Anti-erosive, solid rocket propellant compositions

Details Anti-erosive, solid rocket propellant compositions Anti-erosive, solid rocket propellant compositions

1975-05-21

1976-07-13

Miller, Edward A.

Explosive and thermic compositions or charges

Structure or arrangement of component or product

Solid particles dispersed in solid solution or matrix

149 196, 149 199, 149 20, C06B 4510

Patent

active

039691667

ABSTRACT:
A means for reducing or eliminating the erosive burning which takes place ring the burning phase of solid propelled rocket motors which have a large length-to-diameter ratio and/or slow-burning propellants is disclosed. The means comprises incorporating into the solid propellant, in limited percentages (0.1-1.0%), a silicate selected from talc, kaolinite, kaolin, muscovite mica, and feldspar. The silicate additive is effective for composite or double-base solid propellant compositions. The solid composite propellant compositions can vary widely in formulation ingredients to include numerous ballistic modifiers; however, the general formulation for a composite propellant contains in addition to the silicate, a high solids loading of an inorganic oxidizer such as ammonium perchlorate, a polybutadiene binder with curatives and crosslinking agents, and optional metal fuel, preferably aluminum. The polybutadiene can have carboxyl- or hydroxyl-terminal groups. The crosslinking agent for the carboxyl-terminated polybutadiene can be an epoxy compound. The hydroxyl-terminated polybutadiene can be crosslinked with a diisocyanate crosslinking agent. The double-base propellants include the cast double-base or the castable composite double-base compositions. The double-base propellants can also vary over a wide range in their formulations. In addition to including ballistic additives to meet the required performance criteria, these propellants contain nitrocellulose (12.6% N) or Fluid ball powder, energetic plasticizer such as triethylene glycol dinitrate (TEGDN), crosslinking and curing agents, and optional metal fuel.

REFERENCES:
patent: 3144830 (1964-08-01), DeFries et al.
patent: 3149009 (1964-09-01), Ratliff
patent: 3476622 (1969-11-01), Harada et al.
patent: 3644222 (1972-02-01), Fleming
patent: 3726829 (1973-04-01), Sayles
patent: 3914142 (1975-10-01), Sayles

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