SPHERICAL IGNITER FOR FULL HEAD-END WEB ROCKET MOTORS
Assignee
MORTON THIOKOL, INC., A DE. CORP.
Filed
Oct 15, 1987
Granted
Sep 29, 1992
Location
OGDEN UT US
Abstract
An igniter for full head-end web rocket motors comprises two molded urethane hemispherical shells, each of which is lined with a layer of solid propellant fuel, joined together to form a solid propellant-lined spherical pressure vessel, which spherical pressure vessel is strengthened by a wrapping fiberglass around the girth, includes an igniter initiator having an elongated tubular urethane housing that contains ignition material and serves also as a structural tie between the hemispherical shells, and a mounting foot incorporated in the lower portion of the spherical shell to facilitate bonding to the rocket motor's propellant grain, nozzle ports located in the lower portion of the spherical shell being provided for igniter flaming gas discharge and subsequent rocket motor ignition.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
May 9, 1988
Rescinded
Feb 11, 1992
Duration
3 years, 9 months
Inventor
- 1ROGER A. GROSGEBAUER
Record Details
- Patent number
- US 5150654
- Application
- 07109882
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
Browse by Assignee
MORTON THIOKOL, INC., A DE. CORP.More from this assignee
Related by domain
GAS TURBINE ENGINE COMBUSTOR HAVING TRAPPED DUAL VORTEX CAVITY
General Electric
SOLID ROCKET PROPELLANT
GAS TURBINE ENGINE FAN (U)
General Electric
TURNING VANE ARRANGEMENT FOR IR SUPPRESSORS
SIKORSKY AIRCRAFT CORPORATION
MODULAR ROCKET BOOSTED PENETRATING WARHEAD
LOCKHEED MARTIN CORP.
INTEGRAL SOLID BOOSTER AND HYBRID THRUST SUSTAINING SYSTEM AND PROJECTILE INCORPORATING THE SAME
ENVIRONMENTAL AEROSCIENCE CORPORATION