Abstract: A Hold Down Release Mechanism, HDRM, interface for attachment of a spacecraft to an adjacent structure of a launch vehicle or another spacecraft, wherein the HDRM interface is configured for forming part of a single or multi-point releasable attachment of the spacecraft to said adjacent structure. The HDRM interface includes first and second connector parts, wherein one of the first and second connector parts is fastened to said adjacent structure, and other is fastened to the spacecraft; wherein the first connector part has a tapered projection with a non-circular external surface; wherein the second connector part has a tapered recess with a non-circular interior surface configured for form-lockingly receiving the tapered projection, for enabling transfer of torsion and shear load between the first and second connector parts, when the tapered projection is inserted in the tapered recess and the first and second connector parts are pressed together.

Abstract: An assembly comprising a multiple payload set for a launch vehicle and a stiff and rigid ground support equipment. The multiple payload set comprising a plurality of payloads, wherein the plurality of payloads are interconnected via a non-self-supported connection structure before assembly of the multiple payload set to a dispenser body. Each payload comprises first attachment means attached to the non-self-supported connection structure, wherein the non-self-supported connection structure comprises second attachment means attached to the ground support equipment, for attachment of the multiple payload set to the dispenser body. The ground support equipment is attached to the multiple payload set via the second attachment means to reinforce and secure the multiple payload set to enable transport and maneuverability of the multiple payload set without jeopardizing the non-self-supported connection structure.

Abstract: 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.

Abstract: 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.

Abstract: A Hold Down Release Mechanism, HDRM, interface for attachment of a spacecraft to an adjacent structure of a launch vehicle or another spacecraft, wherein the HDRM interface is configured for forming part of a single or multi-point releasable attachment of the spacecraft to said adjacent structure. The HDRM interface includes first and second connector parts, wherein one of the first and second connector parts is fastened to said adjacent structure, and other is fastened to the spacecraft; wherein the first connector part has a tapered projection with a non-circular external surface; wherein the second connector part has a tapered recess with a non-circular interior surface configured for form-lockingly receiving the tapered projection, for enabling transfer of torsion and shear load between the first and second connector parts, when the tapered projection is inserted in the tapered recess and the first and second connector parts are pressed together.

Abstract: 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.

Abstract: A separation adapter for attaching a payload onto a payload dispenser is provided. The separation adapter comprise a rigid structure comprising: a plurality of payload attachment, each payload attachment means operates separately from the other payload attachments means, and is adapted to securely fasten the payload to the rigid structure in a releasable manner, and at least one payload dispenser attachment means, the at least one payload dispenser attachment means is adapted to securely attach the rigid structure to the payload dispenser in a non-releasable fixed manner A method for attaching a payload onto a payload dispenser using a separation adapter and a payload dispenser for carrying a payload of a satellite launch vehicle are also provided.

Abstract: An assembly comprising a multiple payload set for a launch vehicle and a stiff and rigid ground support equipment. The multiple payload set comprising a plurality of payloads, wherein the plurality of payloads are interconnected via a non-self-supported connection structure before assembly of the multiple payload set to a dispenser body. Each payload comprises first attachment means attached to the non-self-supported connection structure, wherein the non-self-supported connection structure comprises second attachment means attached to the ground support equipment, for attachment of the multiple payload set to the dispenser body. The ground support equipment is attached to the multiple payload set via the second attachment means to reinforce and secure the multiple payload set to enable transport and maneuverability of the multiple payload set without jeopardizing the non-self-supported connection structure.

Abstract: 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.

Abstract: 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.

Abstract: The present disclosure relates to a separable roller screw assembly comprising: a first screw shaft having a first external thread and being axially separated from a second screw shaft having a second external thread; a planetary roller arrangement comprising multiple rotatable rollers radially arrayed about the first and second screw shafts, whilst being encapsulated by a rotatable nut module; the rotatable nut module being coaxially arranged about the first and second screw shafts and configured for maintaining the planetary roller arrangement, the first and second screw shafts in an axially fixed configuration to permit the assembly to carry a load in an axial direction corresponding to an axial tensile force, whilst enabling displacement of the first screw shaft relative to the second screw shaft when said assembly is released from said axially fixed configuration; and wherein each one of the multiple rollers comprises first and second roller external thread regions adapted to engage said first external t

Abstract: 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 is formed.

Abstract: The present disclosure relates to a separable roller screw assembly comprising: a first screw shaft having a first external thread and being axially separated from a second screw shaft having a second external thread; a planetary roller arrangement comprising multiple rotatable rollers radially arrayed about the first and second screw shafts, whilst being encapsulated by a rotatable nut module; the rotatable nut module being coaxially arranged about the first and second screw shafts and configured for maintaining the planetary roller arrangement, the first and second screw shafts in an axially fixed configuration to permit the assembly to carry a load in an axial direction corresponding to an axial tensile force, whilst enabling displacement of the first screw shaft relative to the second screw shaft when said assembly is released from said axially fixed configuration; and wherein each one of the multiple rollers comprises first and second roller external thread regions adapted to engage said first external t

Abstract: 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.

Abstract: A multiple payload set for a launch vehicle, wherein the multiple payload set includes a plurality of payloads. The plurality of payloads is interconnected via a non-self-supported connection structure before assembly of the multiple payload set to a dispenser body. Each payload includes first attachment means attachable to the connection structure. The connection structure includes second attachment means attachable to a ground support equipment, GSE, during attachment of the multiple payload set to the dispenser body.

Abstract: 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.

Abstract: The disclosure concerns a joint (1) for releasably connecting a first space craft element (2) to a second space craft element (3) comprising a first flange (4) on the first space craft element (2) and a second flange (5) on the second space craft element (3). The joint (1) comprises first shoe portions (6) and second shoe portions (13) formed as sectors of a solid of revolution, keeping the flanges (4, 5) 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.

Abstract: A payload joint (10) for detachably attaching to each other two adjacent construction elements (2) in a spacecraft and/or launch vehicle, the payload joint (10) comprises two opposing clamps (11a, 11b) and two opposing flanges of the construction elements collaborating with angled surfaces of the clamps (11a, 11b). The payload joint comprises a bolt that connects the clamps (11a, 11b) and drives them towards each other when tightening the payload joint (10). The payload joint (10) further comprises a bolt cutter (101) arranged for cutting the bolt upon activation.

Abstract: A payload joint (10) for detachably attaching to each other two adjacent construction elements (2) in a spacecraft and/or launch vehicle, the payload joint (10) comprises two opposing clamps (11a, 11b) and two opposing flanges of the construction elements collaborating with angled surfaces of the clamps (11a, 11b). The payload joint comprises a bolt that connects the clamps (11a, 11b) and drives them towards each other when tightening the payload joint (10). The payload joint (10) further comprises a bolt cutter (101) arranged for cutting the bolt upon activation.

Abstract: The disclosure concerns a joint (1) for releasably connecting a first space craft element (2) to a second space craft element (3) comprising a first flange (4) on the first space craft element (2) and a second flange (5) on the second space craft element (3). The joint (1) comprises first shoe portions (6) and second shoe portions (13) formed as sectors of a solid of revolution, keeping the flanges (4, 5) 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.