Abstract: The invention relates to a phase sequencing three-phase network comprising a first side connected to a second side via the network. The first side comprises one endpoint (EP1) and the second side comprises three endpoints (EP2, EP3, and EP4). The network comprises five nodes (NP1-NP5) interconnected via feed line sections (FP1-FP10) comprising at least one transmission line section (R11-R102) each. The invention further relates to an optimization method for the network for deciding characteristic impedance and length of each transmission line section (R11-R102).

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: 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.

Abstract: A microwave transmission line assembly operated in vacuum for satellite antennas and beamforming networks comprising a first ground plane and a conductor strip positioned a distance from the first ground plane. The conductor strip comprises a first strip portion and a second strip portion (6). The first strip portion is positioned at a first distance from the first ground plane and wherein the second strip portion is positioned at a second distance from the first ground plane. The first distance is smaller than the second distance, wherein the first distance is chosen to avoid multipaction.

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 waveguide polarizer for converting between a linearly polarized electromagnetic field in a first waveguide and a circularly polarized electromagnetic field in a second waveguide is provided. The waveguide polarizer includes a structure interconnecting the first and second waveguide which includes a waveguide excitation arrangement with a bifilar helical shape. A circularly polarized antenna arranged to be connected to the first waveguide of the waveguide polarizer and a satellite arrangement are also provided.

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: 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 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.

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: The invention relates to a multifilar helix antenna (1) comprising a wave feed and polarizing section (2) comprising a cover portion (3) comprising a through opening (4). The antenna (1) comprises a helix radiator (5) comprising three or more resonant helical elements (6) evenly distributed about an imaginary circle. Each helical element (6) extends in a longitudinal direction (Z) from the feed and polarizing section (2) through the opening (4) in the cover portion (3) and wound to form the helix radiator (5). Each helical element (6) comprises one or a plurality of wave perturbations (7) separated in the longitudinal direction (Z) and that each set of perturbations are positioned at the same level in the longitudinal direction (Z) to yield an equivalent array of stacked helical radiators, wherein the cover portion (3) comprises a rotationally symmetric corrugated assembly (8).

Abstract: 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 (?) relative the first central member and are connected to the first central member. The first and second elements extend in a first direction circumferentially.

Abstract: The invention relates to a load bearing interface ring (1) for a space craft. The load bearing interface ring (1) comprises a first part (3) and a second part (4). The first part (3) is arranged to carry compression loads and is mounted on an inside surface (11) of the second part (4). The second part (4) is arranged to carry shear and global bending loads. The second part (4) comprises at least two laminate plies (8), where the laminate plies (8) are oriented in a normal plane (12) of a jacket surface (5) of the load bearing interface ring (1).

Abstract: A method for frequency conversion within a satellite-based repeater system. An uplink radio frequency signal having a frequency fRF is received. A first and at least a second local oscillator signal having frequencies fL01 and fLO2, respectively, is generated. The uplink signal is mixed at a first frequency conversion stage with the first local oscillator signal to generate an intermediate signal having a frequency fMF. The intermediate signal is mixed at a second frequency conversion stage with the at least second local oscillator signal to generate a downlink signal having a frequency fIF. The generation and mixing of the signals are performed such that: fLO1 and fLO2>fRF and fIF fMF=fLO1?fRF, and fIF=fLO2?fMF.