An integral propulsion and auxiliary power generation system includes a rocket engine, a liquid propellant supply system, an auxiliary electrical system, and a transmission system. The liquid propellant supply system is configured to supply a liquid fuel and a liquid oxidizer to the rocket engine. The liquid propellant supply system includes a gas generator configured to burn a mixture of the liquid fuel and the liquid oxidizer to generate a combustion gas stream, and a gas turbine configured to convert the kinetic energy of the combustion gas stream into mechanical energy. The auxiliary electrical system includes a power generator configured to convert mechanical energy into electrical energy and an electric load device electrically coupled to the power generator. The transmission system is configured to mechanically couple the gas turbine and the power generator to selectively transfer mechanical energy between the gas turbine and the power generator.

A propulsion system suitable for use in aircrafts (for example propeller plane) is provided. The propulsion system includes at least one propeller hub, which is mountable to at least a portion of the aircraft and includes at least one rotatable propeller blade thereon, propeller blade which is foldable, at least one fuel nozzle which is provided on the propeller hub and used to spray fuel into the section where the propeller blades are folded.

An oblique all-wing (OAW) vehicle and methods are described where the OAW vehicle has a unique configuration and can be used to, for example, launch a payload. The OAW vehicle can include an elongated airfoil body with a longitudinal axis, a top surface, a bottom surface, a first longitudinal end, a second longitudinal end, a first longitudinal edge at a first juncture between the top surface and the bottom surface, and a second longitudinal edge at a second juncture between the top surface and the bottom surface. The elongated airfoil body has an airfoil-shaped cross-section, with the first longitudinal edge defining a leading edge and the second longitudinal edge defining a trailing edge. A rocket engine or other propulsion device is mounted to the elongated airfoil body at the first longitudinal end.

An apparatus and method that improves the operation of aerospace planes or rockets having an integrated flute and hat components whereby the flute functions as a hypersonic refrigeration engine and the hat as a flat plate heat exchanger to achieve an isothermal compression of the incipient hypersonic air in front of the nosecone to reduce hypersonic vibrations during flight, these improvements allow for the reduction in temperature during flight operation allowing for improved cooling of the aerospace plane or rocket.

Embodiments of the invention relate to a hypersonic transport system including: an aircraft which includes a hypersonic lift-to-drag ratio greater than or equal to 2.5, wherein the aircraft includes a secondary propulsion device and position sensors, and wherein the aircraft also includes a variably shaped aerodynamic surface; a main propulsion device which is removably attached to the aircraft; and a control unit which is configured to monitor the aircraft and the main propulsion device.

A propulsion system, such as for an aircraft, for instance an unmanned aircraft system (UAS), includes a rocket motor and an electric motor, with the rocket motor passing through a central opening in the electric motor. The electric motor may be a brushless outrunner electric motor, with a rotor of the electric motor radially outward of a stator of the electric motor. The electric motor may use part of the rocket motor, such as a rocket nozzle (to give a non-limiting example), and may be used to turn blades of a propeller, to propel the aircraft. The propeller blades may be foldable blades, hingedly coupled to a yoke. The blades may deploy after launch of the aircraft, such as from a launcher, for instance a launch tube.

A propulsion system, such as for an aircraft, for instance an unmanned aircraft system (UAS), includes a rocket motor and an electric motor, with the rocket motor passing through a central opening in the electric motor. The electric motor may be a brushless outrunner electric motor, with a rotor of the electric motor radially outward of a stator of the electric motor. The electric motor may use part of the rocket motor, such as a rocket nozzle (to give a non-limiting example), and may be used to turn blades of a propeller, to propel the aircraft. The propeller blades may be foldable blades, hingedly coupled to a yoke. The blades may deploy after launch of the aircraft, such as from a launcher, for instance a launch tube.