US 11,920,543 B2
Rocket propulsion systems and associated methods
Livingston L. Holder, Renton, WA (US); Gary C. Hudson, Renton, WA (US); and Bevin C. McKinney, Renton, WA (US)
Assigned to RADIAN AEROSPACE, INC., Renton, WA (US)
Filed by Radian Aerospace, Inc., Renton, WA (US)
Filed on Mar. 31, 2023, as Appl. No. 18/129,245.
Application 18/129,245 is a continuation of application No. 17/133,090, filed on Dec. 23, 2020, granted, now 11,643,994.
Application 17/133,090 is a continuation of application No. PCT/US2019/040325, filed on Jul. 2, 2019.
Claims priority of provisional application 62/693,829, filed on Jul. 3, 2018.
Prior Publication US 2023/0399997 A1, Dec. 14, 2023
Int. Cl. F02K 9/52 (2006.01); B64G 1/14 (2006.01); B64G 1/40 (2006.01); F02K 9/42 (2006.01); F02K 9/56 (2006.01); F02K 9/60 (2006.01); F02K 9/82 (2006.01); F02K 9/86 (2006.01)
CPC F02K 9/52 (2013.01) [B64G 1/14 (2013.01); B64G 1/401 (2013.01); F02K 9/42 (2013.01); F02K 9/566 (2013.01); F02K 9/605 (2013.01); F02K 9/82 (2013.01); F02K 9/86 (2013.01)] 22 Claims
OG exemplary drawing
 
1. A rocket propulsion system, comprising:
a combustion chamber having a curved, inwardly-facing chamber wall enclosing a combustion zone, the combustion chamber having a generally spherical shape with the curved, inwardly-facing chamber wall exposed to the combustion zone; and
a propellant injector coupled to the combustion chamber and having at least one fuel injector nozzle positioned to direct a flow of cooling fuel tangentially relative to the curved, inwardly-facing chamber wall;
wherein the at least one fuel injector nozzle includes a spray ring having a plurality of orifices;
wherein the propellant injector includes:
a movable fuel piston; and
a movable oxidizer piston;
wherein the oxidizer piston includes an oxidizer piston wall around an oxidizer passageway, the oxidizer piston wall comprises a fuel piston channel extending within the oxidizer piston wall, and the fuel piston is movable within the fuel piston channel.