Ruag Space Ab

Michael Thuswaldner

Örjan Arulf

Magnus Thenander

Jörgen Remmelg

Anders Helmersson

ÖRjan Arulf

The invention relates to a separation device for a spacecraft or launcher. The separation device includes an inner housing divided into at least two portions locked to each other by a locking device in a locking position. The locking device is arranged to move between a locking position and a releasing position. The separation device includes an initiator including means for providing high pressure fluid to an expansion chamber when the separation device is switched from a locked state to a released state. The high pressure fluid in an expansion chamber moves the locking device from the locking position to the releasing position when the separation device is switched from the locked state to the released state. The separation device comprises a dampening arrangement arranged to attenuate a peak load when the separation device is switched from the locked state to the released state.

Separation device for spacecraft and a method for separation

A shock damping element includes a first shock damping structure that includes a multitude of first elements, a multitude of second elements and a first central member. The first elements and the second elements are located at opposite sides of the first central member. The first and second elements extend towards the first central member at a first acute angle (&#x3b1;) relative the first central member and are connected to the first central member. The first and second elements extend in a first direction circumferentially.

Shock damping element

The invention relates to a load bearing interface ring () for a space craft. The load bearing interface ring () comprises a first part () and a second part (). The first part () is arranged to carry compression loads and is mounted on an inside surface () of the second part (). The second part () is arranged to carry shear and global bending loads. The second part () comprises at least two laminate plies (), where the laminate plies () are oriented in a normal plane () of a jacket surface () of the load bearing interface ring ().

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Linkoping, Sweden

Michael Thuswaldner