A rocket engine system including a thrust chamber including walls that define an interior surface and a combustion section which is fluidically coupled to an output section. A coolant source containing a coolant. A means of heating the coolant. At least one port configured to apply the coolant to the interior surface to achieve a film cooling of the interior surface and wherein the coolant source is fluidically coupled to the means of heating and the at least one port.

A system for electromagnetically exciting certain molecules within a volume of gaseous working fluid or charge via transition frequency heating for propulsion, comprising an electrical energy source (EES), an electromagnetic wave generator (EWG), a reflection coefficient measurement device (RCMD), a controllable electrical matching network (EMN), a proportional integral derivative controller (PIDC), and a propulsor cavity (PC), wherein said PC further comprises a transmission line that comprises a waveguide and a radio frequency (RF) window, wherein said RF window provides optical access to a heating zone where the charge resides or passes through, wherein said heating zone resides in the flow path between a propulsion system's charge inlet and nozzle exhaust.

A system for electromagnetically exciting certain molecules within a volume of gaseous working fluid or charge via transition frequency heating for propulsion, comprising an electrical energy source (EES), an electromagnetic wave generator (EWG), a reflection coefficient measurement device (RCMD), a controllable electrical matching network (EMN), a proportional integral derivative controller (PIDC), and a propulsor cavity (PC), wherein said PC further comprises a transmission line that comprises a waveguide and a radio frequency (RF) window, wherein said RF window provides optical access to a heating zone where the charge resides or passes through, wherein said heating zone resides in the flow path between a propulsion system's charge inlet and nozzle exhaust.

Passive reactivity control technologies that enable reactivity control of a nuclear thermal propulsion (NTP) system with little to no active mechanical movement of circumferential control drums. By minimizing or eliminating the need for mechanical movement of the circumferential control drums during an NTP burn, the reactivity control technologies simplify controlling an NTP reactor and increase the overall performance of the NTP system. The reactivity control technologies mitigate and counteract the effects of xenon, the dominant fission product contributing to reactivity transients. Examples of reactivity control technologies include, employing burnable neutron poisons, tuning hydrogen pressure, adjusting wait time between burn cycles or merging burn cycles, and enhancement of temperature feedback mechanisms. The reactivity control technologies are applicable to low-enriched uranium NTP systems, including graphite composite fueled and tungsten ceramic and metal matrix (CERMET), or any moderated NTP system, such as highly-enriched uranium graphite composite NTP systems.

The present disclosure is directed to a supersonic oblique rotating detonation wave engine (SORDE) and systems and methods for generating a supersonic oblique rotating detonation wave. The SORDE is configured to produce and sustain a supersonic oblique rotating detonation wave through the injection of fuel at supersonic speeds into an inlet air flow between Mach 1 and Mach 7. The SORDE and method include injecting fuel into the inlet air in an amount to generate an equivalence ratio of 0.2 to 2.5. Some embodiments include a plurality of fuel injector ports each having a diameter of about 0.010 inches to about 0.040 inches; an annular wedge disposed in or upstream of the detonation chamber with an angle of about 5 degrees to about 40 degrees relative to a longitudinal axis of the engine; and/or a cylindrical center body disposed in or upstream of the detonation chamber.

The present disclosure is directed to a supersonic oblique rotating detonation wave engine (SORDE) and systems and methods for generating a supersonic oblique rotating detonation wave. The SORDE is configured to produce and sustain a supersonic oblique rotating detonation wave through the injection of fuel at supersonic speeds into an inlet air flow between Mach 1 and Mach 7. The SORDE and method include injecting fuel into the inlet air in an amount to generate an equivalence ratio of 0.2 to 2.5. Some embodiments include a plurality of fuel injector ports each having a diameter of about 0.010 inches to about 0.040 inches; an annular wedge disposed in or upstream of the detonation chamber with an angle of about 5 degrees to about 40 degrees relative to a longitudinal axis of the engine; and/or a cylindrical center body disposed in or upstream of the detonation chamber.

A rocket assembly including a main housing extending from a first end to a second end and having a longitudinal axis between the first and second ends. A plurality of tubes, extending from a first end to a second end, with the second end of each tube connected with the first end of the main housing. At least a subset of the plurality of tubes are pivotal relative to the main housing from a first orientation wherein a longitudinal axis of the tube is substantially parallel with the main housing longitudinal axis and a second orientation wherein a longitudinal axis of the tube is substantially parallel with the main housing longitudinal axis.

A rocket assembly including a main housing extending from a first end to a second end and having a longitudinal axis between the first and second ends. A plurality of tubes, extending from a first end to a second end, with the second end of each tube connected with the first end of the main housing. At least a subset of the plurality of tubes are pivotal relative to the main housing from a first orientation wherein a longitudinal axis of the tube is substantially parallel with the main housing longitudinal axis and a second orientation wherein a longitudinal axis of the tube is substantially parallel with the main housing longitudinal axis.