A wing arrangement for an aircraft, comprising a wing having a base section and a tip section pivotably connected to base section such that the tip section is pivotable about a pivot axis between a deployed position and a stowed position. The wing arrangement also comprises a latching arrangement which includes an engagement portion, a latching actuator selectively movable between a first actuator position and a second actuator position, an elastically deformable structure, and a latching element. When the tip section is pivoted from the stowed or deployed position into an engagement position, the elastically deformable structure is initially deformed, and as the tip section pivots further into the deployed or stowed position, the elastic deformation of the elastically deformable structure decreases.

An installation system for a cabin of a vehicle includes at least one built-in component for installation in the cabin, multiple base elements for arrangement on a structurally fixed component of the vehicle and multiple holding devices that can be connected to the at least one built-in component. The holding devices each include a clamping unit with receiving space defined by at least two clamping members, wherein the receiving space can be moved between an open and a closed state through movement of at least one of the clamping members in the direction of the other clamping member in each case and wherein the clamping unit is configured to move the at least one clamping member by pressing the clamping unit onto a base element when the receiving space is in the open state and thereby closing the receiving space including the base element.

A lever-lock release system is configured to releasably couple two objects together, for example a parachute and a payload. The lever-lock release system may comprise a first lever and a second lever, each rotatably coupled to a rigid base. When activated, the levers cascadingly rotate to release a first object and a second object. With these systems and related methods, various failure modes may be eliminated, such as undesired premature deployment of recovery parachutes during aerial delivery.

A slingbar includes a sling attachment member. The sling attachment member includes a frame including a base having a top end and a bottom end, and a hook extending from the bottom end to a hook terminus. The hook terminus and the top end of the base define an opening. The hook, base, and opening bound an interior of the attachment member. A closure element includes an outboard gate hinged to the hook terminus and an inboard gate hinged to the base. The gates have a default state in which each gate extends laterally only part way across the opening.

A tactical extrication and rescue assembly includes a base member including opposite longitudinal ends, the base member comprising at least one mounting element for securing the base member to an article of clothing or gear; a quick de-coupling mechanism; a rescue strap releasably secured to the base member via the quick de-coupling mechanism at one of the opposite longitudinal ends of the base, the first and second end portions including respective first and second connection members. The quick de-coupling mechanism at the longitudinal end base ensures that the quick de-coupling mechanism falls out of the side of the base during use so that a rescuer can easily and readily locate and operate the quick de-coupling mechanism in an emergency, allowing the rescuer to quickly de-couple the rescue strap from the base and, thereby, the rescuer.

The invention relates to a hook (10), which may for example be used with a crane to lift heavy loads. In one embodiment, the hook may have a load-bearing portion (12) and an arm portion (14) where the arm portion can pivot relative to the load-bearing portion between open and closed configurations and may have a locking mechanism (20, 21, 29, 30, 32) that can lock the arm portion with respect to the load-bearing portion in the open configuration of the hook, in which configuration the arm portion and the load-bearing portion together define a discontinuous boundary. The hook may also be provided with a suspension portion (74), and the suspension portion, the load-bearing portion and the arm portion may be pivotally coupled with respect to each other.

Described is a self locking safety spring clip including at least a main body (21) provided with an opening (38) designed to receive a ring. The main body (21) houses a first locking element (25) equipped at an end with a hook-shaped part or hook (26) and rotatable about a first pin (27) integral with the main body, as well as a second locking element (29) opposite the previous one, rotatable about a second pin (30) integral with the main body, the second locking element (29) being equipped with a magnetic element (31) designed to attract the ring thus facilitating the coupling and simultaneously the locking to the hook-shaped part or hook (26).

A wing arrangement for an aircraft, comprising a wing having a base section and a tip section pivotably connected to base section such that the tip section is pivotable about a pivot axis between a deployed position and a stowed position. The wing arrangement also comprises a latching arrangement which includes an engagement portion, a latching actuator selectively movable between a first actuator position and a second actuator position, an elastically deformable structure, and a latching element. When the tip section is pivoted from the stowed or deployed position into an engagement position, the elastically deformable structure is initially deformed, and as the tip section pivots further into the deployed or stowed position, the elastic deformation of the elastically deformable structure decreases.

A bicycle lock includes a U-shaped body and a pivotal portion pivotably connected to the first end of the U-shaped body. A head is formed on the second end of the U-shaped body and includes a lock unit received therein. The lock unit includes a nut and a core unit which is co-rotated with the nut. The nut is rotated by using a key. The core unit includes a core and a restriction plate which is co-rotated with the core and includes a notch. A safety unit is received in the lock unit and includes an engaging member and a resilient member which biases the engaging member to be engaged with a notch of the restriction plate to prevent the core unit from being rotated. The engaging member includes a protrusion which contacts the outer periphery of the nut to prevent the nut from being rotated by unauthorized tools.

A lever-lock release system is configured to releasably couple two objects together, for example a parachute and a payload. The lever-lock release system may comprise a first lever and a second lever, each rotatably coupled to a rigid base. When activated, the levers cascadingly rotate to release a first object and a second object. With these systems and related methods, various failure modes may be eliminated, such as undesired premature deployment of recovery parachutes during aerial delivery.