A connection system is provided for releasably connecting a first component and a second component in a first direction parallel to a reference longitudinal axis, including one or more locking devices and an actuator. Each locking device has a geometrically locked configuration and an unlocked configuration. In the geometrically locked configuration the locking device is capable of reversibly geometrically locking together the first component and the second component in a mutually clamped relationship along the first direction, each locking device comprising at least two linkage elements pivotably mounted to one another about a common clamp axis. The actuator device is configured for transitioning each locking device from the geometrically locked configuration to the unlocked configuration by selectively applying to each respective locking device an unlocking force directly to the respective linkage elements at the respective common clamp axis, in a second direction parallel to a reference transverse axis.

A connection system is provided for releasably connecting a first component and a second component in a first direction parallel to a reference longitudinal axis, including one or more locking devices and an actuator. Each locking device has a geometrically locked configuration and an unlocked configuration. In the geometrically locked configuration the locking device is capable of reversibly geometrically locking together the first component and the second component in a mutually clamped relationship along the first direction, each locking device comprising at least two linkage elements pivotably mounted to one another about a common clamp axis. The actuator device is configured for transitioning each locking device from the geometrically locked configuration to the unlocked configuration by selectively applying to each respective locking device an unlocking force directly to the respective linkage elements at the respective common clamp axis, in a second direction parallel to a reference transverse axis.

A method and device enable the linear separation of two elements attached to each other, through two respective connecting surfaces of these two elements. A connecting layer is placed between both connecting parts. Thermite is used to melt this connecting layer. The thermite can be placed on the other side of the first connecting part towards the first element, a heat protecting plate completing this assembly. The thermite can also be placed in grooves provided on the connecting surface of the second connecting plate to be directly in contact with the connecting layer.

A method and device enable the linear separation of two elements attached to each other, through two respective connecting surfaces of these two elements. A connecting layer is placed between both connecting parts. Thermite is used to melt this connecting layer. The thermite can be placed on the other side of the first connecting part towards the first element, a heat protecting plate completing this assembly. The thermite can also be placed in grooves provided on the connecting surface of the second connecting plate to be directly in contact with the connecting layer.

The invention relates to a method and a device allowing the separation of two stages of an aeronautical vehicle, without affecting the structure of the two stages. The device consists mainly of a connecting ring (13) secured to the two stages of the aeronautical vehicle and comprising a cutting ring (20) on the inner surface (13A) thereof, which contains a mixture of thermite and an intermetallic composition. The triggering of the latter allows the heating and melting of part of the ring (13), which separates into two parts. The invention can be applied to an aeronautical launcher.

A system and method for shedding redundant launcher tank mass, comprising progressing means, and cutting means configured to cut redundant propellant tank wall, the system configured to progress inside the tank, along the tank wall in an initially predetermined rate.

A system and method for shedding redundant launcher tank mass, comprising progressing means, and cutting means configured to cut redundant propellant tank wall, the system configured to progress inside the tank, along the tank wall in an initially predetermined rate.

Separation device assemblies are provided. The assemblies include a plurality of first segment elements, each first segment element having an attachment portion and a frangible portion, the attachment portion of the first segment elements is arranged to fixedly connect to a first structural component and at least one second segment element having an attachment portion and a securing portion, wherein the attachment portion of the at least one second segment element is arranged to fixedly connect to a second structural component. At least two of the plurality of first segment elements are attached to the at least one second segment element adjacent to each other and a first segment joint is formed between adjacent first segment elements. An expansion device cavity is formed between the attached first and second segment elements.

Separation device assemblies are provided. The assemblies include a plurality of first segment elements, each first segment element having an attachment portion and a frangible portion, the attachment portion of the first segment elements is arranged to fixedly connect to a first structural component and at least one second segment element having an attachment portion and a securing portion, wherein the attachment portion of the at least one second segment element is arranged to fixedly connect to a second structural component. At least two of the plurality of first segment elements are attached to the at least one second segment element adjacent to each other and a first segment joint is formed between adjacent first segment elements. An expansion device cavity is formed between the attached first and second segment elements.

A shaped charge comprising a containment shell, an explosive charge placed in the containment shell and having a V-shaped surface, a fuse placed behind the explosive charge, and a layer of projection material placed in front of the V-shaped surface of the explosive charge. A layer of pyrogenic material is used for heating the projection coating. This pyrogenic material can also be mixed with the explosive charge.