a slow burning solid-propellant gas generator system in a solid-propellent gas generator system.