RADIOFREQUENCY ANTENNA FOR A SATELLITE

Abstract

A radiofrequency antenna is adapted to be mounted on a spacecraft. The radiofrequency antenna includes four helical strands of a super elastic shape memory alloy and is configured to move from a deployed configuration to a constrained stacking configuration and to return autonomously to the deployed configuration.

Claims

1. A radio frequency antenna adapted to be mounted on a space vehicle, the antenna comprising: four helical strands of super elastic shape memory alloy and configured to pass from a deployed configuration to a constrained stacking configuration and to return to a self-deployed configuration.

2. The antenna according to claim 1, wherein the super elastic shape memory alloy is a copper-based alloy.

3. The antenna according to claim 1, wherein the super elastic shape memory alloy is a nickel-based alloy.

4. The antenna according to claim 1, wherein the super elastic shape memory alloy is a titanium-based alloy.

5. The antenna according to claim 1, wherein the super elastic shape memory alloy is an iron-based alloy.

6. The antenna according to claim 1, wherein the super elastic shape memory alloy is an alloy selected from the group consisting of CuAlNi, CuAlBe, CuAlMn, FeMnAlNi, NiTiCo and NiTiX.

7. The antenna according to claim 1, wherein the four helical strands are connected in pairs so that the antenna comprises two pairs of strands.

8. The antenna according to claim 1, wherein the antenna is configured to operate in frequency bands between 3 MHz and 10 GHz.

9. The antenna according to claim 1, wherein the antenna is cylindrical in shape.

10. The antenna according to claim 1, wherein the antenna is conical in shape.

11. The antenna according to claim 1, wherein the antenna has a height (H) in the deployed configuration comprised between 0.05 m and 1 m.

12. The antenna according to claim 1, wherein a height ratio between the stacking configuration and the deployed configuration is greater than 10.

13. The antenna according to claim 1, wherein each helical strand has a pitch comprised between 5 mm and 300 mm.

14. The antenna according to claim 1, wherein each helical strand is tubular and has a diameter comprised between 0.5 and 4 mm.

Description

DRAWINGS

[0050] 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:

[0051] FIG. 1 shows a radio frequency antenna according to a variation in the deployed configuration;

[0052] FIG. 2 shows the radiofrequency antenna according to a variation in the deployed configuration; and

[0053] FIG. 3 shows the radiofrequency antenna according to a variation in the stacking configuration.

[0054] 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

[0055] 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.

[0056] For the sake of simplification, identical elements are identified by identical reference signs in all of the figures.

[0057] There is shown in FIG. 1 a radiofrequency antenna 1 according to one variation of the present disclosure. The radio frequency antenna is adapted to be mounted on a space vehicle, in one aspect a satellite, in one form a nano satellite. In other words, the radio frequency antenna 1 is configured to be mounted on the satellite, in one form the nano satellite.

[0058] In this example, the radio frequency antenna 1 is a four-wire antenna. The antenna 1 comprises four helical strands 10 of super elastic shape memory alloy. The super elastic shape memory alloy has features that allow it to spontaneously return to its original shape when applied deformation constraints are removed.

[0059] In one form, the alloy is a copper-based alloy, however the antenna 1 is not limited to this type of alloy and may be made of any metal alloy having super elastic features such as Nickel-based alloys in one form.

[0060] In one form, the super elastic shape memory alloy is an alloy selected from the group consisting of CuAlNi, CuAlBe, CuAlMn, FeMnAlNi, NiTiCo and NiTiX.

[0061] The antennas formed by these alloys have demonstrated optimal behavior under the conditions and under the constraints of space in which the temperature amplitude is very high, in one form ranging from −100 to 200°.

[0062] In addition, the antennas formed by these super elastic alloys have demonstrated optimal return to the deployed position under the conditions and under the spatial constraints.

[0063] The admissible deformation rate for CuAlNi in the monocrystalline state is 10% with a super elastic behavior between 123° K. (−150° C.) and 473° K. (200° C.).

[0064] The admissible deformation rate for CuAlBe in the monocrystalline state is 20% with a super elastic behavior for a temperature between 123° K. (−150° C.) and 343° K. (70° C.).

[0065] The admissible deformation rate for CuAlMn in the monocrystalline state is 8% with a super elastic behavior for a temperature above 4° K. (−269° C.).

[0066] The admissible deformation rate for FeMnAlNi in the monocrystalline state is 10% with super elastic behavior for a temperature above 10° K. (-−63° C.).

[0067] The alloys CuAlNi, CuAlBe, CuAlMn and FeMnAlNi can also be used in the polycrystalline state with an admissible deformation of 3%.

[0068] The admissible deformation rate for NiTiCo in the polycrystalline state is 5% with super elastic behavior for a temperature above 173° K. (−100° C.).

[0069] The admissible deformation rate for NiTiX in the polycrystalline state is 5% with super elastic behavior for a temperature above 163° K. (−110° C.).

[0070] The admissible deformation rate for TiNb in the polycrystalline state is 20% with super elastic behavior for a temperature above 73° K. (−200° C.).

[0071] The antenna 1 is configured to pass from a deployed configuration (FIGS. 1 and 2) to a stacking configuration (FIG. 3) by applying a constraint such as, in one form, compression and to restore its geometry to return to a self-deployed configuration. The deployed configuration corresponds to an initial position in which the antenna was manufactured. In one form, the stacking configuration, in which the antenna is retracted, constitutes a temporary state of the radio frequency antenna which allows it to be placed under a fairing of a launcher.

[0072] In one form, the four helical strands 10 are electrically linked in pairs to the top of the antenna so that the antenna comprises two pairs of strands and has a double helix architecture.

[0073] As shown in FIG. 2, the four strands 10 can be independent of each other so that the antenna has a helical architecture with four strands not electrically bonded in pairs.

[0074] In another form not shown, the strands 10 can all be electrically linked to the top of the antenna.

[0075] These configurations allow the antenna to operate in the frequency bands compatible with space vehicles.

[0076] In the shown variations, the antenna has a height H equal to 173 mm in the deployed configuration and equal to 20 mm in the stacking configuration.

[0077] The order of magnitude of the size ratio between the stacking and deployed configurations is 10.

[0078] In the shown forms, the antenna 1 has a conical shape including a base 30 of a diameter D1 greater than the diameter D2 of the top 20 of the antenna.

[0079] In the shown variations, the diameter D1 of the base 30 of the antenna is equal to 55 mm and the diameter D2 of the top 20 is equal to 42 mm.

[0080] In the shown forms, the helical strands are tubular and have a diameter equal to 1.5 mm.

[0081] Each helical strand 10 forms a helix, with constant pitch P. In the shown form, the pitch P of each strand 10 is equal to 114 mm.

[0082] In a non-shown variant, the antenna can be cylindrical in shape. In this configuration, the diameter D1 of the base 30 of the antenna is equal to the diameter D2 of the top 20 of the antenna.

[0083] The dimensions of the antenna 1 previously described allow the antenna to be configured to operate in a frequency band equal to 1.7 GHz.

[0084] However, the present disclosure at this frequency band and the person skilled in the art will be able to modify the dimensions of the antenna so that the latter is configured to operate in frequency bands between the HF band (in the range of 3 MHz) and the X band (in the range of 10 GHz).

[0085] A method for manufacturing the radiofrequency antenna 1 is described below.

[0086] Each strand 10 is formed in the super elastic shape memory alloy and the dimensions allow the antenna to operate in the selected frequency band.

[0087] The strands 10 are placed on a tool (not shown) comprising helical and circular grooves adapted to receive each of the strands 10.

[0088] The strands 10 are heated and formed on the tooling.

[0089] The radiofrequency antenna is thus manufactured in the deployed configuration (FIGS. 1 and 2) which corresponds to an initial position of the so-called first position antenna.

[0090] One application of the radiofrequency antenna illustrated in FIGS. 1 to 3 resides in its use in aerospace, in one form in the launching of nano satellites.

[0091] The radiofrequency antenna 1 is configured to occupy a stacking configuration (FIG. 3) during launch and to occupy a deployed configuration (FIGS. 1 and 2) during the operational phases of the space vehicle.

[0092] After manufacture, the antenna is maintained in a compact, so-called stacked, or stacking configuration by mechanical constraint (FIG. 3). The antenna undergoes the environments associated with the launch and cruise of the space vehicle in this configuration. After orbiting, the mechanical constraint is removed, the released antenna restores its geometry to return to the deployed configuration thanks to the shape memory alloy of the strands and without the need for heating thanks to the super elastic properties of the alloy.

[0093] Thus, the radio frequency antenna according to the present disclosure is adapted for compactness allowing nano satellite platforms to occupy a reduced volume under the fairing of the launcher and makes it possible to dispense with the heating devices of the prior art.

[0094] Obviously, the present disclosure is not limited to the examples, forms, and/or variations which have just been described and many adjustments can be made to these examples without departing from the scope of the present disclosure. In one form, the different features, forms, variants, and embodiments of the present disclosure can be associated with each other in various combinations insofar as they are not incompatible or exclusive of each other. In one form, all the variants and forms described previously can be combined with one another.

[0095] 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.

[0096] 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”

[0097] The apparatuses and methods described in this application may be partially or fully implemented by a special purpose computer created by configuring a general-purpose computer to execute one or more particular functions embodied in computer programs. The functional blocks, flowchart components, and other elements described above serve as software specifications, which can be translated into the computer programs by the routine work of a skilled technician or programmer.

[0098] 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.