Deployable mast with spontaneous autonomous deployment, and satellite

Patent metadata

Field	Value
Publication number	US-9764857-B2
Application number	US-201514846242-A
Country	US
Kind code	B2
Filing date	Sep 4, 2015
Priority date	Sep 5, 2014
Publication date	Sep 19, 2017
Grant date	Sep 19, 2017

Abstract

A deployable mast with spontaneous autonomous deployment comprises at least one elementary structural block with a longitudinal axis of deployment X, the elementary structural block comprising two, respectively lower and upper platforms parallel to a plane YZ orthogonal to axis X, and N stages stacked on one another parallel to axis X, where N is more than 1, and where i is between 1 and N−1. Each stage comprises at least six flexible longitudinal connection arms which are articulated by tape springs, which arms are, in the deployed position, on planes parallel to axis X and are inclined relative to axis X, the N stages being secured to one another in pairs by means of connection platforms parallel to the plane YZ; two adjacent lower and upper stages are offset angularly relative to one another by rotation around the axis of deployment X.

First claim

The invention claimed is:

1. A deployable mast with spontaneous autonomous deployment comprising:
at least one elementary structural block with a longitudinal axis of deployment X, the elementary structural block comprising two, respectively lower and upper platforms parallel to a plane YZ orthogonal to the axis X, and stages Ei (E 1 , . . . , Ei, Ei+1, . . . , EN) stacked on one another parallel to the longitudinal axis of deployment X, where i is between 1 and N, and where N is more than 1;
wherein each stage (Ei) comprises at least six flexible longitudinal connection arms comprising tape springs, the connection arms being articulated by tape springs, which arms are, in the deployed position, on planes parallel to the axis X and are inclined relative to the axis X, the stages being secured to one another in pairs by means of connection platforms parallel to the plane YZ, in that two adjacent lower and upper stages (Ei, Ei+1) are offset angularly relative to one another by rotation around the axis of deployment X, and
further comprising means for regulation of the speed of deployment of the mast which comprise a main, motorized pulley secured on the lower platform, and secondary, non-motorized pulleys, which can be driven by the main pulley by means of at least one cable or one tape extending along the longitudinal axis of deployment X between the platforms and the secondary pulleys.

2. The deployable mast according to claim 1 , wherein at least one of the secondary pulleys is secured on the upper platform and on each connection platform, and in that a single cable or tape connects the secondary pulleys of the various platforms to the main pulley.

3. The deployable mast according to claim 1 , wherein the secondary pulleys are secured on the lower platform, the main pulley comprises as many stages as secondary pulleys, and the means for regulation of the speed comprise as many said at least one cable or tape as secondary pulleys, which are secured respectively on the upper platform and on each connection platform.

4. The deployable mast according to claim 1 , wherein the secondary pulleys are secured on the lower platform, the main pulley comprises as many stages as secondary pulleys, and the means for regulation of the speed comprise as many said at least one cable or tape as stages of the main pulley and at least one of a mobile platform and the upper platform, the cables or tapes being secured on the upper platform.

5. The deployable mast according to claim 1 , wherein each upper, lower and connection platform comprises securing lugs which are grouped in regularly distributed pairs, each securing lug being dedicated to the securing of an end of one of the at least six flexible longitudinal connection arms.

6. The deployable mast according to claim 5 , wherein the securing lugs are oriented towards the exterior of the mast, and for each pair of securing lugs the connection arms in a folded configuration are oriented by an angle of between 0° and 45° on the plane YZ, tangentially relative to the platform.

7. The deployable mast according to claim 1 , wherein each tape spring has folding areas with a cross-section in the form of an arc of a circle, and non-folding areas with a cross-section in the form of an arc of a circle, and the arc of the circle of the non-folding areas is longer than that of the folding areas.

8. The deployable mast according to claim 7 , wherein the folding areas are situated at the two ends of the connection arm and in an intermediate area, and the cross-sections in the form of an arc of a circle of the areas at the ends are diametrically opposite relative to the cross-section of the intermediate area.

9. The deployable mast according to claim 7 , wherein the folding areas with the cross-section in the form of an arc of the circle are situated at the two ends and in an intermediate area, and the cross-sections of the non-folding areas have a tubular cross-section.

10. The deployable mast according to claim 1 , wherein each connection platform comprises at least six pairs of securing lugs.

11. The deployable mast according to claim 1 , wherein all the connection arms are identical.

12. The deployable mast according to claim 1 , comprising a plurality of the at least one identical structural block stacked on one another.

13. The deployable mast according to claim 1 , wherein a device for locking-release of the deployment is positioned on each connection platform, in order, after the deployment of said platform, to permit the release of the higher adjacent platform.

14. The deployable mast according to claim 13 , wherein the two ends of connection arms are in the form of tape springs and have a profile which varies according to the deployed or folded position of the connection arms, and in that the locking-release device comprises means for locking-release according to said profile.

15. A satellite comprising at least one mast deployable with spontaneous autonomous deployment, according to claim 1 .

Assignees

• Thales Sa

Inventors

• Baudasse Yannick
• Vezain Stéphane
• Lacroix Robin
• Guinot François

Classifications

• H01Q1/1235 Primary

  Collapsible supports; Means for erecting a rigid antenna · CPC title

• B64G1/222 Primary

  for deploying structures between a stowed and deployed state · CPC title

• B64G1/2228

  characterised by the hold-down or release mechanisms · CPC title

• B64G1/2224

  about multiple axes · CPC title