Ignition systems for hybrid and solid rocket motors

Details Ignition systems for hybrid and solid rocket motors Ignition systems for hybrid and solid rocket motors

2005-07-05

2005-07-05

Koczo, Michael (Department: 3746)

Power plants

Reaction motor

Solid and fluid propellant

C060S256000

Reexamination Certificate

active

06912839

ABSTRACT:
An ignition system for a rocket motor includes a soft plastic tube that extends up into the combustion chamber and is coupled to an oxidizer source. Ignition source wires extend through the tube and terminate at a first end at a location which is set back from the end of the tube, and have a second end coupled to an electric power supply. In operation, an oxidizer is introduced into the tube simultaneously with activation of the power supply. The set back portion of the plastic tube becomes fuel for the oxidizer and is consumed, introducing a fire plume into the combustion chamber. The tube introduces additional fuel distinct from the fuel grain or propellant which is in contact with the both the ignition source wires and oxidizer. In addition, the tube will not damage the nozzle as it is being blown of the rocket during the main propulsion phase.

REFERENCES:
patent: 3115007 (1963-12-01), Fox
patent: 3332353 (1967-07-01), Burkhardt et al.
patent: 3334489 (1967-08-01), Vilet
patent: 5582001 (1996-12-01), Bradford et al.
patent: 5715675 (1998-02-01), Smith et al.
patent: 6058697 (2000-05-01), Smith et al.

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