An aircraft includes an airfoil and a hinge member to rotatably couple the airfoil to a structure of an aircraft. The hinge member defines at least a portion of a rotational axis. The aircraft also includes an indexing mechanism coupled to the airfoil and configured to, in a first state, inhibit rotation of the airfoil about the rotational axis, and in a second state, to permit rotation of the airfoil about the rotational axis between a first position and a second position that is angularly indexed relative to the first position. The aircraft further includes an actuator to selectively change a state of the indexing mechanism from the first state to the second state, from the second state to the first state, or both.

Systems and methods of calculating a ballistic solution for a projectile are provided. A ballistic system may include an airborne device, a ballistic computer, a data interface, and a flight module, or any combination thereof. The airborne device (e.g., a drone) may be operable to gather wind data along or adjacent to a flight path of a projectile to a target. The ballistic computer may be in data communication with the airborne device to receive the wind data. The ballistic computer may be configured to calculate a ballistic solution for the projectile based on the wind data. The data interface may be in data communication with the ballistic computer to output the ballistic solution to a user. The flight module may be configured to calibrate a flight path of the airborne device.

The present disclosure provides an assembly including at least one adjustable coupling mechanism. In one aspect, the first coupling mechanism includes a first component having a central axis parallel to its outside surface. The first component further includes an inside surface defined by a bore formed in the first component along a central bore axis. The central bore axis is offset from the central axis. The first component can be coupled to the assembly, uncoupled, rotated about its central axis, and recoupled to change a distance between the first coupling mechanism and another part of the assembly. The first component further includes a plurality of holes formed circumferentially around the bore bottom and extending through the bore bottom and the bottom surface of the first component that can be used to removably couple the first component to the assembly.

The present disclosure provides an assembly including at least one adjustable coupling mechanism. In one aspect, the first coupling mechanism includes a first component having a central axis parallel to its outside surface. The first component further includes an inside surface defined by a bore formed in the first component along a central bore axis. The central bore axis is offset from the central axis. The first component can be coupled to the assembly, uncoupled, rotated about its central axis, and recoupled to change a distance between the first coupling mechanism and another part of the assembly. The first component further includes a plurality of holes formed circumferentially around the bore bottom and extending through the bore bottom and the bottom surface of the first component that can be used to removably couple the first component to the assembly.

An active countermeasure for military rotorcraft against a heat-seeking missile threat involves one or more telescoping booms or poles that are articulated at their proximal end to the fuselage of the rotorcraft and have an IR-radiating decoy mounted on their distal tip. When a missile launch is detected the missile flight path is computed and one or more of the booms are extended and swung out to place the decoy on the shot line of the missile. The decoy is then switched on and lures the missile away from the vulnerable components of the craft, such as the engine, rotors, and fuselage so as to cause a miss or failing that a detonation away from the rotorcraft. The countermeasures are stored compactly against or within the tail when not deployed.

Various embodiments relate to an electromagnetic wave absorber having a honeycomb sandwich structure, which is capable of absorbing broadband electromagnetic waves using electromagnetic properties of a metal-coated dielectric fiber, may comprise: at least two honeycomb core layers in each of which hexagonal units formed of a material comprising the metal-coated dielectric fiber are continuously arranged; and skin layers which are disposed on top surfaces and bottom surfaces of the at least two honeycomb core layers and each include a bottom layer, a top layer, and an intermediate layer. Various other embodiments are possible.

Various embodiments relate to an electromagnetic wave absorber having a honeycomb sandwich structure, which is capable of absorbing broadband electromagnetic waves using electromagnetic properties of a metal-coated dielectric fiber, may comprise: at least two honeycomb core layers in each of which hexagonal units formed of a material comprising the metal-coated dielectric fiber are continuously arranged; and skin layers which are disposed on top surfaces and bottom surfaces of the at least two honeycomb core layers and each include a bottom layer, a top layer, and an intermediate layer. Various other embodiments are possible.

A system and method for distributing control over a drone and an active-payload carried by the drone to loosely coupled drone controller and payload controller, are disclosed. The active-payload includes a self-embedded payload controller and at least one controllable thrust source or moving weight. The drone controller identifies a current active-payload type that is coupled to the drone for performing one or more tasks and selects a control-type, which defines degrees of freedom (DOFs) to be controlled by the drone controller and released DOFs to be controlled by the payload controller, accordingly. The drone and active-payload perform the one or more task, wherein the drone controller controls maneuver instructions in drone controller controlled DOFs and simultaneously and asynchronously the payload controller controls maneuver instructions in the released DOFs by exerting controllable force or torque in the released DOFs by the at least one thrust source and/or moving weight.

The present disclosure relates to an ejecting system (1) for dispensing countermeasure. The system (1) comprising at least one magazine (2) comprising at least one expendable cartridge (3) and a transporting rack (4) extending in a first direction (D1). Further, the system (1) comprises a magazine feeding mechanism (5) arranged to cooperate with said transporting rack (4) to move each of the at least one magazines (2) from a stored position to a loaded position. Further, the system (1) comprises a dispensing means (6) arranged to hold said at least one magazine (2) when said at least one magazine (2) is in a loaded position, wherein the dispensing means (6) comprises an electrical connector arrangement (7). Moreover, the system (1) comprises a first positioning mechanism (8) arranged to move said dispensing means (6) and the at least one magazine (2) from the loaded position to a protruding position.

The present disclosure relates to an ejecting system (1) for dispensing countermeasure. The system (1) comprising at least one magazine (2) comprising at least one expendable cartridge (3) and a transporting rack (4) extending in a first direction (D1). Further, the system (1) comprises a magazine feeding mechanism (5) arranged to cooperate with said transporting rack (4) to move each of the at least one magazines (2) from a stored position to a loaded position. Further, the system (1) comprises a dispensing means (6) arranged to hold said at least one magazine (2) when said at least one magazine (2) is in a loaded position, wherein the dispensing means (6) comprises an electrical connector arrangement (7). Moreover, the system (1) comprises a first positioning mechanism (8) arranged to move said dispensing means (6) and the at least one magazine (2) from the loaded position to a protruding position.