An aircraft has a boom, a propulsion assembly coupled to a first end of the boom, and a first wing coupled to a second end of the boom. The propulsion assembly is coupled to the boom by a rotating joint. A second wing is optionally coupled to the rotating joint. The first wing is coupled to the boom by a rotating joint. The first wing is coupled to the rotating joint by a hinge. A vehicle with roll, pitch, and yaw maneuverability able to mirror the aircraft movements may be coupled to the second end of the boom. The vehicle body may be picked up with a vehicle chassis disconnected from the vehicle body. The boom houses an energy source to power the propulsion assembly. A rudder is coupled to the second end of the boom. A paddle is disposed between the propulsion assembly and the boom.

Methods, systems and apparatuses are disclosed for delivering high triple point propellant to a rocket engine and maintaining the desired phase of the propellant during engine ignition.

A thermal control system may transfer energy (directly or after a delay) to a thrusting device that can be used to slow a reentry vehicle entering a gaseous atmosphere from orbit. The thermal control system may mitigate the heating of the vehicle by transferring heat generated by the viscous interaction between the vehicle and high-altitude portions of a planetary atmosphere to a working fluid. This working fluid may then be routed through and/or ejected through one or more nozzles aligned to produce thrust in a direction that opposes the forward motion of this vehicle. This counter thrust may help to slow the reentry vehicle and reduce the amount of kinetic energy that can be converted into thermal energy. The working fluid may also be stored to use for propulsion after the reentry vehicle slows below hypersonic velocities.

A system and methods are disclosed for an upper stage space launch vehicle that uses gases from the propellant tanks to power an internal combustion engine that produces mechanical power for driving other components including a generator for generation of electrical current for operating compressors and fluid pumps and for charging batteries. These components and others comprise a thermodynamic system from which system enthalpy may be leveraged by extracting and moving heat to increase the efficient use of propellant and the longevity and performance of the launch vehicle.

A microfabricated valve with no moving parts. In one embodiment, the valve includes a reservoir of a liquid that is in fluid communication with an outlet channel having a throat that is less than 100 microns wide. Preferably, the channel is an elongated slit. The configuration of channel is adapted and configured such that surface tension of the liquid prevents flow out of the channel. A heater increases the temperature of the meniscus of the fluid, until a portion of the fluid is ejected from the channel. The ejection of the fluid creates both a thrusting effect and a cooling effect.

The present disclosure discloses a propulsion method based on liquid carbon dioxide phase change and a propulsion device. The method includes the following steps of: accommodating carbon dioxide in a thermally insulated container in a liquid phase form; transiently heating to convert the carbon dioxide from a liquid phase to a gas phase; and jetting carbon dioxide gas after the phase change in a predetermined direction by a predetermined jet-out amount so as to obtain a propulsion force.

A method for creating an artificial reentry corridor. Several modules are deployed in a retrograde orbit relative to target debris. Each module releases a gas plume which, in turn creates an artificial reentry corridor. The debris passes through the corridor and becomes decelerated.

A modular device for a spacecraft includes a propulsion system having a tank, a plenum, and a manifold, wherein the propulsion system is integrally formed with a structural frame of the spacecraft. A method of manufacturing the modular device is also discussed, the method including utilizing an additive manufacturing process to construct the propulsion system.

This invention is pioneering a Strategic Trans-orbital Carrier (herein called a carrier’) which merges the technologies attributes of a plurality commercial jet engines with a plurality reusable rocket engines to provide capabilities permitting a smooth computer-controlled transition from terrestrial air space to insertion into and thru low earth orbit (LEO) and into high geostationary earth orbit (GEO). A carrier would return back to terrestrial air space with carrying approximately 60 tons of any type of customers' defined cargo and passengers which would include intermodal container modules, complete DoD military strategic devices; heavy industrial outfitting apparatuses; building components for infrastructure complexes; personnel and robots; and space defensive materials to an in-situ space complex. With a fleet of carriers', a routine commercial services becomes available that are built to and guided by FAA flight regulations using specific airport with runways greater than 8,000 feet and that can handle a carriers weight.

Cryogenic propellant tank (1) for a spacecraft engine, comprising an external enclosure (10) defining an internal volume, characterized in that the internal volume of the tank comprises a primary volume (V1) and a secondary volume (V2) connected to the primary volume (V1) via a valve (20) configured to selectively allow a passage of fluid from the primary volume (V1) to the secondary volume (V2), or to isolate the secondary volume (V2) from the primary volume (V1), the primary volume (V1) having a primary orifice (11) adapted to be connected to a first pressurization source (41), the secondary volume (V2) having a supply orifice (4) adapted to be connected to a supply line of a spacecraft engine (30), and a secondary orifice (12) adapted to be connected to a second pressurization source (42).