The system extracts water from lunar regolith and includes a regolith intake having a digging bucket that collects lunar regolith soil and a gravel separator that separates and discharges gravel and passes a mixture of ice-regolith powder having ice grains that are about 10-100 microns along the conveyor. A pneumatic separator receives the ice-regolith powder and pneumatically splits the ice-regolith powder into streams of different sized lithic fragments and ice particles per the ratio of inertial force and aerodynamic drag force of the lithic fragments and ice particles. Each split stream may include a magnetic separator that separates further the magnetic and paramagnetic lithic fragments from ice particles to discharge up to 80 percent of lithic fragments to slag.

Provided is a method and system of evaluating a constellation spare strategy based on a stochastic time Petri net, which is applied in the technical field of constellation operation management. The method comprises: constructing a single satellite STPN model and an orbital plane STPN model, and establishing a navigation constellation STPN model that includes multiple spare strategies according to the single satellite STPN model and the orbital plane STPN model; establishing an availability model according to the number of malfunctioning satellites and the constellation value (CV) in the navigation constellation STPN model, and establishing a cost model according to operating costs of the navigation constellation STPN model; and evaluating the navigation constellation STPN model using the availability model and the cost model, and determining a target spare strategy from the multiple spare strategies according to an evaluation result.

A space launch system includes a launch track and an elevating platform for horizontally launching aerospace vehicles at a takeoff velocity. The launch track includes a first portion horizontally oriented with respect to the horizon, a second portion positioned after the first portion and horizontally oriented with respect to the horizon, and a third curved transition portion disposed between the first portion and the second portion. The elevating platform is coupled to the launch track and is configured to receive and position an aerospace vehicle upon the launch track. A magnetic accelerator is disposed along the launch track for propelling the aerospace vehicle down the launch track to reach the takeoff velocity. The magnetic accelerator includes magnetic levitation trains, each comprising a respective plurality of carriers that couple to the aerospace vehicle.

A space launch system includes a launch track and an elevating platform for horizontally launching aerospace vehicles at a takeoff velocity. The launch track includes a first portion horizontally oriented with respect to the horizon, a second portion positioned after the first portion and horizontally oriented with respect to the horizon, and a third curved transition portion disposed between the first portion and the second portion. The elevating platform is coupled to the launch track and is configured to receive and position an aerospace vehicle upon the launch track. A magnetic accelerator is disposed along the launch track for propelling the aerospace vehicle down the launch track to reach the takeoff velocity. The magnetic accelerator includes magnetic levitation trains, each comprising a respective plurality of carriers that couple to the aerospace vehicle.

A rocket landing stabilization system can include one or more upright support structures such as posts, columns, or walls, from which one or more stabilizing elements can be supported. The stabilizing elements can be used to stabilize a rocket as it lands at a landing site. The rocket landing stabilization system can also include a cradle, funnel, or cone to catch or otherwise support a rocket as it lands at the landing site. The rocket landing stabilization system can be located on land or at sea.

A rocket landing stabilization system can include one or more upright support structures such as posts, columns, or walls, from which one or more stabilizing elements can be supported. The stabilizing elements can be used to stabilize a rocket as it lands at a landing site. The rocket landing stabilization system can also include a cradle, funnel, or cone to catch or otherwise support a rocket as it lands at the landing site. The rocket landing stabilization system can be located on land or at sea.

Concurrent rocket engine pre-conditioning and tank filling is disclosed. A disclosed example apparatus includes an inlet valve to supply a rocket propellant tank that is associated with a rocket engine with rocket propellant, and a flow director to direct at least a portion of a flow of the rocket propellant from the inlet valve to a chill line of the rocket engine to thermally condition the rocket engine as the rocket propellant tank is being filled with the rocket propellant.

Concurrent rocket engine pre-conditioning and tank filling is disclosed. A disclosed example apparatus includes an inlet valve to supply a rocket propellant tank that is associated with a rocket engine with rocket propellant, and a flow director to direct at least a portion of a flow of the rocket propellant from the inlet valve to a chill line of the rocket engine to thermally condition the rocket engine as the rocket propellant tank is being filled with the rocket propellant.

The present disclosure relates to a launch system and method. The launch system and method can include at least a preliminary accelerator tube system (PAT) that can be combined with a main accelerator tube system (MAT). The PAT alone or combined with the MAT can be used for launch of a vehicle for testing and/or for delivery of a payload.

The present disclosure relates to a launch system and method. The launch system and method can include at least a preliminary accelerator tube system (PAT) that can be combined with a main accelerator tube system (MAT). The PAT alone or combined with the MAT can be used for launch of a vehicle for testing and/or for delivery of a payload.