CN112198646A - Satellite-borne transmit-receive integrated Cassegrain optical antenna system and application thereof - Google Patents
Satellite-borne transmit-receive integrated Cassegrain optical antenna system and application thereof Download PDFInfo
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- CN112198646A CN112198646A CN202011204367.7A CN202011204367A CN112198646A CN 112198646 A CN112198646 A CN 112198646A CN 202011204367 A CN202011204367 A CN 202011204367A CN 112198646 A CN112198646 A CN 112198646A
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- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 2
- 239000004917 carbon fiber Substances 0.000 claims description 2
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- 239000005350 fused silica glass Substances 0.000 claims description 2
- 239000000463 material Substances 0.000 claims description 2
- 239000007769 metal material Substances 0.000 claims description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 2
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- 229910052710 silicon Inorganic materials 0.000 claims description 2
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 2
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 2
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B19/00—Condensers, e.g. light collectors or similar non-imaging optics
- G02B19/0033—Condensers, e.g. light collectors or similar non-imaging optics characterised by the use
- G02B19/009—Condensers, e.g. light collectors or similar non-imaging optics characterised by the use for use with infrared radiation
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B17/00—Systems with reflecting surfaces, with or without refracting elements
- G02B17/08—Catadioptric systems
- G02B17/0804—Catadioptric systems using two curved mirrors
- G02B17/0808—Catadioptric systems using two curved mirrors on-axis systems with at least one of the mirrors having a central aperture
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B17/00—Systems with reflecting surfaces, with or without refracting elements
- G02B17/08—Catadioptric systems
- G02B17/0864—Catadioptric systems having non-imaging properties
- G02B17/0876—Catadioptric systems having non-imaging properties for light collecting, e.g. for use with a detector
-
- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B19/00—Condensers, e.g. light collectors or similar non-imaging optics
- G02B19/0004—Condensers, e.g. light collectors or similar non-imaging optics characterised by the optical means employed
- G02B19/0028—Condensers, e.g. light collectors or similar non-imaging optics characterised by the optical means employed refractive and reflective surfaces, e.g. non-imaging catadioptric systems
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B19/00—Condensers, e.g. light collectors or similar non-imaging optics
- G02B19/0033—Condensers, e.g. light collectors or similar non-imaging optics characterised by the use
- G02B19/0085—Condensers, e.g. light collectors or similar non-imaging optics characterised by the use for use with both a detector and a source
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/11—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum
- H04B10/118—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum specially adapted for satellite communication
Abstract
The invention discloses a satellite-borne transmitting-receiving integrated Cassegrain optical antenna system and application thereof, and solves the problems that when an existing Cassegrain optical antenna is used as a satellite-borne laser communication terminal transmitting-receiving antenna, wave aberration is large, the error rate of a laser communication system is high, and loss of mixing efficiency is large. The invention comprises an objective lens group and an eyepiece lens group, wherein the objective lens group comprises a primary lens and a secondary lens, the primary lens and the secondary lens are coaxial Cassegrain type optical antennas, and the eyepiece lens group consists of a plurality of lenses. The invention has the advantages of small wave aberration, higher error rate, small loss of mixing efficiency and the like.
Description
Technical Field
The invention relates to the technical field of satellite laser communication, in particular to a satellite-borne transmit-receive integrated Cassegrain optical antenna system and application thereof.
Background
Compared with the traditional microwave communication, the satellite laser communication has the characteristics of high transmission rate, strong anti-interference capability, small terminal volume, light weight and the like, becomes the hot direction of the development of the next generation of wireless communication technology, and has a great application prospect particularly in the communication between satellites without shielding objects and between satellites and the ground. The performance of the transceiving optical antenna, which is used as a key device in satellite laser communication, is directly related to the success of the satellite laser communication, so that designing the transceiving optical antenna with superior performance becomes the key element in the satellite laser communication.
The satellite-borne equipment has high requirements on integration and light weight, and the receiving and transmitting integrated optical antenna can effectively reduce the complexity of the satellite laser communication terminal and effectively reduce the quality of the terminal, so that the satellite-borne equipment is widely researched at home and abroad.
The Cassegrain form is the most common form of an optical antenna system, a primary lens of a common Cassegrain objective adopts a paraboloid, a secondary lens adopts a hyperboloid, the whole system has no spherical aberration, and the optical system has a simple structure and excellent image quality and is widely applied to satellite laser communication terminals.
However, when the conventional cassegrain optical antenna is used as a transmitting and receiving antenna of a satellite-borne laser communication terminal, the problems of large wave aberration, high error rate of a laser communication system, large loss of mixing efficiency and the like exist.
Therefore, it is necessary to design a cassegrain optical antenna applied to a transceiver antenna of a satellite-borne laser communication terminal to solve the above problems.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: when the conventional Cassegrain optical antenna is used as a transmitting and receiving antenna of a satellite-borne laser communication terminal, the problems of large wave aberration, high error rate of a laser communication system and large loss of mixing efficiency exist.
The invention can be realized by the following technical scheme:
the utility model provides an integrative cassegrain optical antenna system of satellite-borne receiving and dispatching, includes objective lens group and eyepiece lens group, objective lens group includes primary mirror and secondary mirror, primary mirror and secondary mirror are coaxial cassegrain type optical antenna, eyepiece lens group comprises a plurality of lenses.
The invention preferably discloses a satellite-borne transmit-receive integrated Cassegrain optical antenna system, wherein the surface of the primary mirror is a paraboloid of revolution, the caliber of the primary mirror is 110mm, the effective caliber of the primary mirror is 100mm, and the curvature radius of the vertex of the primary mirror is 320 mm.
The invention preferably discloses a satellite-borne transmit-receive integrated Cassegrain optical antenna system, wherein a first through hole is formed in the center of a primary mirror, and the diameter of the first through hole is 10 mm.
The invention preferably selects a satellite-borne transmit-receive integrated Cassegrain optical antenna system, the surface of the secondary mirror is a hyperboloid of rotation, the caliber of the secondary mirror is 25mm, the effective caliber of the secondary mirror is 21.4mm, and the curvature radius of the vertex of the secondary mirror is 87.8 mm.
The invention preferably discloses a satellite-borne transmit-receive integrated Cassegrain optical antenna system, and the distance between a primary mirror and a secondary mirror is 128 mm.
The invention preferably discloses a satellite-borne transmit-receive integrated Cassegrain optical antenna system, wherein an objective lens group consists of 4 lenses, the objective lens group is a focal system, the extension of a focal point is minus 10mm, and the focal plane of the objective lens group is superposed with the Cassegrain optical antenna.
The invention preferably selects a satellite-borne transmit-receive integrated Cassegrain optical antenna system, and the reflecting surfaces of the primary mirror and the secondary mirror are plated with high-reflection films for increasing the laser reflection efficiency.
The invention preferably discloses a satellite-borne transmit-receive integrated Cassegrain optical antenna system, wherein the diameter of an entrance pupil of the Cassegrain optical antenna is 100mm, the diameter of an exit pupil of the Cassegrain optical antenna is 10mm, and the magnification of the Cassegrain optical antenna is 10 times.
The invention preferably selects a satellite-borne transmit-receive integrated Cassegrain optical antenna system, and the primary mirror is made of one of microcrystalline glass, fused quartz, silicon carbide, carbon fiber composite materials, silicon wafers and metal materials with small thermal deformation coefficients.
According to the invention, through the design of the antenna structure and size, the Cassegrain optical antenna system with excellent wave aberration, low error rate and low loss of mixing efficiency is obtained.
The application of the satellite-borne transmit-receive integrated Cassegrain optical antenna system is applicable to satellite-borne laser communication terminals with the laser wavelength of 1550 nm.
Compared with the prior art, the invention has the following advantages and beneficial effects:
1. the system field angle of the invention is +/-5 mrad, the wave aberration RMS value in the full field is better than 1/30 wavelength, the wave aberration in the central field is better than 1/50 wavelength, the error rate of the laser communication system can be effectively reduced, and the loss of the frequency mixing efficiency is reduced, therefore, the invention is very suitable for being used as the receiving and transmitting antenna of the satellite-borne laser communication terminal.
2. The emergent light beam of the optical antenna is parallel light, an ideal lens is added on the cross section of the parallel light beam to converge the parallel light beam, the parallel light beam is evaluated through the imaging quality of the ideal lens, and from an imaging surface point chart of the ideal lens, the diameter of a 0-field-of-view light spot RMS is only 0.588 mu m, and the diameter of a +/-5 mrad-of-view light spot RMS is only 0.718 mu m, which indicates that the optical antenna system designed by the invention reaches the diffraction limit level.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the principles of the invention. In the drawings:
FIG. 1 is a schematic view of an optical antenna and eyepiece lens assembly;
FIG. 2 is a geometric structure diagram of the design result of the objective lens set of the optical antenna;
FIG. 3 is a dot-sequence chart analysis of the design result of the objective lens set of the optical antenna;
FIG. 4 is a 0 field wave aberration analysis of the design result of the objective lens set of the optical antenna;
FIG. 5 is an optical antenna transfer function MTF;
FIG. 6 is a 0 field wave aberration analysis of optical antenna design results;
FIG. 7 shows the optical antenna design result 5mrad field of view wave aberration analysis;
FIG. 8 is the optical antenna design result-5 mrad field of view wave aberration analysis;
fig. 9 is a dot diagram of the optical antenna design result.
Reference numbers and corresponding part names in the drawings:
1-primary mirror, 2-secondary mirror, 3-objective lens group and 4-focal plane.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not meant to limit the present invention.
Example 1
As shown in fig. 1 and fig. 2, a satellite-borne transmitting-receiving integrated cassegrain optical antenna system comprises an objective lens group 3 and an eyepiece lens group, wherein the objective lens group 3 comprises a primary lens 1 and a secondary lens 2, the primary lens 1 and the secondary lens 2 are coaxial cassegrain optical antennas, and the eyepiece lens group comprises 4 lenses.
The surface type of primary mirror 1 is the paraboloid of revolution, the bore of primary mirror 1 is 110mm, the effective bore of primary mirror 1 is 100mm, the radius of curvature at the summit of primary mirror 1 is 320mm, first through-hole has been seted up at primary mirror 1 center, the diameter of first through-hole is 10 mm.
The surface type of the secondary mirror 2 is a hyperboloid of revolution, the caliber of the secondary mirror 2 is 25mm, the effective caliber of the secondary mirror 2 is 21.4mm, and the curvature radius of the vertex of the secondary mirror 2 is 87.8 mm.
The distance between the primary mirror 1 and the secondary mirror 2 is 128 mm.
The Cassegrain type optical antenna objective lens consists of a paraboloid primary mirror 1 and a hyperboloid secondary mirror 2, and the focuses of the two quadric surfaces are overlapped.
The Cassegrain optical antenna has an entrance pupil diameter of 100mm, an exit pupil diameter of 10mm and a magnification of 10 times.
The objective lens group 3 is a focal system, the extension of a focal point is-10 mm, and a focal plane 4 of the objective lens group 3 is superposed with the focal plane 4 of the Cassegrain type optical antenna.
The laser optics transmitted from the far end can be treated as parallel light on the surface of the main mirror 1, the light beams are converged to a primary image surface after the parallel light beams are incident, and the imaging process has no spherical aberration. The cassegrain system is an aplanatic system, and when an incident parallel light beam deflects, a large coma aberration occurs on a primary image surface.
The calculation process of the antenna parameters is as follows:
1. determining relative aperture of antenna primary mirror
The relative caliber of the primary mirror of the Cassegrain antenna is restricted by multiple factors, the larger the relative caliber of the primary mirror is, the more the whole antenna is compacted, and the corresponding processing difficulty is higher. The aperture D of the antenna is 100mm, and the relative aperture is 1:1.6 in comprehensive consideration. According to the sign rule, the focal length of the image space of the primary mirror is negative, and then the focal length of the primary mirror is f1’＝-1.6D＝-160mm。
2. Determining cassegrain antenna secondary mirror obscuration ratio alpha
The rejection ratio of the secondary mirror of the Cassegrain antenna is related to the size of the secondary mirror and is similar to the aperture ratio of the primary mirror and the secondary mirror. The design selects a classic value alpha of the cassegrain antenna obscuration ratio as 0.2.
3. Determining the extension Delta of the focal point of an objective lens of a Cassegrain antenna
The Cassegrain antenna objective lens is a focused system, the satellite terminal has the requirements of light weight and miniaturization, the design is to make the system compact, reduce the axial length, and place the focal length of the objective lens on the left side of the main lens, namely the focus extension delta of the objective lens takes a negative value. However, the focal length of the objective lens should not extend far to the left side of the main lens too much, otherwise the eyepiece lens group will enter the opening of the antenna main lens, which results in a great increase of the difficulty of installation and adjustment. The design takes delta-10 mm under comprehensive consideration.
4. Determining the amplification beta value of the secondary lens of a Cassegrain antenna
The secondary power β is determined by the antenna structure, and its value is calculated by the following equation:
substituting the corresponding value, calculating β -3.6875.
5. Calculating the curvature radius r of the primary mirror1And radius of curvature r of secondary mirror2And the distance between the two mirrors
Carry in the corresponding numerical value, calculate r1＝-320mm，r2＝-87.8mm，d＝-128mm。
6. Calculating the coefficient of the quadric surface
The Cassegrain antenna has a paraboloid primary mirror and a conic surface coefficient
The secondary mirror is a paraboloid, and the coefficient of the quadric surface is calculated according to the following formula under the condition of spherical aberration:
brought-in data is calculated and obtained
The antenna eyepiece group adopts a 4-piece structure, can better balance the residual coma aberration and the corrected chromatic aberration of the objective group, and partially balance the field curvature of the objective group.
Fig. 3 is a point array diagram of the objective lens of the cassegrain optical antenna in the invention on the primary image surface. It can be seen from fig. 3 that the cassegrain optical antenna objective lens of the present invention is imaged as an ideal image under a 0-field of view, which illustrates that the design of the present invention has reached a limit effect; the field range of the whole optical antenna is +/-5 mrad, the point diagram shown in fig. 3 simultaneously shows the condition of primary image plane imaging under a 5mrad field and a-5 mrad field, so that large coma aberration is introduced into the images under the two fields, and the aberrations are corrected by a subsequent eyepiece lens group to emit parallel light.
Referring to fig. 4, a schematic diagram of the wavefront aberration of the cassegrain optical antenna objective lens under the 0-field of view of the invention shows that the wavefront aberration of the 0-field of view of the cassegrain optical antenna objective lens is 0, which is a non-aberration point, and this characteristic has a great effect in processing and assembling and can be used as a reference for installation during assembly and adjustment.
Referring to fig. 5, the transfer function of the optical antenna of the present invention is shown, wherein F1 represents the transfer function value of the optical antenna in the 0 view field, F2 represents the transfer function value of the optical antenna in the + 5mrad view field, F3 represents the transfer function value of the optical antenna in the-5 mrad view field, and T and R represent the meridian plane and the sagittal plane, it can be seen that the transfer function curves of the optical antenna designed by the present invention in the three view fields have good coincidence, which indicates that the imaging quality reaches the diffraction limit level.
Referring to fig. 6, fig. 7 and fig. 8, the wave aberration diagrams of the exit beam of the optical antenna of the present invention at different fields of view on the receiving surface are shown. Wherein FIG. 6 is 0 showing the 0 field wave aberration, FIG. 7 is 5mrad field wave aberration, and FIG. 8 is-5 mrad field wave aberration. Numerical calculations show that the 0 field wave aberration RMS value is 0.019 wavelengths and that the + -5mrad field wave aberration RMS values are all 0.031 wavelengths. The optical antenna designed by the invention has wave aberration better than 1/30(0.033) wavelength in the full field of view and wave aberration better than 1/50(0.02) wavelength in the central field of view, can effectively reduce the error rate of a laser communication system, reduces the loss of mixing efficiency, and completely meets the technical requirements of a transmitting-receiving antenna of a satellite-borne laser communication terminal.
The emergent light beam of the optical antenna is parallel light, an ideal lens is added on the cross section of the parallel light beam to converge the parallel light beam in the design, and the parallel light beam is evaluated through the imaging quality of the ideal lens.
Referring to FIG. 9, which is a dot diagram of the imaging surface of the ideal lens, it can be seen that the 0-field spot RMS diameter is only 0.588 μm, and the + -5 mrad-field spot RMS diameter is only 0.718 μm, indicating that the design result reaches the diffraction limit level.
Example 2
The difference between the present embodiment and embodiment 1 is that the reflective surfaces of the primary mirror 1 and the secondary mirror 2 are plated with a high reflective film for increasing the laser reflection efficiency, and the material used for the primary mirror 1 is microcrystalline glass.
Example 3
An application of a satellite-borne transmit-receive integrated cassegrain optical antenna system, the optical antenna system in embodiment 1 or 2 is applied to a satellite-borne laser communication terminal with the laser wavelength of 1550nm, and the field angle of the optical antenna system is +/-5 mrad.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are merely exemplary embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (10)
1. The utility model provides an integrative cassegrain optical antenna system of satellite-borne receiving and dispatching, its characterized in that, includes objective lens group (3) and eyepiece lens group, objective lens group (3) are including primary mirror (1) and secondary mirror (2), primary mirror (1) and secondary mirror (2) are coaxial cassegrain type optical antenna, eyepiece lens group comprises a plurality of lenses.
2. A satellite-borne transmit-receive integrated cassegrain optical antenna system according to claim 1, wherein the surface of the primary mirror (1) is a paraboloid of revolution, the aperture of the primary mirror (1) is 110mm, the effective aperture of the primary mirror (1) is 100mm, and the radius of curvature of the vertex of the primary mirror (1) is 320 mm.
3. The spaceborne transceiving integrated cassegrain optical antenna system according to claim 1 or 2, wherein a first through hole is formed in the center of the primary mirror (1), and the diameter of the first through hole is 10 mm.
4. A satellite-borne transmit-receive integrated cassegrain optical antenna system according to claim 1 or 2, characterized in that the surface of the secondary mirror (2) is a hyperboloid of revolution, the aperture of the secondary mirror (2) is 25mm, the effective aperture of the secondary mirror (2) is 21.4mm, and the radius of curvature of the vertex of the secondary mirror (2) is 87.8 mm.
5. A satellite-borne transceiver-integrated cassegrain optical antenna system according to claim 1 or 2, characterized in that the distance between the primary mirror (1) and the secondary mirror (2) is 128 mm.
6. The spaceborne transmit-receive integrated cassegrain optical antenna system according to claim 1 or 2, characterized in that the objective lens group (3) is composed of 4 lenses, the objective lens group (3) is a focal system, the focus extension is-10 mm, and the focal plane (4) of the objective lens group (3) coincides with the focal plane (4) of the cassegrain optical antenna.
7. A satellite-borne transceiver integrated cassegrain optical antenna system according to claim 1 or 2, characterized in that the reflecting surfaces of the primary mirror (1) and the secondary mirror (2) are coated with a high reflection film that increases the reflection efficiency of the laser light.
8. A spaceborne transmit-receive integrated cassegrain optical antenna system according to claim 1 or 2, characterized in that the cassegrain optical antenna has an entrance pupil diameter of 100mm, an exit pupil diameter of 10mm and a magnification of 10.
9. The spaceborne transmit-receive integrated Cassegrain optical antenna system according to claim 1 or 2, characterized in that the material adopted by the primary mirror (1) is one of microcrystalline glass, fused quartz, silicon carbide, carbon fiber composite material, silicon chip and metal material with small thermal deformation coefficient.
10. Use of a satellite-borne transmit-receive integrated cassegrain optical antenna system, wherein the optical antenna system of any one of claims 1-9 is suitable for a satellite-borne laser communication terminal with a laser wavelength of 1550 nm.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113835205A (en) * | 2021-09-30 | 2021-12-24 | 中国科学院长春光学精密机械与物理研究所 | Catadioptric imaging telescopic optical system |
| RU2783202C2 (en) * | 2021-03-09 | 2022-11-09 | Публичное акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королёва" | Repeater satellite |
| EP4270820A1 (en) * | 2022-04-26 | 2023-11-01 | Airbus Defence and Space GmbH | Laser communication terminal |
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| CN101598849A (en) * | 2008-06-06 | 2009-12-09 | 上海微小卫星工程中心 | Optical imaging system and manufacture method thereof |
| CN103873151A (en) * | 2014-03-10 | 2014-06-18 | 北京遥测技术研究所 | Satellite-borne integration communication system compatible with microwave communication, laser communication and quantum communication |
| CN213122425U (en) * | 2020-11-02 | 2021-05-04 | 重庆两江卫星移动通信有限公司 | Satellite-borne transmitting-receiving integrated Cassegrain optical antenna system |
-
2020
- 2020-11-02 CN CN202011204367.7A patent/CN112198646B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101598849A (en) * | 2008-06-06 | 2009-12-09 | 上海微小卫星工程中心 | Optical imaging system and manufacture method thereof |
| CN103873151A (en) * | 2014-03-10 | 2014-06-18 | 北京遥测技术研究所 | Satellite-borne integration communication system compatible with microwave communication, laser communication and quantum communication |
| CN213122425U (en) * | 2020-11-02 | 2021-05-04 | 重庆两江卫星移动通信有限公司 | Satellite-borne transmitting-receiving integrated Cassegrain optical antenna system |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2783202C2 (en) * | 2021-03-09 | 2022-11-09 | Публичное акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королёва" | Repeater satellite |
| CN113835205A (en) * | 2021-09-30 | 2021-12-24 | 中国科学院长春光学精密机械与物理研究所 | Catadioptric imaging telescopic optical system |
| CN113835205B (en) * | 2021-09-30 | 2023-05-12 | 中国科学院长春光学精密机械与物理研究所 | Refractive and reflective imaging telescopic optical system |
| EP4270820A1 (en) * | 2022-04-26 | 2023-11-01 | Airbus Defence and Space GmbH | Laser communication terminal |
| WO2023208620A1 (en) * | 2022-04-26 | 2023-11-02 | Airbus Defence and Space GmbH | Laser communication terminal |
| RU2793898C1 (en) * | 2022-10-21 | 2023-04-07 | Публичное акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королёва" | Relay satellite |
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