A modular weapon carriage and deployment (MWCD) system includes a strongback structure mountable to an aircraft. Left and right guide struts have respective upper ends attached to the strongback structure in spaced lateral positions. Each guide strut extends downward in a parallel arrangement. Each guide strut comprising a vertically-extending first engaging surface. Left and right suspension modules are engageable to opposite lateral sides of a first airborne store. Each suspension module includes a vertical channel that receives the engaging surface of the corresponding one of the left and right guide struts for relative vertical translation. A locking mechanism controllably locks to first engaging surface of the corresponding one of the left and right guide struts.

A modular weapon carriage and deployment (MWCD) system includes a strongback structure mountable to an aircraft. Left and right guide struts have respective upper ends attached to the strongback structure in spaced lateral positions. Each guide strut extends downward in a parallel arrangement. Each guide strut comprising a vertically-extending first engaging surface. Left and right suspension modules are engageable to opposite lateral sides of a first airborne store. Each suspension module includes a vertical channel that receives the engaging surface of the corresponding one of the left and right guide struts for relative vertical translation. A locking mechanism controllably locks to first engaging surface of the corresponding one of the left and right guide struts.

A terminal lead assembly for use in an integrated drive generator has a body formed of a lead portion and a support portion. The lead portion is received within an aperture in the support portion. The support portion has an outer periphery defined within a plane extending perpendicularly to a central axis of the lead portion. The outer periphery includes two curved portions and straight side portions extending parallel to each other and connecting the curved portions. An integrated drive generator and a method are also disclosed.

The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight.

The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight.

A system for detecting and neutralizing a target aerial vehicle comprises a counter-attack unmanned aerial vehicle (UAV) comprising a flight body and a flight control system supported about the flight body operable to facilitate flight of the UAV, and an aerial vehicle countermeasure supported by the flight body. The system can comprise an aerial vehicle detection system comprising at least one detection sensor operable to detect a target aerial vehicle while in-flight, and operable to provide command data to the counter-attack UAV to facilitate interception of the target aerial vehicle by the counter-attack UAV. Upon interception of the target aerial vehicle, the counter-attack UAV is operable to disrupt operation of the detected target aerial vehicle with the aerial vehicle capture countermeasure, thereby neutralizing the target aerial vehicle. The counter-attack UAV and systems may be autonomously operated. Associated systems and methods are provided.

A system for detecting and neutralizing a target aerial vehicle comprises a counter-attack unmanned aerial vehicle (UAV) comprising a flight body and a flight control system supported about the flight body operable to facilitate flight of the UAV, and an aerial vehicle countermeasure supported by the flight body. The system can comprise an aerial vehicle detection system comprising at least one detection sensor operable to detect a target aerial vehicle while in-flight, and operable to provide command data to the counter-attack UAV to facilitate interception of the target aerial vehicle by the counter-attack UAV. Upon interception of the target aerial vehicle, the counter-attack UAV is operable to disrupt operation of the detected target aerial vehicle with the aerial vehicle capture countermeasure, thereby neutralizing the target aerial vehicle. The counter-attack UAV and systems may be autonomously operated. Associated systems and methods are provided.

Example implementations relate to Additive Manufacturing (AM) pressurization diffusers. An example diffuser includes an integral component configurable for receiving and diffusing pressurant. Particularly, the integral component includes multiple elements manufactured as a single-piece structure, including an inner filter, outer shell, and flange. The inner filter includes micro-diamond holes that enable pressurant received at an opening of the inner filter to diffuse out of the inner filter and subsequently through holes positioned in a shell surface of the outer shell. The flange can position the diffuser such that the opening of the inner filter is in pressurant communication with a pressurant source (e.g., opening of a tank) enabling the diffuser to receive and diffuse pressurant in a predefined pattern. For example, when the diffuser is positioned inside a tank, the diffuser can have a frustum configuration that helps diffuse pressurant upwards towards inner sidewalls of a pressure vessel, tube or channel.

Example implementations relate to Additive Manufacturing (AM) pressurization diffusers. An example diffuser includes an integral component configurable for receiving and diffusing pressurant. Particularly, the integral component includes multiple elements manufactured as a single-piece structure, including an inner filter, outer shell, and flange. The inner filter includes micro-diamond holes that enable pressurant received at an opening of the inner filter to diffuse out of the inner filter and subsequently through holes positioned in a shell surface of the outer shell. The flange can position the diffuser such that the opening of the inner filter is in pressurant communication with a pressurant source (e.g., opening of a tank) enabling the diffuser to receive and diffuse pressurant in a predefined pattern. For example, when the diffuser is positioned inside a tank, the diffuser can have a frustum configuration that helps diffuse pressurant upwards towards inner sidewalls of a pressure vessel, tube or channel.

The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight.