Abrégé

The present invention relates to a separation device for a spacecraft or launcher, the 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 said component is released, said separation device comprising: an inner housing divided into at least two portions for locking onto said component of said 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 said inner housing are prevented from separating, wherein said locking arrangement comprises: a first part arranged to at least partially enclose said at least two portions of said inner housing when said locking arrangement is in the locking configuration, a piston arranged at least partially inside said expansion chamber, and at least one locking element which is held between said first part and said piston when said locking arrangement is in the locking configuration, thereby preventing said first part from releasing said at least two portions of said inner housing.

Classes IPC  ?

• B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
• F16B 31/00 - Assemblages à vis spécialement modifiés en vue de résister à une charge de tractionBoulons de rupture
• F16B 37/10 - Écrous à largage rapide, p. ex. faits de plusieurs partiesÉcrous mobiles le long du boulon après basculement de l’écrou divisés parallèlement ou à peu près parallèlement à l'axe du boulon

Abrégé

A separation device (1) for a spacecraft or launcher (1) comprising a nut (2) divided into at least two nut portions (2a, 2b, 2c) locked to each other by a locking device (3) in a locking position. A releasing device (4) is arranged to switch the locking device (3) from the locking position to a releasing position. The separation device (1) comprises at least two bearing elements (5) arranged between the locking device and the nut (2). The nut (2) comprises an outer envelope surface (6) which comprises as many indentations (7) as the number of bearing elements (5) and locking surfaces (8) between the indentations (7). In the locked state each bearing element (5) is jammed between the locking surface (8) and an inner envelope surface (9) of the locking device (3) and in the released state each bearing element (5) is positioned facing the indentations (7).

Classes IPC  ?

• B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
• F16B 37/08 - Écrous à largage rapide, p. ex. faits de plusieurs partiesÉcrous mobiles le long du boulon après basculement de l’écrou

Abrégé

A microwave transmission line assembly (1) operated in vacuum for satellite antennas and beamforming networks comprising a first ground plane (2) and a conductor strip (4) positioned a distance from the first ground plane (2). The conductor strip (4) comprises a first strip portion (5) and a second strip portion (6). The first strip portion (5) is positioned at a first distance (d1) from the first ground plane and wherein the second strip portion (6) is positioned at a second distance (d2) from the first ground plane (2). The first distance (d1) is smaller than the second distance (2), wherein the first distance (d1) is chosen to avoid multipaction.

Classes IPC  ?

• H01P 3/00 - Guides d'ondesLignes de transmission du type guide d'ondes
• H05K 1/02 - Circuits imprimés Détails

Abrégé

The invention relates to a separation device (1) for a spacecraft or launcher. The separation device (1) comprises an inner housing (2) divided into at least two portions locked to each other by a locking device (3) in a locking position. The locking device (3) is arranged to move between a locking position and a releasing position. The separation device (1) comprises an initiator (5) comprising means for providing high pressure fluid to an expansion chamber (6) when the separation device (1) is switched from a locked state to a released state. The high pressure fluid in an expansion chamber (6) moves the locking device (3) from the locking position to the releasing position when the separation device (1) is switched from the locked state to the released state. The separation device (1) comprises a dampening arrangement (8) arranged to attenuate a peak load when the separation device (1) is switched from the locked state to the released state.

Classes IPC  ?

• B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
• F16B 31/00 - Assemblages à vis spécialement modifiés en vue de résister à une charge de tractionBoulons de rupture
• F16B 37/10 - Écrous à largage rapide, p. ex. faits de plusieurs partiesÉcrous mobiles le long du boulon après basculement de l’écrou divisés parallèlement ou à peu près parallèlement à l'axe du boulon

Abrégé

The invention relates to a separation device (1) for a spacecraft or launcher. The separation device (1) comprises an inner housing (2) divided into at least two portions locked to each other by a locking device (3) in a locking position. The locking device (3) is arranged to move between a locking position and a releasing position. The separation device (1) comprises an initiator (5) comprising means for providing high pressure fluid to an expansion chamber (6) when the separation device (1) is switched from a locked state to a released state. The high pressure fluid in an expansion chamber (6) moves the locking device (3) from the locking position to the releasing position when the separation device (1) is switched from the locked state to the released state. The separation device (1) comprises a dampening arrangement (8) arranged to attenuate a peak load when the separation device (1) is switched from the locked state to the released state.

Classes IPC  ?

• B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
• F16B 31/00 - Assemblages à vis spécialement modifiés en vue de résister à une charge de tractionBoulons de rupture
• F16B 37/10 - Écrous à largage rapide, p. ex. faits de plusieurs partiesÉcrous mobiles le long du boulon après basculement de l’écrou divisés parallèlement ou à peu près parallèlement à l'axe du boulon

Abrégé

A multiple payload set (3) for a launch vehicle, wherein the multiple payload set (3) comprising a plurality of payloads (2). The plurality of payloads is interconnected via a non-self-supported connection structure (16) before assembly of the multiple payload set (3) to a dispenser body (1 ). Each payload (2) comprises first attachment means (17) attachable to the connection structure (16). The connection structure (16) comprises second attachment means (18) attachable to a ground support equipment, GSE, (19) during attachment of the multiple payload set (3) to the dispenser body (1).

Classes IPC  ?

• B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage

Abrégé

A payload dispenser (1)for a launch vehiclecomprising a plurality of panels (2), wherein at least one panel (2) comprisesat least one payload (3) mounted onto the panel (2). The panels (2)are attachable to each other forming a self-supporting dispenser (1). (Figure 1)

Classes IPC  ?

• B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
• B64G 1/00 - Véhicules spatiaux

Abrégé

A payload dispenser (1)for a launch vehicle comprising a plurality of panels (2), wherein at least one panel (2) comprises at least one payload (3) mounted onto the panel (2). The panels (2)are attachable to each other by means of attachment means (4, 6) in form of at least one payload dispenser joint (10) whereby a self-supporting dispenser (1)is formed.

Classes IPC  ?

• F16B 2/12 - Brides ou colliers, c.-à-d. dispositifs de fixation dont le serrage est effectué par des forces effectives autres que la résistance à la déformation inhérente au matériau dont est fait le dispositif externes c.-à-d. agissant par contraction utilisant des mâchoires coulissantes
• B64G 1/00 - Véhicules spatiaux
• B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
• F16B 5/06 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles par brides ou clips

Abrégé

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.

Classes IPC  ?

• B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
• F16B 2/08 - Brides ou colliers, c.-à-d. dispositifs de fixation dont le serrage est effectué par des forces effectives autres que la résistance à la déformation inhérente au matériau dont est fait le dispositif externes c.-à-d. agissant par contraction utilisant des frettes ou des bandes

Abrégé

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 thread and said second external thread, respectively. Moreover, the present disclosure relates to a space craft release mechanism for separating a first space craft element from a second space craft element and comprising a separable roller screw assembly. In addition, the present disclosure relates a clamp band system for a load bearing interface assembly of a space craft comprising a separable roller screw assembly.

Classes IPC  ?

• B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage

Abrégé

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).

Classes IPC  ?

• H01Q 11/08 - Antennes hélicoïdales

Abrégé

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).

Classes IPC  ?

• B64G 1/00 - Véhicules spatiaux
• B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
• B32B 37/02 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par la séquence des opérations de stratification, p. ex. par addition de nouvelles couches à des postes successifs de stratification
• B32B 37/12 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par l'usage d'adhésifs
• B32B 37/16 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par les propriétés des couches toutes les couches existant et présentant une cohésion avant la stratification
• B32B 38/00 - Opérations auxiliaires liées aux procédés de stratification

Abrégé

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).

Classes IPC  ?

• B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
• B64G 1/22 - Parties de véhicules spatiaux ou équipements spécialement destinés à être fixés dans ou sur ces véhicules