A series of the relay of the electromagnetic launcher with a gun and a floating launch platform to launch projectiles in space, wherein the projectile is accelerated along a path using electromagnetic force until the projectile reaches a desired direction and position. The direction of the path is determined by orienting the path in the desired direction using a catcher. the catcher and rail gun projectile as high above as possible, coming close to near space. When the said projectile will reach the last platform, it will be launched by the railgun and ignite its rocket engine to take the payload in space or as required to eliminate the need for large rocket boosters to launch the projectile.

A reaction propulsion device in which a first feed circuit for feeding a main thruster with a first propellant includes a branch connection downstream from a pump of a first turbopump, which branch connection passes through a first regenerative heat exchanger and a turbine of a first turbopump, and in which a second feed circuit for feeding the main thruster with a second propellant includes, downstream from a pump of a second turbopump, a branch-off passing through a second regenerative heat exchanger and a turbine of the second turbopump. At least one secondary thruster is connected downstream from the turbines of the first and second turbopumps.

A Vehicle Based Independent Range System (VBIRS) (10) comprised of individual stacked chambered modules that function as a single integrated system that provides a self-contained space based range capability, and is comprised of a power module (12), an artificial intelligence/autonomous engagement/flight termination system module (20), a satellite data modem module system (30) and a navigation, communications and control module system (40), all of which interface with a VBIRS test and checkout system (52) and a weather data system (116). The artificial intelligence/autonomous engagement/flight termination system module (20) is comprised of an inherent artificial intelligence capability that envelopes and interchanges data with an autonomous engagement controller (22) that contains all missile/rocket autonomous cooperative engagement, destruct decision software and range safety algorithm parameters required for optimum mission planning. VBIRS employed aboard an aircraft or between any combination of launching systems allows that aircraft to launch a missile/rocket from any location on earth, whether the missile/rocket is singularly launched by itself or as a larger group of missiles/rockets launched in a salvo arrangement, while providing collaborative real-time targeting to occur directly between missiles/rockets in conjunction with other missile/rocket launch platforms or stand-alone mission control centers.

A modular satellite for converting solar energy to microwave energy and transmitting the microwave energy to the earth to be converted into electricity includes solar panels configured to convert solar energy into direct current; a magnetron operatively connected to the solar panels to receive the direct current and configured to convert the direct current into microwave energy; a planar wave guide antenna operatively connected to the magnetron to receive the microwave energy and direct the microwave energy to a station on earth; and a coupling system for coupling with another satellite to form an array in response to at least one of locking, unlocking, and navigational commands. The satellite has a mass equal to or less than four kilograms, and a volume equal to or less than three liters.

A vertical take-off and landing spacecraft includes a body, a plurality of engines provided in the body to produce a jet flow and generate thrust, an abnormal signal acquiring unit that acquires an abnormal signal indicative of a presence of an abnormal engine among the plurality of engines, and an engine control unit that outputs a stop signal that stops a specific engine among a plurality of operating engines based on the abnormal signal.

A method of space travel using a high acceleration thrust vehicle in combination with a plurality of low acceleration thrust vehicles. A primary spacecraft has a kinetic launcher that is utilized to discharge a plurality of subsidiary spacecraft in order to navigate the primary spacecraft along a flight path. Each of the plurality of subsidiary spacecraft has a propulsion system, allowing each of the plurality of subsidiary spacecraft to navigate to a refueling point. The refueling point for each of the plurality of subsidiary spacecraft may be a central location or a unique position along a subsequent flight path. Each of the plurality of subsequent spacecraft is then reloaded onto the primary spacecraft or loaded onto a subsequent spacecraft for another voyage. The kinetic launcher can be repositioned in order to control the direction of the acceleration experienced by the primary spacecraft.

The invention is methods for landing rockets with precision using deep reinforcement learning for control. Embodiments of the invention are comprised of three steps. First, sensors collect data about the rocket's physical landing environment, passing information to rocket's database and processors. Second, the processors manipulate the information with a deep reinforcement learning program to produce instructions. Third, the instructions command the rocket's control system for optimal performance during landing.

A system (100) and method (300) for launching multiple satellites from a launch vehicle is provided. The system includes a mechanical structure (102) which has one or more mounting means (104A-F), a control unit (106) for controlling the one or more mounting means for positioning and separating the multiple satellites in the mechanical structure, an image capturing system for monitoring the positioning of each satellite in the mechanical structure. The mounting means are adapted to position the satellites in axial, inclined and radial separations at a distance to ensure that each satellite will not come in contact with each other in short duration as well as long duration of orbit evolution.

In broad embodiment, the present invention is a collection of systems, methods, and devices that describe a magnetic levitation linear accelerator driven hypersonic sled, magnetically coupled to a reusable Space Plane Launch Vehicle, which are accelerated to hypersonic speeds at sea-level altitude, thereby generating a hypersonic thermal shockwave of substantial energy which is then scavenged by methods and devices within the Space Plane Launch Vehicle, allowing it convert a distilled liquid water steam fuel payload, on a controlled basis, into supercritical steam exhaust and then use this supercritical steam exhaust for thrust continuing acceleration, using only electricity and distilled water as consumables and leaving only water vapor as a direct exhaust.

Various implementations of an extinguishable, solid propellant divert system for a flight vehicle are disclosed. Also disclosed are methods for using the divert system to control the flight of a flight vehicle. In one implementation, a divert system includes a hot gas generator pneumatically linked to one or more divert thrusters and an extinguishment valve. The extinguishment valve can be opened to rapidly depressurize the hot gas generator and extinguish the solid propellant burning inside. In another implementation, a method of controlling the trajectory of the flight vehicle includes repeatedly igniting and extinguishing the solid propellant in a hot gas generator and using the hot gas to provide divert thrust for the flight vehicle.