US 11,852,104 B2
Propulsion system with single initiator for multiple rocket motors
Jacob Pinello-Benavides, Tuscon, AZ (US); John Meschberger, Tucson, AZ (US); Stephen Moore, El Dorado Hills, CA (US); and Edward Little, III, El Dorado Hills, CA (US)
Assigned to Raytheon Company, Waltham, MA (US)
Filed by Raytheon Company, Waltham, MA (US)
Filed on Sep. 3, 2021, as Appl. No. 17/466,245.
Prior Publication US 2023/0073547 A1, Mar. 9, 2023
Int. Cl. F02K 9/96 (2006.01); F02K 9/95 (2006.01); F02K 9/32 (2006.01)
CPC F02K 9/95 (2013.01) [F02K 9/32 (2013.01)] 16 Claims
OG exemplary drawing
 
16. A flight vehicle comprising:
a fuselage; and
a propulsion system coupled to the fuselage, the propulsion system including:
a manifold; and
an initiator operatively coupled to the manifold;
wherein the manifold has a plenum therein to which multiple rocket motors are couplable via separate mounts for each of the multiple rocket motors, to provide ignition to the multiple rocket motors;
wherein the plenum is an annular plenum with an ignition charge connected to the initiator therein, wherein the ignition charge is aligned with only one rocket motor of the multiple rocket motors, wherein the ignition charge is in a part but not all of the plenum;
wherein ignition of the initiator fills the plenum with hot gasses, wherein when the hot gasses have fully filled the plenum, the hot gasses enter the separate mounts to ignite separate ignition booster charges in each mount to provide ignition to each of the multiple rocket motors attached to the separate mounts.