Morton Thiokol Inc.

Thiokol Corporation

Tomio Sato

James O Hightower, Jr

James W Hamner

Samuel Zeman

Carl M Rector

Rector, Carl M

Rexford D Atchley

James R Thompson

John M Nelson

Toby T Norris

A testing apparatus and methods for use with a tensile testing machine for simulating thermal, acceleration, and ignition pressurization loads upon a grain support system of a solid rocket motor during ignition. The apparatus includes a pair of antisymmetrically disposed L-shaped test fixtures within which is attached a test specimen. The test specimen is configured to simulate two propellant grain support systems. The grain support systems in the test specimen are antisymmetrically disposed, thereby permitting two specimens to be tested simultaneously by the application of uniaxial tension to the apparatus.

Antisymmetric grain support test device and methods

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.

Solid rocket motor propellants with reticulated structures embedded

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.

High solids ratio solid rocket motor propelant grains and method of

High solids ratio solid rocket motor propellant grains and method of

A ballistic test device for simulating propellant and/or bond and/or strain conditions in a high pressure, high strain rate rocket motor. The device uses internal compliant sleeves which allow radial expansion or growth of propellants, liners and insulation or any combination of all three.

High strain capability ballistic test device for solid propellant rocket

A reinforced split-flap hinge for supporting the unpressurized propellant grain of a rocket motor in a high acceleration environment includes a circular piece of material and an afterwardly spaced first annular piece of material bonded to the convex forward surface of the propellant grain, the material of the circular piece of material and the first annular piece of material being chopped fibers of insulating material in a rubber matrix, with a second annular piece of material bonded to the surface of the circular concave piece of material, the convex forward surface of the propellant grain, and the surface of the first annular piece of material, a third U-shaped annular piece of material having first and second skirts extending aft with a first skirt bonded to the surface of the second annular piece of material, the second and third annular pieces of material being made of fabric reinforced polyisoprene, and a fourth annular piece of insulating material made of powder filled polyisoprene positioned between the forward inner wall of the rocket motor case and the third annular piece of material and bonded on one side to the inner wall of the case and on the other side to the second skirt of the third annular piece of material.

Low mass grain support system for solid propellant rocket motors

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.

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Huntsville, AL, United States of America

Tomio Sato