A carrier rocket system, with a carrier rocket, together with a launch assistance unit, which is detachably connected, or connectable, to the carrier rocket. The carrier rocket system is set up to take off in a horizontal launch via the launch assistance unit when thrust is generated by at least one propulsion unit of the carrier rocket. The launch assistance unit can be detached from the onward-flying carrier rocket after supersonic velocity has been reached, and is set up to fly back to the earth's surface after its detachment from the carrier rocket. The launch assistance unit preferably provides all the necessary structural supports to enable a carrier rocket that has been designed for a vertical launch to use one or more of its essential components without structural modifications. Also disclosed are a take-off method for a carrier rocket system, and a manufacturing method for a carrier rocket system.

Disclosed are systems and methods for carrying an aeronautical or launch vehicle to altitude for release to independent flight. The system may comprise one or more mounting elements affixed to a carrier aircraft along a mounting axis and actuatable from a retention configuration to a release configuration. The retention configuration enables the mounting elements to secure the vehicle to the carrier aircraft. Actuation from retention configuration to release configuration releases the vehicle from the carrier aircraft. A detent element is configured to restrict movement of the vehicle rotationally about, and axially along, a roll axis of the vehicle with respect to the carrier aircraft when the vehicle is secured to the carrier aircraft. The system may include an adaptor beam to which each mounting element is fastened, and by which the affixing is achieved. The retention configuration may enable the mounting elements to secure the vehicle beneath the carrier aircraft.

A system for launching aerospace payloads includes an 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.

An aerospace vehicle that permits horizontal launch and subsequent orbital deployment of a second stage. The vehicle can be returned to Earth for subsequent re-use. Both land-based and water-based launch is disclosed. A rocket propulsion engine is located at the center of gravity of the vehicle and rotates to provide vertical and horizontal thrust.

An autonomous aircraft system an airframe configured with a ventrally located payload bay open to the empennage of said airframe and payload bay terminating with a forward bulkhead which is configured to receive a payload module. The payload bay and the payload module are configured with corresponding fittings for connecting the payload module to the aircraft control systems and for securing the payload module within the payload bay.

A system for providing fuel and oxidant to a rocket in flight, including a rocket having at least one internal tank for storing propellant, at least one external tank for holding a liquid rocket propellant, and at least one umbilical hose in fluidic communication with the at least one internal tank and the at least one external tank. The at least one umbilical hose is configured to automatically disengage from the rocket when the rocket reaches a predetermined state such as a predetermined altitude, for example. The at least one internal tank remains in fluidic communication with the at least one external tank while the at least one umbilical hose is engaged.

A launch system and method for orbital or suborbital air-launch of a payload involving releasably coupling a launch vehicle with a towed aircraft via an articulatable carriage to form an air-launch assembly, towing the air-launch assembly via a tow aircraft and interconnected tow cable to a first altitude, releasing the air-launch assembly from tow at or above the first altitude, activating the towed aircraft propulsion system and initiating a pull-up and climb maneuver of the towed aircraft to a second altitude, articulating the articulatable carriage to shift the air-launch assembly from a stowed position to a deployed position with the launch vehicle spaced from the towed aircraft, releasing the launch vehicle from the articulatable carriage and thus from the towed aircraft, and activating the launch vehicle propulsion system for further altitude gain or to meet specific mission requirements.

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 system for providing fuel and oxidant to a rocket in flight, including a rocket having at least one internal tank for storing propellant, at least one external tank for holding a liquid rocket propellant, and at least one umbilical hose in fluidic communication with the at least one internal tank and the at least one external tank. The at least one umbilical hose is configured to automatically disengage from the rocket when the rocket reaches a predetermined state such as a predetermined altitude, for example. The at least one internal tank remains in fluidic communication with the at least one external tank while the at least one umbilical hose is engaged.

Spacecraft with increased cargo capacities, and associated systems and methods are disclosed, A representative spacecraft system includes a launch vehicle elongated along a launch vehicle axis and having at least one stage carrying a corresponding rocket engine. The representative system further includes an annular support structure carried by the at least one stage and positioned to support a cargo spacecraft having a service module and a cargo module. The cargo module of the cargo spacecraft is positioned along the launch vehicle axis in a direction distal from the support structure, and at least a portion of the service module of the cargo spacecraft positioned within an annulus of the support structure