A hybrid airbreathing rocket engine module (70) comprises an air intake arrangement (62) configured to receive air and a heat exchanger arrangement (63) configured to cool air from the air intake arrangement (62); a compressor (64) configured to compress air from the heat exchanger arrangement (63); and one or more thrust chambers (65). The air intake arrangement (62), the compressor (64), the heat exchanger arrangement (63), and the one or more thrust chambers (65) are arranged generally along an axis (69) of the engine module (70). The heat exchanger arrangement (63) is arranged between the compressor (64) and the one or more thrust chambers (65).

A launch system is provided, including a composite vehicle and a carrier vehicle. The composite vehicle includes a payload vehicle, a booster vehicle and a first coupling system. The payload vehicle is configured for powered spaceflight at least in a space medium, and includes a rocket driven propulsion system. The booster vehicle is configured for powered supersonic/hypersonic aerodynamic flight, includes a ramjet propulsion system, and is configured for transporting the composite vehicle between a first altitude and a second altitude under propulsive power provided by the ramjet propulsion system. The first coupling system is configured for selectively coupling and decoupling the payload vehicle with respect to the booster vehicle. The carrier vehicle is configured at least for powered subsonic/transonic/supersonic aerodynamic flight, and for transporting the composite vehicle to at least the first altitude from a ground location. The launch system also includes a second coupling system for selectively coupling and decoupling the composite vehicle with respect to the carrier aircraft.

An aerodynamic platform or spacecraft including a habitable 1G centripetal force rotating gravity producing interior corridor within an aerodynamic shell and an aerodynamic drone booster launch system with reentry and reuse capability.

An engine system that produces all required thrust for an aerospace vehicle from takeoff through space operation, consisting of airbreathing and non-airbreathing propulsion apparatuses. The airbreathing system consists of a turbine engine, a ram and or scram jet, and the non-airbreathing system is a unique liquid rocket motor. The turbine engine may consist of a turbojet or turbofan configuration. The air breathing turbine, ramjet and scram jet feature a single air inlet system, and combustion fuel. The non-airbreathing rocket system includes separate oxidizer system, and either a separate or same source of combustion fuel as the turbine. Airflow velocities in the turbine bypass duct, and burner system, include subsonic and supersonic velocities for ramjet or scramjet operation. The rocket engine may utilize either cryogenic or a non-cryogenic fuel and oxidizer system.

A geostationary platform is held afloat by a superpressure balloon. A suitable altitude is 25 km. The craft carries electrohydrodynamic thrusters, to overcome winds, held within a scaffold. Sensors determine position, velocity, acceleration and vector. A CPU performs instructions for station-keeping or navigation. A communication system is included to, inter alia, receive instructions from the ground. The craft carries a payload for observation and transmission, cradled in a temperature-controlled chamber. Power to the platform is transmitted in the form of electromagnetic waves (with suitable frequencies including microwaves of 2.45 GHz or 5.8 GHz) from a ground-based transmitter to a receiving antenna on, or affixed to, the balloon which converts the electromagnetic energy to direct current. A step-up voltage converter increases the voltage as required. A ground station monitors craft position and operational efficiency by radar to help ensure safe takeoff, operation, and landing of the craft.

Exemplary air breathing plasma jet engine and method of operation that can be used in electrically powered aircraft and spacecraft as a hybrid between a turbo jet engine and a ramjet or supersonic sonic ramjet (SCRAMJET) engine. The air breathing plasma jet engine includes a compression stage that is configured to compress and slow down incoming air. The compressor can be driven by a high RPM electric motor. The compression stage generates compressed and heated air flow that is passed to a plasma chamber that is configured to add heat to the compressed and heated air flow. The heat are converted to an impulse, e.g., using a converging-diverging (De Laval) nozzle. The system is beneficially configured to reuse the heat byproduct generated in the compression stage.

An aerodynamic platform or spacecraft including a habitable 1G centripetal force rotating gravity producing interior corridor within an aerodynamic shell and an aerodynamic drone booster launch system with reentry and reuse capability.

One or more embodiments relates to an air-breathing plasma thruster including a thruster wall, an anode, a cathode, and at least one ring electrode. The thruster wall defines a cylindrical channel, the cylindrical channel having a first end and an opposing second end in fluid communication with the first end, where the cylindrical channel is adapted to receive incoming airflow. The anode is at the first end of the channel and the cathode is at the second end of the channel opposite the first end. The at least one ring electrode is positioned on the thruster wall.

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.

One or more embodiments relates to an air-breathing plasma thruster including a thruster wall, an anode, a cathode, and at least one ring electrode. The thruster wall defines a cylindrical channel, the cylindrical channel having a first end and an opposing second end in fluid communication with the first end, where the cylindrical channel is adapted to receive incoming airflow. The anode is at the first end of the channel and the cathode is at the second end of the channel opposite the first end. The at least one ring electrode is positioned on the thruster wall.