US 11,988,172 B2
Ignition safety device for a multi-pulse or multi-stage rocket motor system
Shawn Coffee, Tucson, AZ (US); Saifur Ahmed, Oro Valley, AZ (US); Steven D. Jacob, Oro Valley, AZ (US); and Thomas K. Harward, Tucson, AZ (US)
Assigned to Raytheon Company, Tewksbury, MA (US)
Filed by Raytheon Company, Tewksbury, MA (US)
Filed on Nov. 19, 2020, as Appl. No. 16/952,928.
Prior Publication US 2022/0154670 A1, May 19, 2022
Int. Cl. F02K 9/94 (2006.01); F02K 9/95 (2006.01); F42B 15/01 (2006.01); F42C 11/06 (2006.01); F42C 15/40 (2006.01)
CPC F02K 9/94 (2013.01) [F02K 9/95 (2013.01); F42B 15/01 (2013.01); F42C 11/065 (2013.01); F42C 15/40 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An ignition system for igniting a plurality of energetic components in a missile, the ignition system comprising:
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, 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 a first time delay.