Abstract: 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.

Abstract: An improved, projectile launching system that carries the bulk of its weight and ammunition in a mechanical backpack called Turtle. Turtle can be scaled up to carry much larger rounds like torpedoes or artillery shells, for submarines and artillery. The GUN can be scaled up as well.

Abstract: Gas generators may be utilized for launching a projectile. Launch tubes may include gas generators. Methods of launching a projectile may include utilizing gas generators to impart an initial velocity to a projectile.

Abstract: A vehicle for launching from a gun such as a gas gun and having a housing; preferably incorporating a precessional attitude control system; and utilizing a flared base, fins, or active use of the attitude control system during passage through the atmosphere. Subtly canting the fins can produce desired spinning of the vehicle. The propulsion system can employ liquid, hybrid, or solid fuel. A removable aero-shell assists atmospheric flight with thermal protection being provided by anticipated ablation, an ablative aero-spike, or transpirational cooling. And a releasable sabot enhances the effectiveness of the launch.

Abstract: One embodiment includes a launch vessel defining an elongate, linear interior extending from a bottom portion to an exit opening. The embodiment includes a ram slidably disposed in the launch vessel, the ram sealed to the vessel. The embodiment also includes one or more wedges coupled to the launch vessel along the interior proximal the exit opening, with each wedge shape sized to increasingly narrow a cross section of the interior along an exit vector extending from the bottom portion toward the exit opening. In the embodiment, the vessel is to house a charge proximal the bottom portion, the charge to propel the ram along the exit vector, with the one or more wedges sized to stop be ram inside the interior.

Abstract: The disclosed system, device and method for deploying a sub-module from a carrier vehicle generally includes: a sub-module projectile (100) housed within a carrier vehicle; a rolling diaphragm (115) sealed between a first pressure chamber volume (145) and a second sub-module containment volume (e.g., substantially formed on the opposing side of rolling diaphragm 115 relative to pressure chamber 145); and a release mechanism (500), wherein the sub-module projectile (100) is secured until releasable deployment from the carrier vehicle. Disclosed features and specifications may be variously controlled, adapted or otherwise optionally modified to improve ejection, deployment and/or dispersal of a variety of sub-modules from a variety of carrier modules. Exemplary embodiments of the present invention generally provide for the ejection and dispersal of kinetic energy rod warheads from a kill-vehicle.

Abstract: An apparatus for launching a vehicle includes a bag and an inflator in fluid communication with the bag, the inflator configured to generate a gas to inflate the bag. The apparatus is operable to launch the vehicle. A method for launching a vehicle includes the step of providing an apparatus for launching the vehicle, the apparatus comprising a bag and an inflator in fluid communication with the bag. The method further includes the step of activating the inflator, such that a gas flows from the inflator, and the step of inflating the bag with the gas to launch the vehicle.

Abstract: The present invention discloses a missile ejection system and a canister thereof.

Abstract: An apparatus for launching a vehicle includes a bag and an inflator in fluid communication with the bag, the inflator configured to generate a gas to inflate the bag. The apparatus is operable to launch the vehicle. A method for launching a vehicle includes the step of providing an apparatus for launching the vehicle, the apparatus comprising a bag and an inflator in fluid communication with the bag. The method further includes the step of activating the inflator, such that a gas flows from the inflator, and the step of inflating the bag with the gas to launch the vehicle.

Abstract: A cold-gas munitions launch system is disclosed. In the illustrative embodiment, the system includes a munitions canister, a gas generator, and a sled. The sled supports a munition. The gas generator is located in the aft end of the munitions canister. When ignited, the gas generator produces gas, which drives the sled forward. As the sled reaches the end of the canister, the munition is launched by its own inertia, at a velocity that is within the range of about 3 to 9 g. After the munition clears the canister and travels at least about 150 feet from it, the munition's booster is ignited.

Abstract: A cold-gas munitions launch system is disclosed. In the illustrative embodiment, the system includes a munitions canister, a gas generator, and a sled. The sled supports a munition. The gas generator is located in the aft end of the munitions canister. When ignited, the gas generator produces gas, which drives the sled forward. As the sled reaches the end of the canister, the munition is launched by its own inertia, at a velocity that is within the range of about 3 to 9 g. After the munition clears the canister and travels at least about 150 feet from it, the munition's booster is ignited.

Abstract: The illustrative embodiment of the present invention is a munitions launch system. The launch system comprises a canister and a cold launch system. In the illustrative embodiment, the cold launch system comprises a sled and a release system. In the illustrative embodiment, the release system includes a sled release mechanism, which releasably secures the sled to the munitions canister, and a munitions release mechanism, which releasably secures a munition to the sled. Actuation of the sled release mechanism releases the sled for movement within the canister. After the sled moves some minimal distance under applied force, the munitions release mechanism “automatically” actuates, releasing the munition from the sled so that the munition can be ejected from the canister.

Abstract: The illustrative embodiment of the present invention is a munitions launch system. The launch system comprises a canister and a cold launch system. In the illustrative embodiment, the cold launch system comprises a sled and a release system. In the illustrative embodiment, the release system includes a sled release mechanism, which releasably secures the sled to the munitions canister, and a munitions release mechanism, which releasably secures a munition to the sled. Actuation of the sled release mechanism releases the sled for movement within the canister. After the sled moves some minimal distance under applied force, the munitions release mechanism “automatically” actuates, releasing the munition from the sled so that the munition can be ejected from the canister.

Abstract: A missile launcher comprising a canister for housing a missile and piston based launcher, the piston being arrested in the tube after launch of the missile.

Abstract: A missile launcher comprising a canister for housing a missile and piston based launcher, the piston being arrested in the tube after launch of the missile.

Abstract: A launch tube assembly including an aft launch tube portion, a forward launch tube portion, and a transfer sleeve having a first end fixed to and adjacent the forward end of said aft launch tube portion and a second end adjustably receiving the forward launch tube portion. A forward end of the aft launch tube portion faces a rearward end of the forward launch tube portion within the transfer sleeve. An adjustable plenum is present having a volume within the transfer sleeve defined by an adjusted distance between the facing ends of aft and forward launch tube portions. An end cap is pinned to a forward end of the forward launch tube portion, a gas generator housed in the aft launch tube portion, and a countermeasure device is housed in the forward launch tube portion. An adjustably selected volume of the plenum is such that a gas generated by the gas generator will enable propulsion of the countermeasure device at a predetermined acceleration from the forward launch tube portion.

Abstract: A combined defense and navigational system on a naval vessel is disclosed. The disclosed system includes a track-while-scan pulse radar which is controlled to provide either navigational information or tracking information on selected targets. Additionally, the disclosed system includes a plurality of guided missiles, each of which may be vertically launched and directed toward intercept of a selected target either by commands from the track-while-scan radar or from an active guidance system in each such missile. The invention herein described was made in the course of or under a contract or subcontract thereunder, with the Department of Defense.

Abstract: A retrofitable breech is disclosed for use on existing tubes for launching vehicles, such as torpedoes. The breech utilizes gas generators such as commercial off the shelf automotive airbag inflators, for propelling the torpedo from the tube. A plurality, typically three or four, generators are used and are fired in sequence with a controlled time delay. A retrofitable device is also disclosed for activating the weapons securing mechanism to release the torpedo. In addition, a release mechanism is disclosed for pulling the electrical connector plug on the torpedo. The sequence of releasing the torpedo, retraction of the plug and firing the inflators is controlled by a controller upon initiation of the firing sequence.

Abstract: A launch assist system for supplementing the launch acceleration forces of a projectile, rocket or missile. An airtight chamber covered by a flexible elastic membrane supports a platform in the center of the membrane; the platform is electromagnetically coupled to a cocking mechanism that withdraws the platform into the chamber. Air within the chamber is removed and compressed to be stored in a holding tank as the platform is lowered into the chamber and as the flexible elastic membrane extends into the chamber. The electromagnetic coupling may be triggered to release the platform to permit the stored energy in the extended flexible elastic membrane, and in supplemental force members, to apply acceleration forces to a launch vehicle; the compressed air stored in the tank is simultaneously released to fill the chamber as the flexible elastic membrane is withdrawn.

Abstract: A gas generating eject motor includes a case containing an ignitable low temperature gas generant material that does not produce toxic gases upon the combustion thereof. The gas generant material is generally contained with a screen enclosure housed within the case. An igniter is disposed within the gas generant material for selectively igniting the gas generant to thereby generate combustion gases. A nozzle is disposed within an open aft end of the case for focusing and directing the combustion gases generated by the ignited gas generant material. The case is constructed and arranged to be separably attached to the aft end of a rocket to be launched from a launch platform, so that, upon ignition of the gas generant, the combustion gases focused by the nozzle will apply a thrust to the rocket and thereby propel, or eject, the rocket from the launch platform, at which time the combustible propellant of the rocket motor will ignite and the eject motor will be separated from the rocket.

Abstract: A system for boosting the velocity of a rocket utilizing a container having a bottom and a side wall portion extending outwardly from the bottom. The side portion terminates in a peripheral edge and forms a chamber. A platform is supported in the chamber and is movable from a first position to a second position adjacent the peripheral edge of the side wall portion of the container. Exhaust gases are conducted to the chamber such that movement of the platform within the container supporting the rocket takes place.

Abstract: An airborne pneumatic launch tube ejection system to described for launching an aerospace vehicle/payload into orbit. The system can be installed in a jet transport aircraft without requiring structural modifications.

Abstract: An apparatus for launching projectiles from a host aircraft is disclosed. The apparatus comprises: a rotary launcher, a plurality of launch tube assemblies, a plurality of projectile retention means, and a plurality of ejection cartridges. The rotary launcher has a plurality of support fittings thereon, each for securing a tube assembly to the rotary launcher. Each projectile retention means securely retains each projectile within its respective launch tube. Each ejection cartridge is mounted to a respective launch tube assembly and interfaces with a projectile retention means to provide an ejection of that projectile retention means.