Abstract: A system for arresting and recovering test ballistic missiles is adaptable or use in an existing facility and with the existing arresting engine. A long loop of cable encircles a sheave on the nose-end of the test missile and is supported by sheaves mounted on the support structure. The ends of the cable loop are terminated on one side of a singletree device. The other side is connected by a single cable to the arresting engine. One end of the cable loop slidably engages with the singletree and has an end cap. As the test missile is launched the cable loop and singletree are drawn toward a ratchet mechanism which grasps the end cap. An intermittent pulling machine is disposed for anchoring one leg of the cable loop whereby the test missile may be later raised or lowered for recovery. The system effectively doubles the load carrying capacity of an existing arresting engine by providing mechanical advantage.

Abstract: A zero adhesion system whereby a protective missile launch pad is held against an EPM-coated missile skin surface having an intermediary cloth sheet thereinbetween. The pad comprises a steel sheet having perforated cleats defined therein, which sheet is affixed to the underside of the pad and releasably bears against the intermediary cloth sheet. This arrangement operates such that the protective missile launch pad is freely released from the missile at launch without adhesion to the EPM-coated missile skin.

Abstract: Apparatus for preventing a missile's rocket exhaust gases from contacting and adversely affecting, such as by overheating, the launch rails from which a missile may be launched. Such apparatus includes an angled member having first and second leg portions, the end of the first leg portion being pivotably secured to the rail. A member having an angled surface is mounted to the second leg portion. Prior to the launching of said missile, the apparatus is in a first operative position such that it is out of contact with said launch rail. When the exhaust gases are emitted from said missile, a portion of the exhaust is incident upon the angled surface which causes the apparatus to rotatably pivot into contact with the launch rail, whereby portions of two surfaces of the launch rail are protected from the exhaust.

Abstract: A fly trap for capturing umbilical plugs ejected radially outwardly from a missile during the initial portion of the launch, the fly trap comprises impact and retention arms and a ratchet and compression spring which cooperate with a housing to allow the arms to only rotate a limited amount to retain the plug within the arms and prevent it from rebounding into the missile as the missile accelerates in the launch tube.

Abstract: Apparatus for transferring azimuth alignment with modest accuracy to the dance systems of individual missiles in a pod configured for vertical launch. The apparatus includes a mechanical interface between two rods (attached to the missile and oriented to the missile's guidance system) and two v-groove elements (attached to the launch tube and oriented to a northfinder mounted on the pod).

Abstract: The system for aiming of a missile strapdown Inertial Measurement Unit for ases in which the IMU does not possess the capability of self-aiming involves no mechanical link between northfinder and IMU which would require uncoupling prior to launch to avoid expending the northfinder. The technique maintains an automatic, hands-off capability by use of a laser link for azimuth transfer rather than a manual, optical link. The northfinder and laser system are launcher mounted and are therefore not expended with the missile.

Abstract: A transom missile launching system is configured to mount rigidly above the water line on the stern of ships designated to carry missile type ordnance. The missile launcher consists of two symmetrical modules containing eight missile cells each. Missiles are launched in the normal mode from a "all up round" canister at a fixed angle of about 60.degree. from a line athwartship both to port and to starboard. At this angle the probability of launch into a wave in heavy seas due to ship roll is eliminated. The missiles propulsion motor exhaust gases are vented directly overboard at launch without being directed either within the ship or across the weather deck. At ignition a water tight cover at the base of the launching chamber is blown directly overboard into the water by the exhaust gas pressure and a path is therefore provided for the exhaust gas to be discharged directly into the sea.

Abstract: Apparatus for fast, accurate aiming of a missile from a launch vehicle. The pparatus permits fast accurate aiming of a missile inertial measurement unit for cases in which the inertial measurement unit does not possess required performance capability for self-aiming. The apparatus involves no optical link and is not expended with the missile.

Abstract: An airborne missile launcher for air launching of man-portable, tube-launched missiles includes a central support frame with attachment means for detachable attachment to an aircraft or other launching platform, with a central frame member having a launch tube saddle support assembly at each side of the frame member with quick detachable clamp means and an alignment guide for quickly positioning and securing launch tubes into position with auto connecting means for automatically connecting the electronics control system and coolant gas to the launch tube assembly upon clamping the assembly into position. An aerodynamic shell encloses the support structure and includes a quick release cover for providing access to the tube clamp assemblies for loading and unloading launch tubes.

Abstract: A rail launcher for a guided missile is shown to include a pair of movable sections, each actuable first to form a gap in an otherwise continuous rail for receiving a lug affixed to a guided missile and then to return to an initial position, capturing such lug and forming a track.

Abstract: Magnetic position sensing for an object is disclosed wherein the analogue the distance between an object and a sensor is detected for indicating changes in object position in one, two, or three dimensions. An accurate, and continous output signal indicative of object position and incremental changes in that position are obtained. Additionally, magnetic sensing provides motion sensing of a support structure or velocity and acceleration sensing of an object.

Abstract: An electromagnet sensing device which detects the first axial motion of a ssile relative to its launcher to provide timing information and indicate when the missile first moves axially.

Abstract: A rear cover for rocket launch tubes providing a seal between the tube and the rear of the rocket. The rocket is arranged in a manner such that the exhaust of a firing rocket will produce a seal between a sealing member and the rear of the rocket and will seal off the portion of the tube adjacent to the rocket itself, thus preventing exhaust gases from entering this portion of the launch tube.

Abstract: A rear cover for a rocket launch tube which is normally closed and which is capable of breaking away successively in one or more sections in response to the pressure and diameter of the rocket exhaust column or plume. The cover is so arranged that it will successively increase the area interconnecting the launch tube for the rocket with an exhaust duct or manifold as the rocket plume increases in diameter. The cover of an adjacent launch tube which is normally closed will prevent the exhaust gases from entering the launch tube of a stored rocket or the like.

Abstract: A system utilizing a rocket plenum design which is of a form to reduce and control combustion therein. The plenum is provided with two oppositely and upwardly extending exhaust ducts. Provision is made to eliminate blind pockets and stagnation passages in order to prevent possible explosions in the plenum during rocket firing.

Abstract: A rear door for a rocket launch tube provided to prevent rocket exhaust gas flow into an empty launch tube from an associated multiple-rocket plenum chamber. The door is maintained in a stored position while a missile is in the launch tube and is activated when the missile leaves the launcher. The door may be latched open and released by a sensor device at a selected position of the missile as it is leaving the launch tube. Preferably, gases from the launching missile power closure of the door, once the door is released from its open latched position. Once the door closes, a second latch locks it in place to seal off the launch tube from the plenum chamber.

Abstract: Apparatus for controlling the flow of exhaust gases between a plurality of rocket storage chambers, launch tubes or the like (herein referred to as chambers), and a common manifold for ducting rocket exhaust gases to a discharging location comprises a plurality of chamber-to-manifold flow transition sections, each having disposed within vertical portions thereof a pair of flow control doors. The flow control doors, pivotably mounted at upper portions in opposing relationship, are configured and counterbalanced to hang, in static conditions and under the force of gravity alone, in a fully or nearly fully closed condition. Alternatively, un-counterbalanced doors may be configured to hang, under static conditions, at least slightly inwardly inclined towards the vertical axis of the transition portion in which they are hung.

Abstract: 1.

Abstract: A breech and latch mechanism is described herein for use in an aircraft mile ejection launching system. The described mechanism is characterized by a fluid actuated piston that rotates a bell crank and link from a hook locking over-center position to a hook retracting position. The piston acts also as a sequencing valve to pass fluid to pressure actuated ejection rams. A pressure fluid distributing orifice structure and a pyrotechnic cartridge igniting firing pin structure are described also.

Abstract: A sighting and laying system to properly aim the missile gyro axis to a petermined elevation and to orient this same axis in any desired horizontal direction. These functions are performed without any preleveling of the launcher elevating and slewing mechanism and permits the missile launcher to be located on up to a 6.degree. slope in any direction.