A movable spot beam antenna suitable for landing and patrol exploration on the surface of Mars

Abstract

The present invention discloses a high-gain movable spot beam antenna suitable for Mars landing patrol exploration. In the present invention, the feed source is suspended in the center of the reflection surface by three-point support of waveguide D, waveguide E and other two supporting members, which effectively reduces the influence of the supporting structure on the antenna performance. At the same time, by changing the waveguide caliber of waveguide D, waveguide E and the feed source, the feed source is miniaturized and the shielding influence of the feed source is reduced. At the same time, the present invention adopts a non-compact antenna component compression configuration, and the compression mounting surface with height difference and the mounting surface provided by the unfolding support structure meet the working requirements of the antenna after unfolding, and at the same time, the maximum additional envelope after the antenna is installed can be as small as the maximum height dimension of the unfolding drive shaft assembly part, thereby greatly reducing the additional envelope and meeting the application envelope requirements of the Mars rover.

Description

Technical Field

[0001] The present invention relates to the field of microwave antenna technology, and is a high-gain movable spot beam antenna suitable for Mars landing patrol exploration. The antenna system can be applied to my country's Mars exploration mission, and can also be applied to other deep space exploration landing patrols with similar requirements. Background Art

[0002] In the Mars exploration project, the Mars rover that lands on the surface of Mars and conducts landing, patrol and exploration on the surface of Mars needs to be equipped with a high-gain movable spot beam antenna for high-speed communication with the Earth's measurement and control and with the artificial Martian satellite orbiting Mars.

[0003] In order to achieve communication with the Earth and artificial Mars satellites, the high-gain movable spot beam antenna for the Mars rover requires an antenna assembly combined with an unfolding mechanism, a pointing drive mechanism, a compression release mechanism, and related support structures and RF transmission structures to form an antenna system to achieve: ① In the compressed state, the antenna system withstands environmental loads in different states such as launch into orbit, orbit around Mars, entry into the Martian atmosphere, and landing on the surface of Mars without being damaged; ② After landing, the compression can be successfully released under the environmental conditions on the surface of Mars, the antenna can be unfolded, and pointing tracking can be achieved according to work requirements. According to the traditional solution, the weight of the Mars rover high-gain antenna system will be more than 10kg for the realization of such an antenna system. Due to the limitations of the envelope and space, it is difficult to install it on the Mars rover body. After being installed on the Mars rover, the Mars rover envelope perpendicular to its installation surface needs to be increased by more than 400mm. For the Mars rover supporting my country's Mars exploration project, its weight and envelope size are unacceptable. Specifically, the realization of the high-gain movable spot beam antenna for the Mars rover needs to solve the following problems:

[0004] ① The thermal mismatch of materials and structures in the two parallel links of the RF system and the antenna assembly-support structure-mechanism assembly can easily cause additional torque to the rotary joint in the RF link, thereby increasing the resistance distance of the mechanism assembly and hindering the normal rotation of the mechanism. In the RF transmission structure, in order to achieve synchronous rotation with the rotation of the deployment mechanism and the pointing drive mechanism, the RF cable follower or rotary joint solution can usually be selected. In the Mars rover application, due to the large temperature difference on the surface of Mars and the fact that the Mars rover cannot provide cable heating resources, it is more reasonable to use the rotary joint solution. When the rotary joint is selected, the resistance distance of the rotary joint itself can meet the requirements through design, but because the rotary joint is installed in the RF system, the RF system and the antenna assembly-support structure-mechanism assembly are two parallel branches. When the thermal expansion coefficients of the materials used between the two branches are different, there is a problem of thermal matching. When there is a thermal mismatch, a bending moment will be generated on the two components of the relative rotation of the rotary joint, thereby increasing the resistance distance of the rotary joint, thereby increasing the difficulty of adjusting the antenna pointing and even making the antenna pointing impossible to adjust.

[0005] ② The contradiction between the structural volume required for the waveguide aperture rotation implementation method in the RF system and the system interference and transmission performance needs to be resolved. In the RF transmission structure, the feed source to the system RF signal output port is usually connected by waveguide and cable. Due to the performance requirements of the Mars rover's measurement and control communication, when cables are used, the antenna gain and other aspects are difficult to meet the use requirements, so waveguides are needed for connection. When waveguides are used for RF channel connection, due to the relative position of the connected feed source, rotating joints, etc., there is a certain rotation, and it is necessary to adjust the direction of the main mode of waveguide transmission through a combination of curved waveguides or twisted waveguides. In the X-band used in Mars rover communication, the aperture size of the waveguide is large, and due to the envelope requirements of the Mars rover, the antenna assembly itself has a small size. Therefore, the length of the waveguide used for adjusting the direction of the main mode of waveguide transmission is limited. When the direction adjustment is achieved through a combination of curved waveguides, it will bring about greater antenna rotation interference and cause obstacles to the setting of the antenna clamping device, etc., and the shorter twisted waveguide has the disadvantages of large differential loss, which is not conducive to achieving the electrical performance index requirements of the antenna system.

[0006] ③ The additional envelope increase caused by the compression state of the antenna system to the Mars rover is difficult for the Mars rover to accept. In the implementation of the compression of the antenna system, it is usually adopted that the components of the antenna system are concentrated as much as possible and then compressed and installed to form a compact antenna compression state with good mechanical resistance. However, this state causes the direction of the largest size of the reflector surface and feed source assembly and its supporting structure in the antenna assembly to be attached in the direction of the vertical compression installation surface. After superimposing the height of the dual-axis drive mechanism and the compression device, the additional envelope contribution caused by the antenna to the Mars rover envelope will reach an unacceptable level.

[0007] ④ The contradiction between the installation position of the low-addition envelope antenna system and the deployment of the antenna system needs to be resolved. Usually, the bottom surface of the antenna deployment mechanism installation structure and the bottom surface of the antenna clamping installation structure are located in the same plane, so as to simplify the mechanical environment considerations of the antenna installation surface as much as possible, reduce the center of gravity height relative to the lowest installation surface, and thus improve the mechanical resistance of the antenna system. In order to meet energy requirements, payload installation requirements, etc., the antenna installation surface that can be provided on the Mars rover is the top surface of the roof and a side wall, and its top plate protrudes from the side wall due to the above requirements. When the antenna is installed on the roof of the rover, it needs to be installed on the solar panels and other loads in a compressed state, plus its own height envelope. This method not only has a great impact on the solar panels and other loads and increases the coupling between devices, but also greatly exceeds the height envelope of the rover. When installed on the side wall, there are two specific methods. One is to set the installation surface to a more recessed side wall position on the rover. This is convenient for meeting the additional envelope requirements, but the corresponding protruding position on the rover causes the deployment to be restricted and cannot meet the work needs after deployment. The second is to set the installation surface to the side wall of the rover roof that forms a protruding position. At this time, the envelope requirement caused by the installation of the antenna will be unacceptable to the rover.

[0008] ⑤ The antenna system needs to provide a set of installation structures for other payloads of the Mars rover. When the antenna system is deployed and enters the pointing working state, it is located on the top surface of the Mars rover. In order to effectively utilize the top surface space of the Mars rover, the Mars rover requires the antenna system structure to provide an equipment installation structure for the installation of other payloads of the Mars rover, so as to expand the installation space of the Mars rover's payload and increase the number of Mars rover's payload applications.

[0009] In order to solve the above problems, the present invention provides a lightweight, low-additional-envelope movable spot beam antenna that meets the application requirements of Mars exploration. Summary of the invention

[0010] In view of this, the present invention provides a movable spot beam antenna suitable for landing and patrol exploration on the surface of Mars, which can meet the lightweight requirements and low additional envelope requirements of the Mars rover.

[0011] The movable spot beam antenna suitable for landing and patrol detection on the surface of Mars of the present invention comprises an antenna assembly, a waveguide assembly C, a clamping device B, a rotating joint C, a pointing drive shaft B, a waveguide assembly B, a pointing drive shaft A, a rotating joint B, a clamping device A, a waveguide assembly A, an unfolding device and a rotating joint A;

[0012] The antenna assembly includes a feed, a feed support A, a feed support B, a reflective surface, an antenna bracket, a waveguide D and a waveguide E, wherein the reflective surface is mounted on the antenna bracket through a clamping device B to form a first clamping mounting surface; the waveguide D and the waveguide E are interconnected, serving as one of the feed supports, and together with the feed support A and the feed support B, the feed is suspended in the air at the center of the reflective surface;

[0013] The antenna bracket is connected to the pointing drive shaft B through a rotating joint C, and the pointing drive shaft B is connected to the pointing drive shaft A through a rotating joint B; the pointing drive shaft A is installed on the deployment device through a clamping device A to form a second clamping installation surface; the deployment device is installed on the Mars rover;

[0014] One end of the waveguide component C is fixed on the antenna bracket and connected to the rotating joint C, and the other end has a variable waveguide diameter and is connected to the waveguide E; the waveguide component B connects the rotating joint B and the rotating joint C.

[0015] Preferably, the waveguide D adopts a double-bend structure.

[0016] Preferably, the installation points of the waveguide E, feed support A and feed support B on the reflecting surface are located at the edge of the reflecting surface and outside the electrical aperture.

[0017] Preferably, the waveguide component C is obtained by connecting waveguide F, waveguide G, and waveguide H, wherein waveguide F is connected to waveguide E, and its aperture gradually changes to the waveguide aperture of the rotating joint C; waveguide G adopts a compact orthogonal mode conversion waveguide; one end of waveguide H is connected to the rotating joint C and fixed to the antenna bracket.

[0018] Preferably, the waveguide H is bent so that the distance between the waveguide component C and the reflecting surface is as small as possible.

[0019] Preferably, the installation axis of the rotary joint C pointing to the drive shaft B is coaxial with the drive shaft installation axis pointing to the drive shaft B; the installation axis of the rotary joint B pointing to the drive shaft A is coaxial with the drive shaft installation axis pointing to the drive shaft A.

[0020] Preferably, the deployment device is provided with a mounting structure for mounting other payload equipment, including another set of antennas.

[0021] Beneficial effects:

[0022] ① The present invention uses the combination of waveguide D and waveguide E as one of the supports of the feed source, and forms a three-point support together with the feed source support A and the feed source support B, so that the feed source is suspended in the center of the reflective surface, which effectively reduces the influence of the support structure on the antenna performance; ② The feed source, waveguide D and waveguide E adopt non-standard waveguide calibers, which can effectively realize the miniaturization of the feed source, reduce the shielding effect of the feed source, and promote the realization of lightweight system; ③ The port of the waveguide component C is fixed on the antenna bracket, so that under the condition of large temperature difference, the deformation torque of the rotating joint caused by the different thermal deformation of the waveguide and the two branches of the reflective surface-antenna bracket is consumed by the antenna bracket, which effectively reduces the effect of thermal matching of different materials on the rotating joint, reduces the increase of the resistance distance of the rotating joint under high and low temperature environments, and avoids the difficulty of pointing adjustment and the risk of being unable to adjust due to the large resistance distance; ④ In the waveguide component C, the compact orthogonal mode conversion waveguide is used to realize the function of the twist waveguide, which reduces the demand of the twist waveguide on the length direction of the waveguide and reduces the waveguide twisting achieved by bending the waveguide combination. The envelope requirements and performance losses brought about by it; ⑤ The non-compact antenna assembly compression configuration adopted in the present invention reduces the additional envelope increase of the Mars rover after the antenna system is installed; ⑥ The compression installation surface with height difference and the installation surface provided by the deployment support structure not only meet the working requirements after the antenna is deployed, but also make the maximum additional envelope after the antenna is installed to reach the maximum height dimension of the deployment drive shaft assembly part, thereby greatly reducing the additional envelope and meeting the application envelope requirements of the Mars rover; ⑦ The final machine weight formed by various lightweight measures adopted is more than 40% lower than that of the traditional solution, meeting the weight requirements of the Mars rover for the antenna system; ⑧ The fixed idle space in the antenna system after the antenna is deployed is used to provide other payload installation structures for the Mars rover, expand the Mars rover payload installation space, and increase the number of Mars rover payload applications; ⑨ The antenna system formed after adopting the above-mentioned various measures meets all environmental load conditions and functional performance index requirements of the Mars rover during the work of launching the Mars rover from the earth to patrolling the surface of Mars. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of the structure of the antenna system of the present invention;

[0024] Figure 2 It is a schematic diagram of the combination of the antenna component and the waveguide component C of the present invention;

[0025] Figure 3 This is a schematic diagram of the clamping angle of the clamping device B and the antenna assembly of the present invention;

[0026] Figure 4 It is a schematic diagram of the waveguide component B and the peripheral components of the present invention;

[0027] Figure 5 It is a schematic diagram of the combination of the unfolding device and the rotating joint A of the present invention;

[0028] Figure 6 It is a side view of the antenna system of the present invention.

[0029] Among them, 1-antenna assembly, 2-waveguide assembly C, 3-pressing device B, 4-rotating joint C, 5-pointing drive shaft B, 6-waveguide assembly B, 7-pointing drive shaft A, 8-rotating joint B, 9-pressing device A, 10-waveguide assembly A, 11-unfolding device, 12-rotating joint A, 1-1-feed source, 1-2-feed source support A, 1-3-feed source support B, 1-4-reflecting surface, 1-5-antenna bracket, 1-6-waveguide D, 1-7-waveguide E, 2-1-waveguide F, 2-2-waveguide G, 2-3-waveguide H, 11-1-unfolding drive shaft assembly, 11-2-unfolding arm, 11-3-unfolding support structure, 11-4-equipment installation structure, DETAILED DESCRIPTION

[0030] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0031] The present invention provides a movable spot beam antenna suitable for landing and patrol detection on the surface of Mars, comprising an antenna component 1, a waveguide component C2, a clamping device B3, a rotating joint C4, a pointing drive shaft B5, a waveguide component B6, a pointing drive shaft A7, a rotating joint B8, a clamping device A9, a waveguide component A10, an unfolding device 11, and a rotating joint A12, as shown in FIG. Figure 1 shown.

[0032] The antenna assembly 1 is the functional body of the antenna system, such as Figure 2As shown, the antenna assembly 1 is a reflector antenna assembly, including a feed source 1-1, a feed source support A 1-2, a feed source support B 1-3, a reflector 1-4, an antenna bracket 1-5, a waveguide D 1-6 and a waveguide E 1-7, wherein the waveguide D 1-6 and the waveguide E 1-7 adopt a waveguide aperture dedicated to the feed source 1-1, the waveguide D 1-6 and the waveguide E 1-7 are interconnected, the other end of the waveguide D 1-6 is connected to the feed source, and the other end of the waveguide E 1-7 is fixed on the reflector 1-4; the combination of the waveguide D and the waveguide E is used as one of the supports of the feed source 1-1, and the feed support A 1-2 is connected to the feed source, and the other end of the waveguide E 1-7 is fixed on the reflector 1-4; the combination of the waveguide D and the waveguide E is used as one of the supports of the feed source 1-1, and the feed support A 1-3 is connected to the reflector 1-4. 1-2. The feed support B1-3 forms a three-point support, and the feed is fixed and suspended in the center of the reflective surface, which can effectively reduce the volume of the feed and the associated waveguide, reduce the weight of the feed and the associated waveguide, and then reduce the weight of the feed support structure and the weight of the antenna assembly, thereby effectively reducing the load weight of the pointing drive mechanism and the unfolding device, providing a basis for reducing the weight of the pointing drive mechanism and the unfolding device, and laying a foundation for the overall weight reduction of the antenna system. In addition, waveguides D, E, feed support A and feed support B are all made of lightweight, low-scattering cross-section materials, and the support installation points are all at the edge of the reflective surface, which effectively reduces the impact of the support structure on the antenna performance. Among them, waveguide D1-6 can also adjust the RF port provided by the feed located on the non-center plane to the center plane through a double-bend structure, which facilitates the waveguide as a supporting structure and the connection with the waveguide assembly C. In specific implementation, the reflecting surface 1-4 is installed on the antenna bracket 1-5, and the feed source is suspended above the central axis of the reflecting surface through the three-point support formed by the waveguide D1-6, waveguide E1-7, feed support A1-2 and feed support B1-3, and the connection point between the three-point support and the reflecting surface is located at the edge of the reflecting surface and outside the electrical aperture.

[0033] The waveguide assembly C2 is used to connect the rotary joint C and the waveguide E in the antenna assembly, such as Figure 2 As shown, the waveguide assembly C 2 is obtained by connecting waveguide F 2-1, waveguide G 2-2, and waveguide H 2-3. The waveguide F realizes the transition of the feed waveguide caliber to the waveguide caliber of the rotating joint C by gradually changing the waveguide caliber. The waveguide G 2-2 adopts a compact orthogonal mode conversion waveguide to realize the transformation of the main mode direction of waveguide transmission, which reduces the demand of the twist waveguide on the waveguide length direction and reduces the envelope demand and performance loss caused by the waveguide twisting by the bending waveguide combination. The waveguide H 2-3 is connected to the rotating joint C, and the connection flange between it and the rotating joint C is fixed to the antenna bracket 1-5 through the fixed structure 2-3-1, and the displacement of the connection interface with the rotating joint C caused by the thermal matching stress between the waveguide assembly C and the two sets of parallel structures of the reflector-antenna bracket is reduced to a minimum. At the same time, the reasonable setting of the bending structure of the waveguide H 2-3 makes the distance between the waveguide assembly C and the reflector as small as possible, reduces the rotation envelope of the antenna assembly and the waveguide assembly C combination, and avoids rotation interference.

[0034] like Figure 3 As shown, the antenna assembly 1 is pressed by the pressing device B3 in the middle of the antenna bracket 1-5 to form the first pressing installation surface. The contact surface provided by the antenna bracket with the pressing device B3 makes the central axis of the antenna in the antenna assembly 1 form a certain angle a with the normal of the pressing installation surface, and the antenna system located at the highest point of the antenna assembly after pressing is reduced by a dimension d1. The distance d2 between the position of the first pressing installation surface and the lowest point of the edge of the antenna assembly is considered according to the conventional safety distance between structures.

[0035] The directional drive shaft B is connected to the antenna bracket and the rotary joint C, providing the rotation power of the antenna bracket around the axial direction of the directional drive shaft B and the power of the rotary joint C to follow the movement. The directional drive shaft B is composed of a support structure B and a drive shaft B. The antenna bracket is directly connected to the drive shaft B, and the rotary joint C is connected to the antenna bracket and the support structure B. The coaxiality of the two axes is ensured by integrally processing the rotary joint installation axis on the support structure B and the installation axis of the drive shaft B, thereby reducing the additional resistance distance caused by the rotary joint.

[0036] The directional drive shaft A is composed of a support structure A and a drive shaft A. The support structure B is directly connected to the drive shaft A, and the rotary joint B is connected to the support structure B and the support structure A. The rotary joint installation axis on the support structure A and the installation axis of the drive shaft A are processed in one piece to ensure the coaxiality of the two axes, thereby reducing the additional resistance distance caused by the rotary joint. The waveguide component B is used to connect the rotary joint B and the rotary joint C to form a complete radio frequency channel between the rotary joint B and the rotary joint C. The clamping device A clamps the support structure A of the directional drive shaft A at the connection between the directional drive shaft A and the unfolding device to form a second clamping installation surface.

[0037] When implementing it specifically, Figure 4 As shown, the rotating joint C4 is installed on the directional driving shaft B5 and is connected to the rotating joint B8 through the waveguide component B6. The rotating joint B8 is installed on the directional driving shaft A7. The clamping device A9 clamps the structure of the directional driving shaft A7 to form a second clamping installation surface.

[0038] like Figure 5As shown, the deployment device 11 is composed of a deployment drive shaft assembly 11-1, a deployment arm 11-2, a deployment support structure 11-3 and an equipment installation structure 11-4. The deployment support structure 11-3 provides a mounting support structure 11-3-1 for the deployment drive shaft assembly 11-1, a connecting structure 11-3-2 with the Mars rover and a mounting support structure 11-3-3 for the rotary joint A12. The deployment support structure provides a third mounting surface for forming an antenna system with the connection surface of the Mars rover. There is a certain height difference between the mounting surface and the first clamping mounting surface and the second clamping mounting surface. The height difference is determined by the height difference between the convex surface and the concave surface that the Mars rover can provide. The existence of this height difference makes the maximum additional envelope after the antenna is installed to be as small as the maximum height dimension of the deployment drive shaft assembly part, thereby greatly reducing the additional envelope and meeting the application requirements of the Mars rover. In addition to providing a fixed structure for the waveguide assembly A, the deployment arm also utilizes a position without antenna components or features to set up an equipment mounting structure 11-4. The equipment mounting structure 11-4 can provide equipment mounting space and interfaces of a certain size as needed for the installation of other payload equipment on the Mars rover. If necessary, an omnidirectional low-gain antenna can also be integrated and installed at this position.

[0039] like Figure 6 As shown, the unfolding support structure 11-3 provides a third mounting surface for the antenna system formed with the Mars rover connection structure 11-3-2. There is a certain height difference d3 between the mounting surface and the first and second compression mounting surfaces. The height difference d3 is determined by the height difference between the convex surface and the concave surface that the Mars rover can provide. The existence of this height difference allows the maximum additional envelope d4 after the antenna is installed to be as small as the maximum height dimension d5 of the unfolded drive shaft assembly part (i.e., d4≥d5), thereby greatly reducing the additional envelope and meeting the application requirements of the Mars rover. In this specific embodiment, d4=172.5, d3=161, and the additional envelope is reduced by 48.3% compared with the conventional installation. The final weight of the solution adopted in this implementation case is about 6kg, which is more than 40% lighter than the weight of the conventional solution (>10kg).

[0040] In summary, the above are only preferred embodiments of the present invention and are not intended to limit the protection scope of the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A movable spot beam antenna suitable for landing and patrol exploration on the surface of Mars, characterized in that: It comprises an antenna assembly (1), a waveguide assembly C (2), a clamping device B (3), a rotating joint C (4), a directional drive shaft B (5), a waveguide assembly B (6), a directional drive shaft A (7), a rotating joint B (8), a clamping device A (9), a waveguide assembly A (10), an unfolding device (11) and a rotating joint A (12); The antenna assembly (1) comprises a feed source (1-1), a feed source support A (1-2), a feed source support B (1-3), a reflective surface (1-4), an antenna support (1-5), a waveguide D (1-6) and a waveguide E (1-7), wherein the reflective surface (1-4) is mounted on the antenna support (1-5) via a clamping device B (3) to form a first clamping mounting surface; the waveguide D (1-6) and the waveguide E (1-7) are interconnected and serve as one of the feed source supports, and together with the feed source support A (1-2) and the feed source support B (1-3), the feed source (1-1) is suspended in the air at the center of the reflective surface; The antenna bracket (1-5) is connected to the directional drive shaft B (5) via a rotary joint C (4), and the directional drive shaft B is connected to the directional drive shaft A via a rotary joint B (8); the directional drive shaft A (7) is installed on the deployment device (11) via a clamping device A (9) to form a second clamping installation surface; the deployment device (11) and the rotary joint A (12) are installed on the Mars rover; One end of the waveguide component C (2) is fixed on the antenna bracket (1-5) and connected to the rotating joint C (4), and the other end is connected to the waveguide E (1-7) with a variable waveguide aperture; the waveguide component B (6) is connected to the rotating joint B (8) and the rotating joint C (4); the waveguide component A (10) is connected to the rotating joint B (8) and the rotating joint A (12); The waveguide component C (2) is obtained by connecting a waveguide F (2-1), a waveguide G (2-2), and a waveguide H (2-3), wherein the waveguide F (2-1) is connected to the waveguide E (1-7), and the caliber thereof gradually changes to the waveguide caliber of the rotating joint C; the waveguide G (2-2) adopts a compact orthogonal mode conversion waveguide; one end of the waveguide H (2-3) is connected to the rotating joint C and fixed on the antenna bracket (1-5).

2. The antenna according to claim 1, characterized in that The waveguide D (1-6) adopts a double-bend structure.

3. The antenna according to claim 1 or 2, characterized in that: The installation points of the waveguide E (1-7), feed support A (1-2) and feed support B (1-3) on the reflecting surface are located at the edge of the reflecting surface and outside the electrical aperture.

4. The antenna according to claim 1, characterized in that The waveguide H(2-3) is bent so that the distance between the waveguide component C and the reflecting surface is as small as possible.

5. The antenna according to claim 1, wherein: The installation axis of the rotary joint C (4) on the drive shaft B is coaxial with the drive shaft installation axis pointing to the drive shaft B; the installation axis of the rotary joint B (8) on the drive shaft A is coaxial with the drive shaft installation axis pointing to the drive shaft A.

6. The antenna according to claim 1, characterized in that The deployment device is provided with a mounting structure (11-4) for mounting other payload equipment, including another set of antennas.

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