Ruag Space Ab

Saab Ericsson Space Ab

Beyond Gravity Sweden Ab

Saab Aktiebolag

Saab Space Aktiebolag

Ruag Aerospace Sweden Ab

Örjan Arulf

Johan Öhlin

Magnus Thenander

Michael Thuswaldner

Jörgen Remmelg

Anders Helmersson

Magnus Persson

Torbjorn Andersson

Niklas Journath

Kjell Pettersson

Oskar Björfeldt

Daniel Wramell Kristoffersson

Ingvar Bengtsson

Rolf Thörnkvist

Stefan Brick

A separation device for a spacecraft or launcher, separation device being movable from a locked state, in which the separation device is arranged to lock onto a component of a spacecraft or launcher, to a released state, in which component is released, separation device including: an inner housing divided into at least two portions for locking onto component of spacecraft or launcher, and a locking arrangement arranged to move between a locking configuration and a releasing configuration, wherein the locking configuration is such that said at least two portions of inner housing are prevented from separating, wherein said locking arrangement includes: a first part arranged to at least partially enclose said at least two portions of inner housing when locking arrangement is in the locking configuration.

Separation device for a spacecraft

A separation device for a spacecraft or launcher comprising a nut divided into at least two nut portions locked to each other by a locking device in a locking position. A releasing device is arranged to switch the locking device from the locking position to a releasing position. The separation device comprises at least two bearing elements arranged between the locking device and the nut. The nut comprises an outer envelope surface which comprises as many indentations as the number of bearing elements and locking surfaces between the indentations. In the locked state each bearing element is jammed between the locking surface and an inner envelope surface of the locking device and in the released state each bearing element is positioned facing the indentations.

Separation device

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

A payload dispenser for a launch vehicle including a plurality of panels, wherein at least one panel includes at least one payload mounted onto the panel. The panels are attachable to each other by means of attachment means in the form of at least one payload dispenser joint whereby a self-supporting dispenser is formed.

Joint and payload dispenser

A payload dispenser for a launch vehicle includes a plurality of panels. At least one panel includes a payload mounted onto the panel. The panels are attachable to each other to thereby form a self-supporting dispenser.

Payload dispenser

The disclosure concerns a joint () for releasably connecting a first space craft element () to a second space craft element () comprising a first flange () on the first space craft element () and a second flange () on the second space craft element (). The joint () comprises first shoe portions () and second shoe portions () formed as sectors of a solid of revolution, keeping the flanges () together in a longitudinal direction, The shoe portions are positioned next to each other in a circumferential direction the reference to a longitudinal direction of the space crafts. The first shoe portions being arranged to, at a prevailing Coulomb friction, not allow self-locking and the second show portions are arranged to allow self-locking.

Joint and clamp band system for releasably connecting space craft elements

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 ().

Load bearing interface ring for spacecraft

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 ().

Construction and method of use in a carrier rocket or satellite

A device for imparting rotational movement to a satellite during discharge from an adapter of a launcher. The satellite includes a first axis, a second axis, and a third axis passing through a center of gravity. The first axis, the second axis, and the third axis are mutually perpendicular. The device includes at least one line dismountably attached to a first point on the satellite and a first point on the adapter. The at least one line is attached to the satellite and the adapter such that the at least one line imparts a rotational movement to the satellite as the satellite is discharged and separates from the adapter with a discharge velocity in a direction along the first axis. A lock dismountably attaches the at least one line to the satellite.

Device at the adapter of a launcher and a satellite carried by the

A locking device for a band or the like comprising a housing having one end fastened to a first portion of the band. The housing extends in the direction of the prevailing tensile force and is formed with a guide for guiding a link means. This comprises a fastening element fastened at its first end to the second portion of the band and at its second end journally connected to a second link at a distance from its first end. The second link is, at its first end, journaled around an axis provided in the housing transverse to the longitudinal direction of the housing. The locking device also comprises a third link journaled at the first end of the housing and a dowel element which, l via the third link, is able to prevent the second link from being turned around the axis to a position where it is released from the axis so that the locking device is opened.

Growing community of inventors

Linköping, Sweden

Örjan Arulf