US 12,116,958 B2
Rocket motor and components thereof
Stefan Johannes Powell, Christchurch (NZ); Tobias René Knop, Delft (NL); James Robert Powell, Christchurch (NZ); Robert Mark Werner, Christchurch (NZ); and Jeroen Wink, Delft (NL)
Assigned to Dawn Aerospace Limited, Middleton (NZ)
Filed by Dawn Aerospace Limited, Christchurch (NZ)
Filed on Aug. 5, 2021, as Appl. No. 17/394,768.
Claims priority of provisional application 63/061,959, filed on Aug. 6, 2020.
Prior Publication US 2022/0112867 A1, Apr. 14, 2022
Int. Cl. F02K 9/52 (2006.01); F02K 9/42 (2006.01); F02K 9/44 (2006.01); F02K 9/50 (2006.01); F02K 9/56 (2006.01); F02K 9/58 (2006.01); F02K 9/64 (2006.01)
CPC F02K 9/52 (2013.01) [F02K 9/42 (2013.01); F02K 9/44 (2013.01); F02K 9/50 (2013.01); F02K 9/56 (2013.01); F02K 9/58 (2013.01); F02K 9/64 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A rocket motor feed system comprising:
a feed line supplying a gaseous propellant from a gaseous propellant supply;
a sonic choke provided in the feed line, the sonic choke being configured to passively regulate the mass flow rate of the gaseous propellant passing therethrough; and
an injector provided in the feed line, the injector being downstream of the sonic choke wherein;
the injector comprises an injection plate defining a plurality of orifices for injecting the gaseous propellant into a downstream combustor;
the injector is configured to at least substantially isolate a section of the feed line that is upstream of the injector from the downstream combustor; and
the gaseous propellant supplied from the gaseous propellant supply is a fuel.