The present invention relates broadly to a process and apparatus in field of thin-walled structures possessing high strength-to-weight ratio, and particularly to mirror structures utilizing corrugated, or similarly structured, predominantly hollow-core panel structures; and, even more particularly, heat collector structures utilized for concentration of radiant heat. The disclosed invention relates to an optical element utilized for concentrating radiation, and more particularly, high-concentration, reflective concentrators that are constructed from discrete conical concentrators utilizing flexible high-reflectance layers that are produced by roll-to-roll manufacturing. In its first preferred embodiment, the disclosed optical element preferably comprises a quasi-parabolic, multi-frustum, concentration optic.

The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec, and sliding electrical contacts in electrical connection with the electrical heater. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of concentric electrically conductive tubes, as well as an electrical energy source, such as a battery bank and associated inductor.

The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec, and sliding electrical contacts in electrical connection with the electrical heater. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of concentric electrically conductive tubes, as well as an electrical energy source, such as a battery bank and associated inductor.

An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.

An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.

Projectile carrier for a gas gun with a barrel defining a barrel bore arranged to guide a projectile, the projectile carrier including a projectile carrier bore for holding a projectile aligned with a barrel bore of the gas gun and to be sealingly in communication with a pressure chamber when the projectile carrier is in a service position, the projectile carrier being adapted to receive a projectile when in a loading position. The projectile carrier is distinct from the barrel and includes at least one projectile retaining element held in place by at least one locking element arranged to move on the projectile carrier between a locking position, in which the at least one projectile retaining element is engaged with a retention surface included by the projectile, and an unlocked position, in which the projectile is free to move under the effect of pressure in the pressure chamber.

An air cannon has a barrel and a sabot sized to fit within the barrel and configured to engage a projectile located within the barrel forward of the sabot. A flexible cord connects the sabot to a fixed location relative to the barrel. Forward motion of the sabot is decelerated by the cord after the sabot exits the forward end of the barrel, and the sabot is retained by the cord near the forward end of the barrel.

A baffled ram accelerator system includes a ram accelerator tube with an inner surface and an outer surface and a plurality of baffles disposed on the inner surface. The plurality of baffles forms a sequential series of propellant chambers along the longitudinal axis of the ram accelerator tube. An accelerator gun is also disposed on an input end of the ram accelerator tube, and the accelerator gun is positioned to fire a projectile into the ram accelerator tube.

A baffled ram accelerator system includes a ram accelerator tube with an inner surface and an outer surface and a plurality of baffles disposed on the inner surface. The plurality of baffles forms a sequential series of propellant chambers along the longitudinal axis of the ram accelerator tube. An accelerator gun is also disposed on an input end of the ram accelerator tube, and the accelerator gun is positioned to fire a projectile into the ram accelerator tube.

An unmanned aerial vehicle (UAV) launch tube (100) that comprises at least one inner layer of prepreg substrate (370) disposed about a right parallelepiped aperture (305), at least one outer layer of prepreg substrate (380) disposed about the right parallelepiped aperture, and one or more structural panels (341-344) disposed between the at least one inner layer of prepreg substrate (340) and the at least one outer layer of prepreg substrate (380). An unmanned aerial vehicle (UAV) launch tube (100) that comprises a tethered sabot (700,740) configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot (700,740) dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot (700,740) is hollow having an open end oriented toward a high pressure volume and a tether (740) attached within a hollow (910) of the sabot (700) and attached to the inner wall retaining the high pressure volume or attach to the inner base wall (1013). A system comprising a communication node (1500-1505) and a launcher (1520) comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node (1500-1505).