A component assembly comprises a first housing and a second housing jointed by a coupling assembly. The coupling assembly comprises a coupling body and a floating torque ring axially slidably interfaced to the coupling body. The coupling body comprises a first threaded portion engaged with a first threaded coupling section of the first housing, and a second threaded portion engaged with a second threaded coupling section of the second housing. The floating torque ring is radially fixed to the coupling body, and is axially movable relative to the coupling body. Rotation of the floating torque ring causes relative rotation of the coupling body, thereby threadably joining the first housing and the second housing about the coupling body independent of axial positions of the housings due to the axially movable floating torque ring. A method of joining the housings is provided.

Disclosed herein is a snap alignment guard for a nut plate ring. The alignment guard includes a curved elongated body comprising an inner surface and an outer surface. The alignment guard further includes a plurality of couplings extending from the inner surface. Each of the plurality of couplings are configured to engage a nut plate ring to attach the alignment guard to the nut plate ring. The elongated body forms a plurality of apertures defined in the outer surface. Each of the plurality of apertures are configured to receive at least a portion of a nut plate to maintain a circumferential position of the nut plate relative to an inner surface of the nut plate ring.

A joint system including a support device with a plurality of radial extensions extending in at least a first direction from the support device, each individual radial extension of the plurality of radial extensions terminating at a distal engagement end and a receiving device separate from the support device with a notch area to receive the distal engagement ends of each radial extension of the plurality of radial extensions and a contact area upon which a length of the radial extensions of the plurality of radial extensions engage when the distal engagement end of each radial extension of the plurality of radial extensions are engaged within the notch area. At least one radial extension of the plurality of radial extensions is configured to be flexible between a first position to provide for at least one of assembly and disassembly of the support device to the receiving device and a second position when the support device and the receiving device are assembled. Another system and method are also disclosed.

A joint system including a support device with a plurality of radial extensions extending in at least a first direction from the support device, each individual radial extension of the plurality of radial extensions terminating at a distal engagement end and a receiving device separate from the support device with a notch area to receive the distal engagement ends of each radial extension of the plurality of radial extensions and a contact area upon which a length of the radial extensions of the plurality of radial extensions engage when the distal engagement end of each radial extension of the plurality of radial extensions are engaged within the notch area. At least one radial extension of the plurality of radial extensions is configured to be flexible between a first position to provide for at least one of assembly and disassembly of the support device to the receiving device and a second position when the support device and the receiving device are assembled. Another system and method are also disclosed.

An aircraft safety apparatus removably disposed on at least a portion of an aircraft, the aircraft safety apparatus including a parachute canister, including a main body to store at least one item therein, and at least one parachute disposed within at least a portion of the main body to reduce a rate of descent of the aircraft in response to extraction from the main body, and a rocket canister removably connected to at least a portion of the main body to at least partially fill at least a portion of the main body with a combustible gas, and a gas canister removably connected to at least a portion of the main body to at least partially fill at least a portion of the main body with a non-combustible gas.

A cover 10 and method for protecting a missile 15 with stowed wings 20 and connected to a vessel carrying it. The cover 10 includes a spoiler shaped front part 25 for covering a gap between the wings 20 of the missile 15 and the fuselage of the missile 15 for minimizing aerodynamic forces.

A cover 10 and method for protecting a missile 15 with stowed wings 20 and connected to a vessel carrying it. The cover 10 includes a spoiler shaped front part 25 for covering a gap between the wings 20 of the missile 15 and the fuselage of the missile 15 for minimizing aerodynamic forces.

A system for separating composites of a space launch vehicle, comprising non-pyrotechnic separating modules distributed between the composites to be separated and a device for activating the separation modules, which can generate the simultaneous activation of all of the separating modules. The activation device consists of a source of compressed gas, the outlet of which is connected to each separation module.

A system for separating composites of a space launch vehicle, comprising non-pyrotechnic separating modules distributed between the composites to be separated and a device for activating the separation modules, which can generate the simultaneous activation of all of the separating modules. The activation device consists of a source of compressed gas, the outlet of which is connected to each separation module.

The forward firing fragmentation (FFF) munition includes a body, a flight system carried by the body and configured to maneuver the munition in flight, and a warhead carried by the body and including an explosive configured to detonate and expel fragments in a pattern. A near field barrier (near field barrier), such as the guidance system, is carried by the body in front of the warhead and communicatively coupled via a communication link to the flight system. A fragmentation adjustment system is configured to physically displace the near field barrier relative to the warhead while maintaining the communication link between the near field barrier and the flight system until detonation of the explosive.