DEPLOYMENT DEVICE FOR NANO-SATELLITE

Abstract

The present disclosure concerns a device for deploying a nanosatellite including a main structure mounted on a launching vehicle, a support frame carrying the nanosatellite, and a locking/unlocking structure. The locking/unlocking structure includes a first clamping element complementary to a second clamping element of the support frame, and an elastically deformable actuating element to allow, in a locking position, constrain the first clamping element to the second clamping element to retain the support frame to the main structure, and in an unlocking position, release the first clamping element from the second clamping element to release the support frame from the main structure causing it to be ejected.

Claims

1. A deployment device of a nanosatellite comprising: a main structure provided to be mounted on a launching vehicle of the nanosatellite, a support frame provided to carry the nanosatellite and to be ejected from the main structure with the nanosatellite, a locking/unlocking structure adapted to lock/unlock the support frame with respect to the main structure, wherein: the locking/unlocking structure is movably mounted on the main structure, the locking/unlocking structure comprises: a first clamping element complementary to a second clamping element of the support frame, and an elastically deformable actuating element adapted to: in a locking position, constrain the first clamping element to the second clamping element to retain the support frame to the main structure, and in an unlocking position, release the first clamping element from the second clamping element to release the support frame from the main structure causing it to be ejected.

2. The deployment device according to claim 1, wherein the first clamping element and the second clamping element radially and/or axially clamp the locking/unlocking structure with respect to the support frame.

3. The deployment device according to claim 1, wherein the first clamping element and the second clamping element have a toothed profile, wherein the toothed profiles are asymmetrical.

4. The deployment device according to claim 1, wherein the first clamping element and the second clamping element are respectively formed by a circular clamping ring complementary to one other.

5. The deployment device according to claim 4, wherein the circular clamping ring forming the first clamping element comprises a plurality of clamping jaws.

6. The deployment device according to claim 1, wherein the elastically deformable actuating element is formed by a plurality of elastically deformable blades.

7. The deployment device according to claim 1, wherein the locking/unlocking structure comprises a retaining element adapted to retain the locking/unlocking structure to the main structure.

8. The deployment device according to claim 7, wherein the retaining element is formed by a retaining ring complementary to the first clamping element.

9. The deployment device according to claim 1, wherein the elastically deformable actuating element comprises a peripheral shaft guided by a central shaft of the main structure, the peripheral shaft receiving an unlocking elastic compression element to switch from the locking position to the unlocking position.

10. The deployment device according to claim 9, wherein: in the locking position, a first position of the peripheral shaft compresses the unlocking elastic compression element and forces an active position of the elastically deformable actuating element in which the first clamping element engages with the second clamping element and in the unlocking position, a second position of the peripheral shaft releases the unlocking elastic compression element and restores a passive position of the elastically deformable actuating element in which the first clamping element disengages from the second clamping element.

11. The deployment device according to claim 1 further comprises: a thrust plate including a guide tail receivable in a central shaft of the main structure, wherein the support frame of the nanosatellite is in flat abutment on the thrust plate to eject the support frame and separate the support frame from the thrust plate after ejection.

12. The deployment device according to claim 11, wherein the locking/unlocking structure comprises a plurality of thrust elements to provide a pre-loading of the thrust plate.

13. The deployment device according to claim 12, wherein a thrust element from among the plurality of thrust elements comprises a guide body receiving a thrust rod retaining a thrust spring surrounding the guide body and retained between the guide body and the thrust rod, the thrust rod being provided to bear on the thrust plate.

14. The deployment device according to claim 13, wherein the thrust rod is secured to the thrust plate.

15. The deployment device according to claim 1 further comprises a force take-up structure to hold the free end of a central shaft of the main structure, the force take-up structure being formed of a central part surrounding the free end of the central shaft extending from the central part to bear laterally on the main structure.

16. The deployment device according to claim 1 further comprises a retention mechanism adapted to block the actuating element in its locking position and to unblock the elastically deformable actuating element to bring it into its unlocking position.

Description

DRAWINGS

[0092] In order that the disclosure may be well understood, there will now be described various forms thereof, given by way of example, reference being made to the accompanying drawings, in which:

[0093] FIG. 1 represents a detailed view of a deployment device according to the present disclosure in the assembled state.

[0094] FIG. 2 illustrates a sectional view of a support frame represented in FIG. 1 on which a nanosatellite is disposed.

[0095] FIG. 3 illustrates an exploded view of the deployment device represented in FIG. 1.

[0096] FIG. 4A illustrates a half-sectional view of the deployment device represented in FIG. 1 in a locking position.

[0097] FIG. 4B illustrates a half-sectional view of the deployment device represented in FIG. 1 in an unlocking position.

[0098] FIG. 5A illustrates a half-sectional view of the deployment device represented in FIG. 1 in a first ejection phase of the nanosatellite after the unlocking of the device.

[0099] FIG. 5B illustrates a half-sectional view of the deployment device represented in FIG. 1 in a second ejection phase of the nanosatellite after the unlocking of the device.

[0100] FIG. 6 illustrates a top view of the deployment device of FIG. 1 representing an offset of the center of gravity of the nanosatellite relative to the center of thrust of the deployment device.

[0101] FIG. 7A illustrates a main structure of the deployment device represented in FIG. 1 equipped with a locking/unlocking structure in a locking position.

[0102] FIG. 7B illustrates a main structure of the deployment device represented in FIG. 1 equipped with a locking/unlocking structure in an open position.

[0103] FIG. 7C illustrates a main structure of the deployment device represented in FIG. 1 equipped with a locking/unlocking structure in an unlocking position.

[0104] The drawings described herein are for illustration purposes only and are not intended to limit the scope of the present disclosure in any way.

DETAILED DESCRIPTION

[0105] The following description is merely exemplary in nature and is not intended to limit the present disclosure, application, or uses. It should be understood that throughout the drawings, corresponding reference numerals indicate like or corresponding parts and features.

[0106] In FIG. 1, there is represented a deployment device 1 in the assembled state. The deployment device 1 comprises a main structure 2 provided to be mounted on a launching vehicle of the nanosatellite 5 (represented in FIG. 2), a support frame 3 provided to carry the nanosatellite 5 and to be ejected from the main structure 2 with the nanosatellite 5 and a structure 4 for locking/unlocking the support frame 3 with respect to the main structure 2.

[0107] The main structure 2 has a circular shape 20 reinforced on its outline by stiffeners 21, preferably integral therewith.

[0108] The support frame 3 has a circular shape 30 (FIGS. 4A and 4B) at its base to comply in shape matching with the main structure 2, the circular shape 30 is extended by a rectangular shape 31 to comply with the nanosatellite 5, as represented in FIG. 2, according to the Cubesat standard. Of course, the support frame 3 is not limited to this type of nanosatellite 5 and the rectangular shape 31 could be adapted to other shapes of nanosatellites 5.

[0109] In order to provide the fastening of the nanosatellite 5 on the support frame 3, the support frame 3 comprises a plurality of fastening elements 32. This plurality of fastening elements 32 makes it possible to immobilize the nanosatellite 5 on the support frame 3.

[0110] The locking/unlocking structure 4 is represented partially covered by the support frame 3 and will be detailed with reference to FIG. 3.

[0111] In FIG. 3, there is represented an exploded view of the deployment device 1 of FIG. 1.

[0112] The main structure 2 comprises a lower wall 22 and a peripheral wall 23 forming the outline of the main structure 2. A central shaft 24 extends in the center of the main structure 2 from the lower wall 22 to be terminated with free end 24′.

[0113] Furthermore, the main structure 2 carries a plurality of thrust elements 40 associated with the locking/unlocking structure 4 and regularly distributed around the central shaft 24.

[0114] As represented, the locking/unlocking structure 4 comprises, on the one hand, a first clamping element 41 complementary to a second clamping element 42 of the support frame 3, and, on the other hand, an elastically deformable actuating element 43.

[0115] The elastically deformable actuating element 43 allows the switching between: a locking position, to constrain the first clamping element 41 against the second clamping element 42 in order to retain the support frame 3 to the main structure 2, and

[0116] an unlocking position, to release the first clamping element 41 from the second clamping element 42 in order to release the support frame 3 from the main structure 2 causing it to be ejected.

[0117] The first clamping element 41 and the second clamping element 42 are respectively formed by a circular clamping ring 41, 42 complementary to each other.

[0118] More particularly, the circular clamping ring 41 forming the first clamping element 41 comprises a plurality of clamping jaws 410 and the actuating element 43 is formed by a plurality of elastically deformable blades 430.

[0119] As represented, the locking/unlocking structure 4 further comprises a peripheral shaft 44 guided by the central shaft 24 of the main structure 2 and receiving an unlocking elastic compression element 45 ensuring the switching from the locking position to the unlocking position.

[0120] The elastically deformable blades 430 extend from the peripheral shaft 44 to the clamping jaws 410 of the first clamping element 41.

[0121] The jaws 410 and the blades 430 are regularly distributed around the peripheral shaft 44.

[0122] The peripheral shaft 44, the elastically deformable blades 430 and the jaws 410 are advantageously integrally formed, by machining for example.

[0123] In the illustrated example, the first clamping element 41 and the second clamping element 42 form a radial clamping of the locking/unlocking structure 4 with respect to the support frame 3.

[0124] As illustrated, the locking/unlocking structure 4 comprises a retaining element 46 from the locking/unlocking structure 4 to the main structure 2.

[0125] The retaining element 46 is formed herein by a retaining ring 46 provided to engage with the first clamping element 41. The retaining element 46 thus allows the locking/unlocking structure 4 to be axially pre-constrained on the main structure 2.

[0126] In addition to the main structure 2, the support frame 3, the locking/unlocking structure 4, the deployment device 1 comprises a force take-up structure 6 provided to hold the free end 24′ of the central shaft 24, and it comprises a thrust plate 7.

[0127] As represented, the force take-up structure 6 is formed of a central part 60 surrounding the free end 24′ of the central shaft 24 and a peripheral part 61 extending from the central part 60 to bear laterally on the main structure 2.

[0128] The thrust plate 7 includes a guide tail 70 intended to be received in a central shaft 24 of the main structure 2. A plurality of lateral blades 71 extend radially from the peripheral shaft 44 to be joined by a peripheral edge 73. The peripheral edge 73 thus makes it possible to stiffen the plurality of lateral blades 71.

[0129] The thrust plate 7 is advantageously integrally formed, by molding for example.

[0130] The plurality of lateral blades 71 stiffened by the peripheral edge 73 allows supporting the support frame 3 on the thrust plate 7.

[0131] As represented, each lateral blade 71 of the thrust plate 7 comprises an opening 72.

[0132] Each opening 72 of the thrust plate 7 faces a passage 47 formed between two blades 430 of the actuating element 43 of the locking/unlocking structure 4. The opening 72 and the passage 47 are designed to be crossed by a thrust element 40 carried by the main structure 2.

[0133] The peripheral edge 73 has an octagonal shape provided to conform to a shape complementary to an inner outline of the support frame 3.

[0134] Reference is now made to FIG. 4A representing a half-sectional view of the deployment device 1 represented in a locking position.

[0135] As represented, the guide tail 70 of the thrust plate 7 is housed in the central shaft 24 and the thrust plate 7 is in flat abutment against the support frame 3 of the nanosatellite 5 so as to allow the ejection of the support frame 3 and the separation of the support frame 3 from the thrust plate 7 after ejection. The support frame 3 is hollowed out to receive the thrust plate 7.

[0136] In order to provide the axial holding of the support frame 3 relative to the thrust plate 7, a peripheral abutment 74 of the thrust plate 7 is provided.

[0137] A radial play J3 is provided between the support frame 3 and the thrust plate 7 in order to limit the radial constraints that may be applied to the support frame 3 during ejection.

[0138] The support frame 3 bears on the main structure 2 to provide a retaining of the support frame 3. The bearing of the support frame 3 on the main structure 2 is achieved by a correspondence of the slot/groove type.

[0139] It will be noted that the retaining element 46 of the locking/unlocking structure 4 is movably mounted with respect to the main structure 2.

[0140] Such an assembly allows the absorption of a part of the forces transmitted to the main structure 2.

[0141] In this case, the retaining element 46 is mounted in a clearance 230 of the peripheral wall 23 of the main structure 2. The clearance 230 allows an axial stroke of the retaining element 46.

[0142] The represented jaw 410 is engaged with both the retaining element 46 and the support frame 3.

[0143] More particularly, a hook 410A of the jaw 410 is radially in correspondence of a peripheral notch 460A of the retaining ring 46 forming the retaining element 46 and a toothed profile 410B of the jaw 410 corresponds radially to a toothed profile 300B of an inner outline of the support frame 3.

[0144] In the locking position, a first position of the peripheral shaft 44 comes to compress the unlocking elastic compression element 45. The unlocking elastic compression element 45 is caught between the peripheral shaft 44 and the central shaft 24. The first position of the peripheral shaft 44 forces an active position of the blade 430 in which the toothed profile 410B of the jaw 410 engages with the toothed profile 300B of the support frame 3, and in which the hook 410A of the jaw 410 engages with the peripheral notch 460A of the retaining ring 46.

[0145] In this locking position, the peripheral shaft 44 is in the high position.

[0146] The blade 430 is mechanically constrained in a radial direction and is devoid of an axial component.

[0147] As represented in FIGS. 3 and 4A, the central part 60 of the force take-up structure 6 comprises a flat wall 60A from which extends axially a hollow circular projection 60B and radially ribs 60C from the circular projection 60B.

[0148] The hollow circular projection 60B is provided for maintaining the unlocking elastic compression element 45 in the peripheral shaft 44.

[0149] An axial play J1 is provided between the force take-up structure 6 and the thrust plate 7, this to inhibit a static indeterminacy between these two pieces. The hollow circular projection 60B also allows the radial retaining of the free end 24′ of the central shaft 24.

[0150] In the same way, an axial play J2 is provided between the force take-up structure 6 and the actuating element 43, this to inhibit static indeterminacy between these two pieces.

[0151] The peripheral part 61 of the force take-up structure 6 comprises lateral arms 61A extending from the central part 60 to bear laterally on the main structure 2.

[0152] As represented in FIGS. 3 and 4A, the lateral arms 61A bear axially against the lower wall 22 of the main structure 2. It will be noted that these lateral arms 61A are distant from the peripheral wall 23 such that the forces of force take-up structure 6 are only transmitted to the lower wall 22.

[0153] The peripheral part 61 allows taking-up of the forces absorbed by the central part 60. In this case, the forces received by the central shaft 24, the blade 430 and thrust plate 7 are partly transmitted to peripheral part 61 via the central part 60.

[0154] The peripheral part 61 then transmits the forces received from central part 60 to main structure 2.

[0155] Reference is now made to FIG. 4B representing a half-sectional view of the deployment device 1 represented in an unlocking position.

[0156] In the unlocking position, a second position of the peripheral shaft 44 makes it possible to release the unlocking elastic compression element 45 and restores a passive position of the blade 430 in which the toothed profile 410B of the jaw 410 disengages from the toothed profile 300B of the support frame 3, and in which the hook 410A of the jaw 410 disengages from the peripheral notch 460A of the retaining ring 46.

[0157] In this unlocking position, the peripheral shaft 44 is in a low position.

[0158] The blade 430 is brought back to its constrained mechanical state. In this

[0159] state, the blade 430 comprises a radial component and an axial component.

[0160] Reference is now made to FIG. 5A representing a half-sectional view of the deployment device 1 in a first ejection phase of the nanosatellite 5 after the unlocking of the device.

[0161] The plurality of thrust elements 40 represented in FIG. 3 provides a pre-loading of the thrust plate 7. This pre-loading has the effect of ensuring the thrust of the thrust plate 7 during the ejection.

[0162] In FIG. 5A, one of its thrust elements 40 has been represented. The thrust element 40 comprises a guide body 400 fixedly mounted on the main structure 2.

[0163] The guide body 400 receives a thrust rod 401 retaining a thrust spring 402 surrounding guide body 400. The thrust spring 402 is retained between guide body 400 and the thrust rod 401 for compression. This thrust rod 401 is provided to bear on thrust plate 7.

[0164] The thrust rod 401 has a rod head 401A fastened to the thrust plate 7. The rod head 401A passes through the opening 72 of the thrust plate 7 to be fastened thereto.

[0165] As represented, without being limited thereto, a means for fastening the head of the thrust rod 401 to the thrust plate 7 is herein a bolt.

[0166] Furthermore, the thrust rod 401 has the effect of limiting the radial force transmitted to the thrust plate 7.

[0167] When the pre-loading of the thrust plate 7 is carried out, the thrust rod 401 is lowered to compress the thrust spring 402.

[0168] When the thrust rod 401 is released upon unlocking, the thrust rod 401 slides in the guide body 400. The thrust rod 401 then slides to push the thrust plate 7.

[0169] Reference is now made to FIG. 5B representing a half-sectional view of the deployment device 1 in a second ejection phase of the nanosatellite 5 after the unlocking of the device.

[0170] The ejection of the support frame 3 carrying the nanosatellite 5 has been represented. The thrust rod 401 axially retains the thrust plate 7 thanks to its head secured to the thrust plate 7. The nanosatellite 5 is then ejected without the appendage represented by the guide tail 70.

[0171] As represented in FIGS. 5A and 5B, the thrust element 40 may comprise a setting wedge 404 provided on the guide body 400 to set the compression of the spring. The setting wedge may be moved axially along the guide body by means of screws pushing it axially.

[0172] The setting wedge 404 thus allows each thrust element 40 to be set independently to provide the most stable possible thrust of the support frame 3.

[0173] The deployment device 1 has been represented in FIG. 6. The center of gravity 50 of the nanosatellite 5, which in this case is illustrated offset from the center of thrust 10 of the thrust plate 7 has also been represented. The guide tail 70 of the thrust plate 7 and the plurality of thrust elements 40 that may be set by the setting wedge 404 makes it possible to compensate for this offset between the center of gravity 50 and the center of thrust 10 thanks to the compression of the thrust spring 402 independently of the thrust elements 40.

[0174] Reference is now made to FIGS. 7A to 7C where a mechanism 8 for retaining the actuating element 43 has been represented.

[0175] The retention mechanism 8 is provided to block the actuating element 43 in its locking position and to unblock the actuating element 43 in order to bring it into its unlocking position.

[0176] More particularly, the retention mechanism 8 makes it possible to block the peripheral shaft 44 in its first position and to unblock the peripheral shaft 44 in its second position.

[0177] The retention mechanism 8 comprises a blocking/unblocking element 80 which may be engaged radially to block the actuating element 43 in its locking position and may be disengaged radially to unblock the actuating element 43 and to bring it in its unlocking position.

[0178] The blocking/unblocking element 80 is herein formed by a magnetic control member consisting of a cylinder and a piston. Such a control device is also known by “Pin Puller”.

[0179] According to other variants, the control member may be constituted by an actuator, actuated for example by a pyrotechnic charge, an electromagnetic force or any other technology making it possible to fulfill the unlocking function.

[0180] The retention mechanism 8 comprises a cam 81 comprising a circular ramp 810 cooperating with a radial projection 440 of the peripheral shaft 44 able to bring the peripheral shaft 44 from its first position to its second position and vice versa.

[0181] As represented, the circular ramp 810 successively comprises an increasing linear portion 810A between a first position and a second position to allow an increasing linear guiding of the radial projection 440 from the low position to the high position of the peripheral shaft 44, then a flat linear portion 810B between the second position and a third position to allow the holding of the radial projection 440 in the upper position of the peripheral shaft 44, then the circular ramp 810 is interrupted between the third position and the first position to allow the switching of the radial projection 440 directly from the high position to the low position 15 of the peripheral shaft 44.

[0182] An elastic element (not represented) formed by a spiral spring is provided to bring the cam 81 back from a retaining position, where the peripheral shaft 44 is in its first position, to a rest position, where the peripheral shaft 44 is in its second position.

[0183] Furthermore, the retention mechanism 8 comprises a hooking element 82 which may be disposed between the blocking/unblocking element 80 and the cam 81 to maintain the cam 81 in its retained position.

[0184] The hooking element 82 surrounds at least partially the circular ramp 810 and is compressed against the latter by the blocking/unblocking element 80.

[0185] For this, the blocking/unblocking element 80 comprises a thrust plate 800 compressing the hooking element 82 against the circular ramp 810.

[0186] When the blocking/unblocking element 80 disengages radially, the hooking element 82 is elastically biased to be disengaged from the circular ramp 810, thus releasing the cam 81 to return it to its resting position.

[0187] The cam 81 is then elastically rotatably biased thus causing the rotation of the circular ramp 810.

[0188] The rotation of the circular ramp 810 then guides the radial projection 440 of the peripheral shaft 44 along it.

[0189] The radial projection 440 is then driven while causing the switching of the peripheral shaft 44 directly from its first position to its second position.

[0190] This second position of the peripheral shaft 44 brings the actuating element 43, herein the blade 430, into its passive position where the first clamping element 41 disengages from the second clamping element 42 to release the support frame 3.

[0191] The ejection of the support frame 3 of the nanosatellite 5 is then caused by the plurality of thrust elements 40.

[0192] Of course, the present disclosure is not limited to the examples that have just been described and many arrangements could be made to these examples yet without departing from the scope of the present disclosure. In particular, the different features, shapes, variants and forms of the present disclosure could be associated with one other according to various combinations to the extent that these are not incompatible or do not exclude each other. In particular, all of the previously described variants and forms could be combined together.

[0193] Unless otherwise expressly indicated herein, all numerical values indicating mechanical/thermal properties, compositional percentages, dimensions and/or tolerances, or other characteristics are to be understood as modified by the word “about” or “approximately” in describing the scope of the present disclosure. This modification is desired for various reasons including industrial practice, material, manufacturing, and assembly tolerances, and testing capability.

[0194] As used herein, the phrase at least one of A, B, and C should be construed to mean a logical (A OR B OR C), using a non-exclusive logical OR, and should not be construed to mean “at least one of A, at least one of B, and at least one of C.”

[0195] The description of the disclosure is merely exemplary in nature and, thus, variations that do not depart from the substance of the disclosure are intended to be within the scope of the disclosure. Such variations are not to be regarded as a departure from the spirit and scope of the disclosure.