Devices and techniques including possibly mass-produced manufacture of fungible launch vehicles, suitable for customization to payload specification, and programming to achieve specified delivery. Speed of assembly is adjustable to demand for deliveries. Customization occurs after manufacture and delivery and in response to payload specification. Payload specification includes weight and balance, volume, packaging, and release mechanism and order. No individual launch vehicle is manufactured to meet any particular specification. Launch vehicles are delivered from assembly to a launch site or nearby storage. Launch vehicles can be allocated and customized upon demand, at the time of launch. Customization includes adjustment of weight and balance, attitude control, or air launch parameters. Software receives specifications of individual payloads and delivery parameters and determines customizations to achieve those specifications and parameters. Models of operation of launch vehicles and payload delivery can be updated in response to results of a launch.

Devices and techniques including possibly mass-produced manufacture of fungible launch vehicles, suitable for customization to payload specification, and programming to achieve specified delivery. Speed of assembly is adjustable to demand for deliveries. Customization occurs after manufacture and delivery and in response to payload specification. Payload specification includes weight and balance, volume, packaging, and release mechanism and order. No individual launch vehicle is manufactured to meet any particular specification. Launch vehicles are delivered from assembly to a launch site or nearby storage. Launch vehicles can be allocated and customized upon demand, at the time of launch. Customization includes adjustment of weight and balance, attitude control, or air launch parameters. Software receives specifications of individual payloads and delivery parameters and determines customizations to achieve those specifications and parameters. Models of operation of launch vehicles and payload delivery can be updated in response to results of a launch.

A booster system for a launch vehicle includes a plurality of core boosters and a plurality of patchy boosters. The plurality of core boosters and the plurality of patchy boosters are arranged in an inner space of a rocket casing of the launch vehicle, and the plurality of patchy boosters is separatable from the launch vehicle.

A harmless low-consumption on-orbit continuous launch system includes a satellite platform, a launch apparatus and a plurality of CubeSats. The satellite platform carries the launch apparatus and dozens or hundreds of CubeSats, and is launched from a ground into an orbit for on-orbit operation. The launch apparatus is configured to store the plurality of CubeSats and provide power for on-orbit launching of each of the CubeSats. A solid working medium in the launch apparatus is activated by heating to undergo a phase change, and the activated solid working medium expands instantly and is converted into a high-pressure gaseous working medium. The high-pressure gaseous working medium does work to eject the CubeSats, such that the CubeSats obtain a speed increment. The CubeSats enter a transfer orbit towards different target spacecraft through the speed increment applied by the launch apparatus to perform a plurality of different on-orbit serving missions.

An apparatus for launching, recovering, transporting, and storing vehicles is disclosed. The apparatus stabilizes the vehicle while it is in operation or inactive and has a frame connected to at least one stabilizer. In certain configurations, the apparatus stabilizes the vehicle without using the vehicle's onboard landing gear. The apparatus may also include at least one pad connected to the apparatus.

Systems and methods for launching a plurality of spacecraft, provided in a stack of spacecraft, from a launch vehicle traveling along an in-track path include releasing, in a first separation event occurring at a first time, a first spacecraft from the stack of spacecraft using a first separation force having a first separation force in-track component along the in-track path. Subsequently, in a second separation event occurring at a second time, a second spacecraft is released from the stack of spacecraft using a second separation force having a second separation force in-track component along the in-track path, wherein the second time occurs a first time delay after the first time. The first and second separation in-track components may be different, such as by varying a magnitude of the separation force or an angle at which the spacecraft is launched.

An interplanetary transportation system that includes a tunnel that spans between different planetary bodies and uses an electromagnetic propulsion system for propelling space-faring vehicles. The tunnel can be fixed and powered by outer space energy resources, such as the sunlight. The tunnels include fixed spaced rings and a mobile ring. The vehicle can be mounted to the mobile ring, wherein the spaced rings and the mobile ring propels the vehicle using motional EMF.

The invention relates to a device and a method for the connection and linear separation of two elements, such as the two stages of a spacecraft, consisting in using a tube containing a pyrogenic-type material and a glue arranged around the tube, particularly in contact with the elements. The pyrotechnic triggering of the pyrogenic material causes heating and the melting or carbonisation of the glue and the separation of the two elements.

This disclosure describes various techniques and systems for rapid low-cost access to suborbital and orbital space and accommodation of acceleration of sensitive payloads to space. For example, a distributed gas injection system may be used in a ram accelerator to launch multiple payloads through the atmosphere. Additionally or alternatively, multiple projectiles may assemble during flight through the atmosphere to transfer and/or resources to another projectile.

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.