EP0662254B1 - Ajustable-aiming antenna mount, particularly for satellite telecommunication antenna - Google Patents

Abstract

PCT No. PCT/FR93/00937 Sec. 371 Date Mar. 7, 1996 Sec. 102(e) Date Mar. 7, 1996 PCT Filed Sep. 24, 1993 PCT Pub. No. WO94/08360 PCT Pub. Date Apr. 14, 1994The disclosed mount comprises a first dihedral (ABC, BCD) of which one of the planes (ABC) is borne on a support base; means (6) for adjusting the angle ( alpha ) of said first dihedral; a second dihedral (BCD, BDE) of which one of the planes (BCD) is common to the first dihedral and the other plane (BDE) carries means (8) for supporting the antenna, the axis (BC) of the first dihedral and the axis (BD) of the second dihedral being neither parallel nor merged; and means (7) for adjusting the angle ( beta ) of said second dihedral.

Description

The invention relates to an antenna mount, in particular for a satellite telecommunications antenna.

Satellite antennas (terrestrial), just like, more generally, antennas used in the microwave domain, require very precise pointing in a given direction, which can be fixed or mobile. This direction is for example that in which a communication satellite is located, most often a satellite located in a quasi-geostationary or quasi-geosynchronous orbit (this case, nor even that of an antenna for telecommunications by satellite, not being in no way limiting the invention).

The antenna mount, that is to say the mechanism which makes it possible to precisely support and point the antenna, can be of various types.

The type of mount most commonly used for satellite earth stations is the type of mount called "site-azimuth", which is in the form of a basic rigid structure on which is mounted a movable structure in rotation around a vertical axis which, itself, supports a mobile rotating structure around a horizontal axis and integral with the antenna.

Most of the frames used are heavy and of complex structure. Therefore, they are not suitable for mass production, or for mobile, portable or dismountable land stations, where low weight and ease of assembly are essential elements.

On the other hand, light frames are difficult to adjust with precision, whether this adjustment is carried out by hand or motorized. It is also generally necessary to provide a rigid support such as a plate or a support slab.

Another problem encountered with many existing antennas is that they were originally designed to point to quasi-geostationary satellites, therefore according to a fixed pointing. However, over time, due to the depletion of fuel from the satellite position correction engines, most of the satellites which previously were actually geostationary now exhibit a progressively increasing orbital inclination (the geostationary orbit then becoming only geosynchronous), which requires that earth stations be able to perform mobile pointing, at least within a limited range, in order to allow permanent tracking of the satellite.

European patent application EP-A-0 227 930 (SIEMENS) discloses an antenna mount with adjustable pointing, in particular in FIG. 4. This consists of two dihedrons, at variable angles. However, these two dihedral do not have common plans.

The antenna mounts proposed so far do not allow these various imperatives to be satisfactorily reconciled.

One of the objects of the invention is to provide an adjustable antenna mount, in order to allow precise pointing and tracking, in particular of a satellite, which is advantageously foldable to allow easy transport and rapid disassembly / reassembly. , and which is for all that mechanically simple, robust and inexpensive to produce.

To this end, the frame of the invention is characterized in that it comprises: a first dihedral, one of the planes of which is carried by a support base; means for adjusting the angle of this first dihedral; a second dihedral, one of the planes of which is common to the first dihedron and the other plane of which carries the antenna, the axis of the first dihedral and the axis of the second dihedral being neither parallel nor confused; and means for adjusting the angle of this second dihedral.

More precisely, such a frame may include: a first structure, defining a first triangle, integral with said support base; a second structure, defining a second triangle, the first and the second triangle having a common side provided with a first articulated connection, so as to constitute the first dihedron, the means for adjusting the angle of the first dihedron being interposed between the vertex of the first triangle opposite the articulation side and the vertex of the second triangle opposite to this same side; and a third structure, defining a third triangle, the second and the third triangle having a common side provided with a second articulated connection, so as to constitute the second dihedron, the means for adjusting the angle of the second dihedron being interposed between the top of the second triangle opposite to the articulation side and the top of the third triangle opposite to this same side.

Preferably, the means for adjusting the first and second dihedral are separable from said structures, so as to allow the frame to be folded flat by closing the two dihedrons.

Preferably also, the means for adjusting the angles of the first and second dihedral are controlled by calculating means, capable of transforming setpoint values expressed in elevation and azimuth angles into signals for direct control of the position of these adjustment means.

Other characteristics and advantages of the invention will appear on reading the detailed description below, made with reference to the accompanying drawings.

Figure 1 is a schematic explanatory view of the structure of the frame of the invention.

Figure 2 shows how the mount of the invention can be used for an antenna wall mount.

FIG. 3 shows how the structure of the invention can be used for attachment to the antenna ground, in particular for the adaptation of a conventional “site-azimuth” antenna.

FIG. 4 illustrates an embodiment adaptable to a fixed pointing antenna so as to be able to allow slight variations in the pointing direction thereof and thus ensure permanent tracking of the satellite.

FIG. 5 schematically illustrates the device for calculating and controlling the position of the actuators.

Figure 6 is a perspective view showing how it is possible to mechanically produce the frame of the invention in foldable and removable form.

Figure 7 shows the detail of one of the connection elements of the frame of figure 6.

FIGS. 8 and 9 are side views of the element in FIG. 7.

FIG. 10 shows how the mount of the invention can be used as the main mount for a large antenna.

The general structure of the frame of the invention is illustrated in Figure 1: it includes a first triangular structure 1 (triangle ABC) on which is articulated a second structure 2, also triangular (triangle BCD), which itself carries with articulation of a third triangular structure 3 (BDE triangle). Structures 1 and 2 are articulated at 4 along the BC side, and structures 2 and 3 are articulated at 5 along the BD side, i.e. along a different side on the articulation side structures 1 and 2.

Preferably, for simplicity, the triangles ABC, BCD and BDE are all equilateral, but this characteristic is in no way essential.

The structures 1 and 2 thus define a first dihedral ABC, BCD, of variable angle α and adjustable by an actuator 6, manual or motorized, for example a linear electric actuator interposed between the vertices A and D.

Similarly, structures 2 and 3 define a second dihedron BCD, BDE of variable β angle and adjustable by a second linear actuator 7 interposed between the vertices E and C. AD and EC thus constitute struts of variable length and length .

To allow adjustment in all directions, it is essential that the edge of the first dihedral (materialized by the segment BC) and that of the second dihedral (materialized by the segment BD) are neither parallel nor confused because otherwise we would lose the one of the two degrees of freedom of the frame; however, they do not need to be concurrent.

The first structure 1 is fixed and the third structure 3 carries support means for the antenna, for example a ring 8 in the shape of a circle inscribed in the triangle BDE and which will support the dish of the antenna (which may be of dimension greater or less than this support ring 8). It will be noted that, when the antenna is a paraboloid or a section of paraboloid, it will be relatively simple to fix it to a triangular structure such as structure 3, and it is for this reason that triangular structures are preferred for define the dihedral (another reason being the possibility of folding the triangles one on top of the other as will be explained in more detail with reference to FIG. 4). The choice of a triangular structure to define each of the half-planes of each of the dihedrons is however not essential, the triangles ABC, BCD and BDE can simply be virtual triangles defined on structures whose physical contour is not necessarily that of a triangle.

It is easy to understand from this description that by varying the lengths of the segments AD and CE by means of the actuators 6 and 7, the values of α and β and therefore the pointing direction of the antenna will be modified, which makes it possible to point the latter on a very wide range of site and azimuth angles, which greatly exceeds the needs of the simple tracking of satellites in quasi-geosynchronous orbit.

The directions of the segments AD and EC not being orthogonal, in order to obtain a given elevation and azimuth angle, the adjustment of the actuators 6 and 7 must be determined by a preliminary calculation, which will be indicated below.

If A is the azimuth angle, S the site angle, α the dihedral angle ABC, BCD and β the dihedral angle BCD, BDE, it is necessary to solve the equations A = f (α, β ) and S = f (α, β), which can be done by a microprocessor calculator implementing a relatively simple pointing and tracking program.

$$\text{Y = - sin β cos 30° ,}$$

et $$\text{Z = co β cos α + sin β sin 30° sin α.}$$

If we consider the various mobile Cartesian landmarks, we demonstrate that, X, Y and Z being the components of the vector normal to the triangle BDE (i.e. the vector defining the pointing direction), we have, in the case of equilateral triangles: $$\text{X = - cos β sin α + <figure-callout id="30" label="sin β sin" filenames="imgf0004.png" state="{{state}}">sin β sin</figure-callout> 30 ° cos α,}$$

$$\text{Y = - <figure-callout id="30" label="sin β cos" filenames="imgf0004.png" state="{{state}}">sin β cos</figure-callout> 30 °,}$$

and $$\text{Z = co β cos α + <figure-callout id="30" label="sin β sin" filenames="imgf0004.png" state="{{state}}">sin β sin</figure-callout> 30 ° sin α.}$$

et $${\text{S = arctg [Z/(X}}^{\text{2}}{\text{+Y}}^{\text{2}}{\text{)}}^{\text{1/2}}\text{].}$$

The azimuth angle A and the site angle S can be deduced from these X, Y and Z values by the following relationships: $$\text{A = arctg (X / Y)}$$

and $${\text{S = arctg [Z / (<figure-callout id="2" label="X" filenames="imgf0001.png,imgf0005.png" state="{{state}}">X</figure-callout>}}^{\text{2}}{\text{+ Y}}^{\text{2}}{\text{)}}^{\text{1/2}}\text{].}$$

As we can see, this determination involves only simple calculations, easy to implement by a microprocessor incorporated in the frame control system or a microcomputer performing, among other things, this task, which will not be burdensome very moderately the overall cost of the frame with its control system.

From the point of view of the configuration of use, the first structure 1 can be simply placed on the ground, as illustrated diagrammatically in FIG. 1.

It can also, as illustrated in FIG. 2, be fixed to a wall 10, a configuration which is quite often found in antennae for satellites and which thus makes it possible to have a continuously adjustable mount supporting the antenna, here constituted of a simple dish 9.

In the example of FIG. 3, the mount of the invention rests on the ground by the first structure 1, but the third structure 3 does not directly carry the antenna as in the case of FIGS. 1 and 2, but a mount d pre-existing antenna 11 of the site-azimuth type, consisting of a vertical shaft 12 carrying an assembly 13 movable around a vertical axis 14 on which the support 15 of the antenna is articulated around a horizontal axis 16. This configuration allows you to continue using a fixed-pointing antenna mount even when, over time, the end-of-life satellites show variations significant of their pointing direction, variations which can typically reach 5 ° and which require a motorized permanent tracking system to compensate for these variations.

Figure 4 illustrates a possible form of construction, mechanically very simple, suitable for this type of situation. The pre-existing antenna is mounted on a barrel 12 provided with a support tripod 17. The additional mount, produced according to the teachings of the invention, consists of tubular profiles with square section, of steel or aluminum, which can be common profiles assembled by traditional methods (welded or mechanically welded assembly). The joints used can be of an extremely simple type, for example of the same type as those used for door or window hinges.

From a static point of view, it will be noted that the triangular construction of the frame of the invention takes up all the loads at intersections, which ensures excellent robustness and allows the use of relatively light materials for its production. As regards the joints, they essentially only undergo the gravity constraints and the additional stresses of the wind, providing pointing tolerances which compare quite favorably with those of conventional solutions.

The actuators 6 and 7 may consist of an electric actuator system with a body 18 and a movable rod 19 provided respectively with fasteners 20 and 21 which will be fixed to homologous fasteners 22 and 23 of the triangular structures. The motor 24 of each of the two actuators is electrically connected to a control system, the two actuators being physically and electrically independent. Optionally, to allow a rough coarse preliminary pointing or to compensate for a slope, it may be useful to place an additional support leg, fixed or adjustable, such as 25 under one of the vertices A, B or C of the triangle of the first structure.

FIG. 5 schematically shows the control circuit, which comprises an electronic and electrical block 26 for calculating the coordinates and for controlling the respective motors 24 of the actuators 6 and 7; this box 26 receives its power supply by a line 27 and by lines 28, the conventional site instructions S and azimuth A (in digital or analog form), which are processed within the unit 26 by transformation of coordinates to determine the length of the struts controlled by cylinders 6 and 7 to obtain the desired angles of elevation and azimuth.

Figure 6 shows a form of implementation particularly suitable for the production of a removable and portable frame. The frame is produced essentially from profiles 29 of square section constituting the three sides of each of the three triangles (these profiles are therefore nine in number), profiles which are connected together by connecting pieces 30, five in number .

These connecting pieces 30, which define the vertices of the triangles ABC, BCD and BDE, are not identical due to the particular geometry of each of the vertices. However, they are all made from the same essential elements, illustrated by way of example in FIGS. 7 to 9 for the connecting piece 30 located furthest back in the perspective view (and therefore corresponding to the apex B), which is the most complex: the connecting parts comprise at least one fixing plate 31 (two plates in the case of the part illustrated in FIGS. 7 to 9) provided with holes 32 allowing fixing to the ground or to an antenna support, as appropriate (lower plates or upper plates). Segments 33, defining between them the various angles of the triangles, end at 34 in the form of male parts coming to fit inside the profiles constituting the sides of the triangles, the connection with the latter being effected for example by means of '' a screw or pin system.

The part 30 also carries, in the case of the four connecting parts other than that shown in FIGS. 7 to 9, a vertical support 35 allowing the fixing of the jacks in the holes 22 and 23 made in these parts 35. The connection between the respective fasteners 22 and 23 is preferably made by easily removable means (nested or screwed mounting), in order to be able to disassemble the actuators quickly and fold the assembly flat, which is very interesting in the case of portable stations, when transportability and speed of implementation are essential characteristics.

The connecting pieces 30 also carry the hinges 36 making it possible to articulate between the three triangles of the frame; these hinges and their arrangement are particularly clearly visible in FIGS. 8 and 9.

FIG. 10 shows an embodiment adapted to a case, quite different from the previous one, where the mount of the invention serves as a primary, fixed mount for a large diameter antenna and purely and simply replaces the traditional mount site- azimuth. To this end, the antenna support triangle 3 is connected to the antenna 37 at three equidistant points 38, integral with the annular element 39 of the antenna support frame located on the back of the reflector. The lower triangle 1, for its part, is placed on a fixed base 40, for example a concrete base, or at the top of a building. The actuators 6 and 7 perform the same functions as in the embodiments explained above, but with, in the present case very much greater opening angles α and β, insofar as it is no longer a question of compensating for a slight failure to score, but to carry out the pointing itself.

Claims (4)

1. An adjustable-aiming antenna mount, in particular for a telecommunications antenna aiming at a satellite, comprising

   - a first dihedron (ABC, BCD) one of whose planes (ABC) is carried by a supporting base (10),

   - means (6) for adjusting the angle (α) of this first dihedron, characterized in that it comprises, moreover, a second dihedron (BCD, BDE), one of whose planes (BCD) is common with the first dihedron and whose other plane ((BDE) carries means (8) for supporting the antenna (9), the axis (BC) of the first dihedron and the axis (BD) of the second dihedron being neither parallel nor coincident, and

   - means (7) for adjusting the angle (β) of this second dihedron.
2. The mount of claim 1, comprising,

   - a first structure (1) defining a first triangle (ABC), joined to the said supporting base,

   - a second structure (2) defining a second triangle (BCD), the first and the second triangle having a common side (BC) provided with a first articulated link (4) so as to constitute the first dihedron, the means (6) for adjusting the angle of the first dihedron being interposed between the apex (A) of the first triangle opposed to the articulation side and the apex (D) of the second triangle opposed to this same side, and

   - a third structure (3) defining a third triangle (BDE), the second and the third triangle having a common side (BD) provided with a second articulated link (5) so as to constitute the second dihedron, the means (7) for adjusting the angle of the second dihedron being interposed between the apex (D) of the second triangle opposed to the articulation side, and the apex (E) of the third triangle opposed to this same side.
3. The mount of claim 2 in which the means for adjusting the first and the second dihedron are separable from the said structures, so as to allow the mount to be folded flat by closing the two dihedrons.
4. The mount of claim 1, in which the means (6, 7) for adjusting the angles of the first and of the second dihedron are controlled by computer means (26) capable of transforming the set-point values expressed as the angles of elevation (S) and of the azimuth (A) into signals for directly controlling the position of these adjustment means.

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