Airbus Defence and Space Sas

Thales

Centre National Detudes Spatiales

Eads Astrium Sas

Andrew Walker

Christian Flemin

Fabrice Mena

Philippe Cael

Bruno Trancart

Vincent Claudet

Franck Levallois

Raphaël Hache

Typhaine Coquard

Jean-Pierre Guerin

Catherine Berthomieu

Carole Chossiere

A method for assembling devices on a satellite structure is disclosed including attaching the devices to a first face of a plate drilled with a through-hole provided with a fluid connector, on a second face of the plate, depositing a continuous peripheral bead of polymerisable adhesive composition and depositing a plurality of discontinuous and disjointed inner beads of polymerisable adhesive composition, pressing the second face of the plate against a continuous face of the structure, performing suction so as to create a pressure differential between the plate and the structure, at least partially polymerising the polymerisable adhesive compositions so as to form adhesive joints between the plate and the structure, and interrupting the suction.

Method for assembling a plurality of devices on a satellite structure and satellite structure supporting a plurality of devices

A method for attaching a heat-emitting device and a capillary heat pipe to a panel of a spacecraft wall is disclosed including the steps of: a) positioning a capillary heat pipe on a portion of the panel; attaching female attachment bodies to the panel, the female attachment bodies protruding relative to the capillary heat pipe; c) placing a thermally-conductive and self-curing paste over a portion of the capillary heat pipe or over a heat-emitting device; d) placing a heat-emitting device on the thermally-conductive and self-curing paste and on the female attachment bodies, said heat-emitting device bearing against and being in direct contact with the female attachment bodies, and e) attaching the heat-emitting device and said capillary heat pipe to the panel by attaching male attachment members to the female attachment bodies.

Method for attaching a heat-emitting device, spacecraft wall and spacecraft

A heat transfer device is disclosed having a housing including a first main wall and a second main wall, the housing having a sealed internal cavity, a liquid contained in the internal cavity, and a mixer able to set the liquid in motion, the heat transfer device being able to be switched between a first state and a second state in which the liquid is in motion and transfers heat by convection between the first main wall and the second main wall, the thermal conductance between the first main wall and the second main wall in the first state being four times less than the thermal conductance between the first main wall and the second main wall in the second state.

Heat transfer device and spacecraft comprising such a heat transfer device

Disclosed is a heat exchange device for effecting a heat exchange between a heat transfer fluid of a first network of capillary heat pipes and a heat transfer fluid of a second network of capillary heat pipes. The heat exchange device includes a solid block provided with a first channel and a second channel which are independent of one another, the first channel having at least one opening intended to be connected to a capillary heat pipe of the first network, the second channel having at least one opening intended to be connected to a capillary heat pipe of the second network, the first channel having a portion which lies near a portion of the second channel such that the heat transfer fluid of the first network is able to exchange heat with the heat transfer fluid of the second network via the heat exchanging portions.

Heat exchange device for artificial satellite, wall and assembly of walls comprising such a heat exchange device

A telecommunications satellite stabilized on three axes includes a set of dissipative equipment constituting a payload of the satellite. The satellite includes support data transmission antennas and is substantially parallelepipedal in shape with the panels forming two opposite faces, east and west faces. The panels form two additional opposite faces, north and south faces, and include radiator surfaces on their external faces. The radiator surfaces are configured to cool the electronic equipment of the satellite. The equipment installed on the north and south panels dissipate thermal power corresponding to less than 25% of the total dissipated power.

Telecommunications satellite architecture

Disclosed is an artificial satellite including one face from the North face and the South face supporting at least one main radiator having an outer face turned towards space and an inner face opposite the outer face. The satellite includes a bearing structure carrying the North face, the South face, the East face and the West face. At least one part of the at least one main radiator protrudes from at least one face from the East face and the West face. The inner face of the at least one protruding part is covered with a high infrared emissivity material. The value of the dimension of the at least one protruding part is between 19% and 50% of the value of the distance between the East and West faces.

Artificial satellite

Disclosed is an artificial satellite including a battery pack capable of dissipating heat, at least one radiator capable of conveying the heat dissipated by the battery pack into space, and a low-dissipation equipment item having an individual power flux density of less than 250 watts/m. The satellite includes a thermally insulating cover delimiting, together with the radiator, an interior isothermal zone in which thermal control takes place by radiation, the battery pack and the low-dissipation equipment being arranged in thermally insulating cover. The battery pack has an operating range of between 0&#xb0; C. and 50&#xb0; C. and preferably of between 10&#xb0; C. and 30&#xb0; C.

Artificial Satellite

Disclosed is artificial satellite including: a mounting structure supporting equipment-bearing walls; a launcher-adapter rigidly connected to the mounting structure; a first radiator; and at least one first system for transporting heat by a fluid, including at least one duct having a first heat-exchange section and a second heat-exchange section, the second heat-exchange section being capable of being in thermal contact with the first radiator. The first heat-exchange section is in thermal contact with at least one portion of the launcher-adapter. Also disclosed is a method for filling a tank of propellant gas of the artificial satellite.

Artificial satellite and method for filling a tank of propellent gas of said artificial satellite

Space craft comprising a body, at least one pair of supporting arms, a first device mounted on a first supporting arm and a second device mounted on a second supporting arm. The first arm is rotatably mounted on the body of the craft about an axis of rotation. The second arm is fixed to the body, and in which craft of the first device and the second device at least one is offset from the axis of rotation of the first arm. The pair of supporting arms further comprises a hollow module for the rotatable mounting of the first arm on the body. The mounting module comprising an opening through which the axis of rotation and the second supporting arm pass.

Space craft comprising at least one pair of supporting arms, said arm pair being equipped with a hollow mounting module, and method for employing such a craft

A device for thermal monitoring a piece of equipment, which is integrated on a craft placed in a forced vacuum environment, an outside part of the equipment projecting outside of a wall of the craft and being subjected to a solar radiation flux, includes an absorbent screen that is suitable for being placed between the outside part of the equipment and the wall of the craft, whereby this absorbent screen has&#x2014;on at least one portion of its front face, designed to be placed on the side removed from the wall of the craft&#x2014;an absorptivity &#x3b1;that is the largest possible in the field of solar radiation, coupled to a low emissivity &#x3b5;in the infrared spectrum. The absorbent screen is made of a very heat-conductive material and has&#x2014;on at least a portion of its rear face, suitable for being oriented toward the wall of the craft&#x2014;a high emissivity &#x3b5;in the infrared spectrum, typically greater than or equal to 0.7.

Absorbent dome for a radiating collector tube

The invention concerns a space craft, such as a telecommunication geostationary satellite, comprising a body, at least one main telecommunication antenna having a specific orientation relative to the body, at least a omnidirectional antenna having a field of view opposite to that of the main antennae and at least a radiator extensible by tilting about an axis linked to the craft body between a stowing position wherein it is pressed against the body and an extended position. The axis is positioned substantially in the plane of one surface of the body parallel to the orientation of the omnidirectional antenna and to the surfaces or the surface bearing the main antenna. The radiator tilts at an angle close to 180&#xb0; from a position wherein it is pressed against one surface bearing a solar panel to a position wherein it extends substantially in the plane of the surface which bears it when it is stowed.

Growing community of inventors

Toulouse, France

Andrew Walker