Abstract: An assembly comprising a multiple payload set for a launch vehicle and a stiff and rigid ground support equipment. The multiple payload set comprising a plurality of payloads, wherein the plurality of payloads are interconnected via a non-self-supported connection structure before assembly of the multiple payload set to a dispenser body. Each payload comprises first attachment means attached to the non-self-supported connection structure, wherein the non-self-supported connection structure comprises second attachment means attached to the ground support equipment, for attachment of the multiple payload set to the dispenser body. The ground support equipment is attached to the multiple payload set via the second attachment means to reinforce and secure the multiple payload set to enable transport and maneuverability of the multiple payload set without jeopardizing the non-self-supported connection structure.

Abstract: A cover for an empty rail missile launcher that can be used in flight. The cover is shaped to reflect radar signals transmitted by a radar transmitter away from the radar transmitter to reduce detectibility by radar. The cover may also be coated with radar absorbent material to reduce detectibility by radar. Hangers are used to mount the cover to the rail missile launcher. The cover is provided with a grounding mechanism to dissipate precipitation static. A restraint mechanism is provided to prevent the cover from inadvertently sliding off the rail missile launcher.

Abstract: A finless mortar tube made of a superalloy includes, seriatim, a breech end, a beginning taper point, an ending taper point, a lower clamp region, an upper clamp region, and a muzzle end. The nominal wall thickness of the tube is constant from forward of the breech end to the beginning taper point and the nominal wall thickness of the tube decreases from the beginning taper point to the ending taper point. The mortar tube is capable of a substantial increase in the rate of fire compared to conventional mortar tubes.

Abstract: A launch device may be prepared for launch. The launch device may be assembled in a horizontal position on a mobile device. A lifting device attached to the mobile device may be coupled to the launch device. The launch device may be moved to a launch site using the mobile device. The launch device may be moved to a vertical position at the launch site using the lifting device. The launch device may be launched.

Abstract: In a ground launcher, two or more housing-transportation-launch assemblies for respective missiles are placed one on top of the other and connected releasably and interchangeably to each other; each housing-transportation-launch assembly has a respective outer casing, which in turn has longitudinal end walls breakable from inside the casing, and a deflecting body for deflecting the exhaust gas of the engine of the missile; a guide and protection assembly being interposed between the casing and the missile to guide the missile in the set launch direction, and to protect the missile against shock or vibration.

Abstract: A solid-fuel rocket assembly including an elongate fuel container having a long axis, and an inner surface spaced outwardly from, and generally circumsurrounding, that axis, and a continuous, elastomeric, heat-insulative, intumescence-behavior jacket adhered to the container's inner surface and defining a central chamber for receiving an elongate body of solid fuel. This structure implements a method for minimizing, in a solid-fuel rocket, heat damage to the wall of a solid-fuel container during burning of contained solid fuel including the steps of (a) producing dual-interface, continuous-presence, heat-insulative barriering in the zone existing between the container and burning fuel, with such barriering being characterized by (1) interfacially following any heat-produced deformations in the container wall, and (2) interfacially confronting the burning fuel with a tendency for intumescence-driven barrier-thickening.

Abstract: A capsule adapted for disposition in a submarine launch tube for retaining the missile until launch thereof. The capsule includes a cylindrically shaped housing including a plurality of layers of glass fibers and layers of graphite, the layers including an outer layer of glass fibers defining an outer skin of the housing, and an inner layer of glass fibers. A titanium flange is fixed on the housing and in contact with the layers of graphite. An adhesive layer is disposed on the outer skin and an interface support pad is mounted on the outer skin and retained thereon by the adhesive layer. A layer of metal foil is disposed inboard of the adhesive layer and between the outer layer of glass fibers and the inner layer of glass fibers, to serve as a barrier to products of galvanic reaction occurring between the graphite layers and the titanium flange.

Abstract: A steam generator missile ejection system has a vessel that contains water that becomes the pressurized steam source for missile ejection. A heating system within the vessel heats the water to steam and to the desired launch pressure. The heater is controlled to sequence operation and heat generation with a command from a controller shortly before initiation of a firing valve. A valve controls piping from the vessel to direct steam to a piping header and onto the ejection chamber of a launch tube. This event provides the launch pulse required to eject the payload from the missile tube. The launch energy requirements can be modulated by varying the pre-launch temperature of the water in the pressure vessel and can be controlled by an opening rate and length of open duration of the valve.