公开(公告)号：US20210277831A1

公开(公告)日：2021-09-09

申请号：US16811673

申请日：2020-03-06

Applicant: GOODRICH CORPORATION

Inventor： Brian Wilson ,  Kevin Mueller

IPC: F02C7/272 ,  F02K9/95

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.

公开(公告)号：US11883985B2

公开(公告)日：2024-01-30

申请号：US17022931

申请日：2020-09-16

Applicant: GOODRICH CORPORATION

Inventor： Brian Wilson ,  Jean C. Rodriguez

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

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：US20220080629A1

公开(公告)日：2022-03-17

申请号：US17022931

申请日：2020-09-16

Applicant: GOODRICH CORPORATION

Inventor： Brian Wilson ,  Jean C. Rodriguez

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

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：US20190249971A1

公开(公告)日：2019-08-15

申请号：US15897909

申请日：2018-02-15

Applicant: GOODRICH CORPORATION

Inventor： Brian Wilson ,  Patrick Carver ,  German Ramirez

IPC: F42C15/34 ,  F42C19/10 ,  F42C15/32

CPC classification number: F42C15/34 ,  F42C15/32 ,  F42C19/10 ,  F42D1/043

Abstract: The present disclosure provides a low energy explosive transfer adapter. The low energy explosive transfer adapter may comprise an adapter housing comprising a firing pin chamber situated within the adapter housing comprising an inlet and a stopping surface opposite the inlet. The low energy explosive transfer adapter may further comprise a primer chamber connected to the firing pin chamber and an output tube connected to the primer chamber.