A reusable floating device suitable for launching a space rocket has a support structure which includes a toroidal balloon housing and a rigid platform attached thereto; an elongated rigid structure surrounded by said support structure, releasably connected thereto, and adapted for attachment to a space rocket; at least one buoyant gas balloon within said balloon housing; and a compressor module and at least one rigid-walled tank carried by said platform. The compressor module is in confined flow communication with the at least one buoyant gas balloon and the at least one rigid-walled tank.

A carriage for use in a rocket launch system for cooperating with an electromotive cableway traction drives conveyed beneath a two axis pivot anchored to the earth, elevated into a co-axial transfer tube leading to three primary tether cables whose weight is offset by balloons. The carriage has traction drives which grip cables from which they derive power and rotate to drive the carriage from the low altitude to the high altitude. The traction drives rotate in the opposite direction as the carriage descends the cable following the launch of a rocket under gravitational force. The kinetic energy of the traction drive is converted to electrical energy which is fed back to the cables during descent of the carriage.

A high altitude vehicle is brought to a desired altitude above sea-level prior to the transfer of fuel and/or oxidant from an airplane to the high altitude vehicle. The high altitude vehicle may be towed to the desired altitude by a tow airplane or may reach the desired altitude under its own power. At the desired altitude, the high altitude vehicle is connected to the tow airplane via a tow cable. Alternatively, the high altitude vehicle may be mechanically carried by the tow airplane. Fuel and/or oxidant is transferred to the high altitude vehicle from the tow airplane via respective fuel and/or oxidant lines. The high altitude vehicle then separates from the tow airplane and proceeds to high altitude under its own power. The high altitude vehicle weighs less and may have smaller wings than a comparable vehicle configured for self-powered, fully fueled flight from takeoff.

A method of propulsion includes providing a high-speed-launch ramjet boost (HSLRB) stage and HSLRB engine attached to a launch aircraft providing a speed ?1.5 Mach. The HSLRB engine includes a combustion system and inlet(s) for air flow to the fuel injectors. A variable geometry (VG) nozzle having a nozzle actuator exhausts gas from combustion. A processor receives sensing signals from sensor(s) during flight that provides control signals to the nozzle actuator for dynamically controlling an aperture size of the VG nozzle, and if the inlet is a VG inlet to an inlet actuator to dynamically control the VG inlet shape. The HSLRB engine is ignited while attached to the aircraft at 1.5 to 1.99 Mach if assisting the aircraft to accelerate to 2.0 Mach, or at a speed of ?2.0 Mach if the aircraft can accelerate to 2.0 Mach autonomously, then the HSLRB stage is separated from the aircraft.

Provided are methods and systems for a modular multi-stage aerospace system having a first-stage vehicle that lifts and accelerates and is capable of achieving velocities of Mach 2.5, the first-stage vehicle powered by at least one turbine engine, and capable of autonomous and remote control; and a second-stage atmospheric flight vehicle capable of velocities of Mach 5.0, the second-stage atmospheric flight vehicle powered by at least one hydrogen-fueled turboramjet engine, and capable of carrying an internal payload; wherein the first-stage vehicle is adapted to support the second-stage atmospheric flight vehicle, as the first-stage vehicle reaches velocities sufficient to launch the second-stage atmospheric flight vehicle, and the second-stage atmospheric flight vehicle is capable of travel 12,000 miles.

The invention relates to a method for deflecting space debris comprising steps of: launching (E2) a thruster (2) by means of a sounding rocket (1) at a target altitude close to that of the one or more debris to be deflected. generating (E3) by the thruster a gas cloud (G) above the sounding rocket.

An air launched rocket for placing payloads in earth orbit comprising a lifting body having a cross sectional shape of an airfoil extending in a spanwise direction between a first and a second wing tip. The lifting body further comprises at least one rocket engine positioned at the first wing tip oriented for propelling the lifting body in the spanwise direction. The air launched rocket is combined with a carrier aircraft which is removably attached to a suction surface of the airfoil.

A high altitude vehicle is brought to a desired altitude above sea-level prior to the transfer of fuel and/or oxidant from an airplane to the high altitude vehicle. The high altitude vehicle may be towed to the desired altitude by a tow airplane or may reach the desired altitude under its own power. At the desired altitude, the high altitude vehicle is connected to the tow airplane via a tow cable. Alternatively, the high altitude vehicle may be mechanically carried by the tow airplane. Fuel and/or oxidant is transferred to the high altitude vehicle from the tow airplane via respective fuel and/or oxidant lines. The high altitude vehicle then separates from the tow airplane and proceeds to high altitude under its own power. The high altitude vehicle weighs less and may have smaller wings than a comparable vehicle configured for self-powered, fully fueled flight from takeoff.

A system for launching aerospace payloads includes a wingless, unmanned modified lifting body spacecraft (100), with a payload compartment in the forward section of the spacecraft. The spacecraft is propelled by hybrid rockets clustered in the aft section of the spacecraft. Reaction control system (RCS) modules control the flight path and its associated avionics hardware and software. This system also includes a carrier aircraft (200) configured to air-launch the spacecraft. The carrier aircraft includes a flight operations control system, which monitors the spacecraft's payload and monitors and controls launch and flight operations of the spacecraft. A ground-based mission control system monitors and controls the spacecraft's payload and monitors and controls the launch and flight operations of the spacecraft.

Systems, methods and device for payload transportation and high altitude atmospheric payload deployment. A gondola includes a frame which is configured to carry a payload, such as a rocket. The gondola includes a control system using a plurality of propellers to provide orientation changes. In the instance of a carried rocket, the system provides timed release such that the rocket is released in desired direction and pitch angle.