Abstract: A missile launcher is provided with pyrotechnically-operated means for jettisoning the missile. The missile is hung under a sub-rail latched to the underside of the main launcher body and upon operation of the jettisoning means the sub-rail/missile combination is slid rearwardly to disengage the latches after which the combination is given a downward thrust away from the launcher body, the thrust being imparted just forward of the collective center of gravity of the missile/launcher combination to cause its downward departure to be assisted by negative lift. The jettisoning means may consist of a lever and linkage actuated by a gas-operated piston-and-cylinder.

Abstract: A solenoid-operated device, and especially a weapon-arming device, subject to inertial forces is provided in which the solenoid armature is operatively coupled to a counterbalancing mass operatively constrained to move in synchronism with but oppositely to the armature, inertial forces on the armature acting equally and oppositely on the counterbalancing mass. The counterbalancing mass surrounds the solenoid coaxially and has an annular extension provided internally with rack teeth that mesh with sprockets free to rotate on fixed pins, these sprockets also being in mesh with rack teeth on an extension of the armature. An armature retraction spring bears on a shoulder on the counterbalancing mass.

Abstract: An aircraft ejector release unit (E.R.U.) is provided in which ejection is accomplished by a pair of angularly moving ejection arms carrying pivotal thrust pads and both mechanically actuated by a common gas-operated piston-and-cylinder unit. The gas piston operates a crank that turns a central lever assembly coupled by actuating rods to rotate triangular cranks disposed near opposite ends of the E.R.U. Control links pivotally mounted at their upper ends on the E.R.U. body are pivotally connected at their lower ends to the ends of the ejection arms, and when the triangular cranks are rotated the ejection arms are extended by unfolding of the ejection arms and the control links, there being a pivotal connection between each crank and the respective ejection arm at a location intermediate the ends of the arm. Before the ejection arms extend, initial movement of the central lever assembly unlocks store suspension hooks of the self-releasing, sear type.

Abstract: An airborne missile launcher is provided which is of modular construction to carry a variety of different missiles. A main body section has top attachment points, whereby it is carried by an aircraft, and sub-rail hangers at its underside to receive alternative missile-carrying sub-rails each of which sub-rails has one or more longitudinal tracks for carrying one or more types of missile. The sub-rail may be mounted in telescopically sliding relationship with the main body section. To complete the launcher body, forward and aft body sections are attached to the main body section, each of the forward and aft body sections being selected from a number of different such sections to suit different types of missile. For certain missile types, the forward and aft sections may be simply a plastics fairing; for certain other missile types, the forward and aft section may house a missile umbilical retraction mechanism and other operative means.

Abstract: A missile launcher having fore and aft two-stage double-acting ejection rams is provided with a choked flow gas system to prevent interaction between the rams and avoid back pressure in the breech chambers. Two gas cartridges in two breech chambers supply ejection gas pressure and a third cartridge in a third breech chamber supplies gas for subsequently retracting the rams. The ejection gas pressure also actuates mechanisms for releasing fore and aft missile suspension hooks and crutching assemblies, and for withdrawing an umbilical electrical service plug. Each ram comprises an outer casing, an inner fixed hollow shroud tube and two relatively-moving members with annular pistons that extend telescopically from within the space between the casing and the shroud tube, the ejection gas being admitted down the interior of the shroud tube. The aft ram has a yoke to engage the missile and the forward ram a side plate.

Abstract: A powered linear actuator is provided primarily for releasing stores from aircraft, having dual closed loop servo motor systems driving a screw jack. The dual motors, which have samarium cobalt permanent magnets, drive the screw jack through differential gearing and each has an armature lock which functions automatically if a motor circuit fails thereby enabling the other motor to continue driving the actuator alone. Potentiometer feedback is applied to dual error amplifiers or polarized relays that compare the feedback position signal with the input command signal and drive separate motor energization channels. A replaceable plug-in resistor is provided in series with the potentiometer track so that the actuator stroke can readily be changed by changing one value plug-in resistor for another.