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Development of HTPB Propellant for Ballistic Missiles.

AD786472

Publication Date	1974
Personal Author	Thompson, G.; Day, E. E.
Page Count	26
Abstract	The program objective is to develop a family of solid propellants for ballistic missiles based on an HTPB (hydroxyl terminated polybutadiene) binder, and to demonstrate one optimized propellant formulation by large scale motor firings. Specifically, five propellants have been formulated and are being characterized to the point that they will be ready for motor advanced development programs. These five propellants are compatible with two optimized missile systems: (1) a weight constrained small diameter three stage ballistic missile, and (2) a length constrained large diameter ballistic missile. In addition, a formulation which is typical of the entire series was fully defined, characterized, and demonstrated in the static firing of a Third Stage Minuteman III Motor (TU-775/01). Two additional Third Stage Minuteman III motors have been instrumented and loaded as structural test vehicles (TU-775/02 and TU-775/03).
Keywords	Solid rocket propellants Combustion Polybutadiene Aging(Materials) Guided missiles Stress strain relations Pressure Test equipment Performance(Engineering)
Source Agency	Air Force
NTIS Subject Category	81H - Rocket Propellants
Corporate Authors	Thiokol Corp Brigham City Utah Wasatch Div; Air Force Rocket Propulsion Lab., Edwards AFB, Calif.
Supplemental Notes	See also Quarterly progress rept. no. 8, AD-779 817.
Document Type	Technical Report
Title Note	Quarterly progress rept. no. 9, Apr-Jun 74.
NTIS Issue Number	197425
Contract Number	F04611-72-C-0048

Development of HTPB Propellant for Ballistic Missiles.

Development of HTPB Propellant for Ballistic Missiles.
AD786472

Publication Date	1974
Personal Author	Thompson, G.; Day, E. E.
Page Count	26
Abstract	The program objective is to develop a family of solid propellants for ballistic missiles based on an HTPB (hydroxyl terminated polybutadiene) binder, and to demonstrate one optimized propellant formulation by large scale motor firings. Specifically, five propellants have been formulated and are being characterized to the point that they will be ready for motor advanced development programs. These five propellants are compatible with two optimized missile systems: (1) a weight constrained small diameter three stage ballistic missile, and (2) a length constrained large diameter ballistic missile. In addition, a formulation which is typical of the entire series was fully defined, characterized, and demonstrated in the static firing of a Third Stage Minuteman III Motor (TU-775/01). Two additional Third Stage Minuteman III motors have been instrumented and loaded as structural test vehicles (TU-775/02 and TU-775/03).
Keywords	Solid rocket propellants Combustion Polybutadiene Aging(Materials) Guided missiles Stress strain relations Pressure Test equipment Performance(Engineering)
Source Agency	Air Force
NTIS Subject Category	81H - Rocket Propellants
Corporate Authors	Thiokol Corp Brigham City Utah Wasatch Div; Air Force Rocket Propulsion Lab., Edwards AFB, Calif.
Supplemental Notes	See also Quarterly progress rept. no. 8, AD-779 817.
Document Type	Technical Report
Title Note	Quarterly progress rept. no. 9, Apr-Jun 74.
NTIS Issue Number	197425
Contract Number	F04611-72-C-0048