Solid propellant combustion apparatus

Details Solid propellant combustion apparatus Solid propellant combustion apparatus

1993-03-19

1998-09-15

Nelson, Peter A.

Ammunition and explosives

Powder form

Rocket propellent grain

60248, 60254, C06D 506, F02K 502

Patent

active

058082310

ABSTRACT:
Solid propellant combustion apparatus such as a rocket motor, incorporating a combustion termination valve for providing two combustion phases from a single propellant charge system, the valve comprising a valve body (50) surrounding an opening (52) in the pressure vessel of the combustion apparatus, a valve member (60), retaining means (65) for releasably retaining said valve member in sealing engagement with the valve body whereby to hold the valve closed during a first combustion phase, valve opening means (68) operable on command for releasing said retaining means whereby to cause the valve member (61) to disengage from the valve body thereby opening the valve to terminate said first combustion phase by rapid de-pressurisation of the combustion gases through said opening, and valve closure means (72) operable on command to move the valve member (61) into sealing engagement with the valve body whereby to close the valve prior to re-ignition of the propellant charge for a second combustion phase.

REFERENCES:
patent: 3065597 (1962-11-01), Adamson et al.
patent: 3173252 (1965-03-01), Ziegenhagen
patent: 3293855 (1966-12-01), Cuttill et al.
patent: 4023355 (1977-05-01), McDonald
patent: 4075832 (1978-02-01), Diesinger et al.
patent: 4840024 (1989-06-01), McDonald
patent: 5133183 (1992-07-01), Assoka et al.
United Kingdom Search Report.

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