Highly Reliable Space Optical Transmission Device in the Cabin under Dynamic Rotation Conditions

Abstract

A high-reliability in-cabin space optical transmission device based on dynamic rotation conditions belongs to the field of wireless high-speed optical communication technology. To solve the problems of large dynamic deviation of the optical axis and low optical coupling efficiency in the existing technology for wireless optical signal transmission between cabins, the device includes a payload cabin, a platform cabin, and a laser, a transmitting single-mode optical fiber, a first glass tube, a first pressure relief device, a first aspherical lens, a second aspherical lens, a second pressure relief device, a second glass tube, a receiving single-mode optical fiber, and an optical amplifier that are coaxially arranged in sequence; the payload cabin and the platform cabin do not contact each other; the laser, the transmitting single-mode optical fiber, the first glass tube, the first pressure relief device, and the first aspherical lens are arranged in the payload cabin; the second aspherical lens, the second pressure relief device, the second glass tube, the receiving single-mode optical fiber, and the optical amplifier are arranged in the platform cabin; in the present invention, when the payload cabin rotates dynamically, the energy attenuation of the optical system is reduced, and the power fluctuation is weakened, effectively improving the efficiency and stability of space optical transmission.

Description

Technical Field

[0001] The present invention belongs to the technical field of wireless high-speed optical communication, and particularly relates to a highly reliable in-cabin space optical transmission device under dynamic rotation conditions. Background Art

[0002] In recent years, with the continuous development of space technology, related satellite remote sensing, observation, and communication fields have flourished. Satellites obtain more and more data, and on-board systems are faced with the problem of real-time data transmission of up to gigabit levels within the system. Compared with the traditional microwave signal transmission mode, fiber optic communication has become one of the main solutions for in-cabin data transmission due to its advantages such as high bandwidth, low power consumption, and strong anti-interference ability. As the functions integrated in on-board systems become more diverse, fixed payload cabins are gradually upgraded to rotatable modes, enabling different terminals to work simultaneously. However, the dynamic relationship between the payload cabin and the platform cabin during their relative movement also increases the difficulty of high-speed information transmission between the two cabins. As fixed connection methods, microwave cables and optical fibers are very susceptible to the relative movement between the cabins, resulting in a decline in signal quality. The wireless optical information transmission mode inherits the advantage of high-speed transmission of fiber optic communication and avoids the increase in bit error rate caused by the change in the mode of the optical signal in the fiber due to the stress generated by the relative movement between the two cabins.

[0003] The payload cabin rotates relative to the platform cabin. During the rotation process, the optical axis of the payload cabin will deviate. This deviation includes the translation deviation and angular deviation of the optical axis. Among them, the angular deviation of the optical axis starts from the center of the shafting at a certain distance behind the bearing. As the length of the bearing increases and the payload weight increases, the optical axis deviation during the rotation of the payload cabin will show violent fluctuations. The traditional space optical transmission scheme uses a symmetric optical system to achieve near-parallel light transmission and converges into a Gaussian-distributed light spot on the receiving target surface. The energy is mainly concentrated at the center position of the light spot. This method can obtain the best coupling efficiency through high-precision alignment under static conditions. However, under the dynamic rotation of the payload cabin, the light beam emitted by the payload cabin is affected by the optical axis deviation between the cabins, and only part of the light spot can enter the target surface, resulting in extremely large and violent fluctuations in the light intensity loss of the device.

[0004] The Chinese patent application number is "202210116019.7", and the patent name is "Ultra-high-speed and highly reliable wireless optical communication device between cabins for multiple data under dynamic conditions". It describes an in-cabin high-speed wireless laser communication device that uses a conventional collimator to achieve space optical signal transmission. However, this device does not consider the relative optical axis dynamic error between cabins under dynamic conditions. Under the rotating state of the system, the optical power of the communication system will show large fluctuations, reducing the communication quality of the system and making the reliability of this scheme decrease in actual use. Summary of the Invention

[0005] In order to solve the problems of large dynamic deviation of the optical axis and low optical coupling efficiency in the wireless optical signal transmission between compartments in the prior art, the present invention proposes a highly reliable in-cabin space optical transmission device based on dynamic rotation conditions.

[0006] The technical solution of the present invention to solve the problems is as follows:

[0007] A highly reliable in-cabin space optical transmission device based on dynamic rotation conditions, the device includes a payload compartment, a platform compartment, and a laser, a transmitting single-mode optical fiber, a glass tube 1, a pressure relief valve 1, an aspherical lens 1, an aspherical lens 2, a pressure relief valve 2, a glass tube 2, a receiving single-mode optical fiber, and an optical amplifier arranged coaxially in sequence;

[0008] The payload compartment and the platform compartment do not contact each other;

[0009] The payload compartment is provided with a laser, a transmitting single-mode optical fiber, a glass tube 1, a pressure relief valve 1, and an aspherical lens 1;

[0010] The platform compartment is provided with an aspherical lens 2, a pressure relief valve 2, a glass tube 2, a receiving single-mode optical fiber, and an optical amplifier;

[0011] The laser is connected to the glass tube 1 by fusion splicing through the transmitting single-mode optical fiber; the pressure relief valve 1 is placed at the front end of the glass tube 1; the aspherical lens 1 is placed at the front end of the pressure relief valve 1; the aspherical lens 2 is placed in front of the aspherical lens 1; the pressure relief valve 2 is placed at the front end of the aspherical lens 2; the glass tube 2 is placed at the front end of the pressure relief valve 2; the glass tube 2 is connected to the receiving single-mode optical fiber by fusion splicing, and the receiving single-mode optical fiber and the optical amplifier are connected by a flange.

[0012] The laser beam emitted by the laser is filtered by the transmitting single-mode optical fiber and then outputs a single-mode Gaussian spot beam, which reaches the pressure relief valve 1 after passing through the glass tube 1. The pressure relief valve 1 forms a vacuum layer by discharging the internal air. The beam reaches the aspherical lens 1 through the pressure relief valve 1, and the beam is converged by the aspherical lens 1. The beam emitted by the aspherical lens 1 forms a defocused spot on the incident surface of the receiving single-mode optical fiber after passing through the aspherical lens 2, the pressure relief valve 2, and the glass tube 2. The central energy of the defocused spot is dispersed to the surrounding; the beam enters the optical amplifier through the receiving single-mode optical fiber for processing.

[0013] The beneficial effects of the present invention are:

[0014] In the present invention, the transmitting optical system adopts a converging optical structure, and the receiving optical system adopts a diverging optical structure. When the payload cabin rotates, by adjusting the energy distribution of the transmitted light beam between the payload cabin and the platform cabin, the optimization of the spot size on the receiving target surface in the platform cabin is achieved. At the receiving end of the optical system in the present invention, by adjusting the position of the receiving end face of the single-mode fiber, an optical defocus amount is introduced into the system, so that the spot energy at the receiving target surface position generates a homogenizing effect, the energy attenuation of the optical system during the dynamic rotation of the payload cabin is reduced, the power fluctuation is weakened, and the efficiency and stability of space light transmission are effectively improved. Brief Description of the Drawings

[0015] Figure 1 FIG. 1 is a schematic diagram of the high-reliability space light transmission device in the cabin based on the dynamic rotation condition of the present invention;

[0016] Figure 2 FIG. 2 is a schematic diagram of the actual working state of the device when the payload cabin of the present invention rotates;

[0017] FIG. 3 is a comparison diagram of the space light coupling efficiency between the prior art and the present invention, where 3(a) is a schematic diagram of the space light coupling efficiency of the existing space light transmission device, and 3(b) is a schematic diagram of the space light coupling efficiency of the present invention. Detailed Description of the Embodiments

[0018] The present invention will be further described in detail below with reference to the drawings.

[0019] As Figure 1 shown, a high-reliability space light transmission device in the cabin based on the dynamic rotation condition includes a payload cabin 1, a platform cabin 2, and a laser 3, a transmitting single-mode fiber 4, a first glass tube 5, a first pressure relief device 6, a first aspherical lens 7, a second aspherical lens 8, a second pressure relief device 9, a second glass tube 10, a receiving single-mode fiber 11, and an optical amplifier 12 arranged coaxially in sequence.

[0020] The payload cabin 1 and the platform cabin 2 do not contact each other.

[0021] The payload cabin 1 is provided with a laser 3, a transmitting single-mode fiber 4, a first glass tube 5, a first pressure relief device 6, and a first aspherical lens 7 as a transmitting optical system, and they are all connected to the payload cabin 1 through mechanical tooling.

[0022] The platform cabin 2 is provided with a second aspherical lens 8, a second pressure relief device 9, a second glass tube 10, a receiving single-mode fiber 11, and an optical amplifier 12 as a receiving optical system, and they are all connected to the platform cabin 2 through mechanical tooling.

[0023] The laser 3 is connected to the first glass tube 5 by fusion splicing through a single-mode fiber 4 for emission; a first pressure relief device 6 is placed at the front end of the first glass tube 5; an aspheric lens 7 is placed at the front end of the first pressure relief device 6; an aspheric lens 8 is placed in front of the aspheric lens 7; a second pressure relief device 9 is placed at the front end of the aspheric lens 8; a second glass tube 10 is placed at the front end of the second pressure relief device 9; the second glass tube 10 is connected to a receiving single-mode fiber 11 by fusion splicing, and the receiving single-mode fiber 11 is connected to an optical amplifier 12 through a flange.

[0024] The working process of the present invention is as follows:

[0025] The laser emitted by the laser 3 is filtered by the single-mode fiber 4 for emission and then outputs a single-mode Gaussian spot beam. After being transmitted through the first glass tube 5, it reaches the first pressure relief device 6. The first pressure relief device 6 forms a vacuum layer by discharging the internal air. The beam reaches the aspheric lens 7 after passing through the first pressure relief device 6, and the beam is converged by the aspheric lens 7. The beam emitted from the aspheric lens 7 forms a defocused spot at the incident surface of the receiving single-mode fiber 11 after passing through the aspheric lens 8, the second pressure relief device 9, and the second glass tube 10. The central energy of the defocused spot is dispersed to the surrounding; this beam enters the optical amplifier 12 through the receiving single-mode fiber 11 for processing.

[0026] Embodiment:

[0027] The focal length of the aspheric lens 7 is 11 mm, and the distance from the first end of the first glass tube 5 to the incident surface of the aspheric lens 7 is 11.15 mm.

[0028] The focal length of the aspheric lens 8 is 9 mm. The output surface of the aspheric lens 8 is the vacuum medium generated by the second pressure relief device 9. Behind the second pressure relief device 9 is the second glass tube 10. The distance from the output surface of the aspheric lens 8 to the end of the second glass tube 10 is 8.87 mm.

[0029] As Figure 2 As shown, when the payload compartment 1 rotates, affected by inertia and mechanical vibration noise, the optical axes of the payload compartment 1 and the platform compartment 2 will undergo periodic offset and deflection. When the optical signal emitted by the laser 3 in the payload compartment 1 passes through the single-mode fiber 4 for emission, the first glass tube 5, the first pressure relief device 6, and the aspheric lens 7, the emitted beam cannot be aligned with the center of the aspheric lens 8 when it reaches the aspheric lens 8. After the beam passes through the aspheric lens 8, the second pressure relief device 9, and the second glass tube 10, a spot is formed at the incident end face of the receiving single-mode fiber 11. The size of the spot is larger than the fiber end face of the receiving single-mode fiber 11, and the spot shows periodic jitter. When the spot jitters, most of the optical energy can still be transmitted through the receiving single-mode fiber 11 to the optical amplifier 12 for optical amplification and processing.

[0030] As shown in Figure 3, the relative positions of the payload compartment 1 and the platform compartment 2 are as Figure 2When rotating under the conditions shown, a comparison of the beam cross-sections at the end face of the receiving single-mode fiber between the present invention and the existing space optical transmission device. The existing space optical transmission device is shown in Fig. 3(a). This device uses a symmetric optical system, and the focus of the optical system is located at the end face of the receiving single-mode fiber. When the payload module offsets or deflects relative to the platform module, the light intensity distribution at the end face is elliptical, and a large amount of light energy deviating from the center position cannot enter the receiving single-mode fiber, and its system coupling efficiency is only about 6.6%. As shown in Fig. 3(b), the solution of the present invention uses the optical system of the payload module to emit a beam with a certain degree of convergence, and the optical system of the platform module receives it in a large field-of-view mode. The light intensity distribution at the end face is nearly circular, effectively increasing the light energy entering the receiving single-mode fiber, and its system coupling efficiency reaches about 53.2%. Therefore, the space optical coupling efficiency of the present invention under dynamic rotation conditions is improved by 46.6% compared with the prior art.

Claims

1. A highly reliable in-cabin space optical transmission device under dynamic rotation conditions, characterized in that The device comprises a payload cabin (1) and a platform cabin (2), and a laser (3), a transmitting single-mode optical fiber (4), a first glass tube (5), a first pressure relief device (6), a first aspheric lens (7), a second aspheric lens (8), a second pressure relief device (9), a second glass tube (10), a receiving single-mode optical fiber (11) and an optical amplifier (12) which are coaxially arranged in sequence. The load cabin (1) and the platform cabin (2) do not contact each other; The payload cabin (1) is provided with a laser (3), a transmitting single-mode optical fiber (4), a glass tube (5), a pressure relief device (6) and an aspheric lens (7); The platform cabin (2) is provided with two aspherical lenses (8), two pressure relief devices (9), two glass tubes (10), a receiving single-mode optical fiber (11) and an optical amplifier (12); The laser (3) is connected to the glass tube (5) by fusion splicing through the transmitting single-mode optical fiber (4); the pressure relief device (6) is placed at the front end of the glass tube (5); the aspheric lens (7) is placed at the front end of the pressure relief device (6); the aspheric lens (8) is placed in front of the aspheric lens (7); the pressure relief device (9) is placed at the front end of the aspheric lens (8); the glass tube (10) is placed at the front end of the pressure relief device (9); the glass tube (10) is connected to the receiving single-mode optical fiber (11) by fusion splicing, and the receiving single-mode optical fiber (11) is connected to the optical amplifier (12) by flange. When the payload cabin (1) rotates, the optical axes of the payload cabin (1) and the platform cabin (2) will be periodically offset and deflected due to the influence of inertia and mechanical vibration noise, so that the optical signal emitted by the laser (3) in the payload cabin (1) passes through the transmitting single-mode optical fiber (4), the glass tube (5), the pressure relief device (6), and the aspheric lens (7). When the emitted light beam reaches the aspheric lens (8), it cannot be aligned with its center; After the light beam passes through the second aspheric lens (8), the second pressure relief device (9), and the second glass tube (10), a light spot is formed at the incident end face of the receiving single-mode optical fiber (11). The light spot size is larger than the optical fiber end face of the receiving single-mode optical fiber (11), and the light spot shows periodic beating. When the light spot is beating, most of the light energy can still be transmitted to the optical amplifier (12) through the receiving single-mode optical fiber (11) for light amplification and processing.

2. The high-reliability in-cabin space optical transmission device based on dynamic rotation conditions according to claim 1, wherein The laser (3), the emitting single-mode optical fiber (4), the glass tube (5), the pressure relief device (6) and the aspheric lens (7) are all connected to the load compartment (1) through mechanical tooling.

3. The high-reliability in-cabin space optical transmission device based on dynamic rotation conditions according to claim 1, wherein The second aspheric lens (8), the second pressure relief device (9), the second glass tube (10), the receiving single-mode optical fiber (11) and the optical amplifier (12) are all connected to the platform cabin (2) through mechanical tooling.

4. The highly reliable in-cabin space optical transmission device based on dynamic rotation conditions according to claim 1, characterized in that, The laser beam emitted by the laser (3) is filtered by the transmitting single-mode optical fiber (4) and then outputs a single-mode Gaussian spot beam. After being transmitted through the first glass tube (5), it reaches the first pressure relief device (6). The first pressure relief device (6) forms a vacuum layer by discharging the internal air. The light beam reaches the first aspherical lens (7) after passing through the first pressure relief device (6). The light beam is converged by the first aspherical lens (7). The light beam emitted from the first aspherical lens (7) forms a defocused light spot on the incident surface of the receiving single-mode optical fiber (11) after passing through the second aspherical lens (8), the second pressure relief device (9), and the second glass tube (10). The central energy of the defocused light spot is dispersed to the surroundings. Then, the light beam enters the optical amplifier (12) through the receiving single-mode optical fiber (11) for processing.

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