A rocket injector is provided with multiple sets of manifolds for supplying propellants to injector elements. Sensors transmit the temperatures of the propellants to a suitable controller which is operably connnected to valves between these manifolds and propellant storage tanks. When cryogenic propellant temperatures are sensed, only a portion of the valves are opened to furnish propellants to some of the manifolds. When lower temperatures are sensed, additional valves are opened to furnish propellants to more of the manifolds
Injector manifold assembly for bipropellant rocket engines providing for fuel propellant to serve as...
The effect of elevated chamber pressure on combustion efficiency and heat transfer has been determin...
One propulsion option of a Mars ascent/descent vehicle is multiple high-pressure, pump-fed rocket en...
A rocket injector is provided with multiple sets of manifolds for supplying propellants to injector ...
The gas flow near the injector of a liquid propellant rocket was investigated by rapidly inserting b...
A method for temperature control of the combustion gases in the peripheral zone of a rocket combusto...
A low pressure loss injector element is disclosed for the main combustion chamber of a rocket engine...
An injector for liquid fueled rocket engines wherein a generally flat core having a frustoconical do...
A high number of liquid oxygen and gaseous hydrogen orifices per unit area are provided in an inject...
A report discusses a cryogenic reaction control system (RCS) that integrates a Joule-Thompson (JT) d...
The successful hot fire demonstration of a pulsing liquid hydrogen/liquid oxygen and gaseous hydroge...
The performance and stability of liquid rocket engines is determined to a large degree by atomizatio...
A rocket of the 1000-pound-thrust class using liquid oxygen and JP-4 fuel as propellant was installe...
As thrust levels increase and as rocket engines fire for longer periods of time, the difficulties en...
There is renewed interest in cryogenic oxygen storage for an advanced second-generation orbital mane...
Injector manifold assembly for bipropellant rocket engines providing for fuel propellant to serve as...
The effect of elevated chamber pressure on combustion efficiency and heat transfer has been determin...
One propulsion option of a Mars ascent/descent vehicle is multiple high-pressure, pump-fed rocket en...
A rocket injector is provided with multiple sets of manifolds for supplying propellants to injector ...
The gas flow near the injector of a liquid propellant rocket was investigated by rapidly inserting b...
A method for temperature control of the combustion gases in the peripheral zone of a rocket combusto...
A low pressure loss injector element is disclosed for the main combustion chamber of a rocket engine...
An injector for liquid fueled rocket engines wherein a generally flat core having a frustoconical do...
A high number of liquid oxygen and gaseous hydrogen orifices per unit area are provided in an inject...
A report discusses a cryogenic reaction control system (RCS) that integrates a Joule-Thompson (JT) d...
The successful hot fire demonstration of a pulsing liquid hydrogen/liquid oxygen and gaseous hydroge...
The performance and stability of liquid rocket engines is determined to a large degree by atomizatio...
A rocket of the 1000-pound-thrust class using liquid oxygen and JP-4 fuel as propellant was installe...
As thrust levels increase and as rocket engines fire for longer periods of time, the difficulties en...
There is renewed interest in cryogenic oxygen storage for an advanced second-generation orbital mane...
Injector manifold assembly for bipropellant rocket engines providing for fuel propellant to serve as...
The effect of elevated chamber pressure on combustion efficiency and heat transfer has been determin...
One propulsion option of a Mars ascent/descent vehicle is multiple high-pressure, pump-fed rocket en...