CN111901032A - An integrated spaceborne optical sensor system - Google Patents

Abstract

The invention discloses an integrated spaceborne optical sensor system, comprising a visible photon system, a laser communication subsystem and a control center. Among them, the visible photonic system and the laser communication subsystem share the sensor lens. At the same time, the visible photon system is communicatively connected to the star-sensing detection module and space target detection module of the control center to achieve star-sensing attitude determination and space target situational awareness, and the laser communication subsystem is connected to the tracking control module and laser communication of the control center. The modules are communicatively connected, and the laser communication networking is realized according to the output information of the visible photonic system.

Description

An integrated spaceborne optical sensor system

technical field

The invention relates to the technical field of aerospace, in particular to an integrated spaceborne optical sensor system.

Background technique

With the rapid improvement of satellite technology, commercial aerospace and microsatellites have become more and more widely used. At the same time, in order to achieve some specific space missions, it is often necessary to arrange a group of satellites according to certain rules to form a satellite constellation. The low-orbit small constellation networking application has become the current development trend of microsatellites.

For a satellite constellation, the satellite system used in its networking needs to meet the requirements of networking, intelligence and low-cost integration. This requires that the sensors and other equipment carried by satellites are also developing towards miniaturization and integration.

High-precision attitude measurement and communication between constellations are the basis for satellite constellations to complete their tasks. One of the most commonly used sensors for satellite attitude measurement is the star sensor, and laser communication has also become a popular research field of inter-satellite communication due to its communication frequency bandwidth and strong anti-electromagnetic interference ability. However, the existing high-precision star sensors and laser communication devices are large in size and weight, and are difficult to meet the requirements of miniaturization and cost reduction.

SUMMARY OF THE INVENTION

Aiming at some or all of the problems in the prior art, the present invention provides an integrated spaceborne optical sensor system, including:

Shared optical path unit, including sensor lens and light splitting optical path unit;

a visible photonic system, including a CMOS detector, the visible photonic system is configured to receive the visible light entering through the light splitting light path unit, and convert the visible light signal into a digital image;

a laser communication subsystem, including a tracking system and a laser, the tracking system is communicatively connected to the laser for controlling the angle of the laser, and the laser is used for emitting laser light; and

Control Center, including:

a star-sensing detection module, with a built-in star table map, and the star-sensing detection module is communicatively connected with the visible photon system for determining the attitude of the satellite;

a space target detection module, connected communicatively with the visible photon system and the star-sensing detection module, for detecting the space target and determining the relative orientation of the space target;

The tracking control module is communicatively connected with the star-sensing detection module, the space target detection module and the tracking system, and is used to calculate the laser emission angle information according to the satellite attitude and relative orientation information, and to The angle information is sent to the tracker

aiming system;

The laser communication module is used to process the laser signal, and then realize the laser communication networking.

Further, the control center is an integrated chip.

Further, the visible photonic system further includes a first optical path unit, the first optical path unit is located between the common optical path unit and the CMOS detector, and is used for focusing the visible light entering through the common optical path unit on a on the target surface of the CMOS detector.

Further, the visible photon system adopts a staring imaging mode, so as to realize the detection of a wide range of space targets and space debris.

Further, the laser communication module includes a communication receiving device, a communication transmitting device and a calibration device, wherein:

The communication receiving device receives the modulated communication signal transmitted by the counterpart communication terminal;

The communication transmitting device modulates and encodes the information to be transmitted to form communication light; and

The calibration device calibrates the direction consistency of the transmitting channel and the receiving channel, so that the two are consistent.

The invention provides an integrated spaceborne optical sensor system, which integrates passive visible light imaging technology and active laser communication technology by using a miniaturized structure. It includes a visible photon system, which can realize real-time detection of space debris at a low signal-to-noise ratio through the associated detection technology when the on-orbit dim and weak moving target is high. According to numerical calculation and ground verification, the UK amount The supervision subsystem can detect space targets with a signal-to-noise ratio of 5dB, thereby increasing the detection star magnitude to 10th magnitude star @ 30ms exposure time, obtaining space target information in the field of view, and possessing the ability of situational awareness of space targets in the field of view. And the control center of the system has a built-in star table map, which can realize the star-sensing function and determine the satellite attitude. At the same time, the system also includes a laser communication subsystem, which can obtain satellite attitude information according to the visible photon system. And the relevant azimuth information of the target star, realize the inter-satellite laser communication networking, and carry out accurate tracking and communication. In terms of structure, the visible photonic system and the laser communication subsystem share the sensor lens, which realizes the fusion of multi-satellite optical equipment, effectively reduces the volume and weight of the satellite payload, and realizes the high integration of satellite sensors.

Description of drawings

In order to further clarify the above and other advantages and features of the various embodiments of the present invention, a more specific description of the various embodiments of the present invention will be presented with reference to the accompanying drawings. It is understood that these drawings depict only typical embodiments of the invention and are therefore not to be considered limiting of its scope. In the drawings, the same or corresponding parts will be denoted by the same or similar numerals for clarity.

1 shows a schematic diagram of an integrated spaceborne optical sensor system according to an embodiment of the present invention;

2 shows a schematic structural diagram of an integrated spaceborne optical sensor system according to an embodiment of the present invention;

FIG. 3 shows a structural block diagram of an integrated spaceborne optical sensor system according to an embodiment of the present invention; and

FIG. 4 shows a schematic diagram of the workflow of an integrated spaceborne optical sensor system according to an embodiment of the present invention.

Detailed ways

In the following description, the present invention is described with reference to various examples. However, one skilled in the art will recognize that the various embodiments may be practiced without one or more of the specific details or with other alternative and/or additional methods, materials or components. In other instances, well-known structures, materials, or operations are not shown or described in detail so as not to obscure the concepts of the present invention. Similarly, for purposes of explanation, specific quantities, materials and configurations are set forth in order to provide a thorough understanding of the embodiments of the invention. However, the invention is not limited to these specific details. Furthermore, it is to be understood that the various embodiments shown in the drawings are illustrative representations and have not necessarily been drawn to correct scale.

In this specification, reference to "one embodiment" or "the embodiment" means that a particular feature, structure or characteristic described in connection with the embodiment is included in at least one embodiment of the present invention. The appearances of the phrase "in one embodiment" in various places in this specification are not necessarily all referring to the same embodiment.

It should be noted that the embodiments of the present invention describe the process steps in a specific order, but this is only to illustrate the specific embodiment, rather than limiting the sequence of the steps. On the contrary, in different embodiments of the present invention, the sequence of each step can be adjusted according to the adjustment of the process.

In order to meet the development needs of satellite miniaturization, the present invention provides an integrated spaceborne optical sensor system, which integrates passive visible light imaging technology and active laser communication technology through integrated design and miniaturized structure, and has star-sensitive star detection. Attitude determination function, space target detection space debris prediction function and laser communication networking function between satellites are integrated into one. The technical solutions of the present invention will be further described below with reference to the accompanying drawings of the embodiments.

An integrated spaceborne optical sensor system, as shown in Figure 1, includes a sensor lens 001 and a sensor body 002, wherein the sensor lens 001 is used to capture light, and the sensor body 002 is arranged with a visible photon system, a laser The communication subsystem and the control center are used to process the captured light, and then realize the functions of star-sensing attitude determination, debris detection and laser communication.

As shown in FIG. 2 , the sensor lens 001 includes a primary mirror 101 and a secondary mirror 102. Through calculation, select the primary mirror and secondary mirror that meet the requirements, and assemble the sensor lens according to the calculated installation parameters. The sensor lens 001 uses It captures light including visible light and laser light and transmits it to the sensor body.

The sensor body 002 is provided with a splitting optical circuit unit 201 , a laser communication subsystem 202 , a visible photonic system 203 and a control center 204 .

The light splitting light path unit 201 and the sensor lens 001 form a common light path unit. After the light enters the sensor body 002 through the sensor lens 001, it is divided into two paths through the light splitting light path unit 201, and one path enters the laser communication subsystem 202. The other way enters the visible photon system 203 .

As shown in FIG. 3 , the visible photonic system 203 includes a detector 2031, and the visible photonic system 203 is configured to receive the visible light entering through the light splitting light path unit 201, and perform photoelectric conversion on the visible light signal to convert it into a digital signal image; in an embodiment of the present invention, the visible photonic system 203 further includes a first optical path unit 2032, the first optical path unit 2032 is located between the light splitting optical path unit 201 and the detector 2031, the The first optical path unit 2032 focuses the visible light entering through the light splitting optical path unit 201 on the target surface of the detector 2031 . In an embodiment of the present invention, the detector 2031 adopts a CMOS detector. In an embodiment of the present invention, the visible photon system 203 adopts the staring imaging mode to realize the detection of a large range of space targets and space debris. Sensitive positioning needs.

The laser communication subsystem 202 includes a tracking system 2021 and a laser 2022, the tracking system 2021 and the laser 2022 are communicatively connected, and the tracking system 2021 receives an instruction sent by the control center, controls the The angle of the laser 2022, the laser 2022 receives the parameters calculated by the control center, forms a laser that meets the requirements, and constitutes a communication transmitting device.

The control center 204 includes a star-sensing detection module 2041, a space target detection module 2042, a tracking control module 2043 and a laser communication module 2044. In an embodiment of the present invention, the control center 204 is an integrated chip, which is arranged in the Inside the sensor body, the laser communication subsystem 202 and the visible photonic system 203 are communicably connected.

The star-sensing detection module 2041 and the space target detection module 2042 are communicatively connected to the visible photonic system, and can receive digital images obtained by the visible photonic system through photoelectric conversion.

The star-sensing detection module 2041 has a built-in star table map, which first performs preliminary processing on the digital image to extract the image star target, then reads the star target position, calculates the star light observation vector in combination with the calibration parameters, and runs the star map matching algorithm Perform star matching, and finally determine the starlight inertial vector. According to the observation vector and the extreme inertial attitude matrix of the inertial vector, it is converted into an attitude quaternion to realize the determination of the satellite attitude.

The space target detection module 2042 is communicably connected to the star-sensing detection module 2041 at the same time, and can receive the satellite attitude parameters of the star-sensing detection module 2041 and the star matching result, combined with the star target information in the digital image, On the one hand, the space debris situation in the field of view can be sensed in real time, and on the other hand, the relative azimuth of the target star to be communicated can be determined. In an embodiment of the present invention, the relative azimuth includes the relative angle between the satellite and the target star.

The tracking control module 2043 and the laser communication module 2044 are communicatively connected with the laser communication subsystem 202 to jointly realize the laser communication networking function.

The tracking control module 2043 is communicatively connected with the star-sensing detection module 2041 , the space target detection module 2042 and the tracking system 2021 , and receives the satellite attitude information calculated by the star-sensing detection module 2041 , and the relative azimuth information with the target star to be communicated calculated by the space target detection module 2042, calculate the laser emission angle information, and send the angle information to the tracking system 2021; In an implementation of the present invention In an example, the angle information includes a pitch angle and an azimuth angle.

The laser communication module 2044 is used for processing laser signals, thereby realizing laser communication networking. In an embodiment of the present invention, the laser communication module 2044 includes a communication receiving device, a communication transmitting device, and a calibration device, wherein:

The communication receiving device demodulates the received modulated communication signal transmitted by the other party's communication terminal to obtain the transmitted information;

The communication transmitting device modulates and encodes the information to be transmitted, and sends it to the laser 2022 to form communication light; and

The calibration device calibrates the direction consistency of the transmitting channel and the receiving channel, so that the two are consistent.

4 shows a schematic diagram of the workflow of an integrated spaceborne optical sensor system provided by the present invention, including:

Step 401, light capture. The sensor lens 001 captures the light emitted or reflected by the space target to realize the imaging of the space target, the space target includes but is not limited to: stars, satellites, space debris, etc.; the light includes visible light and laser light, and Other infrared, ultraviolet and other light rays; after the light rays pass through the light splitting optical path unit, the visible light part enters the visible photonic system 203, and the laser light enters the laser communication subsystem 202;

Step 402, acquiring image information. Photoelectric conversion is performed on the visible light entered by the visible photonic system 203 via the spectroscope to obtain image information;

Step 403, the satellite attitude is determined. The star-sensing detection module 2041 performs matching according to the built-in star table map to determine the satellite attitude;

Step 404: Awareness of the space debris situation and determining the relative orientation of the target. The space target detection module 2042 extracts the space detection target according to the star matching result of the star-sensing detection module 2041, realizes the space debris situational awareness, and at the same time, determines the relative orientation information of the target to be communicated;

Step 405, determine the laser angle. The tracking control module 2043 calculates the pitch and azimuth angle of the laser according to the satellite attitude information and the relative orientation information of the target to be communicated, and sends it to the tracking system 2021, and the tracking system 2021 controls the laser according to the above-mentioned information. 2022 perspective; and

Step 406, perform laser communication. The laser communication module 2044 modulates and encodes the information to be transmitted to form communication light, which is emitted by the laser 2022, and at the same time, decodes the laser light entering through the splitting optical path unit, receives the information, and then realizes the inter-satellite laser communication networking .

The integrated spaceborne optical sensor system provided by the present invention integrates passive visible light imaging technology and active laser communication technology by using a miniaturized structure. It includes a visible photon system, which can realize real-time detection of space debris at a low signal-to-noise ratio through the associated detection technology when the on-orbit dim and weak moving target is high. According to numerical calculation and ground verification, the UK amount The supervision subsystem can detect space targets under the condition of a signal-to-noise ratio of 5dB, thereby increasing the detection magnitude to 10-magnitude stars@30ms exposure time, obtaining space target information in the field of view, and possessing the ability of situational awareness of space targets in the field of view. And the control center of the system has a built-in star table map, which can realize the star-sensing function and determine the satellite attitude. At the same time, the system also includes a laser communication subsystem, which can obtain satellite attitude information according to the visible photon system. And the relevant azimuth information of the target star, realize the inter-satellite laser communication networking, and carry out accurate tracking and communication. In terms of structure, the visible photonic system and the laser communication subsystem share the sensor lens, which realizes the fusion of multi-satellite optical equipment, effectively reduces the volume and weight of the satellite payload, and realizes the high integration of satellite sensors.

While various embodiments of the present invention have been described above, it should be understood that they have been presented by way of example only, and not limitation. It will be apparent to those skilled in the relevant art that various combinations, modifications and changes can be made therein without departing from the spirit and scope of the present invention. Therefore, the breadth and scope of the invention disclosed herein should not be limited by the above-disclosed exemplary embodiments, but should be defined only in accordance with the appended claims and their equivalents.

Claims (6)

1. an integrated spaceborne optical sensor system, is characterized in that, comprises: Shared optical path unit, including sensor lens and light splitting optical path unit; a visible photonic system, including a detector, the visible photonic system is configured to receive visible light entering via the light splitting light path unit and convert the visible light into a digital image; a laser communication subsystem including a tracking system and a laser, the tracking system being communicatively coupled to the laser, the tracking system being configured to be able to control the angle of the laser; and Control Center, including: a star-sensing detection module, with a built-in star table map, and the star-sensing detection module is communicatively connected with the visible photon system, and the star-sensing detection module is configured to determine the attitude of the satellite; a space target detection module, connected communicatively with the visible photon system and the star-sensing detection module, the space target detection module is configured to detect the space target and determine the relative orientation of the space target; A tracking control module is communicatively connected with the star-sensing detection module, the space target detection module and the tracking system, and the tracking control module is configured to calculate the laser light according to the satellite attitude and relative orientation The angle information of the launch, and the angle information is sent to the tracking and aiming system; The laser communication module is configured to be able to process the laser signal, thereby realizing the laser communication networking. 2 . The integrated spaceborne optical sensor system according to claim 1 , wherein the control center is an integrated chip. 3 . 3. The integrated spaceborne optical sensor system according to claim 1, wherein the controller is a CMOS controller. 4 . The integrated spaceborne optical sensor system according to claim 1 , wherein the visible photon system further comprises a first optical path unit, and the first optical path unit is located between the common optical path unit and the detector. 5 . Meanwhile, the first optical path unit is configured to focus the visible light entering through the common optical path unit on the target surface of the detector. 5 . The integrated spaceborne optical sensor system according to claim 1 , wherein the visible photon system adopts a staring imaging mode. 6 . 6. The integrated spaceborne optical sensor system according to claim 1, wherein the laser communication module comprises a communication receiving device, a communication transmitting device and a calibration device, wherein: The communication receiving device receives the modulated communication signal transmitted by the counterpart communication terminal; The communication transmitting device modulates and encodes the information to be transmitted to form communication light; and The calibration device calibrates the direction consistency of the transmitting channel and the receiving channel, so that the two are consistent.

Images