Abstract: The invention presented here relates to a device in a spacecraft comprising a carrier rocket, a satellite and a detachable adapter (4) for connecting a satellite to the carrier rocket, where the adapter (4) comprises a wall structure (14, 15) for supporting the satellite on the carrier rocket, and is fixed at its lower rim to the carrier rocket and is fixed at its upper rim to the satellite. The device is characterised in that the adapter (4) is divided essentially across the longitudinal direction of the spacecraft and that both of the adapter parts (12, 13) are detachably connected to each other. The invention comprises the said adapter design and a method for separating the invented device.

Abstract: A quadrifilar helix antenna (1) comprising a first and a second set of helical antenna elements (2a-5a, 2b-5b) symmetrically arranged around a longitudinal axis extending through the axial center of the antenna (1). The antenna (1) is excited from feeding points (2c-5c) in a local ground plane at the bottom (6) of the antenna. The helical antenna elements (2a-5a) of the first set are interconnected in respective top ends of the elements at the top (7) of the antenna. The bottom ends of the first set are in galvanic contact with the respective feeding points (2c-5c). The antenna is characterized in that the top ends of helical antenna elements (2b-5b) of the second set are arranged in an open circuit and remain unconnected. The bottom ends of the helical antenna elements (2b-5b) of the second set each includes a connection (2d-5d) to the local ground plane.

Abstract: The invention concerns a reflector and a satellite antenna system comprising such a reflector. In the satellite antenna system, microwave radiation from one or more feed horns (5) is emitted at the reflector (1), which comprises first and second reflector elements (2, 3). Upon reflection of the radiation from the reflector elements (2, 3), a distinct beam shape for the reflected microwave energy is generated. The reflector elements (2, 3) are disposed at a fixed distance from one another so that radiation that passes the first reflector element (2) strikes the second element. The first reflector element (2) comprises a lattice structure aimed toward the feed horn, which lattice structure consists of plates (8) of electrically conductive material, wherein the distance between the plates and the depth of said plates are adapted for reflection of polarization parallel to the plates.

Abstract: A construction intended for a carrier rocket or a satellite, comprising a first construction part (21), which is made of a composite material comprising two essentially parallel walls (23, 24) and a core (25) arranged between these walls, a second construction part (22) and means (26, 31; 26?, 31, 39) for joining the first and the second construction parts (21, 22). Said means (26, 31; 26?, 31, 39) comprising a first fastening element (26) provided with several threads (27), or several first fastening elements (26, 26?) provided with at least one thread (27) each, said first fastening element/elements (26; 26?) being arranged between the walls (23, 24) of the first construction part (21) in such a way that the threads (27) are accessible via the end surface (28) of the first construction part that faces the second construction part (22).

Abstract: A radio occultation instrumentation system includes a first satellite arranged with a transmitter for transmitting a signal with a carrier frequency and a second satellite arranged with a receiver for receiving the signal. The receiver receives information I(x,v) regarding the position and velocity of the first and second satellite and provides a prediction of the Doppler shift displacement of the carrier frequency of the signal for use in tracking the signal. The predicted Doppler shift displacement is also used to determine atmospheric conditions.

Abstract: A flange (1) for a space vessel (2), which flange (1) is arranged so as to reduce a shock or impact wave that occurs upon the release of a coupling (5). The coupling (5) is intended to impart a radially inwardly acting force to hold together two separable space vessel parts (3, 4) via two flanges (1, 6) belonging to respective space vessel parts (3, 4). The first flange (1) comprises at least one weakened point (9) so that it has a substantially broken annular shape, in order to thus reduce its energy-absorbing capacity when it is bent inward by the force (F).

Abstract: A joint (4) on a spacecraft (1) for holding together a first craft part (2) and a second craft part, (3) detachable from the first craft part (2). The joint (4) comprises a first flange (5) fixed on the first craft part (2), and a second flange (6) fixed on the second craft part (3), and a number of clamps (7) having a first (7a) and a second (7c) clamp lip, the said clamps being distributed about the periphery of the flanges (5, 6). The clamps transfer radial forces from a tightening device (8), fitted to the clamps (7), so as to fasten the two flanges (5, 6) together. The first flange (5) is clamped between a first clamp surface (7b) on the first clamp lip (7a), and a separation surface (6b) on the second flange (6). These surfaces (7b, 6b) form an acute angle &dgr;, the apex of which is directed in towards the spacecraft (1).

Abstract: A device for releasably connecting a first part and a second part of a spacecraft. A clamp is operable to releasably connect the first part and the second part of the spacecraft and to store a prestress strain energy releaseable upon separation of the first part and second part of the spacecraft. The clamp includes a first end and a second end. At least one energy storing system is operable to convert at least a portion of the prestress on the clamp to rotational energy upon opening of the clamp and separation of the first part and the second part of the spacecraft. The energy storing system includes a first fitting part that includes a threaded section, a second fitting part that includes a threaded section, and a connecting device that includes a threaded section complementary to and operable to engage the threaded section of the first fitting part and the second fitting part. The connecting device is operable to link the first end and the second end of the clamp.

Abstract: A mechanically simple dual-frequency (or wide band) quadrifilar helix antenna (1). It includes four helix shaped radiating elements (2-5) where each helix element consists of two or more parallel helices (2a, 2b, 3a, 3b, 4a, 4b, 5a, 5b) of different lengths that are in galvanic contact at, or close to, the feeding point (2c, 3c, 4c, 5c). The four feeding points (2c, 3c, 4c, 5c) of the helix elements (2-5) are located at the bottom of the helix, meaning that the feedings of the helix elements are located at the end (6) of the helix pointing in the direction opposite to the direction of its main radiation.

Abstract: A joint in a space vehicle to hold together a first part of the vehicle and a second part of the vehicle that can be separated from the first part, in which the joint includes a first flange member (1) attached to the first part of the vehicle and a second flange member (2) attached to the second part of the vehicle. A number of clamps (4) equipped with two clamping lips (5, 6) are distributed around the perimeter of the flange members (1, 2) that transfer radial force from a tensioning means (7), arranged around the clamps (4), to both of the flange members (1, 2) in order to press these together, whereby rolling members (8) are arranged between at least one of the clamping lips (5, 6) of the respective clamps (4) and the adjacent first (1) or second (2) flange member.

Abstract: An antenna element for circular polarization comprising a ground plane with first to fourth radiation members in the form of helical wires symmetrically arranged around a symmetry axis. The antenna element further comprises a distribution network arranged below the ground plane. Outer lower ends of the radiation members are attached in a supporting manner, electrically conducting, to the ground plane. Upper ends of the radiation members face away from the ground plane and are electrically interconnected.

Abstract: An antenna element intended for transmission and reception of orthogonal polarizations having a good polarization purity of electomagnetic radiation is described. It comprises a ground plane (2) and at least one radiation disc (1) connected to two ports (4, 5) for the supply of a desired electromagnetic radiation, preferably in the microwave range. The distance between the ground plane (2) and the radiation disc (1) is a fraction of the wavelength .lambda. of the radiation. The antenna element is in particular characterized in that the ports (4, 5) are located at an electric distance of 90.degree. from each other and that a quarterwave transformer (6) is added between the ground plane (2) and the radiation disc (1) that is shaped so that the transmission line impedance between the ports (4, 5) is reduced in order to make the ports radiationally independent of each other.

Abstract: An antenna element including a ground plane. A support supports a conical structure. The support is made of a dielectric material. A bottom portion of the support is attached to the ground plane. Four conical radiation means are symmetrically arranged around the support. Each radiation elements includes a helical wire having a top end and a bottom end. The bottom ends of the radiation elements are attached to the ground plane. Four coaxial cables including conductors are provided. One coaxial cable is connected to the top end of each radiation element for providing each radiation element with a microwave signal for emitting two orthogonally polarized radiations. A distribution network divides an incoming signal into four subsignals offset in phase in relation to each other. One of the subsignals is provided to each of the four radiation elements. Adaption elements adapts an output impedance of the distribution network to an input impedance of the radiation elements.