Ignition safety device for a multi-pulse or multi-stage rocket motor system

A missile comprising:

• a plurality of energetic components;
• and
• an ignition system for igniting the plurality of energetic components, the ignition system including:
• a plurality of energetic initiators operatively coupled to a modular ignition safety device, the modular ignition safety device including logic circuitry configured to:
• receive a flight profile mode selection input;
• and
• selectively control a first sequential activation or a second sequential activation of the plurality of energetic initiators based on the flight profile mode selection input, wherein the first sequential activation includes a first time delay between the activation of each of the plurality of energetic initiators and the second sequential activation includes a second time delay between the activation of each of the plurality of energetic initiators, the second time delay being greater than the first time delay.

A method of selectively activating a plurality of energetic initiators to ignite a plurality of energetic components in a missile, the method comprising:

• receiving a flight profile mode selection input;
• controlling a first sequential activation of the plurality of energetic initiators when the flight profile mode selection input is a flight velocity mode input, wherein the first sequential activation includes a first time delay between the activation of each of the plurality of energetic initiators;
• and
• controlling a second sequential activation of the plurality of energetic initiators when the flight profile mode selection input is a flight distance mode input, wherein the second sequential activation includes a second time delay between the activation of the plurality of energetic initiators, the second time delay being greater than the first time delay.