Ignition systems for hybrid and solid rocket motors

An ignition system for a rocket motor, comprising:

• a) a first tube having a first end and a second end;
• b) a second tube having first and second ends;
• c) a pair of wires having first and second ends, said first ends of said wires terminating near said first end of said first tube;
• d) a power supply coupled to said second ends of said wires;
• e) a first fluid oxidizer source which supplies an oxidizer to said second end of said first tube;
• and
• f) a second fluid oxidizer source which supplies an oxidizer to said second end of said second tube,
• wherein said first fluid oxidizer source supplies said oxidizer at a first flow rate into said second end of said first tube, and
• wherein said second fluid oxidizer source supplies said oxidizer at a second flow rate into said second end of said second tube, said second flow rate being greater than said first flow rate.

A rocket, comprising:

• a) a rocket motor having a combustion chamber;
• and
• b) an ignition system for said rocket motor,
• said ignition system including,
• i) a plastic first tube having a first end and a second end, said first end extending into said combustion chamber,
• ii) a pair of wires having first and second ends, said first ends of said wires terminating near said first end of said first tube,
• iii) a power supply coupled to said second ends of said wires and adapted to create an ignition spark across said first ends of said wires, and
• iv) a first fluid oxidizer source which supplies an oxidizer to said second end of said first tube.