Abstract: A translating harness includes an umbilical within a translating assembly to define a translation distance. A method for operating the translating harness incudes launching a vehicle from a tube of a host system, the translating harness between a host system and the vehicle; completing a translation length of the translation harness; and disconnecting a vehicle connector of the translating harness from the vehicle while the vehicle is within the tube.

Abstract: A cable routing apparatus, for supporting an electric charging cable, includes a mounting plate and a pulley-bracket assembly, which is pivotally attachable to the mounting plate. The pulley-bracket assembly includes a pulley support member having a pulley support plate and at least one pulley support arm extending downwardly from the support plate. The pulley-bracket assembly further includes a pulley wheel for supporting part of the cable thereon, and a pulley axle extending through a central hub of the pulley wheel. A housing may be provided for covering the pulley-bracket member, and parts of the pulley support member may, optionally, be integrated into the housing. A kit including two of the described cable routing apparatus along with an intermediate pulley bracket and other components, as well as a method of installing the kit in a garage to provide a cable routing system are also described.

Abstract: An imaging connection device is provided for use with a vehicle and a trailer. The vehicle includes a hitch assembly, a wired vehicle interface, and a vehicle communications unit, and the trailer includes a tow assembly and a wire harness. The imaging connection device includes a housing defining a first connector configured to mate with the wired vehicle interface and a second connector configured to mate with the wire harness; a connector interface at least partially arranged within the housing and extending between the first connector and the second connector; a camera unit at least partially arranged within the housing and configured to capture image data representing a side view of the hitch assembly; and a wireless communications unit at least partially arranged within the housing and configured to transmit the image data captured by the camera unit to the vehicle communications unit for display on a display device.

Abstract: A guidance section connector interface system operable with smart or guided rockets to be launched from a rocket launcher comprising a rocket connector of a rocket in electronic communication with a guidance system of a guidance head of the rocket, a connector saver, and a launcher connector of a rocket launcher. The connector saver can be configured to connect the rocket connecter to the launcher connector. The connection between the connector saver and the rocket connector is configured to release upon launching the rocket, wherein the connector saver remains connected to the launcher connector to protect the launcher connector from the extreme conditions within the rocket launcher at launch.

Abstract: An umbilical cable disconnect device is disclosed. The umbilical cable disconnect device includes a base having an opening configured to receive an umbilical cable, a cutter extending into the opening of the base, and a spacer component disposed in the opening between the cutter and the umbilical cable. The spacer component maintains separation of the cutter and the umbilical cable prior to disconnect of the umbilical cable. The cutter is operable to penetrate the spacer component in response to displacement of the disconnect device relative to the umbilical cable to facilitate cutting of the umbilical cable by the cutter to disconnect the umbilical cable.

Abstract: A guidance section connector interface system operable with smart or guided rockets to be launched from a rocket launcher comprising a rocket connector of a rocket in electronic communication with a guidance system of a guidance head of the rocket, a connector saver, and a launcher connector of a rocket launcher. The connector saver can be configured to connect the rocket connecter to the launcher connector. The connection between the connector saver and the rocket connector is configured to release upon launching the rocket, wherein the connector saver remains connected to the launcher connector to protect the launcher connector from the extreme conditions within the rocket launcher at launch.

Abstract: Systems and methods for launching munitions are provided. In some embodiments, the system may include a launcher coupled to a vehicle and configured to retain a munition during transport by a vehicle and configured to route electrical signals from the vehicle to the munition. The system may also include a flexible, peel-away connector coupled to the launcher, the peel-away connector comprising an adhesive for coupling to at least a portion of the munition. The flexible, peel-away connector may be configured to route electrical signals from the launcher to the munition during transport and detach from the munition as the munition exits from the launcher during a launch.

Abstract: A weapon interface system, and methods of operating the same. The weapon interface system is coupled to an electrical interconnection system of a delivery platform and a weapon system coupled to a rack system. The weapon interface system includes a translation interface configured to provide an interface between the electrical interconnection system and an inductive power and data circuit. The weapon interface system also includes a weapon coupler, coupled to the translation interface, configured to provide an inductive coupling to the weapon system to provide mission information thereto.

Abstract: The invention relates to a separator device for separating the on-board and ground portions of a launcher fueling module, the device comprising: a locking system having a locking finger (50) mounted on the ground portion (22) and having a blocking portion (523), and a locking pin (42) on the on-board portion (21) co-operating by engaging with the blocking portion (523) in order to hold the on-board portion (21) and the ground portion (22) in a locking position. The separator system further comprises an actuation system that, under vertical movement of the launcher (10), enables the blocking portion (523) to be disengaged from the locking pin (42), whereby the on-board portion (21) is suitable for being separated from the ground portion (22). The invention also provides a method of separating the on-board and ground portions of a launcher fueling module, which method is implemented by means of such a separator device.

Abstract: A deployable raceway harness assembly for use with a multi-stage rocket includes a first cable bundle configured to extend across a second stage of a multi-stage rocket from a guidance unit to a first stage of the rocket. The deployable raceway harness assembly includes a deployable raceway cover configured for detachable coupling with the multi-stage rocket. The deployable raceway cover extends over at least the first cable bundle and a second cable bundle. The first cable bundle is fastened to the deployable raceway cover. The second cable bundle is configured to extend from the guidance unit to the second stage and is shorter than the first cable bundle. An in-flight deployment mechanism is configured to detach the deployable raceway cover and the first cable bundle extending across the second stage from the multi-stage rocket in-flight leaving the second cable bundle extending to the second stage in place.

Abstract: A blind-mating rocket launcher connector and protection system having a connector, a floating connector member, a cam, a connector cover, and a linkage between the cam and connector cover whereby the connector may mate with a second connector when the cam is displaced despite misalignments between the first and second connector. For the preferred embodiment, the floating connector member has multiple degrees of freedom with a reduced diameter portion and a lengthwise key whereby the connector is capable of mating with an aerodynamic hood of a rocket. The preferred embodiment biases and closes the connector cover upon the connector prior to a plume of the rocket passes the connector whereby exposure of the connector to the deleterious effects of the plume are minimized.

Abstract: Methods and apparatus for launching an effector according to various aspects of the present invention may include a fire control system. The fire control system may be responsive to a sensor, such as a radar, and may be connected to the effector, such as via a launcher. The file control system may be adapted to generate a fire control solution according to the data from the sensor, initiate a launch of the effector, and provide the fire control solution to the effector after initiating the launch.

Abstract: The invention relates to a separator device for separating the on-board and ground portions of a launcher fueling module, the device comprising: a locking system having a locking finger (50) mounted on the ground portion (22) and having a blocking portion (523), and a locking pin (42) on the on-board portion (21) co-operating by engaging with the blocking portion (523) in order to hold the on-board portion (21) and the ground portion (22) in a locking position. The separator system further comprises an actuation system that, under vertical movement of the launcher (10), enables the blocking portion (523) to be disengaged from the locking pin (42), whereby the on-board portion (21) is suitable for being separated from the ground portion (22). The invention also provides a method of separating the on-board and ground portions of a launcher fueling module, which method is implemented by means of such a separator device.

Abstract: Systems and methods for launching munitions are provided. In some embodiments, the system may include a launcher coupled to a vehicle and configured to retain a munition during transport by a vehicle and configured to route electrical signals from the vehicle to the munition. The system may also include a flexible, peel-away connector coupled to the launcher, the peel-away connector comprising an adhesive for coupling to at least a portion of the munition. The flexible, peel-away connector may be configured to route electrical signals from the launcher to the munition during transport and detach from the munition as the munition exits from the launcher during a launch.

Abstract: Methods and apparatus for communications between a fire control system and an effector according to various aspects of the present invention may include a communications link. The communications link may be coupled to a launcher for the effector and the effector. The communications link is detachably coupled to at least one of the launcher and the effector. The communications link may be adapted to transmit a fire control solution to the effector after initiating the launch.

Abstract: An apparatus comprising a housing having an opening, a connector unit, a moveable door, and a biasing system. The connector unit is located inside the housing. The connector unit is capable of providing an electrical connection to a complementary connector unit. The moveable door is capable of being moved into an open position and a closed position, wherein the closed position covers the opening. The biasing system is capable of aligning the connector unit with the complementary connector unit and causing the connector unit to engage the complimentary connector unit.

Abstract: In one embodiment, an automated system for mating a launch device to a launch platform may include a launch platform having a first electrical connector, and a interface member attached to the launch device. The interface member may include a second electrical connector configured to automatically couple to the first electrical connector of the launch platform.

Abstract: A retractable umbilical system includes an umbilical connector assembly, a latching connector assembly, and a retracting umbilical extending between the umbilical connector assembly and the latching connector assembly. The umbilical connector assembly is configured to bias the retracting umbilical into a retracted configuration. The latching connector assembly is configured to selectively retain the retracting umbilical in an extended configuration. The umbilical connector assembly includes a roller that is in contact with the retracting umbilical.

Abstract: An umbilical cord retractor assembly and method is provided for retracting an umbilical cord from a torpedo or other vehicle prior to launching the vehicle. A guide arm is utilized to guide a slide member along a predetermined path within the guide arm. The slide is connected through a link to the umbilical cord such that the umbilical cord is pulled to a predetermined position within the launch tube out of the way of the fins, shroud, and propeller of the vehicle. Prior to activation of the retractor assembly, the slide is affixed in position within the guide arm by a lock. A spring under tension applies a force to the slide. A release cord pulls a pin from the slide to release the cord at a desired time, thereby retracting the umbilical cord to the predetermined position within the launch tube.

Abstract: An umbilical cable for delivering electrical signals between an aircraft and a smart weapon carried by the aircraft. The umbilical cable includes cabling comprising a plurality of conductive wires, a first connector provided on one end of the cabling and configured to connect to the aircraft, and a second connector provided on the other end of the cabling and configured to connect to the smart weapon. The umbilical cable further includes an interface circuit electrically coupled between the first connector and the second connector via the plurality of conductive wires. The interface circuit is configured to receive via the first connector a non-standard combination of signals comprising at least one of data signals, control signals and power signals not receivable directly by the smart weapon to carry out operations.

Abstract: An umbilical cable for delivering electrical signals between an aircraft and a smart weapon carried by the aircraft. The umbilical cable includes cabling comprising a plurality of conductive wires, a first connector provided on one end of the cabling and configured to connect to the aircraft, and a second connector provided on the other end of the cabling and configured to connect to the smart weapon. The umbilical cable further includes an interface circuit electrically coupled between the first connector and the second connector via the plurality of conductive wires. The interface circuit is configured to receive via the first connector a non-standard combination of signals comprising at least one of data signals, control signals and power signals not receivable directly by the smart weapon to carry out operations.

Abstract: A rocket assisted payload launch system includes a heavy gauge metal shipping container that houses an array of containerized concentric launch tubes, or canisters. Spacers on each containerized concentric launch tube contact the adjacent tubes and retain the centers of the tubes a predetermined distance apart, and in a vertical orientation. A missile including rocket assisted payload (RAP) can be inserted into the open upper end of each tube, which also has a curved, closed bottom end. Umbilical cords are connected to each tube for providing target location information to the missile placed therein. A sequence controller selects the rocket assisted payload to be fired, and initiates the firing sequence by delivering power, via the umbilical cord, to the selected missile. The sequence controller may be manually operated, or may be operated, automatically, via a datalink, in the preferred mode of operation.

Abstract: The passive dynamically disconnecting arm features an arm having two ends wherein attached to the first end is a housing having both a plunger and an electrical connector providing positive engagement force during shock or vibration. The second end of the arm features a trunnion and torsion spring. The arm features a slot wherein a rod is placed inside operatively coupled to both the plunger and trunnion. When an object is attached to the electrical connector, the spring-loaded plunger compresses preventing the rod from moving and causing the second end of the rod to couple with a divot within the trunnion. When the object moves a predetermined distance, the spring-loaded plunger decouples from the rod and the electrical connector detaches from the object. The arm, by means of a torsion spring attached to the arm's second end, translates and rotates out of the object's path without striking the object.

Abstract: A device for retaining an element ejected by a pyrotechnic device when it is fired comprises at least one metal cap placed behind the nozzle of the device and designed to receive the ejected element, the cap being held in position by curved rigid links. The kinetic energy of the captured element carries along the cap and the captured element and the motion of the assembly is braked by the deformation of the rigid links. Application especially to the retaining of the rear igniter of a missile.

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.