Abstract: A cylinder has an insulating gas boundary layer (IGBL) across the cylinder wall inner surface, the IGBL formed by injection of an insulator fluid into the combustion chamber of the cylinder. In one implementation, a pressure differential is engineered between the top region of the cylinder and the bottom region of the cylinder. In yet another implementation, the insulator injection pressure is temporally modified in synchronicity with the piston cycle and/or in accordance with other temporal factors to provide appropriate IGBL coverage.

Abstract: Implementations described herein provide a high efficiency steam cycle that includes a steam turbine cycle coupled to output of a high performance steam piston topping (HPSPT) cycle. The HPSPT cycle includes a piston-cylinder assembly that extracts work from an expanding fluid volume and operates in a thermal regime outside of thermal operational limits of a steam turbine. The steam turbine cycle utilizes heat, transferred at the output of the HPSPT cycle, to generate turbine work.

Abstract: An apparatus and system disclosed herein provides detonation wave arrestor including a detonation wave deflector and a burst element. The detonation wave arrestor disclosed herein attenuates and defects the propagation of a detonation wave characterized by a supersonic flame front propagation. The detonation wave arrestor provides deflection of detonation wave towards the burst element. The rupture of the burst element provides venting of hot gases remaining from the detonation, thus providing separation and attenuation of combusted gas residuals. The detonation wave arrestor disclosed herein may be used in a combustible fuel delivery system.

Abstract: Separate pressure vessels for oxidizer and fuel components in a combustion/decomposition system add weight and complexity to the system. The fuel and oxidizer can be pre-mixed within a single pressure vessel, but can be unacceptably volatile in a mixed configuration. Providing separate fuel and oxidizer compartments within a singular pressure vessel reduces the weight and complexity of the system, while maintaining the non-volatility of separately stored fuel and oxidizer. The fuel and oxidizer can be selectively mixed within the pressure vessel when desired.

Abstract: A clustered, fixed cant, throttleable rocket assembly is used to propel and a steer a vessel in terrestrial or extraterrestrial applications. The fixed cant of each of at least three individual rockets in the cluster provides the steering input to the overall assembly. More specifically, by changing the propellant flow rate to the individual rocket engines relative to one another, the overall thrust vector of the rocket assembly may be selected to provide a desired steering input to the vessel. A measured vessel orientation may be compared with a desired vessel orientation to determine what steering input is required to achieve the desired vessel orientation.

Abstract: Propellants flow through specialized mechanical hardware that is designed for effective and safe ignition and sustained combustion of the propellants. By integrating a micro-fluidic porous media element between a propellant feed source and the combustion chamber, an effective and reliable propellant injector head may be implemented that is capable of withstanding transient combustion and detonation waves that commonly occur during an ignition event. The micro-fluidic porous media element is of specified porosity or porosity gradient selected to be appropriate for a given propellant. Additionally the propellant injector head design integrates a spark ignition mechanism that withstands extremely hot running conditions without noticeable spark mechanism degradation.

Abstract: The fluids and heat transfer theory for regenerative cooling of a rocket combustion chamber with a porous media coolant jacket is presented. This model is useful for calculating temperature distributions in a coolant fluid and combustion chamber or heat source as well as the associated fluid pressure drop through the coolant jacket. This model for fluids and heat transfer theory can be used to design a regeneratively cooled rocket engine.

Abstract: The presently disclosed technology relates to carbon-on-carbon (C/C) manufacturing techniques and the resulting C/C products. One aspect of the manufacturing techniques disclosed herein utilizes two distinct curing operations that occur at different times and/or using different temperatures. The resulting C/C products are substantially non-porous, even though the curing operation(s) substantially gasify a liquid carbon-entrained filler material that saturates a carbon fabric that makes up the C/C products.

Abstract: The presently disclosed linear detonation wave diverter provides a structure and method for quickly and controllably venting a detonation event out of the diverter without igniting working fluid upstream of a microporous barrier within the linear detonation wave diverter. Further, the detonation wave is linearly vented out of the diverter upon the failure of a burst member, which provides a low resistance path for detonation waves to exit the detonation wave diverter.

Abstract: The presently disclosed technology relates to using a combustion/decomposition heater fed by a working fluid stored within a storage tank to thermally pressurize the storage tank. The thermal pressurization may be used to maintain a desired pressure within the storage tank, even as the working fluid within the storage tank is drawn down. Further, a feedback mechanism may also be incorporated that varies the thermal energy added to the working fluid within the storage tank to maintain the desired pressure within the storage tank.

Abstract: The fluid and heat transfer theory for regenerative cooling of a rocket combustion chamber with a porous media coolant jacket is presented. This model is used to design a regeneratively cooled rocket or other high temperature engine cooling jacket. Cooling jackets comprising impermeable inner and outer walls, and porous media channels are disclosed. Also disclosed are porous media coolant jackets with additional structures designed to transfer heat directly from the inner wall to the outer wall, and structures designed to direct movement of the coolant fluid from the inner wall to the outer wall. Methods of making such jackets are also disclosed.

Abstract: A thermal variation source (e.g., a heater or a heat sink) is used to induce a temperature gradient across an interior surface of a storage tank. The storage tank stores a working fluid (e.g., a fuel, and oxidizer, or a monopropellant) that may have pockets of gaseous-phase working fluid interspersed within liquid-phase working fluid, or vice versa. In the absence of gravity or other significant forces on the working fluid, the temperature gradient is sufficient to cause phase-separation of the working fluid and allow either the liquid-phase or the gaseous-phase working fluid to be withdrawn from the storage tank, as desired.

Abstract: Propellants flow through specialized mechanical hardware that is designed for effective and safe ignition and sustained combustion of the propellants. By integrating a micro-fluidic porous media element between a propellant feed source and the combustion chamber, an effective and reliable propellant injector head may be implemented that is capable of withstanding transient combustion and detonation waves that commonly occur during an ignition event. The micro-fluidic porous media element is of specified porosity or porosity gradient selected to be appropriate for a given propellant. Additionally the propellant injector head design integrates a spark ignition mechanism that withstands extremely hot running conditions without noticeable spark mechanism degradation.

Abstract: Propellants flow through specialized mechanical hardware that is designed for effective and safe ignition and sustained combustion of the propellants. By integrating a micro-fluidic porous media element between a propellant feed source and the combustion chamber, an effective and reliable propellant injector head may be implemented that is capable of withstanding transient combustion and detonation waves that commonly occur during an ignition event. The micro-fluidic porous media element is of specified porosity or porosity gradient selected to be appropriate for a given propellant. Additionally the propellant injector head design integrates a spark ignition mechanism that withstands extremely hot running conditions without noticeable spark mechanism degradation.

Abstract: A throttleable exhaust venturi is described herein that generates strong suction pressures at an exhaust outlet by accelerating an incoming ambient fluid stream with the aid of a venturi to high gas velocities and injecting a combustion exhaust stream into the ambient fluid stream at an effective venturi throat. A mixing element downstream of the venturi throat ensures that the mixed fluid stream recovers from a negative static pressure up to local atmospheric pressure. A physical and the effective throat of the venturi are designed to promote mixing and stabilize the ambient fluid flow to ensure that high velocity is achieved and the effective venturi is operable over a variety of combustion exhaust stream mass flow rates.

Abstract: A throttleable exhaust venturi is described herein that generates strong suction pressures at an exhaust outlet by accelerating an incoming ambient fluid stream with the aid of a venturi to high gas velocities and injecting a combustion exhaust stream into the ambient fluid stream at an effective venturi throat. A mixing element downstream of the venturi throat ensures that the mixed fluid stream recovers from a negative static pressure up to local atmospheric pressure. A physical and the effective throat of the venturi are designed to promote mixing and stabilize the ambient fluid flow to ensure that high velocity is achieved and the effective venturi is operable over a variety of combustion exhaust stream mass flow rates.

Abstract: Propellants flow through specialized mechanical hardware that is designed for effective and safe ignition and sustained combustion of the propellants. By integrating a micro-fluidic porous media element between a propellant feed source and the combustion chamber, an effective and reliable propellant injector head may be implemented that is capable of withstanding transient combustion and detonation waves that commonly occur during an ignition event. The micro-fluidic porous media element is of specified porosity or porosity gradient selected to be appropriate for a given propellant. Additionally the propellant injector head design integrates a spark ignition mechanism that withstands extremely hot running conditions without noticeable spark mechanism degradation.

Abstract: High performance propellants flow through specialized mechanical hardware that allows for effective and safe thermal decomposition and/or combustion of the propellants. By integrating a sintered metal component between a propellant feed source and the combustion chamber, an effective and reliable fuel injector head may be implemented. Additionally the fuel injector head design integrates a spark ignition mechanism that withstands extremely hot running conditions without noticeable spark mechanism degradation.

Abstract: An alternative or supplement to combustion within an engine is decomposition of nitrous oxide into two parts nitrogen, one part oxygen. This decomposition releases thermal energy that may be captured and converted to useful work. Traditional combustion engines are limited to oxidizer/fuel ratio ratios near the proportional mixture of fuel and oxidizer that achieves complete combustion of the fuel. The presently disclosed technology increases the oxidizer/fuel ratio above that of all traditional combustion engines and still achieves useable power output primarily through decomposition of nitrous oxide. Decomposition of nitrous oxide into nitrogen and oxygen in an engine outputs two parts nitrogen and one part oxygen, which is roughly equivalent to oxygen rich atmospheric air. Output of carbon dioxide and other undesirable chemical compounds is avoided when compared to combustion of a carbon-hydrogen fuel and an oxidizer containing oxygen.

Abstract: A supersonic combustor as a component of a rocket nozzle offers improved utilization of available chemical energy that may be released from combustion gasses flowing through the rocket nozzle. A subsonic combustor sub-sonically accelerates an exothermically reacting combustion gas up to a nozzle throat. The supersonic combustor expands and super-sonically accelerates the exothermically reacting combustion gas beyond the nozzle throat. The dimensions of the supersonic combustor may be selected such that the supersonic combustor achieves a slow rate of cooling of the combustion gasses without creating shockwaves within the supersonic combustor. A supersonic discharge expands and super-sonically accelerates the now substantially non-reacting combustion gas through a supersonic discharge of the rocket nozzle. The momentum of the combustion gas leaving the supersonic discharge propels the rocket nozzle in the opposite direction due to the principle of conservation of momentum.