FASTENING OF A MIRROR TO A SUPPORT

Abstract

A system for fastening a mirror to a support is disclosed including intermediate structures, for example bipod structures. At least some of the intermediate structures are provided with torsion devices making it possible to at least partially compensate for optical aberrations of an instrument that includes the mirror. Each torsion device may comprise an elastic element and a variator. The variator is designed to control a deformation of the elastic element, resulting in a torque which is applied to the mirror.

Claims

1. A fastening system for fastening a mirror to a support of said mirror, comprising the following components: at least three intermediate structures, each intended to be connected to the support by a first interface of the intermediate structure, and to be rigidly connected to the mirror by a second interface of the intermediate structure, so that the at least three intermediate structures perform together a rigid fastening of the mirror to the support, the intermediate structures being angularly distributed around a center of the mirror while being apart from said center, wherein the fastening system further comprises at least one torsion device, each torsion device being dedicated to only one of the intermediate structures and comprising: at least one elastic element, which has two ends, a first of said ends being connected to the first interface of the intermediate structure, and a second of said ends being rigidly connected to the second interface of said intermediate structure, the elastic element being arranged to apply a torque to the mirror, directly to said mirror or through the second interface of the intermediate structure; and a variator, which is coupled to the elastic element so as to modify a value of the torque applied to the mirror directly or through the second interface of the intermediate structure.

2. The fastening system according to claim 1, wherein each elastic element comprises a strip which extends between the first and the second end of said elastic element, and the variator is arranged to move the first end so as to produce a bending deformation of the strip, the bending deformation producing, at the second end, the torque which is applied to the mirror.

3. The fastening system according to claim 2, wherein a material of the elastic element of each torsion device is identical to a material of the intermediate structure to which said torsion device is dedicated.

4. The fastening system according to claim 1, wherein each variator has a mechanical operation or an operation based on at least one piezoelectric cell, for moving the first end of the elastic element relative to the support.

5. The fastening system according to claim 4, wherein each variator has a mechanical operation suitable for manual actuation, or said variator is suitable for remote actuation by means of an electrical command sent to said variator.

6. The fastening system according to claim 1, wherein each elastic element comprises a thermal deformation bimetallic strip assembly which extends between the first and the second end of said elastic element, and the variator is adapted for applying a temperature variation to the bimetallic strip assembly, such that said bimetallic strip assembly produces, at the second end, the torque which is applied to the mirror in response to the temperature variation.

7. The fastening system according to claim 1, comprising two or three intermediate structures which are each provided with a torsion device independent of the torsion device of each other intermediate structure.

8. The fastening system according to claim 1, wherein each torsion device is arranged so that the torque which is applied to the mirror, by being generated by said torsion device, is parallel to a first axis which is directed towards the center of the mirror, or is parallel to a second axis which is tangent to a peripheral edge of the mirror at a location of the mirror which is closest to the intermediate structure to which said torsion device is dedicated.

9. The fastening system according to claim 1, wherein each intermediate structure is connected to the mirror by the second interface of said intermediate structure, at the peripheral edge of the mirror, and said second interface is adapted for applying the torque to said peripheral edge of the mirror.

10. A radiation collecting or optical instrument, comprising a mirror, a support, and a fastening system according to claim 1, said fastening system rigidly connecting the mirror to the support.

11. The optical instrument according to claim 10, forming a telescope, and wherein the mirror which is connected to the support by the fastening system is a primary mirror of the telescope.

12. A method for adjusting a radiation collecting or optical instrument, wherein said instrument comprises a mirror, a support, and a fastening system according to claim 1, the mirror being rigidly fastened to the support by means of intermediate structures, the method comprising executing at least once a sequence which comprises the following steps: 1) characterizing at least one optical aberration of the instrument which at least partially results from a deviation in a shape of the mirror, relative to a reference shape identified for said mirror; and 2) for at least one of the intermediate structures, adjusting the variator of the torsion device which is dedicated to said intermediate structure, so as to reduce said at least one optical aberration of the instrument.

13. The method according to claim 12, wherein the optical aberration that is reduced by executing step (2) comprises at least an astigmatism of the instrument, a trefoil of the instrument, or a combination of astigmatism and trefoil of the instrument.

14. The method according to claim 12, wherein the radiation collecting or optical instrument is installed on board a satellite, and wherein the sequence which comprises steps and 1) and 2) is executed during an integration of the instrument into the satellite, on Earth before launching said satellite, and/or executed or repeated on board the satellite after said satellite has been placed in orbit around the Earth.

Description

BRIEF DESCRIPTION OF FIGURES

[0038] The features and advantages of the invention will become more clearly apparent from the following detailed description of some non-limiting embodiments, with reference to the appended figures, in which:

[0039] [FIG. 1a] is a partial perspective view of an instrument which corresponds to a first embodiment of the invention, in which the elastic element is a strip which is perpendicular to a peripheral edge of the mirror;

[0040] [FIG. 1b] is an enlargement showing an intermediate structure of the instrument of [FIG. 1a], with the associated torsion device;

[0041] [FIG. 1c] is a further enlargement showing the torsion device within the intermediate structure of [FIG. 1b];

[0042] [FIG. 2] shows a second embodiment of the invention, in which the elastic element is a strip which is parallel to a peripheral edge of the mirror;

[0043] [FIG. 3] shows a third embodiment of the invention, in which the elastic element is a thermal deformation bimetallic strip assembly; and

[0044] [FIG. 4] is a diagram of the steps of a method according to the invention, for adjusting an instrument which comprises a mirror.

DETAILED DESCRIPTION OF THE INVENTION

[0045] For clarity sake, the dimensions of the elements represented in these figures correspond neither to actual dimensions nor to actual dimension ratios. Furthermore, identical references indicated in different figures designate elements which are identical or which have identical functions.

[0046] [FIG. 1a] shows certain elements or parts of elements of an instrument according to the invention. This instrument, which may be a telescope, comprises a support 1 and a mirror 2. The mirror 2, which may be the primary mirror of the telescope, may have a circular peripheral edge, designated with the reference B. The reference C designates the location of a center of the mirror 2. Depending on the design of the instrument, the mirror 2 may have a central opening, and the center C may then be located within this central opening. For example, the mirror 2 may be made of silicon carbide (SiC), and its radius may be on the order of several tens of centimeters.

[0047] The support 1 may be made of an alloy based on titanium (Ti) and/or aluminum (Al), for example. Its dimensions may be adapted so that the mirror 2 is fastened to the support 1 at several locations on the edge B, for example at three locations which are each separated from their neighbors by approximately 120° (degrees) around the center C. However, such an angular distribution of the locations for fastening the mirror 2 to the support 1 is not essential. Indeed, it is sufficient that the distribution of the locations for fastening the mirror 2 to the support 1 provides the mirror with sufficient stability, and reduces vibrations which could affect the mirror and/or the support.

[0048] The “3” reference numbers each designate an intermediate structure which connects the mirror 2 to the support 1, all of them together forming a rigid connection of the mirror to the support. Preferably, the number and the design of the intermediate structures 3 are chosen so as to form an isostatic connection. For example, three intermediate structures 3 may be used, each being of the bipod type. Thus, each intermediate structure 3 may comprise two rigid segments, designated by 3a and 3b. The two segments 3a and 3b of a same bipod-type intermediate structure 3 each connect a common location of the edge B of the mirror 2 to two locations of the support 1 that are distanced from each other. In this manner, each intermediate structure 3 forms a triangle, which is isosceles when its two segments 3a and 3b have identical lengths. The materials of segments 3a and 3b can be adapted according to mechanical and thermal criteria. For example, segments 3a and 3b may be made of an alloy based on iron (Fe) and nickel (Ni), known by the name INVAR®. As can be seen in [FIG. 1b] and [FIG. 1c], the two ends of each segment 3a are designated by the references 3a.sub.1 and 3a.sub.2. Similarly, the two ends of each segment 3b are designated by the references 3b.sub.1 and 3b.sub.2. In each intermediate structure 3, the ends of segments 3a.sub.1 and 3b.sub.1 are connected to the support 1 at a distance from each other in order to form a bipod. For example, these segment ends 3a.sub.1 and 3b.sub.1 are each connected to the support 1 using a bolt and nut type of assembly. For this example of an intermediate structure, the segment ends 3a.sub.1 and 3b.sub.1 form the first interface of the intermediate structure 3, which is intended to be connected to the support 1 when the instrument is assembled. The segment ends 3a.sub.2 and 3b.sub.2 are rigidly connected to the edge B of the mirror 2, at the same location on this edge B. For example, they may be bolted together to a fastening bracket 20 which is integrated into the mirror 2 at its peripheral edge B. The segment ends 3a.sub.2 and 3b.sub.2 in a same intermediate structure 3 form the second interface of this intermediate structure, which is intended to be connected to the mirror 2 when the instrument is assembled. All the intermediate structures 3 used to connect the mirror 2 to the support 1 may be identical, but this is not essential to implementing the invention.

[0049] According to the invention, a torsion device is added to at least one of the intermediate structures 3. Preferably, such a torsion device is added separately to each of the intermediate structures 3. It may be designed to produce a torque, or a non-zero torque component, which is parallel to one of the axes A.sub.1 or A.sub.2, this torque being evaluated at the second interface of the corresponding intermediate structure 3. A.sub.1 is an axis which connects this second interface of the intermediate structure to the center C of the mirror 2, being directed towards the center C, and A.sub.2 is an axis which is tangent to the peripheral edge B of the mirror 2 at the location of the intermediate structure concerned. For example, the axis A.sub.2 may be oriented in the forward direction, also called the trigonometric or counterclockwise direction, around the reflecting surface of the mirror 2. Each torsion device is adapted to produce torque such that this torque is in the same direction as axis A.sub.1 or A.sub.2, or in the opposite direction, or such that the torque component along axis A.sub.1 or A.sub.2 is positive or negative.

[0050] Each torsion device comprises an elastic element 4, having two opposite ends which are designated by the references 4.sub.1 and 4.sub.2, and a variator 5. In certain embodiments, such as the one shown in FIGS. [1a]-[1c], the variator 5 may connect end 4.sub.1 of the elastic element 4 to the support 1, or to a location in the corresponding intermediate structure 3 which is close to the support 1. Preferably, the variator 5 may connect end 4.sub.1 of the elastic element 4 to the first interface of the intermediate structure 3. In other embodiments, end 4.sub.1 of the elastic element 4 may be connected to the support 1, or to the first interface of the intermediate structure 3, independently of the variator 5, and the variator 5 may be designed to generate a controlled deformation of the elastic element 4. [FIG. 3] shows another such embodiment, which will be presented below. In all cases, the second end 4.sub.2 of the elastic element 4 is rigidly connected to the second interface of the intermediate structure 3. For example, end 4.sub.2 of the elastic element 4 and the ends of segments 3a.sub.2 and 3b.sub.2 may be bolted together to the mirror 2. The variator 5 is designed to control the torque so that it is in the same direction as axis A.sub.1 or A.sub.2, or in the opposite direction, or has a positive or negative component along axis A.sub.1 or A.sub.2, when this torque is evaluated at the second interface of the intermediate structure 3 concerned. In the embodiments which are now described in detail with reference to FIGS. [1]-[3], the elastic element 4 has an elongated shape between its two ends 4.sub.1 and 4.sub.2, but such a shape is not essential and those skilled in the art will know how to identify alternative shapes which are also capable of producing torques for which the values are controllable, and which have suitable elastic features.

[0051] In the embodiment of FIGS. [1a]-[1c], the rigid connection between the strip which forms the elastic element 4 and the mirror 2 is designed so that the strip is oriented substantially perpendicular to the edge B of the mirror 2, and the variator 5 is a tie bar of adjustable length which connects end 4.sub.1 of the strip to a point which is fixed relative to the support 1. The tie bar which constitutes the variator 5 can then be oriented substantially parallel to the edge B, when no torque is produced. For example, the tie bar may be composed of two male threaded segments 5.sub.1 and 5.sub.2, and a female threaded tube 5.sub.3 into which the male threaded segments 5.sub.1 and 5.sub.2 can screwed to a greater or lesser extent. Thus, rotation of the threaded tube 5.sub.3, which may be performed manually by an operator for example, produces an elongation or a shortening of the tie bar depending on the direction of rotation and the number of turns. Male threaded segment 5.sub.1 is connected to the support 1, and male threaded segment 5.sub.2 is connected to end 4.sub.1 of the elastic element 4, for example using a combination of concave and convex washers. When the tie bar which forms the variator 5 is lengthened or shortened, it imposes a curvature on the strip which forms the elastic element 4, with a resulting torque at end 4.sub.2. For the embodiment represented, this torque is parallel to axis A.sub.1, and is at least partially applied to the edge B of the mirror 2. It then causes a local deformation of the reflecting surface of the mirror 2, which has a rotational component around axis A.sub.1 in the vicinity of the intermediate structure 3 concerned. This local rotational component makes it possible to compensate for an optical aberration of the mirror 2 which could be caused by the locking of the second interface of the intermediate structure 3 on the bracket 20 of the mirror 2. For such an embodiment of the invention, the strip of the elastic element 4 and the tie bar of the variator 5 may advantageously be composed of the same alloy as segments 3a and 3b of each intermediate structure 3. Indeed, under these conditions, the value of each torque which is applied to the mirror 2 can be substantially independent of the temperature at which the instrument is used, or can have a reduced dependency on this temperature.

[0052] [FIG. 2] corresponds to [FIG. 1c] for another arrangement of the strip of the elastic element 4 and of the tie bar of the variator 5: the strip is substantially parallel to the edge B of the mirror 2 at the location of the intermediate structure 3 considered, and the tie bar may be oriented substantially perpendicular to the edge B, when no torque is produced. The operation of the torsion device is then similar to what has been described in connection with [FIG. 1c],

[0053] The use of a tie bar as described above is suitable for an optical aberration compensation operation which is carried out manually by an operator. Such embodiments are therefore suitable for instruments which are accessible to an operator at the time the operation is performed. Such is the case for a telescope which is installed on board a satellite, and for which the optical aberration compensation operation is carried out on Earth, for example during integration of the satellite.

[0054] In other embodiments of the invention, the manually operated tie bar which forms the variator 5 may be replaced by an electrically controlled tie bar, which may for example incorporate a stepper motor. In this case, each torsion device may further comprise part of a controller (not shown), which makes it possible to control the length of the tie bar. Such other embodiments can allow adjusting the value of each torque remotely, including once the satellite carrying the instrument has been placed in orbit.

[0055] [FIG. 3] shows yet another possible embodiment of the invention, in which the elastic element 4 is composed of a bimetallic strip assembly which extends between ends 4.sub.1 and 4.sub.2. Such bimetallic strip assemblies are known to those skilled in the art, and are composed of two strips of different alloys, which are rigidly connected to each other at ends 4.sub.1 and 4.sub.2. The two strips are designated by the references 4a and 4b. The respective alloys of the two strips 4a and 4b are selected to have different values for their coefficient of thermal expansion. Their common end 4.sub.2 is still rigidly connected to the mirror 2, and their other common end, corresponding to reference 4.sub.1, may be connected to a point which is fixed relative to the support 1 by a rod 6 of constant length. Thus, the variator 5 may be composed of a heating system which is arranged to vary the temperature of the bimetallic strip assembly 4a-4b. In particular, it may comprise at least one heating element, for example based on at least one electrical resistor or one radiating element. When this heating element is activated, the bimetallic strip assembly 4a-4b deforms by bending and bearing against the end of the rod of constant length 6. It then produces, by reaction, a torque at end 4.sub.2. In [FIG. 3], the solid-line representation of the bimetallic strip assembly 4a-4b can correspond to the application to the mirror 2 of a torque of a determined value and sign, and the dotted lines indicated for the bimetallic strip assembly 4a-4b can correspond to the application to the mirror 2 of another value for the torque, with a sign which may be the opposite sign.

[0056] The implementation of the torsion devices is now described with reference to [FIG. 4]. The mirror 2 has been rigidly fastened to the support 1 by means of the intermediate structures 3 during a preliminary step, denoted /0/. This step /0/ is performed on Earth, for example when integrating the telescope into a satellite. Steps /1/ and /2/ of the method of the invention may then also be carried out on Earth, for example during additional steps of integrating the telescope into the satellite. Alternatively, steps /1/ and /2/ may be performed under the conditions of use of the telescope, i.e. once the satellite has been placed in orbit. The adjustments which are then applied to the variators 5 directly take into account the actual conditions of use of the telescope, in particular the intensity of the gravitational field which is in effect during this use.

[0057] Step /1/ consists of characterizing at least one optical aberration of the telescope, for example astigmatism, which results from a difference between the actual shape of the mirror 2 and its nominal shape. However, other optical aberrations of the telescope may be characterized alternatively or in addition to astigmatism, such as trefoil aberrations. Several methods may be used for these characterizations of optical aberrations, which are known to those skilled in the art so it is not necessary to repeat them in this description. For example, specific devices may be used to characterize the shape of the wave front which results from the reflection on the mirror 2 of radiation from a distant source.

[0058] A calculation unit (not shown) can then determine the deformations of the mirror 2 to be produced by the torsion devices described above, in order to compensate at least partially for some of the optical aberrations which have been characterized in step /1/. The calculation unit then determines the values of the torques which are necessary to generate these deformations, then the length modifications to be applied to the elastic elements 4 of FIGS. [1a]-[1c] or [2] to produce these torque values. For the embodiment of [FIG. 3], the calculation unit determines the temperature of each bimetallic strip assembly 4a-4b, which is necessary to produce the desired torque value. Finally, in step /2/, the variators 5 are adjusted manually or by dedicated commands, according to the values determined by the calculation unit.

[0059] It is possible for the sequence of steps /1/ and /2/ to be repeated one or more times in order to gradually improve the compensation for the optical aberrations of the telescope.

[0060] Typically, each torque to be applied may be on the order of a few Newton-meters (N•m), or less than 1 N•m. It is thus possible to rotate the optical surface of the mirror 2 by a few tens of nanometers (nm) locally, in the vicinity of each intermediate structure 3, about a direction which is parallel to the optical surface of the mirror.

[0061] It is understood that the invention may be reproduced by modifying secondary aspects of the embodiments described in detail above, while retaining at least some of the advantages cited. In particular, each intermediate structure, the elastic element, and the variator for each torsion device may have different designs and configurations from those shown in the figures. Similarly, the mirror to which the invention is applied may have no central opening, all the cited materials have been cited only as non-limiting examples and may be changed depending on the design of the instrument, and any cited numerical values again have been cited for illustrative purposes only and may be changed depending on the application considered. Finally, the instrument to which the invention is applied may have any function, and may be intended for any conditions of use, not necessarily on board a satellite. For example, it may be intended to collect radiofrequency radiation, and may be installed on Earth while being supported by a fixed structure.