Liner for a solid propellant rocket motor
AssigneeUnited Technologies Corporation
InventorsBernard R. Felix, Stephen E. Slosarik
Life of this patent
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Abstract
A curable liner for a solid propellent rocket motor includes a radiopaque material uniformly blended therein to provide a sufficient density difference between the propellant and insulator to enhance non-destructive X-ray evaluation of the liner propellant interface. Up to 10% powdered tungsten is added to a liner component mixture prior to incorporation in a rocket motor. Utilizing this radiopaque material in the liner mixture allows detection of previously undetectable voids, disbands or flaws at the liner propellant interface, thereby reducing the potential for failure of the rocket motor during operation.
Claims7
A curable liner for a solid propellant rocket motor, said liner comprising a curable mixture of components formulated to bond a propellant to an insulator disposed within the motor, the improvement characterized by:
- a radiopaque material, uniformly blended with the uncured liner component formulation, said material added in an amount sufficient to block the passage of x-rays through the propellant-liner-insulation interface, thereby enhancing the definition of flaws during non-destructive x-ray testing, without detrimentally affecting the bonding or burning properties of the cured liner.
Dependencies are inferred from the claim text.