Hydrazinium nitroformate based high performance solid propellants
AssigneeNederlandse Organisatie voor toegepast-natuurwetenschappelijk onderzoek TNO
InventorsJeroen Louwers, Antonius Eduard Dominicus Maria Van Der Heijden, Petrus Johannes Maria Elands
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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.
Claims15
A solid propellant for rocket motors, gas generators and comparable devices, comprising a cured composition of solid hydrazinium nitroformate, an unsaturated hydroxyl terminated hydrocarbon compound binder and a curing agent, wherein the hydrazinium nitroformate when dissolved in water as a 10 wt. % aqueous solution prior to being incorporated into the propellant has a pH of at least 4.
A solid propellent for rocket motors, gas generators and comparable devices comprising a cured composition of containing hydrazinium nitroformate, an unsaturated hydroxyl terminated hydrocarbon compound binder and a curing agent, said propellant being obtained by preparing a mixture of solid hydrazinium nitroformate, an unsaturated hydroxyl terminated hydrocarbon compound binder and a curing agent, followed by curing said mixture, the solid hydrazinium nitroformate, prior to being incorporated into the propellant, having a pH of at least 4 when dissolved in water as a 10 wt. % aqueous solution.
Dependencies are inferred from the claim text.