A gas generator includes a housing sized and configured to be located within a launch tube for a projectile. The housing defines a first propellant chamber; at least a second propellant chamber comprising a ring situated concentrically around the first propellant chamber; an expansion chamber; at least one first aperture between the first propellant chamber and the expansion chamber; and at least one second aperture between the at least a second propellant chamber and the expansion chamber. The gas generator also includes at least one propellant within each of the first propellant chamber and the at least a second propellant chamber of the housing; and a pyrotechnic delay connecting the first propellant chamber and the second propellant chamber. A launch tube assembly includes a tube containing at least one projectile and a gas generator. Related methods of launching a projectile are also disclosed.

A gas generator includes a housing sized and configured to be located within a launch tube for a projectile. The housing defines a first propellant chamber; at least a second propellant chamber comprising a ring situated concentrically around the first propellant chamber; an expansion chamber; at least one first aperture between the first propellant chamber and the expansion chamber; and at least one second aperture between the at least a second propellant chamber and the expansion chamber. The gas generator also includes at least one propellant within each of the first propellant chamber and the at least a second propellant chamber of the housing; and a pyrotechnic delay connecting the first propellant chamber and the second propellant chamber. A launch tube assembly includes a tube containing at least one projectile and a gas generator. Related methods of launching a projectile are also disclosed.

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.

Various embodiments of this disclosure relates to a methods and related apparatuses for rapidly and visually determining and verifying multiple interface alignments of parts within a system. In particular, embodiments of the invention are directed to methods and related apparatuses enabling rapid visual determining and verifying multiple interface alignments of parts within at least one first system interface part that cooperatively engage with at least one second system's interface part each having at least one system-sub-system assembly alignment datum that requires the at least one first and second system's interface parts cooperatively and engagingly align within multiple respective tolerances of alignment.

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.

Apparatus and methods relating to a missile canister that utilizes a variable obturator assembly. The variable obturator assembly can include a plurality of gates that adjust based upon canister pressure at a base plate. In a maximum pressure situation experienced during successful missile egress from the canister, one or more of the gates can open in response to canister flyout pressure so as to increase flow area through the base plate, thereby reducing canister pressure. In a restrained firing scenario, the plurality of gates remain closed thereby preventing missile exhaust gases from flow up past the base plate which could lead to heating of a rocket motor and warhead. The variable obturator assembly can have multiple individual gates that are mounted to the base plate with a hinge assembly, with the gates held in a closed position against the base plate with a spring assembly.

Apparatus and methods relating to a missile canister that utilizes a variable obturator assembly. The variable obturator assembly can include a plurality of gates that adjust based upon canister pressure at a base plate. In a maximum pressure situation experienced during successful missile egress from the canister, one or more of the gates can open in response to canister flyout pressure so as to increase flow area through the base plate, thereby reducing canister pressure. In a restrained firing scenario, the plurality of gates remain closed thereby preventing missile exhaust gases from flow up past the base plate which could lead to heating of a rocket motor and warhead. The variable obturator assembly can have multiple individual gates that are mounted to the base plate with a hinge assembly, with the gates held in a closed position against the base plate with a spring assembly.

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.

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.