The present invention relates to a device for deploying two instruments. It applies in particular to the field of space equipment which must be deployed in orbit and more particularly to space equipment for satellites, such as antennas, mirrors or other instruments. However, the invention applies to any other field in which it is desirable to deploy a set of at least two instruments of a supporting structure.

The invention is described in this patent application in the space field, with the main example of antennas as instruments since antennas are particularly concerned by the invention. Nevertheless, the invention can be applied in a similar way to other instruments and / or in a context other than spatial.

It is a common practice to place antennas on a satellite to send bandwidth to Earth. The existing solutions consist in using a single or double stacking mechanism for storing the antennas on the satellite and a set of arms with a set of motors dedicated to each antenna for the deployment of each antenna. It appears that the number of antennas per face of the satellite is limited. In addition, in order to be able to deploy several antennas, the solutions of the prior art involve a high number of arms and motors. This has negative consequences on the external layout of the satellite and results in a complex deployment kinematics. Finally,

The invention aims to overcome all or part of the problems mentioned above by proposing a deployment device having the advantage of being compact, saving space and weight on board the satellite and simplifying the external layout. .

To this end, the subject of the invention is a deployment device intended to be positioned on a supporting structure, comprising:

• a first instrument and a second instrument,

• a deployment mechanism comprising:

o a main arm connected to one face of the supporting structure at a first attachment point on the one hand and to the first instrument on the other hand, the second instrument being connected to the main arm, o a main motor configured to actuate the arm main in relation to the face,

o a secondary motor configured to actuate the second instrument relative to the main arm,

the two instruments being able to pass from a configuration stored one on top of the other on the face of the supporting structure to a deployed configuration in which the two instruments are at a distance from each other and from the supporting structure , and / or vice versa.

Advantageously, the deployment mechanism comprises a secondary arm connected to the main arm at a second attachment point on the one hand and to the second instrument on the other hand.

Advantageously, the main motor is configured to actuate the main arm in rotation with respect to the face of the supporting structure along a main axis of rotation.

Advantageously, the face of the supporting structure extends along an XY plane defined by a first X axis and by a second Y axis substantially perpendicular to the first X axis and the main axis is parallel to the XY plane.

Advantageously, the main axis is secant to the XY plane.

Advantageously, the main axis is perpendicular to the XY plane.

According to one embodiment, N being an integer greater than or equal to 1, at least the main arm and / or the secondary arm if it is present is connected to the instrument to which the arm is connected by N arm sections and N motors, each associated with an arm section and configured to actuate the associated arm section, so as to position the instrument to which said arm is connected relative to the other of the two instruments.

According to one embodiment of the invention, the instruments are antennas.

The invention also relates to a satellite comprising at least one deployment device as described in this application.

The invention will be better understood and other advantages will appear on reading the detailed description of an embodiment given by way of example, description illustrated by the attached drawing in which:

• Figure 1 schematically shows a deployment device in the stored configuration according to the invention,

FIG. 2 schematically represents a deployment device in the deployed configuration according to the invention,

• Figure 3 schematically shows a deployment device according to the invention,

FIG. 4 schematically represents a deployment device according to the invention in stored configuration, during deployment and in deployed configuration,

• Figure 5 schematically shows a top view of the face of the supporting structure on which rests an embodiment of the deployment device according to the invention,

• Figure 6 schematically shows a top view of the face of the supporting structure on which rests another embodiment of the deployment device according to the invention,

FIG. 7 schematically represents another embodiment of a deployment device according to the invention in the deployed configuration,

• Figure 8 schematically shows a view of the deployment kinematics of two deployment devices according to the invention,

FIG. 9 diagrammatically represents a satellite comprising at least one deployment device according to the invention.

For the sake of clarity, the same elements will bear the same references in the different figures.

FIG. 1 schematically represents a deployment device 10 in the stored configuration according to the invention. The deployment device 10 according to the invention is intended to be positioned on a supporting structure 80, for example a satellite. It comprises a first instrument 1 1 and a second instrument 12, for example antennas, and a deployment mechanism 13. The two instruments 1 1, 12 are able to switch from a configuration stored one on top of the other on the face 81 of the supporting structure 80 (as shown in FIG. 1) to a deployed configuration in which the two instruments 1 1, 12 are at a distance from each other and from the supporting structure 80, and / or vice versa. In the stored configuration, the instruments 1 1, 12 are one on top of the other. They can be laid one on top of the other with contact of the face of one on one face of the other. But they can also be on top of each other without physical contact between them. Also, the instruments 1 1, 12 one on top of the other in the stored configuration are not necessarily superimposed in their entirety. One instrument can be partially above the other instrument.

In the stored configuration, the two antennas can be stored opposite or opposite. In other words, an active surface of one of the antennas can be in front of an active surface or in front of an inactive surface of another antenna.

It should be noted that the invention is described with two antennas, but it is obvious that the same principle applies to three antennas, or more, by superimposing them in the stored configuration and by deploying them in a similar way to what will be explained. below.

FIG. 2 schematically represents the deployment device 10 in the deployed configuration according to the invention. The deployment mechanism 13 comprises a main arm 14 connected to a face 81 of the supporting structure 80 at a first attachment point 82 on the one hand and to the

first instrument 1 1 on the other hand. The second instrument 12 is connected to the main arm 14. It also comprises a main motor 15 configured to actuate the main arm 14 relative to the face 81, and a secondary motor 16 configured to actuate the second instrument 12 relative to the main arm 14 The main motor 15 is advantageously positioned at the level of the first attachment point 82. The main motor 15 can be a single motor. The main motor 15 is to be understood as a set of motors, for example two motors, or three depending on the actuation needs. Thus, the deployment device according to the invention allows the deployment of two antennas using only two sets of motors (main motor and secondary motor) and a single arm.

FIG. 3 schematically represents the deployment device 10 according to the invention. The deployment device 10 can also include an additional motor 17 allowing the orientation of the first instrument 11.

FIG. 4 schematically represents a deployment device 20 according to the invention in stored configuration, during deployment and in deployed configuration.

In the stored configuration, the two instruments 11, 12 are one on top of the other and close to the face 81 of the supporting structure 80.

Once the satellite is in position to perform its mission, the deployment device 20 is activated to switch to its deployed configuration. The main motor 15 actuates the main arm 14 which is then moved relative to the supporting structure 80. The instruments 11, 12 are still in a vis-à-vis position.

In the deployed configuration, once the main arm 14 has reached its deployed position, the two instruments are moved relative to each other. The secondary motor 16 actuates the second instrument 12 and orients it to the desired position. At the end of deployment, that is to say in the deployed configuration, the two instruments 11, 12 are at a distance from each other and from the supporting structure 80.

Two scenarios can be envisaged for the displacement of the two instruments relative to each other. If an instrument, for example 1 1, is stored on instrument 12 with the active face of instrument 11 facing the inactive face of instrument 12 (that is, instrument 12 "turns its back" on the instrument 11), then the secondary motor 16 can be configured to move the second instrument 12 in rotation about an axis substantially perpendicular to the main arm 14. The two instruments, thus in offset positions, look in the same direction.

If an instrument, for example 1 1, is stored on instrument 12 with the active face of instrument 1 1 facing the active face of instrument 12 (that is, instrument 12 looks at instrument 1 1), then the secondary motor 16 is configured to move the second instrument in rotation about an axis located in one of the planes between the two instruments in the stored position. The two instruments, thus in deployed positions, then look in the same direction. The same deployment takes place for the two instruments 1 1, 12 stored with their inactive faces facing each other.

It is also possible to change the two instruments 11, 12 from the deployed position to the stored configuration by proceeding in reverse: the secondary motor 16 actuates the second instrument 12 to orient it vis-à-vis the first instrument, and the main motor 15 actuates the main arm 14 to bring it back to the vicinity of the face 81 of the supporting structure 80.

In another embodiment of the invention, the deployment mechanism 13 may comprise a secondary arm 21 connected to the main arm 14 at a second attachment point 22 on the one hand and to the second instrument 12 on the other hand. The secondary arm 21 makes it possible to determine the orientation of the second instrument 12 relative to the first instrument 11 and to the supporting structure 80.

FIG. 5 schematically represents a top view of the face 81 of the supporting structure 80 on which an embodiment of the deployment device 40 according to the invention rests. As explained previously, the main motor 15 is configured to actuate the main arm 14. Preferably, the actuation of the main arm 14 is done in rotation with respect to the face 81 of the supporting structure 80 along a main axis of rotation 31.

If the face 81 of the supporting structure 80 is defined as extending along an XY plane defined by a first X axis and by a second Y axis, perpendicular or substantially perpendicular to the first X axis, the main axis 31 may be parallel to the XY plane, as shown in figure 5.

La figure 6 représente schématiquement une vue de dessus de la face 81 de la structure porteuse 80 sur laquelle repose un autre mode de réalisation du dispositif de déploiement 30, 50, 60 selon l’invention. Dans ce mode de réalisation, l’axe principal 31 peut être sécant au plan XY. Sur les autres figures, l’axe principal 31 forme un angle avec la face 81 en configuration déployée et cet angle se situe entre 20 et 40°, préférentiellement à environ 30°. Il peut être perpendiculaire au plan XY, c’est-à-dire à 90°, comme représenté sur la figure 6.

FIG. 7 schematically represents another embodiment of a deployment device 70 according to the invention in the deployed configuration. At least one arm, that is to say the main arm 14 and / or the secondary arm 21, can be connected to the instrument 11, respectively 12 to which the arm is connected, by one or more arm sections 71 1, 712 and one or more motors 721, 722, each associated with an arm section and configured to actuate the associated arm section, so as to position the instrument 1 1, respectively 12 to which said arm is connected relative to the other of the two instruments. In the example shown,

On the same principle, the secondary arm 21 could be connected to the instrument 12 by another arm section 713 with a motor 723 (71 N and 72N, N being equal to 3), to orient the instrument 12 connected to the arm.

secondary 21. Other arm sections are possible. If an arm is connected for example by three arm sections to its instrument, then three other motors will be associated with it.

N being an integer greater than or equal to 1, at least one of the arms 14, 21 can be connected to the instrument 1 1, 12 to which the arm is connected by N arm sections 71 N and N motors 72N, each associated with an arm section and configured to actuate the associated arm section, so as to position the instrument 1 1, 12 to which said arm is connected relative to the other of the two instruments.

FIG. 8 schematically represents a view of the deployment kinematics of two deployment devices according to the invention. Each device comprises a first instrument 11 and a second instrument 12 (as discussed above, it could include more than two instruments), a deployment mechanism 13 comprising the main arm 14 connected to the face 81 of the supporting structure 80 of a on the one hand and to the first instrument 1 1 on the other hand, a main motor configured to actuate the main arm 14 relative to the face 81, and a secondary motor 16 configured to actuate the second instrument 12 relative to the main arm 14.

By deploying, each deployment device travels a certain predefined trajectory and its elements (arms and instruments) during this trajectory occupy a certain volume which is also predefined. In order to ensure the correct deployment of the devices without collision, the arms (main and secondary), arm sections and motors are positioned according to the need and to the constraints of arrangement on a case-by-case basis.

The invention provides a solution making it possible to reduce by a factor of 2 the number of arms and mechanisms on a face of a satellite. This solution also leads to a reduction in the on-board weight and the cost of equipment. Finally, the deployment of the two instruments at a distance from one another after the deployment of the main arm 14 at a distance from the supporting structure 80 brings new possibilities in terms of arrangement of antennas.

FIG. 9 schematically represents a satellite 90 comprising at least one deployment device according to the invention. In FIG. 8, the satellite comprises two deployment devices 10, 20. It can include three or more. The deployment devices can be identical to one another, or different according to the variants presented above.

The devices shown here include two antennas 1 1, 12, but each deployment device can include more than two instruments.

Finally, the deployment devices can be on a single face of the supporting structure 80 or else on different faces of the supporting structure 80 depending on the desired use of the instruments.

CLAIMS

1. Deployment device (10, 20, 30, 40, 50, 60, 70) intended to be positioned on a supporting structure (80), characterized in that it comprises:

• a first instrument (1 1) and a second instrument (12),

"A deployment mechanism (13) comprising:

o a main arm (14) connected to a face (81) of the supporting structure (80) at a first attachment point (82) on the one hand and to the first instrument (1 1) on the other hand, the second instrument (12) being connected to the main arm (14),

o a main motor (15) configured to operate the main arm

(14) with respect to the face (81),

o a secondary motor (16) configured to actuate the second instrument (12) relative to the main arm (14),

and in that the two instruments (1 1, 12) are able to switch from a configuration stored one on top of the other on the face (81) of the supporting structure (80) to a deployed configuration in which the two instruments (1 1, 12) are at a distance from each other and from the supporting structure (80), and / or vice versa.

2. Deployment device (20, 30, 40, 50, 60, 70) according to claim 1, characterized in that the deployment mechanism (13) comprises a secondary arm (21) connected to the main arm (14) in a second attachment point (22) on the one hand and to the second instrument (12) on the other hand.

3. Deployment device (30, 40, 50, 60, 70) according to claim 1 or 2, characterized in that the main motor (15) is configured to actuate the main arm (14) in rotation relative to the face. (81) of the supporting structure (80) along a main axis of rotation (31).

4. Deployment device (40, 70) according to any one of claims 1 to 3, characterized in that the face (81) of the supporting structure (80) extends along a plane (XY) defined by a first axis (X) and by a second axis (Y) substantially perpendicular to the first axis (X), and in that the main axis (31) is parallel to the plane (XY).

5. Deployment device (50, 60, 70) according to any one of claims 1 to 3, characterized in that the face (81) of the supporting structure (80) extends along a plane (XY) defined by a first axis (X) and by a second axis (Y) substantially perpendicular to the first axis (X), and in that the main axis (31) intersects with the plane (XY).

6. Deployment device (60, 70) according to claim 5, characterized in that the main axis (31) is perpendicular to the plane (XY).

7. Deployment device (70) according to one of claims 1 to 6, N being an integer greater than or equal to 1, characterized in that at least the main arm (14) and / or the secondary arm (21 ) if present is connected to the instrument (1 1, 12) to which the arm is connected by N arm sections (71 N) and N motors (72N), each associated with an arm section and configured to actuate the associated arm section, so as to position the instrument (1 1, 12) to which said arm is connected relative to the other of the two instruments.

8. Deployment device (10, 20, 30, 40, 50, 60, 70) according to any one of the preceding claims, characterized in that the instruments are antennas.

9. Satellite (90) characterized in that it comprises at least one deployment device (10, 20, 30, 40, 50, 60, 70) according to one of the preceding claims.