Thales

Aerospatiale Societe Nationale Industrielle

Silvain Legrand

Alain Mistral

Gael Blons

Yannick Baudasse

Gerard Albert Vezain

Bernard Boulanger

Rodolphe Chaix

Olivier Damiano

Pierre Jouanne

Christian Masse

Damien Legloire

Alain Chaix

Yves Alabrebis

Gaël Blons

A device and a method intended to fit an insert in an orifice formed in a structure. The device is a fitting vehicle comprising the insert to be fitted, a polymerizable adhesive, and an applicator. The applicator comprises: an open enclosure in which the insert and the adhesive can be held; deployment means that are able to push back the insert and the adhesive out of the open enclosure so as to allow the insert to be fitted in the orifice in the structure. The fitting vehicle is configured to allow the polymerization of the adhesive held in the open enclosure of the applicator to be initiated. Advantageously, the adhesive is microencapsulated in the form of microcapsules of resin and hardener; the step of polymerization of the adhesive being initiated by rupturing of the microcapsules.

Method and device for fitting inserts by bonding by way of controlled polymerization

A structure comprises at least two unfurling panels and a spacing and knock prevention device intended to prevent the panels from knocking together when they are furled against one another. The knock prevention device comprises a holder fixed to the first panel, a cap forming a buffer against which the second panel bears in a bearing direction, and a damper disposed in a space formed between the holder and the cap. The cap and the holder form two elements. A first of the two elements comprises at least one lug. The second of the two elements comprises at least one housing intended to receive the lug. The cap is configured such that the lug passes into the housing by elastic deformation of the cap.

Knock prevention device for unfurling structure

A monolithic mechanical-thermal structure which is suitable for a space environment is provided, in which the structure contains at least one hole. The walls of the hole are lined with filaments. The monolithic mechanical-thermal structure may be made of metal. And a process for manufacturing the structure is also provided.

Mechanical-thermal structure suitable for a space environment

A structure comprises at least two unfurling panels and a knock prevention device intended to prevent the panels from knocking together when they are furled against one another. The knock prevention device comprises a one-piece element comprising two plates and arms connecting the two plates. A first of the two plates is fixed to the first panel. A second of the two plates forms a buffer against which the second panel comes to rest. The arms form an elastic element between the two plates.

Unfurling structure with knock prevention device

The method and device provided herein relates to the field of screwed joints for panels and, in particular, for sandwich panels used in aerospace applications. It relates to a method for attaching a headless rivet nut to a wall of such a panel. The method comprises: injecting a predetermined quantity of adhesive into a blind hole made in the wall of the panel; fitting the headless rivet nut onto a rivet nut setting tool, the rivet nut setting tool comprising a pierced anvil and a mandrel passing through the anvil, the mandrel being screwed into the rivet nut so as to press the rivet nut onto the anvil; positioning the headless rivet nut in the blind hole, the anvil coming to press against the wall of the panel; setting the rivet nut so as to squeeze the wall of the panel between the anvil and a flange formed by deformation of the rivet nut.

Method for attaching a headless rivet nut to a sandwich panel

The present invention consists of an active tie-rod device making it possible to hold and smoothly release space appendages. The active tie-rod device includes a fixed base, an active tie-rod screwed into the said fixed base, a retractable release mechanism for the active tie-rod making it possible, in the stowed position, to hold the said active tie-rod in place, and a nut for tensioning the assembly. The active tie-rod includes an internal heater, and consisting at least partially of a material with a high coefficient of thermal expansion, so that, under the action of the internal heater, the active tie-rod can expand, retracting the retractable release mechanism for the active tie-rod, and consequently allowing the smooth release of the said space appendages.

Active tie-rod system for holding and smoothly releasing space appendages

The invention relates to devices for releasing the stacking tie-rods that are used for holding deployable structures, in particular solar panels of artificial satellites. The device of the invention is self-releasing in order to enable such deployable structures to be released via the top portion of the stacking column. The invention consists in holding together the members () that are to be deployed by means of a tie-rod () having a nut () screwed onto its free end. The force for holding the stack together is transmitted by modules () which are themselves held together by said force. When the stacking tension is reduced, resilient means, such as two flat spring blades (), cause the modules to move away from the tie-rod, thus enabling the members of the deployable structure to be released.

Stacking tie-rod release device for a deployable structure

A solar generator panel includes at least one reflector for reflecting solar radiation onto at least one photovoltaic cell. The reflector takes the form of a flexible material blade, a first end of which is fixed to the panel and a second end of which remains free. The material has mechanical properties such that, in a first position, in the absence of vertical pressure, it maintains itself erect so that its free end points to outer space, thereby defining an upper face that faces outer space and an opposite lower face that faces the panel, and, in a second position, in response to vertical pressure, it orients its upper face toward the plane of the panel. One particular application is to high-power solar panels for satellites.

Solar generator panel and a spacecraft including it

The present invention relates to a device for the suspension and translational guidance of an item of apparatus (1) intended to be displaced, parallel to its longitudinal axis (X--X) with respect to a stationary support (2), having one pair of suspension elements (4A, 4B) spaced along said longitudinal axis (X--X) while being flexible parallel to said axis, and controllable actuating means (10) intended to exert a force parallel to said axis (X--X) on said suspension elements. According to the invention, each of said suspension elements (4A, 4B) consists of at least one pair of blades (5A, 5B, 6A, 6B), one end of one of said blades being secured to said support (2) and one end of the other of said blades being secured to said item of apparatus (1), the other ends of said blades being secured to each other.

Growing community of inventors

Nice, France

Silvain Legrand