James S Hightower

US Patent:

44296347, Feb 7, 1984

Filed:

Mar 12, 1980

Appl. No.:

6/129542

Inventors:

James D. Byrd - Huntsville AL
James O. Hightower - Huntsville AL

Assignee:

Thiokol Corporation - Chicago IL

International Classification:

F42B 100

US Classification:

102290

Abstract:

Bonding of hydroxy terminated polybutadiene based propellant grains to rocket motor liners and of the liner to the motor case is greatly improved by incorporating an aziridine in a urethane cured hydroxy terminated polybutadiene based liner.

US Patent:

47643196, Aug 16, 1988

Filed:

Sep 18, 1986

Appl. No.:

6/908761

Inventors:

James O. Hightower - Huntsville AL
Tomio Sato - Huntsville AL
James W. Hamner - Huntsville AL

Assignee:

Morton Thiokol, Inc. - Chicago IL

International Classification:

C06B 2100

US Classification:

264 34

Abstract:

A high acceleration high performance solid rocket motor grain such as for a ballistic defense missile or rocket assisted projectile comprises a propellant material which includes a highly plasticized binder so that the grain has a solids ratio equal to at least about 95 percent. In order that the grain with such a solids ratio may have adequate strength and withstand high acceleration forces, a reticulated structure is embedded therein. A method of constructing a rocket motor having such a grain is also disclosed.

US Patent:

46007326, Jul 15, 1986

Filed:

Dec 16, 1983

Appl. No.:

6/562332

Inventors:

Kenneth E. Junior - Madison AL
James D. Byrd - Huntsville AL
James O. Hightower - Huntsville AL

Assignee:

Thiokol Corporation - Chicago IL

International Classification:

C08K 336
C08K 322

US Classification:

523138

Abstract:

An elastomeric composition suitable for use as a rocket motor case insulation is disclosed. The composition comprises a vulcanizable elastomeric material and reinforcing polybenzimidazole polymer fibers in combination with a powder filler. A preferred embodiment utilizes polyisoprene as the elastomer and silica as the powder filler. These compositions have better erosion resistance than asbestos-reinforced compositions, and do not pose the environmental or safety risks associated with asbestos-reinforced insulation.

US Patent:

49157540, Apr 10, 1990

Filed:

Mar 8, 1988

Appl. No.:

7/165641

Inventors:

James O. Hightower - Huntsville AL
Tomio Sato - Huntsville AL
James W. Hamner - Huntsville AL
Carl M. Rector - Brownsboro AL

Assignee:

Morton Thiokol, Inc. - Chicago IL

International Classification:

C06B 4510

US Classification:

149 194

Abstract:

A high acceleration high performance solid rocket motor grain such as for a ballistic defense missile or rocket assisted projectile comprises a propellant material which includes a highly plasticized binder so that the grain has a solids ratio equal to at least about 95 percent. In order that the grain with such a solids ratio may have adequate strength and withstand high acceleration forces, a reticulated structure is embedded therein. A method of constructing a rocket motor having such a grain is also disclosed.

US Patent:

47562510, Jul 12, 1988

Filed:

Sep 18, 1986

Appl. No.:

6/908762

Inventors:

James O. Hightower - Huntsville AL
Tomio Sato - Huntsville AL

Assignee:

Morton Thiokol, Inc. - Chicago IL

International Classification:

C06D 506

US Classification:

102289

Abstract:

A solid propellant grain which comprises an homogeneous mass of propellant material including an oxidant. A variable burn rate is provided by embedding a reticulated structure in a portion only of the propellant mass. The reticulated structure may be coated with a high thermal conductivity material to provide an increased burning rate. The coat of material is selected to preferably provide improved bonding to the propellant mass.

US Patent:

40849929, Apr 18, 1978

Filed:

Apr 22, 1976

Appl. No.:

5/679101

Inventors:

James O. Hightower - Huntsville AL
James W. Hamner - Huntsville AL
Richard L. Matthews - Huntsville AL

Assignee:

Thiokol Corporation - Newtown PA

International Classification:

C06B 4508

US Classification:

149 17

Abstract:

Finely divided aluminum oxide increases the burning rate, reduces the pressure exponent at high pressures and stabilizes the combustion of solid propellant compositions.

US Patent:

51272237, Jul 7, 1992

Filed:

Aug 7, 1989

Appl. No.:

7/391712

Inventors:

James O. Hightower - Huntsville AL
Tomio Sato - Huntsville AL

Assignee:

Thiokol Corporation - Ogden UT

International Classification:

F02K 1100
F02G 100

US Classification:

60253

Abstract:

A linerless rocket motor is provided by the bonding of a reticulated support structure, which is embedded in an homogenous mass of propellant material including an oxidant, to the inner wall of the rocket motor case. An inexpensive, safe, and easy to manufacture igniter is comprised of an homogeneous mass of propellant material including an oxidant and a reticulated support structure embedded therein. A light weight, high crush strength, and high strain capability sliver for a rocket motor comprises a block of inert material and a reticulated support structure of carbon, graphite, or a non-combustible material embedded therein. A rocket motor is prevented from accidental propulsion during a fire by attaching a propellant block to the outer side of the rocket motor base. The propellant block burns and produces heat during the fire to weaken the motor case so that pressure resulting from burning of propellant in the rocket motor will burst a hole in the rocket motor case to relive the pressure. A reticulated support structure is preferably embedded in the propellant block to render the block rigid enough not to deform during long term storage and during field handling and to resist aging conditions which would otherwise cause it to become brittle.

US Patent:

41207092, Oct 17, 1978

Filed:

Apr 25, 1973

Appl. No.:

5/354293

Inventors:

James W. Hamner - Huntsville AL
James O. Hightower - Huntsville AL
Carl M. Rector - New Market AL

Assignee:

Thiokol Corporation - Newtown PA

International Classification:

C06B 4510

US Classification:

149 1992

Abstract:

A technique for improving the processibility of composite propellants through reduction of the catalytic effect of iron oxide upon the polymer/curing agent reaction.