Ruag Space Ab

Saab Ericsson Space Ab

Jörgen Remmelg

Örjan Arulf

Magnus Thenander

Michael Thuswaldner

Anders Helmersson

Rolf Thörnkvist

Daniel Wramell Kristoffersson

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 includes 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

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.

A construction intended for a carrier rocket or a satellite, comprising a first construction part (), which is made of a composite material comprising two essentially parallel walls () and a core () arranged between these walls, a second construction part () and means () for joining the first and the second construction parts (). Said means () comprising a first fastening element () provided with several threads (), or several first fastening elements (') provided with at least one thread () each, said first fastening element/elements (&#x2032;) being arranged between the walls () of the first construction part () in such a way that the threads () are accessible via the end surface () of the first construction part that faces the second construction part (). Said first fastening element/elements (&#x2032;) further being so arranged that the centre axis of the respective thread () extends essentially in parallel with the walls (). Said means further comprising several second fastening elements () provided with a thread (), which second fastening elements extend through cavities () in the second construction part () and are screwed into said first fastening element/elements (&#x2032;) so as to secure the two construction parts () to each other. The invention also relates to a method for joining a first construction part () and a second construction part ().

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Vikingstad, Sweden

Jörgen Remmelg