CN112394501B - Satellite-borne flexible radio frequency laser integrated communication antenna - Google Patents
Satellite-borne flexible radio frequency laser integrated communication antenna Download PDFInfo
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- CN112394501B CN112394501B CN202011213950.4A CN202011213950A CN112394501B CN 112394501 B CN112394501 B CN 112394501B CN 202011213950 A CN202011213950 A CN 202011213950A CN 112394501 B CN112394501 B CN 112394501B
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- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B17/00—Systems with reflecting surfaces, with or without refracting elements
- G02B17/02—Catoptric systems, e.g. image erecting and reversing system
- G02B17/06—Catoptric systems, e.g. image erecting and reversing system using mirrors only, i.e. having only one curved mirror
- G02B17/0668—Catoptric systems, e.g. image erecting and reversing system using mirrors only, i.e. having only one curved mirror having non-imaging properties
- G02B17/0673—Catoptric systems, e.g. image erecting and reversing system using mirrors only, i.e. having only one curved mirror having non-imaging properties for light condensing, e.g. for use with a light emitter
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- G02B5/00—Optical elements other than lenses
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- G02B5/10—Mirrors with curved faces
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- G—PHYSICS
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- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B7/00—Mountings, adjusting means, or light-tight connections, for optical elements
- G02B7/18—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors
- G02B7/182—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors for mirrors
- G02B7/183—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors for mirrors specially adapted for very large mirrors, e.g. for astronomy, or solar concentrators
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Abstract
The invention provides a satellite-borne flexible radio-frequency laser integrated communication antenna which comprises a hollow radio-frequency reflecting system, a radio-frequency laser main mirror system arranged in the hollow part of the radio-frequency reflecting system, a radio-frequency laser secondary mirror system arranged above the radio-frequency laser main mirror system, a radio-frequency laser path separating mirror arranged at the rear part of the radio-frequency laser main mirror system and used for separating radio frequency and laser, a fixing system used for unfolding and tightening the radio-frequency reflecting system, a radio-frequency feed source and a laser receiving and transmitting unit, wherein the radio-frequency feed source and the laser receiving and transmitting unit are arranged on two sides of the radio-frequency laser path separating mirror. The invention aims to solve the problem of a satellite-borne radio-frequency laser integrated communication antenna, provides a satellite-borne flexible radio-frequency laser integrated communication antenna aiming at the integrated communication requirements of satellites, deep space radio frequency and lasers, and has the characteristics of compact structure, deployable performance, small volume, light weight, high reliability, high laser radio-frequency transmission efficiency and the like while realizing the integrated transmission and reception of radio frequency and lasers.
Description
Technical Field
The invention relates to the technical field of communication, in particular to a satellite-borne flexible radio-frequency laser integrated communication antenna.
Background
With the development of diversification of space and deep space exploration tasks, application requirements of high speed, light weight, miniaturization, integration and integration are provided for satellite and deep space communication loads. For satellite and deep space communication applications, although radio frequency communication is difficult to meet the requirement of future deep space exploration tasks on high-speed data return, the reliability and the communication rate of a radio frequency communication link are high, so that the radio frequency communication is still a main communication means for satellite and deep space exploration. The laser communication has the characteristics of high communication rate, strong directivity, small load volume, light weight, low power consumption and the like, can meet the requirements of future satellite and deep space exploration activities on high-speed communication, ultra-long distance transmission and the like, and has good application prospect in the fields of future satellite and deep space exploration. The high reliability and high speed application requirements of the satellite and deep space communication link are considered, and it is expected that the satellite, deep space radio frequency communication and laser communication will complement each other and be developed in a fusion manner in the future.
The requirement of integration and integration of the communication load by the satellite and the deep space flight platform is more obvious due to the limitation of space carrying conditions, so that the carrying resource requirement of the communication load on the flight platform is further reduced. Therefore, the integration of the radio frequency communication load and the laser communication load into an integrated communication load becomes an effective solution for improving the reliability of the satellite and the deep space communication link, improving the compatibility of the satellite and the deep space communication system, improving the quality of the satellite and the deep space communication, and saving the resources of the satellite and the deep space flight platform. In a satellite and deep space radio frequency and laser integrated communication system, the design of a radio frequency and laser integrated antenna is very important.
In the prior art, chinese patent publication No. CN106571511A, filed on 2016, 11, 15, 2016, describes a lightweight foldable radio frequency and laser hybrid film communication antenna. The technology realizes the design of a common antenna for radio frequency and laser. However, the feed source of the antenna is placed at the focal position of the radio frequency main reflecting surface, namely the back surface of the secondary mirror of the optical antenna, and the structure of the feed source device additionally increases the loss caused by the central blocking of the optical system, so that the utilization rate of the optical antenna is reduced. Meanwhile, the folding and unfolding states of the radio frequency reflecting surface are realized through the sliding of the connecting rods on the connecting shafts, the seven connecting rods not only increase the overall quality of the antenna, but also reduce the reliability of the antenna in a mode of connecting the supporting ribs and the connecting shafts through the connecting rods, and the satellite-borne radio frequency reflecting surface is not beneficial to satellite-borne application. In the prior art, a coaxial conformal antenna for laser/millimeter wave composite communication is introduced in a chinese patent with publication number CN108565559A, which is applied in 2018, 4, month and 11. Although the technology realizes the design of a common antenna of radio frequency and laser, the laser/millimeter wave common primary mirror is made of microcrystalline materials, cannot be folded or furled, cannot simultaneously meet the requirements of small envelope and large-caliber gain of satellite-borne communication during rocket carrying, and is not suitable for satellite-borne application. In the prior art, a coaxial deployable antenna for laser microwave composite communication is introduced in chinese patent publication No. CN110445545A, which is applied in 5/2/2018. The feed source of the technology is also placed at the focal position of the radio frequency main reflecting surface, the structure of the feed source device increases the loss caused by the central blocking of the optical system, and the secondary mirror support frame adopts a truss structure, so that the utilization rate of the optical antenna can be additionally and greatly reduced. Therefore, the prior art does not thoroughly solve the problem of the satellite-borne radio frequency laser integrated communication antenna.
Disclosure of Invention
The invention aims to solve the problem of a satellite-borne radio-frequency laser integrated communication antenna, provides a satellite-borne flexible radio-frequency laser integrated communication antenna aiming at the integrated communication requirements of satellites, deep space radio frequency and lasers, and has the characteristics of compact structure, deployable performance, small volume, light weight, high reliability, high laser radio-frequency transmission efficiency and the like while realizing the integrated transmission and reception of radio frequency and lasers.
The invention provides a satellite-borne flexible radio-frequency laser integrated communication antenna which comprises a hollow radio-frequency reflecting system, a radio-frequency laser main mirror system arranged in the hollow part of the radio-frequency reflecting system, a radio-frequency laser secondary mirror system arranged above the radio-frequency laser main mirror system, a radio-frequency laser path separating mirror arranged at the rear part of the radio-frequency laser main mirror system and used for separating radio frequency and laser, and a fixing system connected with the radio-frequency reflecting system and used for unfolding and tightening the radio-frequency reflecting system;
the radio frequency reflection system comprises a flexible radio frequency main reflection surface and a back support rib which is arranged on the back of the flexible radio frequency main reflection surface and plays a supporting role;
the primary mirror system comprises a primary mirror chamber and a radio frequency laser multiplexing primary mirror fixed on the upper part of the primary mirror chamber;
the radio frequency laser secondary mirror system comprises a secondary mirror support frame, a secondary mirror fixing structure and a radio frequency laser shared secondary mirror, wherein the secondary mirror support frame is fixed at the upper end of the primary mirror chamber and used for controlling the distance between the primary mirror system and the radio frequency laser secondary mirror system;
the fixing system comprises a locking rope structure fixed on the outer edge of the flexible radio frequency main reflecting surface and used for tightening the flexible radio frequency main reflecting surface, and a supporting rib locking structure fixed at the joint of the flexible radio frequency main reflecting surface and the main mirror chamber and used for locking the flexible radio frequency main reflecting surface in an unfolded state.
The satellite-borne flexible radio-frequency laser integrated communication antenna further comprises a radio-frequency feed source and a laser receiving and transmitting unit which are arranged on two sides of the radio-frequency laser path separating mirror as an optimal mode.
The satellite-borne flexible radio-frequency laser integrated communication antenna is characterized in that as an optimal mode, a flexible radio-frequency main reflecting surface is of a metal mesh structure capable of being unfolded and tightened; the flexible radio frequency main reflecting surface is fixed with the back support rib in a bonding way; the back support rib is high-modulus carbon fiber with a variable cross-section hollow beam structure.
The invention relates to a satellite-borne flexible radio-frequency laser integrated communication antenna, which is characterized in that as an optimal mode, a radio-frequency laser multiplexing primary mirror is a paraboloid which is consistent with a curved surface of a radio-frequency reflecting system in an unfolding state, a radio-frequency laser sharing secondary mirror is a hyperboloid, and the radio-frequency laser multiplexing primary mirror and the radio-frequency laser sharing secondary mirror are all optical glass with metal films and dielectric films sequentially plated on the surfaces; the radio frequency laser path separating mirror is optical glass with a high-reflectivity dielectric film plated on the surface.
The invention relates to a satellite-borne flexible radio-frequency laser integrated communication antenna, which is characterized in that as a preferred mode, a main mirror chamber is a round shape, the outer ring of the main mirror chamber is provided with at least one group of fixing rings for fixing the bottom ends of back support ribs, and the upper end of each fixing ring is provided with a hole site for connecting a secondary mirror support frame.
The satellite-borne flexible radio-frequency laser integrated communication antenna is an optimal mode, and the number of the fixing rings is 8-12.
According to the satellite-borne flexible radio-frequency laser integrated communication antenna, as an optimal mode, a secondary mirror support frame is of a four-wing beam structure, and is made of invar steel;
and the secondary mirror fixing structure is provided with a fine adjustment device for fine adjustment of the position of the radio-frequency laser shared secondary mirror.
The invention relates to a satellite-borne flexible radio-frequency laser integrated communication antenna, which is characterized in that a locking rope structure comprises rope connecting holes fixed on two sides of the outer edge of the back of a back supporting rib, a damper arranged in the rope connecting holes and a locking rope corresponding to the rope connecting holes in shape and size.
According to the satellite-borne flexible radio-frequency laser integrated communication antenna, as a preferable mode, a cutting device for self-unlocking of the integrated communication antenna is further arranged on the outer edge of the back support rib.
According to the satellite-borne flexible radio-frequency laser integrated communication antenna, as a preferred mode, the support rib locking structure is an annular locking hinge.
And in the rocket launching stage, the satellite-borne flexible radio-frequency laser integrated communication antenna is in a furled state. At the moment, the flexible radio frequency main reflecting surface is connected with the back support rib in a gluing mode, and the locking rope structure and a connecting port at the upper end of the back support rib are in a tightened state.
And in the on-orbit working stage, the satellite-borne flexible radio frequency laser integrated communication antenna is in an unfolded state. And the control of the unfolding speed is realized by controlling the damping. After the flexible radio frequency reflecting surface is unfolded, the back supporting rib is in a flat state and is locked with the main mirror chamber through the supporting rib locking structure, so that the flexible radio frequency reflecting surface is completely matched with the surface shape of the radio frequency laser multiplexing main mirror, and a full-caliber radio frequency main reflecting surface is formed. When radio frequency signals pass through the antenna, the radio frequency signals can completely enter the radio frequency laser shared secondary mirror through the full-caliber main reflecting surface; in a similar way, the laser signal can enter the radio frequency laser shared secondary mirror through the radio frequency laser multiplexing primary mirror. The laser and the radio frequency signal are reflected by the radio frequency laser shared secondary mirror and pass through a central hole of the radio frequency laser multiplexing primary mirror, the rear end is provided with a radio frequency laser path separating mirror, the radio frequency signal and the laser signal are separated and respectively enter respective rear end signal processing systems, namely a radio frequency feed source and a laser receiving and transmitting unit.
The radio frequency laser shared main mirror is fixed on the main mirror chamber, wherein the radio frequency laser multiplexed main mirror is matched with parameters such as curvature of the flexible radio frequency main reflecting surface in an unfolded state, so that an incident radio frequency signal is reflected and then enters the radio frequency laser path separating mirror, and the incident radio frequency signal is reflected by the radio frequency laser path separating mirror and then enters the communication receiving system.
The bottom end of the secondary mirror support frame is fixed at the upper end of the primary mirror chamber; the radio frequency laser shared secondary mirror is fixed at the top end of the secondary mirror support frame. The secondary mirror support frame mainly plays a role in controlling the distance between the primary mirror and the secondary mirror and fixing the radio-frequency laser shared secondary mirror.
The back support rib is of a hollow structure from thin to thick, is made of high-modulus carbon fiber, improves the rigidity of the structure, has the advantages of small thermal expansion coefficient, fatigue resistance, simple forming process and the like, and is suitable for the design requirement of long service life.
The surface shape of the radio frequency laser multiplexing main mirror is matched with the flexible radio frequency main reflecting surface, the materials are optical glass metal coating films and dielectric films, high reflection of radio frequency and laser can be achieved, and the transmission efficiency of the antenna is improved.
The secondary mirror support frame is made of invar steel and is characterized by small linear expansion coefficient, small deformation along with temperature change, capability of ensuring the center distance of the primary mirror and the secondary mirror and enhancing the stability of the antenna in an environment with large temperature difference change.
The secondary mirror fixing structure is provided with a 'one-top three-pull' fine adjustment device for installation and adjustment of the secondary mirror, so that errors such as off-axis, inclination, deviation and the like do not occur between the secondary mirror and the primary mirror.
The radio frequency laser path separating mirror has the functions of high-efficiency radio frequency transmission and high-efficiency laser reflection, so that the radio frequency and the laser path are separated.
The invention has the following advantages:
(1) the invention adopts the radio frequency and laser to share the secondary mirror and the main feed structure, and the secondary mirror support adopts the four-wing beam structure, thereby effectively reducing the optical loss caused by the feed-forward structure and the truss structure and improving the optical transmission efficiency.
(2) The invention adopts the mode of fixing the radio frequency main reflecting surface by adopting the modes of the hollow back supporting rib, the supporting rib locking structure and the locking rope structure, thereby not only reducing the weight of the antenna, but also increasing the reliability of the radio frequency antenna in the unfolding state.
(3) The invention adopts the flexible radio frequency main reflecting surface with the metal net structure to support two states of contraction and expansion, and ensures that the whole machine has compact structure and light weight while realizing high reflectivity.
(4) The invention adopts the design of a laser radio frequency common reflection surface high reflection film system, realizes the simultaneous high reflection of radio frequency and laser by the way of sequentially plating a metal film and a dielectric film on the surface of optical glass, and greatly improves the transmission efficiency of the antenna.
Drawings
Fig. 1 is a schematic view of a folded state of a satellite-borne flexible radio-frequency laser integrated communication antenna in an embodiment 1;
fig. 2 is a schematic view of a satellite-borne flexible radio-frequency laser integrated communication antenna in an unfolded state in embodiment 1.
FIG. 3 is a schematic view of a folded state of an embodiment 2-6 of a satellite-borne flexible radio frequency laser integrated communication antenna;
fig. 4 is a schematic view of the unfolding state of an embodiment 2-6 of a satellite-borne flexible radio-frequency laser integrated communication antenna.
Reference numerals:
1. a radio frequency reflection system; 11. a flexible radio frequency main reflecting surface; 12. a back support rib; 2. a radio frequency laser primary mirror system; 21. a main mirror chamber; 22. a radio frequency laser multiplexing primary mirror; 3. a radio frequency laser secondary mirror system; 31. a secondary mirror support frame; 32. a secondary mirror fixing structure; 33. the radio frequency laser shares the secondary mirror; 4. a radio frequency laser path separating mirror; 5. a fixation system; 51. locking the cord structure; 52. a support rib locking structure; 6. a radio frequency feed source; 7. a laser transceiver unit.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.
Example 1
As shown in fig. 1-2, a satellite-borne flexible rf laser integrated communication antenna includes a hollow rf reflection system 1, a rf laser primary mirror system 2 disposed in the hollow of the rf reflection system 1, a rf laser secondary mirror system 3 disposed above the rf laser primary mirror system 2, a rf laser path splitter 4 disposed at the rear of the rf laser primary mirror system 2 for splitting rf and laser, and a fixing system 5 connected to the rf reflection system 1 for spreading and tightening the rf reflection system 1;
the radio frequency reflection system 1 comprises a flexible radio frequency main reflection surface 11 and a back support rib 12 which is arranged on the back of the flexible radio frequency main reflection surface 11 and plays a supporting role;
the primary mirror system 2 comprises a primary mirror chamber 21 and a radio frequency laser multiplexing primary mirror 22 fixed on the upper part of the primary mirror chamber 21;
the radio frequency laser secondary mirror system 3 comprises a secondary mirror support frame 31 fixed at the upper end of the primary mirror chamber 21 and used for controlling the distance between the primary mirror system 2 and the radio frequency laser secondary mirror system 3, a secondary mirror fixing structure 32 fixed at the top of the secondary mirror support frame 31 and a radio frequency laser shared secondary mirror 33 fixed at the lower part of the secondary mirror fixing structure 32;
the fixing system 5 comprises a locking rope structure 51 fixed on the outer edge of the flexible radio frequency main reflecting surface 11 for tightening the flexible radio frequency main reflecting surface 11 and a supporting rib locking structure 52 fixed at the joint of the flexible radio frequency main reflecting surface 11 and the main mirror chamber 21 for locking the flexible radio frequency main reflecting surface 11 in the unfolding state.
Example 2
As shown in fig. 3-4, a satellite-borne flexible radio-frequency laser integrated communication antenna comprises a hollow radio-frequency reflecting system 1, a radio-frequency laser primary mirror system 2 arranged in the hollow of the radio-frequency reflecting system 1, a radio-frequency laser secondary mirror system 3 arranged above the radio-frequency laser primary mirror system 2, a radio-frequency laser path separating mirror 4 arranged at the rear part of the radio-frequency laser primary mirror system 2 and used for separating radio frequency and laser, a fixing system 5 connected with the radio-frequency reflecting system 1 and used for unfolding and tightening the radio-frequency reflecting system 1, a radio-frequency feed source 6 and a laser transceiving unit 7 arranged at two sides of the radio-frequency laser path separating mirror 4;
the radio frequency reflection system 1 comprises a flexible radio frequency main reflection surface 11 and a back support rib 12 which is arranged on the back of the flexible radio frequency main reflection surface 11 and plays a supporting role;
the primary mirror system 2 comprises a primary mirror chamber 21 and a radio frequency laser multiplexing primary mirror 22 fixed on the upper part of the primary mirror chamber 21;
the radio frequency laser secondary mirror system 3 comprises a secondary mirror support frame 31 fixed at the upper end of the primary mirror chamber 21 and used for controlling the distance between the primary mirror system 2 and the radio frequency laser secondary mirror system 3, a secondary mirror fixing structure 32 fixed at the top of the secondary mirror support frame 31 and a radio frequency laser shared secondary mirror 33 fixed at the lower part of the secondary mirror fixing structure 32;
the fixing system 5 comprises a locking rope structure 51 fixed on the outer edge of the flexible radio frequency main reflecting surface 11 for tightening the flexible radio frequency main reflecting surface 11 and a supporting rib locking structure 52 fixed at the joint of the flexible radio frequency main reflecting surface 11 and the main mirror chamber 21 for locking the flexible radio frequency main reflecting surface 11 in the unfolding state.
Example 3
As shown in fig. 3-4, a satellite-borne flexible radio-frequency laser integrated communication antenna comprises a hollow radio-frequency reflecting system 1, a radio-frequency laser primary mirror system 2 arranged in the hollow of the radio-frequency reflecting system 1, a radio-frequency laser secondary mirror system 3 arranged above the radio-frequency laser primary mirror system 2, a radio-frequency laser path separating mirror 4 arranged at the rear part of the radio-frequency laser primary mirror system 2 and used for separating radio frequency and laser, a fixing system 5 connected with the radio-frequency reflecting system 1 and used for unfolding and tightening the radio-frequency reflecting system 1, a radio-frequency feed source 6 and a laser transceiving unit 7 arranged at two sides of the radio-frequency laser path separating mirror 4;
the radio frequency reflection system 1 comprises a flexible radio frequency main reflection surface 11 and a back support rib 12 which is arranged on the back of the flexible radio frequency main reflection surface 11 and plays a supporting role; the flexible radio frequency main reflecting surface 11 is a metal net structure which can be unfolded and tightened; the flexible radio frequency main reflecting surface 11 is fixed with the back support rib 12 by gluing; the back support rib 12 is high modulus carbon fiber with a variable cross-section hollow beam structure;
the primary mirror system 2 comprises a primary mirror chamber 21 and a radio frequency laser multiplexing primary mirror 22 fixed on the upper part of the primary mirror chamber 21; the radio frequency laser multiplexing primary mirror 22 is a paraboloid which is consistent with the curved surface of the radio frequency reflecting system 1 in the unfolding state, the radio frequency laser sharing secondary mirror 33 is a hyperboloid, and the radio frequency laser multiplexing primary mirror 22 and the radio frequency laser sharing secondary mirror 33 are all optical glass with metal films and dielectric films sequentially plated on the surfaces; the radio frequency laser path separating mirror 4 is optical glass with a high-reflectivity dielectric film plated on the surface; the main mirror chamber 23 is a round shape with at least one group of fixing rings for fixing the bottom ends of the back support ribs 12 arranged on the outer ring, and the upper ends of the fixing rings are provided with hole sites for connecting the secondary mirror support frames 31;
the radio frequency laser secondary mirror system 3 comprises a secondary mirror support frame 31 fixed at the upper end of the primary mirror chamber 21 and used for controlling the distance between the primary mirror system 2 and the radio frequency laser secondary mirror system 3, a secondary mirror fixing structure 32 fixed at the top of the secondary mirror support frame 31 and a radio frequency laser shared secondary mirror 33 fixed at the lower part of the secondary mirror fixing structure 32; the secondary mirror support 31 is of a four-wing beam structure, and the secondary mirror support 31 is made of invar steel;
the fixing system 5 comprises a locking rope structure 51 fixed on the outer edge of the flexible radio frequency main reflecting surface 11 for tightening the flexible radio frequency main reflecting surface 11 and a supporting rib locking structure 52 fixed at the joint of the flexible radio frequency main reflecting surface 11 and the main mirror chamber 21 for locking the flexible radio frequency main reflecting surface 11 in the unfolding state.
Example 4
As shown in fig. 3-4, a satellite-borne flexible radio-frequency laser integrated communication antenna comprises a hollow radio-frequency reflecting system 1, a radio-frequency laser primary mirror system 2 arranged in the hollow of the radio-frequency reflecting system 1, a radio-frequency laser secondary mirror system 3 arranged above the radio-frequency laser primary mirror system 2, a radio-frequency laser path separating mirror 4 arranged at the rear part of the radio-frequency laser primary mirror system 2 and used for separating radio frequency and laser, a fixing system 5 connected with the radio-frequency reflecting system 1 and used for unfolding and tightening the radio-frequency reflecting system 1, a radio-frequency feed source 6 and a laser transceiving unit 7 arranged at two sides of the radio-frequency laser path separating mirror 4;
the radio frequency reflection system 1 comprises a flexible radio frequency main reflection surface 11 and a back support rib 12 which is arranged on the back of the flexible radio frequency main reflection surface 11 and plays a supporting role; the flexible radio frequency main reflecting surface 11 is a metal net structure which can be unfolded and tightened; the flexible radio frequency main reflecting surface 11 is fixed with the back support rib 12 by gluing; the back support rib 12 is high modulus carbon fiber with a variable cross-section hollow beam structure;
the primary mirror system 2 comprises a primary mirror chamber 21 and a radio frequency laser multiplexing primary mirror 22 fixed on the upper part of the primary mirror chamber 21; the radio frequency laser multiplexing primary mirror 22 is a paraboloid which is consistent with the curved surface of the radio frequency reflecting system 1 in the unfolding state, the radio frequency laser sharing secondary mirror 33 is a hyperboloid, and the radio frequency laser multiplexing primary mirror 22 and the radio frequency laser sharing secondary mirror 33 are all optical glass with metal films and dielectric films sequentially plated on the surfaces; the radio frequency laser path separating mirror 4 is optical glass with a high-reflectivity dielectric film plated on the surface; the main mirror chamber 23 is a round shape with at least one group of fixing rings for fixing the bottom ends of the back support ribs 12 arranged on the outer ring, and the upper ends of the fixing rings are provided with hole sites for connecting the secondary mirror support frames 31; the number of the fixing rings is 8-12;
the radio frequency laser secondary mirror system 3 comprises a secondary mirror support frame 31 fixed at the upper end of the primary mirror chamber 21 and used for controlling the distance between the primary mirror system 2 and the radio frequency laser secondary mirror system 3, a secondary mirror fixing structure 32 fixed at the top of the secondary mirror support frame 31 and a radio frequency laser shared secondary mirror 33 fixed at the lower part of the secondary mirror fixing structure 32; the secondary mirror support 31 is of a four-wing beam structure, and the secondary mirror support 31 is made of invar;
the fixing system 5 comprises a locking rope structure 51 fixed on the outer edge of the flexible radio frequency main reflecting surface 11 for tightening the flexible radio frequency main reflecting surface 11 and a supporting rib locking structure 52 fixed at the joint of the flexible radio frequency main reflecting surface 11 and the main mirror chamber 21 for locking the flexible radio frequency main reflecting surface 11 in the unfolding state.
Example 5
As shown in fig. 3-4, a satellite-borne flexible radio-frequency laser integrated communication antenna comprises a hollow radio-frequency reflecting system 1, a radio-frequency laser primary mirror system 2 arranged in the hollow of the radio-frequency reflecting system 1, a radio-frequency laser secondary mirror system 3 arranged above the radio-frequency laser primary mirror system 2, a radio-frequency laser path separating mirror 4 arranged at the rear part of the radio-frequency laser primary mirror system 2 and used for separating radio frequency and laser, a fixing system 5 connected with the radio-frequency reflecting system 1 and used for unfolding and tightening the radio-frequency reflecting system 1, a radio-frequency feed source 6 and a laser transceiving unit 7 arranged at two sides of the radio-frequency laser path separating mirror 4;
the radio frequency reflection system 1 comprises a flexible radio frequency main reflection surface 11 and a back support rib 12 which is arranged on the back of the flexible radio frequency main reflection surface 11 and plays a supporting role; the flexible radio frequency main reflecting surface 11 is a metal net structure which can be unfolded and tightened; the flexible radio frequency main reflecting surface 11 is fixed with the back support rib 12 by gluing; the back support rib 12 is high modulus carbon fiber with a variable cross-section hollow beam structure;
the primary mirror system 2 comprises a primary mirror chamber 21 and a radio frequency laser multiplexing primary mirror 22 fixed on the upper part of the primary mirror chamber 21; the radio frequency laser multiplexing primary mirror 22 is a paraboloid which is consistent with the curved surface of the radio frequency reflecting system 1 in the unfolding state, the radio frequency laser sharing secondary mirror 33 is a hyperboloid, and the radio frequency laser multiplexing primary mirror 22 and the radio frequency laser sharing secondary mirror 33 are all optical glass with metal films and dielectric films sequentially plated on the surfaces; the radio frequency laser path separating mirror 4 is optical glass with a high-reflectivity dielectric film plated on the surface; the main mirror chamber 23 is a round shape with at least one group of fixing rings for fixing the bottom ends of the back support ribs 12 arranged on the outer ring, and the upper ends of the fixing rings are provided with hole sites for connecting the secondary mirror support frames 31;
the radio frequency laser secondary mirror system 3 comprises a secondary mirror support frame 31 fixed at the upper end of the primary mirror chamber 21 and used for controlling the distance between the primary mirror system 2 and the radio frequency laser secondary mirror system 3, a secondary mirror fixing structure 32 fixed at the top of the secondary mirror support frame 31 and a radio frequency laser shared secondary mirror 33 fixed at the lower part of the secondary mirror fixing structure 32; the secondary mirror support 31 is of a four-wing beam structure, and the secondary mirror support 31 is made of invar steel; a fine adjustment device for fine adjustment of the position of the radio-frequency laser shared secondary mirror 33 is arranged on the secondary mirror fixing structure 32;
the fixing system 5 comprises a locking rope structure 51 fixed on the outer edge of the flexible radio frequency main reflecting surface 11 for tightening the flexible radio frequency main reflecting surface 11 and a supporting rib locking structure 52 fixed at the joint of the flexible radio frequency main reflecting surface 11 and the main mirror chamber 21 for locking the flexible radio frequency main reflecting surface 11 in an unfolded state; the locking rope structure 51 includes rope coupling holes fixed to both sides of the outer edge of the back support rib 12, dampers disposed inside the rope coupling holes, and locking ropes having shapes and sizes corresponding to the rope coupling holes; a cutting device for self-unlocking of the integrated communication antenna is further arranged on the outer edge of the back support rib 12; the support rib locking structure 52 is an annular locking hinge.
Example 6
As shown in fig. 3-4, a satellite-borne flexible rf laser integrated communication antenna, wherein the rf band is Ka band and the laser band is 1550nm band;
the basic structure of this embodiment is the same as that of embodiment 5, specifically, the flexible radio frequency main reflecting surface 11 is a gold wire mesh structure; the back support rib 12 adopts a variable cross-section hollow beam type structure, and is made of high-modulus carbon fibers, and the number of the back support ribs is 12;
the main mirror chamber 21 is of a circular structure, the outer ring is provided with N groups of fixing rings, and the upper end of the main mirror chamber is provided with a hole site for connecting the secondary mirror support frame 31; the radio frequency laser multiplexing primary mirror 22 adopts a paraboloid structure and is made of a microcrystalline surface sequentially plated with aluminum film and titanium dioxide/silicon dioxide (TiO)2/SiO2) A dielectric film, wherein the reflectivity of the aluminum film to Ka is more than or equal to 96 percent, and TiO2/SiO2The reflectivity of the dielectric film to 1550nm is more than or equal to 98 percent;
the lower end of the secondary mirror support frame 31 is of a circular structure and is provided with a hole site connected with the main mirror chamber 21, the upper end is provided with an outer circular ring which is connected with an inner circular ring through a four-beam structure, and the inner circular ring is provided with a hole site connected with a secondary mirror fixing structure 32; the secondary mirror fixing structure 32 is a circular structure, the outer ring is provided with a hole site connected with the secondary mirror support frame 31, and the inside is provided with a structure for fixing the radio frequency laser shared secondary mirror 33 and a one-top-three-pull fine adjustment device; the radio frequency laser shared secondary mirror 33 adopts a hyperboloid structure, and the material of the hyperboloid structure is the same as that of the radio frequency laser multiplexing primary mirror 22;
the locking rope is made of high-strength aramid fiber; the rope connecting hole is made of high-modulus carbon fiber; the damper is made of aluminum alloy;
the radio frequency laser path separating mirror 4 is coated with titanium dioxide/silicon dioxide (TiO)2/SiO2) The microcrystalline glass of the dielectric film has Ka transmittance of not less than 90 percent and TiO2/SiO2The reflectivity of the dielectric film to 1550nm is more than or equal to 98 percent.
The method of use of examples 1-6 is:
and in the rocket launching stage, the satellite-borne flexible radio-frequency laser integrated communication antenna is in a furled state. At this time, the flexible rf main reflective surface 11 and the back support rib 12 are connected by gluing, and the locking rope structure 51 and the connection port at the upper end of the back support rib 12 are in a tightened state.
And in the on-orbit working stage, the satellite-borne flexible radio-frequency laser integrated communication antenna is in an unfolded state. At this time, the back support rib 12 is in a flat state, and the support rib locking structure 52 locks the fixed end of the back support rib 12 to the side of the main mirror chamber 21, so that the flexible rf main reflecting surface 11 is in a stable working state.
The radio frequency laser shared main mirror 22 is fixed on the main mirror chamber 21, wherein the radio frequency laser multiplexed main mirror 22 is matched with parameters such as curvature of the flexible radio frequency main reflecting surface 11 in an unfolded state, so that an incident radio frequency signal is reflected and then enters the radio frequency laser path separating mirror 4, and enters a communication receiving system, namely a radio frequency feed source 6 and a laser receiving and transmitting unit 7 after being reflected by the radio frequency laser path separating mirror 4.
The bottom end of the secondary mirror support frame 31 is fixed at the upper end of the primary mirror chamber 21; the radio frequency laser shared secondary mirror 33 is fixed at the top end of the secondary mirror support frame 31. The secondary mirror support frame 31 mainly plays a role in controlling the distance between the primary mirror and the secondary mirror and fixing the radio frequency laser shared secondary mirror 33.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.
Claims (10)
1. The utility model provides a flexible radio frequency laser integration communication antenna of satellite-borne which characterized in that: the radio frequency laser device comprises a hollow radio frequency reflecting system (1), a radio frequency laser primary mirror system (2) arranged in the hollow part of the radio frequency reflecting system (1), a radio frequency laser secondary mirror system (3) arranged above the radio frequency laser primary mirror system (2), a radio frequency laser path separating mirror (4) arranged at the rear part of the radio frequency laser primary mirror system (2) and used for separating radio frequency and laser, and a fixing system (5) connected with the radio frequency reflecting system (1) and used for unfolding and tightening the radio frequency reflecting system (1);
the radio frequency reflection system (1) comprises a flexible radio frequency main reflection surface (11) and a back support rib (12) which is arranged on the back of the flexible radio frequency main reflection surface (11) and plays a supporting role;
the primary mirror system (2) comprises a primary mirror chamber (21) and a radio frequency laser multiplexing primary mirror (22) fixed on the upper part of the primary mirror chamber (21);
the radio frequency laser secondary mirror system (3) comprises a secondary mirror support frame (31) fixed at the upper end of the primary mirror chamber (21) and used for controlling the distance between the primary mirror system (2) and the radio frequency laser secondary mirror system (3), a secondary mirror fixing structure (32) fixed at the top of the secondary mirror support frame (31) and a radio frequency laser shared secondary mirror (33) fixed at the lower part of the secondary mirror fixing structure (32);
the fixing system (5) comprises a locking rope structure (51) fixed on the outer edge of the flexible radio frequency main reflecting surface (11) and used for tightening the flexible radio frequency main reflecting surface (11), and a supporting rib locking structure (52) fixed at the joint of the flexible radio frequency main reflecting surface (11) and the main mirror chamber (21) and used for locking the flexible radio frequency main reflecting surface (11) in an unfolded state.
2. The satellite-borne flexible radio-frequency laser integrated communication antenna according to claim 1, characterized in that: the radio frequency laser path splitting mirror also comprises a radio frequency feed source (6) and a laser transceiving unit (7) which are arranged on two sides of the radio frequency laser path splitting mirror (4).
3. The satellite-borne flexible radio frequency laser integrated communication antenna according to claim 1, characterized in that: the flexible radio frequency main reflecting surface (11) is a metal net structure which can be unfolded and tightened; the flexible radio frequency main reflecting surface (11) is fixedly bonded with the back support rib (12); the back support rib (12) is high-modulus carbon fiber with a variable cross-section hollow beam structure.
4. The satellite-borne flexible radio frequency laser integrated communication antenna according to any one of claims 1 to 3, characterized in that: the radio frequency laser multiplexing primary mirror (22) is a paraboloid which is consistent with the curved surface of the radio frequency reflecting system (1) in the unfolding state, the radio frequency laser sharing secondary mirror (33) is a hyperboloid, and the radio frequency laser multiplexing primary mirror (22) and the radio frequency laser sharing secondary mirror (33) are all optical glass with metal films and dielectric films sequentially plated on the surfaces; the radio frequency laser path separating mirror (4) is optical glass with a high-reflectivity dielectric film plated on the surface.
5. The satellite-borne flexible radio-frequency laser integrated communication antenna according to claim 4, characterized in that: the primary mirror chamber (23) is in a circular shape with an outer ring provided with at least one fixing ring for fixing the bottom end of the back support rib (12), and the upper end of the fixing ring is provided with a hole site for connecting the secondary mirror support frame (31).
6. The satellite-borne flexible radio-frequency laser integrated communication antenna according to claim 5, characterized in that: the number of the fixing rings is 8-12.
7. The satellite-borne flexible radio-frequency laser integrated communication antenna according to claim 1, characterized in that: the secondary mirror support frame (31) is of a four-wing beam structure, and the secondary mirror support frame (31) is made of invar steel;
and a fine adjustment device for fine adjustment of the position of the radio-frequency laser shared secondary mirror (33) is arranged on the secondary mirror fixing structure (32).
8. The satellite-borne flexible radio-frequency laser integrated communication antenna according to claim 1, characterized in that: the locking rope structure (51) comprises rope connecting holes fixed on two sides of the outer edge of the back support rib (12), dampers arranged inside the rope connecting holes and locking ropes corresponding to the rope connecting holes in shape and size.
9. The satellite-borne flexible radio-frequency laser integrated communication antenna according to claim 8, characterized in that: a cutting device for self-unlocking the integrated communication antenna is also arranged on the outer edge of the back support rib (12).
10. The satellite-borne flexible radio-frequency laser integrated communication antenna according to claim 1, characterized in that: the support rib locking structure (52) is an annular locking hinge.
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| CN202011213950.4A CN112394501B (en) | 2020-11-04 | 2020-11-04 | Satellite-borne flexible radio frequency laser integrated communication antenna |
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