FR3081841A1 - DEPLOYABLE CARRIER DEVICE FOR SATELLITE EQUIPMENT - Google Patents

Abstract

The object of the invention is a carrier device for equipping a satellite in the form of a telescopic mast consisting of nesting cylindrical segments (2, 2a, 21, 22) which contain an inflatable tube (3) for deploying the mast and are provided with means (4, 6) for attaching equipment carried by the mast.

Description

DEPLOYABLE CARRIER DEVICE FOR SATELLITE EQUIPMENT

Field of the invention

The present invention relates to a telescopic structure for satellite, in the form of a carrying device for equipment of a deployable satellite by means of an inflatable tube, in particular for producing a mast such as a satellite antenna mast which is mounted collapsed during the launch of the rocket carrying the satellite and which will be deployed once the satellite is in position.

Technological background

In order to deploy members on a satellite, inflatable masts are known and in particular inflatable masts which can be solidified by polymerization of reinforcement devices or solidification of the envelope of the inflatable tube making the mast.

These devices however require a gas generator adapted to maintain the pressure in the mast at least the time of the polymerization of the armature or the tube.

These devices also require the design of inflatable tubes which are resistant to the spatial environment and for this purpose use complex multilayers combining strong tightness, great lightness and great resistance to UV rays in particular.

Brief description of the invention

In view of this prior art, the present invention aims to reduce the capacity of the gas generator and simplify the production of the inflatable tube by producing a telescopic mast in the form of nesting segments in which there is a simple inflatable tube which must be kept inflated only for the time required. mast deployment.

Furthermore, the invention relates to means for mutual snap-fitting and retaining the segments.

To do this, the present invention provides a carrier device for equipping a satellite in the form of a telescopic mast, consisting of nesting cylindrical segments which contain an inflatable mast deployment tube and are provided with means for attaching a equipment carried by the mast.

Preferably, a gas generator and the folded inflatable tube are housed inside the nested nesting segments.

Advantageously, the device comprises a cover for supporting an item of equipment and the lower face of which constitutes a bearing face during deployment of the inflatable tube.

According to a particular embodiment, retractable rod locks are adapted to lock together the nested segments in the folded mast position.

The attachment means are ears or flanges.

The segments in the folded mast position, the collar or the ears of a segment of rank n may possibly rest on the edge of the segment of rank n-1 which surrounds it.

The ears may in particular comprise holes for the passage of antenna cables deploying with the mast.

The device preferably comprises a support base for the outermost segment and the gas generator. The antenna cables can in particular be placed on the mast in a helical manner.

According to a first embodiment, the segments are provided with mutual latching means mast in the unfolded position and ribs opposing rotation of the segments relative to each other.

Brief description of the drawings

Other characteristics and advantages of the invention will become apparent on reading the following description of a nonlimiting example of embodiment of the invention with reference to the drawings which represent:

In Figure 1: a perspective view of a structure according to the invention deployed;

In FIGS. 2A to 2C: schematic views of the elements of the structure of FIG. 1 folded back and of the details of these elements;

In FIG. 3A: sectional views of devices for retaining the structure in the folded position;

In Figure 3B: a schematic sectional view of the folded structure at the devices of Figure 2;

In FIGS. 4A to 4C: detailed views of means for retaining rotation and for locking the segments;

In FIGS. 5A and 5B: detailed perspective cross-section views of alternative means for retaining rotation and for guiding the segments;

In FIGS. 6A to 6C: detailed views of means for locking the segments;

In Figures 7 A to 7C: perspective views and transparency of the means of Figures 5A to 6C;

In FIGS. 8A to 8F: the representation of the arrangement of strands of an antenna as a function of the deployment of the mast;

In Figure 9: the representation of the angular positioning of the mast segments for winding the antenna strands.

Detailed description of embodiments of the invention

The invention relates to a telescopic structure deployable by means of an inflatable tube.

The telescopic structure 1 as shown deployed in FIG. 1 is produced from nesting segments 2, here 6 segments 2a to 2f which can be produced from various materials such as a fiberglass-based composite or a thermoplastic (for example PEEK) loaded glass or not in the case where they carry an antenna in particular or possibly metallic or carbon materials for other applications.

According to the example, the segments 2 of the mast carry turns 5 of an antenna which will deploy with the mast. The mast can also carry one or more collectors to be placed at a distance from the satellite or even carry solar panels.

As shown in the schematic view of FIG. 2A, the segments 2a to 2f of cylindrical shape fit into each other to allow the structure to be folded up and unfolded.

The segments 2 are annular segments nested one inside the other when the mat is folded. They comprise an upper part provided with a rim or legs 4 as shown in FIG. 2B which carry antenna strands or wires or cables connecting to an apparatus carried by the mast.

The mast is deployable under the action of an inflatable tube 3 of size shown diagrammatically in FIG. 2C which is housed inside the segments.

The segments of the invention are constructed in such a way that the pressure in the inflatable tube 3 disposed inside the smallest segment does not have to be maintained after the mast has been deployed, the mast retaining its deployed shape without maintaining the pressure in the tube.

To do this, the segments 2a to 2f from the smallest to the largest are locked to each other in the deployed position by locking means which will be described below, which reduces the amount of gas that an initiated gas generator must generate. for deploying the mast and inflating the inflatable tube. This makes it possible to reduce the volume and the mass of the generator and of the tube, the generator being able in particular in this application to be a simple and inexpensive generator.

Returning to FIG. 2A, in the folded position, the segments are fitted with the rim or the legs of a more internal segment above or in contact with the edge of a more external segment.

The mast has a cover 6 fixed to the innermost segment 2a which will become the distal segment of the mast. On this cover can be fixed the end of the antenna, a sensor or any other equipment intended to be used at a distance from the satellite.

Returning to FIG. 1, the legs or the rim are provided with notches or holes crossed by the strands 5 of the antenna or for guiding one or more electrical cables for supplying one or more sensors or the like equipment at the end of the mast.

In FIG. 3A is shown a device 7 for temporarily locking the segments in the folded position known as pinpullers in English for retractable rod lock. This device comprises an actuator and a retractable rod 7a shown deployed in the top view and retracted in the bottom view.

According to FIG. 3B, two of said latches 7 are arranged back to back or one above the other spade head inside the internal segment. The rods 7a of the retractable rod locks pass through the segments which are provided with holes adapted so as to lock these segments in the folded position during the flight of the rocket carrying the satellite until the mast is deployed.

Once the satellite is correctly positioned, the rods 7a are retracted then the inflatable tube 3 is inflated by means of its gas generator 8 which deploys the mast.

According to FIGS. 4A to 4C, the segments are provided with mutual latching means, mast in the deployed position.

According to FIG. 4A and on the enlargement of FIG. 4B, the interior of an external segment 21 comprises ribs 10 along generatrices of the segment and a housing 11 while an internal segment 22 comprises a spring tongue 12 provided with 'a lug 12a as shown in Figure 4C. The lug 12a is dimensioned to be retained laterally between the ribs 10 during the deployment of the mast and the sliding of the internal segment out of the external segment until it is positioned under the action of the spring tab in the housing 11 to lock the segments in the deployed position. According to the example shown, the lug 12a is arranged on the external face of the internal segment and the ribs and the housing on the internal face of the external segment.

FIGS. 5A to 7C represent an improved device realizing a lower stop between the segments in the folded position, an upper stop in the unfolded position as well as a locking of the segments between them and moreover allowing an easy assembly and disassembly of the segments for the tests before launch.

To do this, the device firstly comprises a pin / cam path combination with, as shown in FIG. 5A:

- on the internal face of a segment 21 ′, a bayonet-type inlet groove 17 opening into an elongated groove 18 which opens neither on the upper face of the segment nor on the lower face but which defines two extreme stopping points 18a, 18b and,

- On the outer face of a segment 22 ', a pin 19 as shown in Figure 5B adapted to slide in the inlet groove and then in the elongated groove.

The movement of the pin in the groove 18 between the stopping points is shown diagrammatically in FIGS. 6A to 6C. The position of FIG. 6A is a folded mast position where the segments are nested and the pin 19 is in abutment on a bottom stopping point 18b. The position of FIG. 6B is an intermediate position for which the pin 19 is halfway between the stops. The position of FIG. 6C is a deployed mast position where the segments are in extension with the pin 19 in abutment against the upper stopper 18a.

The elongated groove further blocks the rotating segments from each other.

This configuration which can be reversed between the internal and external segments makes it possible to assemble and disassemble the segments by pushing insertion then rotation of the internal segment in the external segment so that the pegs enter the groove 17, slide to the bottom of this groove and then join groove 18 and can slide there also. For the disassembly of the mast and therefore to bring out the internal segment from the external segment, the reverse is done by rotation and extraction of the pins by the inlet groove 17.

For locking the segments in the deployed position, the device comprises spring tabs 13 facing inwards on an external segment 21 'according to the example in FIG. 7A. When the segments are in the folded mast position, these tongues 13 are placed under stress against the external wall of the internal segment 22 ′ as shown in FIG. 6A. During deployment, the tongues are received in guide grooves 16 of the internal segment 22 'as shown in FIG. 6B. When the mast is in the deployed position as shown in Figures 6C, these tabs are released and their free end snaps against the lower edge 22'a of the internal segment.

The grooves / tongues 13, 16 participate in the indexing of the segments when the tongues slide in these grooves.

Thus the pins 19 and the grooves 18 retain the internal segment in the high position and in the low position in the external segments and the spring tabs 13 lock the mast segments in the deployed position.

It should be noted that to assemble the segments according to FIG. 7C, it is necessary to push the spring tabs 13 outwards, for example using an annular tool.

To limit the deployment forces of the mast, the guide groove 16 as shown in particular in FIGS. 6A and 6C and receiving the spring tongue comprises a ramp-shaped end portion 16a against which the spring tongue 13 slides before locking the segments.

To disassemble the segments, the tongue 13 is capable of being erased by introduction of the annular tool introducing itself into an external segment to allow the tongues 13 to be erased and thus allow the internal segment to slide out of the segment. external.

As regards the case of a mast carrying an antenna, as seen above, the antenna strands are arranged between the segments according to a configuration shown in FIGS. 8A to 8F.

In this example, the segments are provided with flanges 41, 41 ′ instead of ears, but an embodiment where the flanges are replaced by pierced ears distributed around the upper edge of the segments is possible.

FIG. 8A represents two segments 2p, 2q inserted one inside the other, mast in the folded position.

The antenna strands 51, 52 visible through the flanges 41, 41 'are folded in the form of a half-loop. The progressive deployment of the mast is shown in Figures 8B to 8E. The half-loops unfold progressively upon leaving the internal segment 2q from the external segment 2p up to the position in FIG. 8F for which the antenna strands are stretched and the segments in the mast position deployed.

It should be noted that the passages of the strands are angularly offset to give a helical shape to the strands around the segments in particular in the case of an RF antenna.

FIGS. 8C to 8F show two strands 51, 52 whole, the upper part of a third strand 53 and the lower part of a fourth strand 54 when they are tensioned.

Figure 9 shows schematically for a mast with six sections 2a to 2f two variants of folding two strands 501 and 50Γ. The strand 501 has half loops all oriented on the same side which gives small bending radii to the strand at the crossings between segments while the strand 501 'comprises an alternation of half right and left loops so that the folding of the strand at the crossings between the segments are not bent. The second variant for which the antenna strands 501 ′ are folded in half-loops alternately right and left mast deduces the folding of the strands at the level of the holes 4a for passage of the strands between the segments to reduce the deformations of the strands at points 5 of passage of the strands between the segments and gives a better distribution of the half-loops between the strands.

As seen above, when the mast carries an antenna, the segments carry strands 51, 52, 53, 54 of the antenna passing through the segments through holes 4a in the ears 4 or the flanges 41 of the segments.

The segments as shown, are angularly offset between them to give a helical shape to the strands of the antenna.

The angular offset of the successive segments accumulate to obtain a total angle Θ preferably 360 °.

The invention defined by the claims is not limited to the examples shown and in particular the number of segments can be different from the number of segments represented.

Claims (10)

1 - Carrier device for equipping a satellite in the form of a telescopic mast characterized in that it consists of nesting cylindrical segments (2, 2a, 21, 22) which contain an inflatable tube (3) for deploying the mast and are provided with means (4, 6) for attaching equipment carried by the mast. 2 - carrier device according to claim 1 for which a gas generator (8) and the inflatable tube (3) folded are housed inside the nested nesting segments. 3 - Support device according to claim 1 or 2 comprising a cover (6) supporting an equipment and the underside of which constitutes a bearing face during deployment of the inflatable tube (3). 4 - Support device according to claim 1, 2 or 3 comprising latches (7) with retractable rod (7a) adapted to lock together the nested segments in the folded mast position. 5 - Carrier device according to any one of the preceding claims for which the attachment means are ears (4) or flanges. 6 - A carrying device according to claim 5 for which and for which, segments in the folded mast position, the collar or the ears of a segment of rank n rest on the edge of the segment of rank n-1 which surrounds it. 7 - Support device according to claim 5 or 6 for which the ears have holes for antenna cables (5) deploying with the mast. 8 - Carrier device according to claim 7 for which the antenna cables are arranged on the mast in a helical manner. 9 - Support device according to any one of the preceding claims comprising a base (100) supporting the outermost segment (2b) and the gas generator (8). 10- carrier device according to any one of the preceding claims for which the segments are provided with mutual latching means (11, 12) mast in the unfolded position and ribs (10) opposing rotation of the segments by compared to others.