Hydrazinium nitroformate based high performance solid propellants
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United States of America Patent
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Jul 12, 2005
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N/A
app pub date -
May 19, 1999
filing date -
May 20, 1998
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Abstract
The present invention is directed to a solid propellant for rocket motors, gas generators and comparable devices, comprising a cured composition of hydrazinium nitroformate and an unsaturated hydroxyl terminated hydrocarbon compound.
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