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.

The present invention relates to a casing intended to be externally applied, connected or fixed to the fuselage or to a wing of an aircraft or to a central or wing station/hardpoint of an aircraft, the casing entirely or partly delimiting a housing zone (HZ) of a super-orbital, orbital or sub-orbital launch vehicle.

The present invention presents an adjustable speed reusable rocket with attachable wings system which is optimized for multiple purpose, such as space travel, high-speed long-distance travel between different addresses on earth, etc. The rocket system comprises an adjustable speed rocket propulsion system (rocket booster), an attachable wings system, a payload or space shuttle and may include slider wings system, etc. Firstly, the rocket system flies at a lift force caused by the attachable wings system at a low speed (e.g., Mach 0.5˜3). While the rocket system reaches relatively high altitude (e.g., 25,000 meters), at this altitude, the air density is extremely low comparing with the surface of earth at zero sea level, and then the attachable wings system may detach from the rocket system and fly to a designated location as a glider or by its engine on a runway, and the rocket system begins to fully initiate propulsion system and exert the payload to forward at a super high speed. Comparing with rocket fully initiate propulsion system from earth surface, the aerodynamic friction and the aerodynamic heat caused by air is extremely small and low.

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.

Systems and methods for production of hydrogen peroxide, such as high-test peroxide, are disclosed. Representative systems and methods also include aerospace systems and space exploration missions implementing systems and methods for production of hydrogen peroxide. A representative system for making hydrogen peroxide can include: a water electrolyzer for receiving water and separating at least some of the water into hydrogen and oxygen; a proton-exchange membrane cell for receiving water, hydrogen from the water electrolyzer, and oxygen from the water electrolyzer and for combining the hydrogen, the oxygen, and the water into a first hydrogen peroxide solution having a first concentration of hydrogen peroxide in water; and a hydrogen peroxide concentrator for removing at least some of the water from the first hydrogen peroxide solution to yield a second hydrogen peroxide solution that has a second concentration of hydrogen peroxide in water that is greater than the first concentration.

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.

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 electromagnetic lock release mechanism includes: a frame, an ejection unit, a satellite unit, a lock release unit, and a lock release drive unit; the ejection unit includes an ejection spring, an ejection jack, and a spring sleeve; the lock release unit includes a locking pin, a locking slider, an unlocking spring, and a base; the lock release drive unit includes an electromagnet limit nut, an electromagnet moving core, and an electromagnet. Advantages of the present invention are as follows. The present invention is a point positioning lock release mechanism that can be used to separate micro-satellites and rockets and repeatedly tested, which provides reliable locking and separating of satellites and rockets in a complex mechanical environment, and can be repeatedly tested on the ground. The separation is entirely a mechanism action without pollution.

The invention relates to an aerial transport device by means of connections with supply lines and cables for the transport of electricity, liquids and goods, at the limit of the atmospheres of the planets, in areas with low gravitational attraction, so that the flight can take place in the formation. The aerial transport device by means of flight devices (A, A1n, B, Bn, A4) that are in motion and connected between them, characterized in that the system can supply (P1) and simultaneously transport physical objects, liquids, and energy (P) to and from the outer space of dense atmospheres (D) and to reach the maximum limit of the environment density suitable for space flight devices (A3) with aerodynamic load as well as for horizontal air transport (A4, A2, P, An, A3). The invention is technical device for transporting in space with flying devices and move in formation flight of at least three forming connections.