Roger A Grosgebauer
Land Surveyors in Ogden, UT

License number
Utah 118286-9925
Issued Date
Jun 15, 1964
Expiration Date
Dec 31, 1999
Category
Engineer/Land Surveyor
Type
Engineer in Training - Obsolete
Address
Address
Ogden, UT

Personal information

See more information about Roger A Grosgebauer at radaris.com
Name
Address
Phone
Roger Grosgebauer, age 97
1664 Hislop Dr, Ogden, UT 84404
(801) 399-1420
Roger A. Grosgebauer
Ogden, UT
(801) 399-1420
Roger A Grosgebauer, age 97
1664 Hislop Dr, Ogden, UT 84404
(801) 399-1420
Roger A Grosgebauer, age 97
2154 Deer Run Dr, Ogden, UT 84405
(801) 479-0669

Professional information

Roger Grosgebauer Photo 1

Radial Pulse Motor Igniter-Sustain Grain

US Patent:
4999997, Mar 19, 1991
Filed:
Nov 18, 1985
Appl. No.:
6/799371
Inventors:
Roger A. Grosgebauer - Ogden UT
C. Max White - Brigham City UT
Assignee:
Thiokol Corporation - Ogden UT
International Classification:
F02K 904
US Classification:
60256
Abstract:
A radial pulse rocket motor having a nozzle at the aft end includes longitudinally spaced hollow boost and sustain propellant grains in the combustion chamber thereof with an elongated tubular thermal barrier covering substantially the whole of the interior surface of the sustain grain to enable the production of separate boost and sustain pulses. At the forward end of the motor, mounted within a reentrant motor bulkhead position, is a multiple pulse arm-fire device which, when commanded, produces an igniting signal that is transmitted to a boost igniter for igniting the boost grain and a subsequent igniting signal that is transmitted to a sustain igniter for igniting the sustain grain. The sustain igniter is positioned in surrounding relation to the motor forward bulkhead reentrant portion, the multiple pulse arm-fire device, and the forward end of the tubular barrier, and comprises a consumable, molded, polyurethane case having two interlocking tubes with a thin 0. 10 inch (2. 5 mm.


Roger Grosgebauer Photo 2

Spherical Igniter For Full Head-End Web Rocket Motors

US Patent:
5150654, Sep 29, 1992
Filed:
Oct 15, 1987
Appl. No.:
7/109882
Inventors:
Roger A. Grosgebauer - Ogden UT
C. Max White - Brigham City UT
Assignee:
Thiokol Corporation - Ogden UT
International Classification:
F42C 1908
US Classification:
102202
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.


Roger Grosgebauer Photo 3

Pulsed Rocket Motor

US Patent:
4829765, May 16, 1989
Filed:
Dec 27, 1985
Appl. No.:
6/813808
Inventors:
Christopher W. Bolieau - Brigham City UT
Roger A. Grosgebauer - Ogden UT
Assignee:
Morton Thiokol, Inc. - Chicago IL
International Classification:
F02K 906
US Classification:
60250
Abstract:
A segmented rocket motor case includes wedge members for forcing the case segments into position to remove free play at the joint thereof which may otherwise interfere with or upset the missile's guidance system and throw it off target. A lap joint member for such a joint includes a shoulder having a surface for attachment of a membrane seal assembly for a pulsed rocket motor. A through bulkhead initiator communicates from the forward segment via a fitting which extends through the membrane seal assembly with an igniter for the propellant grain within the aft segment to eliminate the necessity of running explosive transfer lines along the outside of the case from a safe and arm device and other controls at the head end of the rocket motor.