A light and small inter-satellite laser communication terminal

Abstract

The utility model provides a kind of light inter-orbital laser communication terminal of small and light, including optical head and processor module of light connection;Optical head includes first plane mirror, main telescope, second plane mirror, fast mirror, dichroic mirror, first narrowband filter, beam splitter, beam receiving collimator, second narrowband filter, tracking collimating camera, signal light emission collimator, pre collimating mirror, shutter and corner reflector;Processor module includes power module, integrated communication module and optical amplifier module in turn stacked in sequence.The utility model reduces the quality of whole machine by reasonable layout;The key components of optical machine main body are all used composite material with high specific stiffness, while reducing quality, ensure force thermal stability;Integrated processor design is carried out, integrated communication module, optical amplifier and secondary power supply are designed as a whole, reduce metal shielding material, reduce processor weight on the basis of ensuring radiation resistance performance.

Description

Technical Field

[0001] This utility model relates to the field of communication technology, specifically to a lightweight and miniaturized inter-satellite laser communication terminal. Background Technology

[0002] As a high-precision opto-mechatronics integrated device, inter-satellite laser communication terminals, especially the optical path part, have very high requirements for structural strength, rigidity and precision. The overall structural design must not only meet the mechanical strength, but also the servo electronic control must meet the requirements of laser communication tracking. Therefore, traditional laser communication terminal products are relatively heavy and cannot be used for flat-panel satellite applications.

[0003] To meet the requirements of flat-panel satellite platforms, a highly integrated, lightweight, and miniaturized inter-satellite laser communication terminal is needed. Summary of the Invention

[0004] This invention addresses the problem of excessive size and weight in laser communication terminals by providing a lightweight and miniaturized inter-satellite laser communication terminal. The terminal includes an optical head for optical connection and a processing module. The optical head comprises a first plane mirror, a main telescope, a second plane mirror, a fast-reflecting mirror, a dichroic mirror, a first narrowband filter, a beam splitter, a beam receiving collimator, a second narrowband filter, a tracking and aiming camera, a signal light emitting collimator, a pre-aiming mirror, a shutter, and a corner reflector. The processing module consists of a power supply module, an integrated communication module, and an optical amplifier module stacked sequentially. This invention reduces the overall weight through a rational layout. Key components of the optical engine are made of composite materials with high specific stiffness, ensuring mechanical and thermal stability while reducing weight. An integrated processing module design combines the integrated communication module, optical amplifier, and secondary power supply into one unit, reducing the amount of metal shielding material and minimizing processor weight while maintaining radiation resistance.

[0005] This utility model provides a lightweight and miniaturized inter-satellite laser communication terminal, including an optical head for optical connection and a processing module;

[0006] The optical head includes a first plane mirror, a main telescope, a second plane mirror, a fast-reflecting mirror, a dichroic mirror, a first narrowband filter, and a beam splitter, which are connected in sequence. A beam receiving collimator is connected in sequence to the transmission output end of the beam splitter. A second narrowband filter and a tracking aiming camera are connected in sequence to the refraction output end of the beam splitter. A signal light emitting collimator and a pre-aiming mirror are located in sequence on the input optical path of the dichroic mirror. A shutter and a corner reflector are located in sequence on the transmission output optical path of the dichroic mirror.

[0007] The processor module includes a power supply module, an integrated communication module, and an optical amplifier module stacked in sequence. The power supply module provides secondary power to the integrated communication module. The integrated communication module includes a laser transceiver module and an FPGA that are electrically connected. The laser transceiver module performs the conversion of laser emission and reception light.

[0008] The first narrowband filter is located on the transmission output light path of the dichroic mirror, the corner reflector is located on the refraction output light path of the dichroic mirror, the beam receiving collimator is connected to the optical amplifier module through an optical fiber, the signal light transmitting collimator is optically connected to the laser transceiver module, and the tracking aiming camera is connected to the FPGA.

[0009] In a preferred embodiment of the lightweight inter-satellite laser communication terminal described in this invention, the first plane mirror, the second plane mirror, and the fast-reflecting mirror all undergo optical path deflection.

[0010] In a preferred embodiment of the miniaturized inter-satellite laser communication terminal described in this utility model, the first plane mirror, the second plane mirror, and the fast-reflecting mirror are all 45° plane mirrors.

[0011] The present invention discloses a lightweight inter-satellite laser communication terminal. In a preferred embodiment, the optical amplifier module includes an optical switch, an optical amplifier main module that is optically connected to the optical switch and uses the same structure and packaging, and a cold backup.

[0012] In a preferred embodiment of the lightweight inter-satellite laser communication terminal described in this utility model, the first plane mirror, the main telescope, the second plane mirror, the fast-reflecting mirror, the dichroic mirror, the first narrowband filter, the beam splitter, the beam receiving collimator, the second narrowband filter, the tracking and aiming camera, the signal light emitting collimator, the advance aiming mirror, the shutter, and the corner reflector are all encapsulated in an optical box, and the optical box is made of aluminum alloy.

[0013] The output end of the main telescope is connected to the telescope tube, which is made of carbon fiber.

[0014] The present invention discloses a lightweight inter-satellite laser communication terminal, in which, as a preferred embodiment, the main telescope includes a rotating shaft and a bearing housing made of titanium alloy.

[0015] In a preferred embodiment of the lightweight inter-satellite laser communication terminal described in this utility model, the optical box is internally connected to a fixed base, and the fixed base is made of aluminum alloy.

[0016] This invention overcomes design challenges such as high speed, long distance, lightweight, miniaturization, and low power consumption, proposing a high-speed, long-distance, lightweight, and miniaturized inter-satellite laser communication terminal based on a highly integrated optical head and processor. This invention can be applied to large-scale constellation inter-satellite communication, and is also suitable for applications involving planar satellite inter-satellite communication in multi-satellite launch scenarios.

[0017] This project employs a refined structural design approach. During the structural design phase, more detailed modeling and structural characteristic assessments were conducted for each component. While meeting requirements, lightweight materials were rationally selected for each component. Larger parts such as the fixed base and optical box are made of aluminum alloy, while high-rigidity precision parts such as the shaft and bearing housing are made of titanium alloy. The telescope barrel is made of carbon fiber. Furthermore, the laser modulation and optical amplifier, as well as the overall structure, were integrated into a single design to optimize the terminal system.

[0018] In the design of this invention, a rough model of the overall structure is first created and simulation analysis is performed. Based on the simulation analysis results of the strength requirements of each part, the overall structure is decomposed and segmented. Then, a refined model is created on the decomposed structure. The modeling not only considers the structural configuration but also selects appropriate materials based on characteristics such as strength and machinability. After the refined modeling is completed, simulation analysis is performed again using software. After the simulation, the structural parts are finely adjusted based on the simulation analysis results. This process of adjustment and re-analysis is repeated multiple times to ultimately achieve the weight reduction design goal. This invention features structural optimization. The main structural components of the product are selected for optimal force transmission paths through topology optimization, size optimization, and integration optimization to meet performance requirements. Within the integrated communication module, this invention adopts a system architecture of laser transceiver module plus FPGA, integrating the laser modulation function into the laser transceiver module, improving hardware utilization efficiency and significantly reducing hardware size.

[0019] This utility model has the following advantages:

[0020] (1) This utility model has a reasonable layout. By reasonably designing the position of each reflector, the product layout is more compact, thereby reducing the overall weight of the machine.

[0021] (2) The present invention has made material selection. The key components of the optical engine body are all made of composite materials with high specific stiffness, which reduces the weight while ensuring mechanical and thermal stability.

[0022] (3) The present invention has made compact selection of components. The selection of components in the main body of the optical engine has taken into account the balance between performance and lightweight. For example, the selection of ultra-thin bearings has reduced the size and weight of related parts.

[0023] (4) This utility model has an integrated processor design: the integrated communication module, optical amplifier and secondary power supply are designed as one unit, reducing the metal shielding material and reducing the weight of the processor while ensuring radiation resistance. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of a lightweight, miniaturized inter-satellite laser communication terminal.

[0025] Figure 2 This is a block diagram of the optical head of a lightweight, miniaturized inter-satellite laser communication terminal.

[0026] Figure label:

[0027] 1. Optical head; 11. First plane mirror; 12. Main telescope; 13. Second plane mirror; 14. Quick-reflecting mirror; 15. Dichroic mirror; 16. First narrowband filter; 17. Beam splitter; 18. Beam receiving collimator; 19. Second narrowband filter; 1a. Tracking aiming camera; 1b. Signal light emitting collimator; 1c. Advance aiming scope; 1d. Shutter; 1e. Corner reflector; 2. Processor module; 21. Power supply module; 22. Integrated communication module; 23. Optical amplifier module. Detailed Implementation

[0028] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.

[0029] Example 1

[0030] like Figure 1 , 2 As shown, a lightweight inter-satellite laser communication terminal includes an optical head 1 with optical connection and a processing module 2.

[0031] The optical head 1 includes a first plane mirror 11, a main telescope 12, a second plane mirror 13, a fast-reflecting mirror 14, a dichroic mirror 15, a first narrowband filter 16, and a beam splitter 17, which are connected in sequence. A beam receiving collimator 18 is connected to the transmission output end of the beam splitter 17. A second narrowband filter 19 and a tracking aiming camera 1a are connected in sequence to the refraction output end of the beam splitter 17. A signal light emitting collimator 1b and a pre-aiming mirror 1c are located in sequence on the input optical path of the dichroic mirror 15. A shutter 1d and a corner reflector 1e are located in sequence on the transmission output optical path of the dichroic mirror 15.

[0032] The processor module 2 includes a power supply module 21, an integrated communication module 22 and an optical amplifier module 23 stacked in sequence. The power supply module 21 is used to provide secondary power to the integrated communication module 22. The integrated communication module 22 includes a laser transceiver module and an FPGA that are electrically connected. The laser transceiver module performs the conversion of laser emission and reception light.

[0033] The first narrowband filter 16 is located on the transmission output light path of the dichroic mirror 15, the corner reflector 1e is located on the refraction output light path of the dichroic mirror 15, the beam receiving collimator 18 is connected to the optical amplifier module 23 through an optical fiber, the signal light transmitting collimator 1b is optically connected to the laser transceiver module, and the tracking aiming camera 1a is connected to the FPGA.

[0034] The first plane mirror 11, the second plane mirror 13 and the fast-reflecting mirror 14 all have optical path deflection and are all 45° plane mirrors;

[0035] The first plane mirror 11, the main telescope 12, the second plane mirror 13, the fast-reflecting mirror 14, the dichroic mirror 15, the first narrowband filter 16, the beam splitter 17, the beam receiving collimator 18, the second narrowband filter 19, the tracking aiming camera 1a, the signal light emitting collimator 1b, the advance aiming mirror 1c, the shutter 1d, and the corner reflector 1e are all encapsulated in an optical box, which is made of aluminum alloy.

[0036] The output end of the main telescope 12 is connected to the telescope tube, which is made of carbon fiber; the main telescope 12 includes a rotating shaft and a bearing housing made of titanium alloy.

[0037] The optical box has an internal connecting and fixing base, which is made of aluminum alloy.

[0038] The optical amplifier module 23 includes an optical switch, an optical amplifier main module that is optically connected to the optical switch and uses the same structure for packaging, and a cold backup.

[0039] The lightweight inter-satellite laser communication terminal of this embodiment has self-calibration functions for transmitting and receiving optical axes, and features low weight, small size, low power consumption, and high integration.

[0040] The optical head 1 consists of an optical antenna, a coarse pointing mechanism, a rear optical path module, and a thermal control component, realizing functions such as optical signal transmission and reception, beam pointing control, acquisition and tracking control, and optical head thermal control. The optical head includes a first plane mirror 11, a main telescope 12, a second plane mirror 13, a fast-reflecting mirror 14, a dichroic mirror 15, a first narrowband filter 16, a beam splitter 17, a beam receiving collimator 18, a second narrowband filter 19, a tracking and aiming camera 1a, a pre-aiming scope 1c, a signal light transmitting collimator 1b, a shutter 1d, and a corner reflector 1e.

[0041] The signal light is reflected by the first plane mirror 11, expanded in the main telescope 12, and then enters the rear optical path through the second plane mirror 13. After being reflected by the fast mirror 14, it enters the dichroic mirror 15, which transmits the signal light with the correct wavelength to the first narrowband filter 16. The filtered signal light is split by the beam splitter 17 and enters the beam receiving collimator 18 and the second narrowband filter 19, respectively, before entering the tracking and aiming camera 1a.

[0042] The emitted beam enters the rear optical path through the signal light emitting collimator 1b, is reflected by the advance aiming mirror 1c and enters the dichroic mirror 15. A portion of the transmitted light passes through to the shutter 1d and the corner reflector, while most of the partially reflected light is reflected by the fast reflector 14 to the second plane mirror 13. After being expanded by the main telescope 12, it is emitted into space along with the first plane mirror 11.

[0043] The coarse pointing assembly adopts a periscope structure. The main telescope 12 has the advantages of large rotation angle, high precision, structural stability, and small outer envelope in the locked state. The azimuth axis movement and the pitch axis movement are independent of each other. The pitch axis is located at the bottom of the mechanism and adopts a scheme of direct drive by a torque motor and high-precision grating feedback to ensure high precision and high dynamic response. The azimuth axis is located on one side of the pitch axis and is also driven by a direct drive by a torque motor and high-precision grating feedback. The azimuth reflector assembly and the transmission telescope assembly are mounted on the azimuth axis and rotate with the axis. The pitch reflector assembly is mounted on the pitch axis through a support structure. Each optical lens is precisely assembled and adjusted to ensure the optical stability of the front optical path. Following the principles of miniaturization, lightweight, high specific stiffness, and high reliability, the main parts of the turntable body are made of 30% aluminum-based silicon carbide.

[0044] The optical antenna module mainly comprises a refractive, focusless beam expander system, employing a focusless Galilean design. Multiple lenses form the beam expander optical path, guiding the incoming parallel light into the rear optical path. Simultaneously, the collimated light from the rear optical path is collimated and emitted through the focusless telescope. The system achieves orbital self-testing and real-time on-orbit self-calibration via the signal light transmission axis and communication reception light. A shutter 1d and corner reflector 1e are placed behind the dichroic mirror 15. In self-test mode, when shutter 1d is open, the signal light passes through the internal optical path, with a small portion of its energy transmitted through the dichroic mirror 15. This energy is then reflected by the corner reflector 1e, reflected again by the dichroic mirror 15, reflected by the first narrowband filter 16 and beam splitter 17, filtered by the second narrowband filter 19, and enters the tracking and aiming camera 1a. The resulting light spot represents the transmission optical axis, reflecting internal variations in transmission accuracy. Without adding an extra self-test light source or increasing weight, the signal light transmission acts as the self-calibration light source, enabling communication reception optical axis self-testing. In self-calibration mode, shutter 1d opens, and the self-calibration light source passes through fast reflector 14. A small portion of the light is reflected by dichroic mirror 15 and then enters corner reflector 1e to accelerate shutter 1d. The light then returns along the original optical path and is transmitted through beam splitter 17 into the communication receiving optical fiber.

[0045] The rear optical path module includes a fine tracking module, a pre-aiming module, a tracking camera, a laser emission and reception module, a beam splitter, a polarization device, and an optical path folding mirror.

[0046] The optical head 1 performs functions such as optical signal transmission and reception, beam pointing control, acquisition and tracking control, and optical head thermal control. Among them, the optical antenna module greatly reduces the size and weight of the optical head while ensuring maximum rotation angle and high-precision pointing. The rear optical path module has made lightweight materials and integrated the structure of its fine tracking module, pre-aiming module, tracking camera, laser emission and reception module, beam splitter, polarization device, and optical path folding mirror, further reducing the size and weight of the optical head.

[0047] Optical head 1 is configured according to the coupling relationship of the processing assembly, and its structure is as follows: Figure 1 As shown, the mechanism measures 200mm*200mm*120mm and weighs 6.5kg.

[0048] The processor module 2 consists of a power supply module 21, an integrated communication module 22, and an optical amplifier module 23. It is used for secondary power conversion, optical signal generation, power amplification, low-noise amplification, reception and detection, to realize high-speed bidirectional data transmission and bidirectional high-precision pseudorange measurement, and to support on-board routing and forwarding of service data.

[0049] The power module 21 converts the primary power supplied by the satellite platform into the secondary power required by the processor, and isolates the laser terminal from the satellite power supply network to improve electromagnetic compatibility.

[0050] The integrated communication module 22 includes a laser transceiver module, a high-speed service data interface module, a reconfiguration module, and a time-frequency interface module. The laser transceiver module is used to complete the modulation of the transmitted light and the conversion and code synchronization of the received light. It adopts an integrated FGPA design to integrate communication, measurement and control and reconfiguration functions, reducing the size and weight of the module.

[0051] In this embodiment, the processor module 2 includes a storage unit, a telemetry and remote control unit, a reconfiguration interface unit, a PROM, a FLASH, a service interface unit, a time and frequency interface unit, an FPGA, a laser transceiver unit, a clock recovery unit, a clock unit, a power supply module 21, a configuration unit, an optical head interface unit, and an optical amplifier interface unit. The optical head interface unit is connected to the optical head 1, and the optical amplifier interface unit is connected to the optical amplifier module 23. The telemetry and remote control unit, the reconfiguration interface unit, the service interface unit, and the time and frequency interface unit are all connected to the satellite platform.

[0052] The integrated communication module 22 is used for telemetry, remote control, reconstruction, routing, laser data modulation and demodulation, etc.

[0053] The optical amplifier module 23 adopts a stand-alone cold backup method, and the master-slave switching is realized through an optical switch. It uses the same structural packaging to reduce the module size and weight.

[0054] Through the aforementioned miniaturization and lightweight design, the power module 21, integrated communication module 22, and optical amplifier module 23 are structurally unified and stacked. This reduces planar partitions between the power module 21 and integrated communication module 22, and between the integrated communication module 22 and optical amplifier module 23, further reducing the processing weight. Processor module 2, as shown... Figure 1 As shown, its dimensions are 180.5mm*164mm*80mm, and its weight is 2.5kg.

[0055] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. A lightweight, miniaturized inter-satellite laser communication terminal, characterized in that: Includes an optical head (1) for optical connection and a processing module (2); The optical head (1) includes a first plane mirror (11), a main telescope (12), a second plane mirror (13), a fast mirror (14), a dichroic mirror (15), a first narrowband filter (16), and a beam splitter (17) connected in sequence. A beam receiving collimator (18) is connected in sequence to the transmission output end of the beam splitter (17). A second narrowband filter (19) and a tracking aiming camera (1a) are connected in sequence to the refraction output end of the beam splitter (17). A signal light emitting collimator (1b) and a pre-aiming mirror (1c) are located in sequence on the input optical path of the dichroic mirror (15). A shutter (1d) and a corner reflector (1e) are located in sequence on the transmission output optical path of the dichroic mirror (15). The processor module (2) includes a power supply module (21), an integrated communication module (22) and an optical amplifier module (23) stacked in sequence. The power supply module (21) is used to provide secondary power to the integrated communication module (22). The integrated communication module (22) includes a laser transceiver module and an FPGA that are electrically connected. The laser transceiver module performs the conversion of laser emission and reception light. The first narrowband filter (16) is located on the transmission output light path of the dichroic mirror (15), the corner reflector (1e) is located on the refraction output light path of the dichroic mirror (15), the beam receiving collimator (18) is connected to the optical amplifier module (23) through an optical fiber, the signal light emitting collimator (1b) is optically connected to the laser transceiver module, and the tracking aiming camera (1a) is connected to the FPGA.

2. The lightweight and compact inter-satellite laser communication terminal according to claim 1, characterized in that: The first plane mirror (11), the second plane mirror (13) and the fast mirror (14) all perform optical path deflection.

3. The lightweight and compact inter-satellite laser communication terminal according to claim 2, characterized in that: The first plane mirror (11), the second plane mirror (13) and the fast-reflecting mirror (14) are all 45° plane mirrors.

4. The lightweight and compact inter-satellite laser communication terminal according to claim 1, characterized in that: The optical amplifier module (23) includes an optical switch, an optical amplifier main module that is optically connected to the optical switch and packaged using the same structure, and a cold backup.

5. The lightweight and compact inter-satellite laser communication terminal according to claim 1, characterized in that: The first plane mirror (11), the main telescope (12), the second plane mirror (13), the fast-reflecting mirror (14), the dichroic mirror (15), the first narrowband filter (16), the beam splitter (17), the beam receiving collimator (18), the second narrowband filter (19), the tracking aiming camera (1a), the signal light emitting collimator (1b), the advance aiming mirror (1c), the shutter (1d), and the corner reflector (1e) are all encapsulated in an optical box, the optical box being made of aluminum alloy. The output end of the main telescope (12) is connected to the telescope tube, which is made of carbon fiber.

6. A lightweight, miniaturized inter-satellite laser communication terminal according to claim 1, characterized in that: The main telescope (12) includes a rotating shaft and bearing housing made of titanium alloy.

7. The lightweight and compact inter-satellite laser communication terminal according to claim 5, characterized in that: The optical box is internally connected to a fixed base, which is made of aluminum alloy.

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