CN111901032B - Integrated satellite-borne optical sensor system - Google Patents
Integrated satellite-borne optical sensor system Download PDFInfo
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- CN111901032B CN111901032B CN202010864350.8A CN202010864350A CN111901032B CN 111901032 B CN111901032 B CN 111901032B CN 202010864350 A CN202010864350 A CN 202010864350A CN 111901032 B CN111901032 B CN 111901032B
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/18521—Systems of inter linked satellites, i.e. inter satellite service
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
- G01C21/24—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 specially adapted for cosmonautical navigation
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01V—GEOPHYSICS; GRAVITATIONAL MEASUREMENTS; DETECTING MASSES OR OBJECTS; TAGS
- G01V8/00—Prospecting or detecting by optical means
- G01V8/10—Detecting, e.g. by using light barriers
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Abstract
The invention discloses an integrated satellite-borne optical sensor system which comprises a visible photon system, a laser communication subsystem and a control center. The sensor lens is shared by the visible photon system and the laser communication subsystem. Meanwhile, the visible photon system is communicably connected with the star sensitive detection module and the space target detection module of the control center to realize star sensitive attitude determination and space target situation perception, the laser communication subsystem is communicably connected with the tracking control module and the laser communication module of the control center, and laser communication networking is realized according to output information of the visible photon system.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to an integrated satellite-borne optical sensor system.
Background
With the rapid improvement of the satellite technology level, the application of commercial aerospace and microsatellites is more and more extensive, and meanwhile, in order to realize some specific space tasks, a group of satellites are often required to be arranged according to a certain rule to form a satellite constellation. The application of the low-orbit mini-constellation networking becomes the development trend of the current microsatellites.
For satellite constellations, the networking satellite system needs to meet the requirements of networking, intelligence and low-cost integration. This requires that sensors and other devices mounted on the satellite be miniaturized and integrated.
High precision attitude measurement and inter-constellation communication are the basis for satellite constellation task completion. The most common sensor for satellite attitude measurement is a star sensor, and laser communication is also a popular research field of inter-satellite communication due to the advantages of wide communication frequency band and strong anti-electromagnetic interference capability. However, the conventional high-precision star sensor and laser communication device have large volume and weight, and are difficult to meet the requirements of miniaturization and low cost.
Disclosure of Invention
Aiming at solving part or all problems in the prior art, the invention provides an integrated satellite-borne optical sensor system, which comprises:
the common light path unit comprises a sensor lens and a light splitting light path unit;
the visible photon system comprises a CMOS detector and is used for receiving the visible light entering through the light splitting light path unit and converting a visible light signal into a digital image;
the laser communication subsystem comprises a tracking system and a laser, wherein the tracking system is connected with the laser in a communication mode and used for controlling the angle of the laser, and the laser is used for emitting laser; and
a control center comprising:
the star sensitive detection module is internally provided with a constant star chart, is connected with the visible photon system in a communication way and is used for determining the satellite attitude;
the space target detection module is connected with the visible photon system and the star sensor detection module in a communication mode and used for detecting the space target and determining the relative direction of the space target;
a tracking and aiming control module which is communicably connected with the satellite sensitive detection module, the space target detection module and the tracking and aiming system and is used for calculating laser emission angle information according to the satellite attitude and relative azimuth information and sending the angle information to the tracking and aiming system
An aiming system;
and the laser communication module is used for processing the laser signal so as to realize laser communication networking.
Further, the control center is an integrated chip.
Further, the visible photon system further comprises a first light path unit, wherein the first light path unit is located between the common light path unit and the CMOS detector and is used for focusing the visible light entering through the common light path unit on the target surface of the CMOS detector.
Further, the visible photon system adopts a staring imaging mode to realize detection of large-range space targets and space debris.
Further, the laser communication module comprises a communication receiving device, a communication transmitting device and a calibration device, wherein:
the communication receiving device receives a modulated communication signal transmitted by a counterpart communication terminal;
the communication transmitting device modulates and codes information to be transmitted to form communication light; and
the calibration device calibrates the direction consistency of the transmitting channel and the receiving channel to make the direction consistency consistent.
The integrated satellite-borne optical sensor system provided by the invention utilizes a miniaturized structure to integrate a passive visible light imaging technology and an active laser communication technology. The system comprises a visible photon system, the visible photon system can realize real-time detection of space debris under a lower signal-to-noise ratio through a high-time correlated detection technology of a track dark weak moving target, according to numerical calculation and ground verification, the UK amount supervision subsystem can detect a space target under the condition that the signal-to-noise ratio is 5dB, thereby increasing the equivalence of the detection star to 10 equines @30ms exposure time, obtaining the target information in the field of view, having the capability of sensing the situation of the target in the field of view, and a constant star chart is arranged in the control center of the system, which can realize the star sensitive function and determine the satellite attitude, and simultaneously, the system also comprises a laser communication subsystem, the inter-satellite laser communication networking system can realize inter-satellite laser communication networking and carry out accurate tracking and aiming and communication according to the satellite attitude information obtained by the visible photon system and the related azimuth information of a target satellite. In the aspect of structure, the visible photon system and the laser communication subsystem share the sensor lens, so that the integration of multiple satellite-borne optical devices is realized, the volume and the weight of a satellite load are effectively reduced, and the high integration of the satellite sensor is realized.
Drawings
To further clarify the above and other advantages and features of embodiments of the present invention, a more particular description of embodiments of the present invention will be rendered by reference to the appended drawings. It is appreciated 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 reference numerals for clarity.
FIG. 1 shows a schematic diagram of an integrated on-board optical sensor system according to an embodiment of the invention;
FIG. 2 is a schematic structural diagram of an integrated satellite-borne optical sensor system according to an embodiment of the invention;
FIG. 3 is a block diagram of an integrated satellite-borne optical sensor system according to an embodiment of the invention; and
fig. 4 shows a schematic workflow diagram of an integrated satellite-borne optical sensor system according to an embodiment of the present invention.
Detailed Description
In the following description, the present invention is described with reference to examples. One skilled in the relevant art will recognize, however, that the 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 to avoid obscuring aspects of the invention. Similarly, for purposes of explanation, specific numbers, 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. Further, it should be understood that the embodiments shown in the figures are illustrative representations and are not necessarily drawn to scale.
Reference in the specification 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 invention. The appearances of the phrase "in one embodiment" in various places in the specification are not necessarily all referring to the same embodiment.
It should be noted that the embodiment of the present invention describes the process steps in a specific order, however, this is only for the purpose of illustrating the specific embodiment, and does not limit the sequence of the steps. Rather, in various embodiments of the present invention, the order of the steps may be adjusted according to process adjustments.
In order to meet the development requirement of satellite miniaturization, the invention provides an integrated satellite-borne optical sensor system which integrates a passive visible light imaging technology and an active laser communication technology by utilizing a miniaturized structure through integrated design and has the functions of detecting and positioning star-sensitive stars, detecting space debris and forecasting space debris of space targets and networking laser communication among satellites. The technical solution of the present invention is further described below with reference to the accompanying drawings of the embodiments.
An integrated satellite-borne optical sensor system is shown in fig. 1 and comprises a sensor lens 001 and a sensor main body 002, wherein the sensor lens 001 is used for capturing light, and a visible photon system, a laser communication subsystem and a control center are arranged in the sensor main body 002 and used for processing the captured light, so that functions of satellite-sensitive attitude determination, debris detection, laser communication and the like are achieved.
As shown in fig. 2, the sensor lens 001 includes a primary mirror 101 and a secondary mirror 102, the primary mirror and the secondary mirror meeting requirements are selected through calculation, the sensor lens is assembled according to the calculated installation parameters, and the sensor lens 001 is used for capturing light including visible light and laser and transmitting the light to the sensor body.
A light splitting optical path unit 201, a laser communication subsystem 202, a visible light photon system 203 and a control center 204 are arranged in the sensor body 002.
The light splitting optical path unit 201 and the sensor lens 001 form a common optical path unit, and light passes through the sensor lens 001 and enters the sensor main body 002, then passes through the light splitting optical path unit 201 and is divided into two paths, wherein one path enters the laser communication subsystem 202, and the other path enters the visible photon system 203.
As shown in fig. 3, the optical subsystem 203 includes a detector 2031, and the optical subsystem 203 is configured to receive the visible light entering via the light splitting optical path unit 201, perform photoelectric conversion on the visible light signal, and convert the visible light signal into a digital image; in an embodiment of the present invention, the optical 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, and 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 one embodiment of the present invention, the detector 2031 is a CMOS detector. In an embodiment of the invention, the visible light photon system 203 adopts a staring imaging mode to realize detection of large-range space targets and space debris, the detection star equivalence can reach 10 equistars @30ms exposure time, and the requirement of star sensitive positioning is met.
The laser communication subsystem 202 includes a tracking system 2021 and a laser 2022, the tracking system 2021 is communicably connected to the laser 2022, the tracking system 2021 receives the instruction sent by the control center to control the angle of the laser 2022, and the laser 2022 receives the parameters calculated by the control center to form a laser meeting the requirements, thereby constituting a communication transmitter.
The control center 204 includes a star sensor detection module 2041, a spatial target detection module 2042, a tracking control module 2043, and a laser communication module 2044, and in one embodiment of the present invention, the control center 204 is an integrated chip disposed in the sensor body and communicatively connected to the laser communication subsystem 202 and the visible light subsystem 203.
The star sensor detection module 2041 and the spatial object detection module 2042 are communicably connected to the visible light subsystem, and can receive digital images obtained by photoelectric conversion of the visible light subsystem.
The star-sensitive detection module 2041 is internally provided with a constant star atlas, and is configured to perform primary processing on the digital image to extract an image star target, read a star target position, calculate a star light observation vector by combining calibration parameters, perform star matching by running a star atlas matching algorithm, finally determine a star light inertial vector, convert the star light inertial vector into an attitude quaternion according to an extreme inertial attitude matrix of the observation vector and the inertial vector, and determine a satellite attitude.
The space target detection module 2042 is communicably connected to the satellite sensitive detection module 2041, and is capable of receiving satellite attitude parameters of the satellite sensitive detection module 2041 and star matching results, and in combination with the star target information in the digital image, on one hand, the space debris situation in the field of view can be sensed in real time, and on the other hand, the relative orientation of the target star to be communicated can be determined.
The tracking control module 2043 and the laser communication module 2044 are communicably connected to the laser communication subsystem 202, and jointly implement a laser communication networking function.
The tracking control module 2043 is communicably connected to the satellite-sensitive detection module 2041, the spatial target detection module 2042, and the tracking system 2021, and receives satellite attitude information calculated by the satellite-sensitive detection module 2041 and relative azimuth information of a target satellite to be communicated, calculated by the spatial target detection module 2042, calculates laser emission angle information, and sends the angle information to the tracking system 2021; in one embodiment of the invention, the angular information comprises a pitch angle and an azimuth angle.
The laser communication module 2044 is used for processing laser signals, so as to implement 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 opposite communication terminal to acquire transmitted information;
the communication transmitting device modulates and encodes information to be transmitted and transmits the information to the laser 2022 to form communication light; and
the calibration device calibrates the direction consistency of the transmitting channel and the receiving channel to make the direction consistency consistent.
Fig. 4 is a schematic work flow diagram of an integrated satellite-borne optical sensor system provided by the present invention, including:
at step 402, image information is obtained. Performing photoelectric conversion on visible light entering through a spectroscope by the visible photon system 203 to acquire image information;
in step 403, the satellite attitude is determined. The star sensor detection module 2041 performs matching according to a built-in fixed star chart to determine the satellite attitude;
and step 404, sensing the space debris situation and determining a targeted relative position. The space target detection module 2042 extracts a space detection target according to the fixed star matching result of the star sensitive detection module 2041, realizes spatial debris situation awareness, and determines targeted relative orientation information to be communicated;
at step 405, the laser angle is determined. The tracking control module 2043 calculates the pitch and azimuth angles of the laser according to the satellite attitude information and the relative azimuth information of the target to be communicated, and sends the calculated pitch and azimuth angles to the tracking system 2021, and the tracking system 2021 controls the angle of the laser 2022 according to the information; and
The integrated satellite-borne optical sensor system provided by the invention utilizes a miniaturized structure to integrate a passive visible light imaging technology and an active laser communication technology. The system comprises a visible photon system, the visible photon system can realize real-time detection of space debris under a lower signal-to-noise ratio through a high-time correlated detection technology of a track dark weak moving target, according to numerical calculation and ground verification, the UK amount supervision subsystem can detect a space target under the condition that the signal-to-noise ratio is 5dB, thereby increasing the equivalence of the detection star to 10 equines @30ms exposure time, obtaining the target information in the field of view, having the capability of sensing the situation of the target in the field of view, and a constant star chart is arranged in the control center of the system, which can realize the star sensitive function and determine the satellite attitude, and simultaneously, the system also comprises a laser communication subsystem, the inter-satellite laser communication networking system can realize inter-satellite laser communication networking and carry out accurate tracking and aiming and communication according to the satellite attitude information obtained by the visible photon system and the related azimuth information of a target satellite. In the aspect of structure, the visible photon system and the laser communication subsystem share the sensor lens, so that the integration of multiple satellite-borne optical devices is realized, the volume and the weight of a satellite load are effectively reduced, and the high integration of the satellite sensor is realized.
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 persons skilled in the relevant art that various combinations, modifications, and changes can be made thereto without departing from the spirit and scope of the invention. Thus, the breadth and scope of the present invention disclosed herein should not be limited by any of the above-described exemplary embodiments, but should be defined only in accordance with the following claims and their equivalents.
Claims (6)
1. An integrated on-board optical sensor system, comprising:
the common light path unit comprises a sensor lens and a light splitting light path unit, the sensor lens comprises a primary mirror and a secondary mirror, and the sensor lens is configured to capture visible light and laser and transmit the visible light and the laser to the light splitting light path unit;
a visible photon system including a detector, the visible photon system being configured to receive the visible light entering via the light splitting optical path unit and convert the visible light into a digital image;
a laser communication subsystem comprising a tracking system communicatively coupled with a laser, the tracking system configured to be capable of controlling an angle of the laser; and
a control center comprising:
a satellite-sensitive detection module with a built-in constant star chart and communicably connected with the visible photon system, wherein the satellite-sensitive detection module is configured to determine satellite attitude;
a spatial target detection module communicatively coupled with the visible photon system and the star sensitive detection module, the spatial target detection module configured to detect a spatial target and determine a relative orientation of the spatial target;
a tracking control module communicably connected to the satellite-sensitive detection module, the spatial target detection module, and the tracking system, the tracking control module configured to calculate angle information of laser emission according to the satellite attitude and relative orientation, and send the angle information to the tracking system;
and the laser communication module is configured to process the processing of the laser signal so as to realize laser communication networking.
2. The integrated on-board optical sensor system of claim 1, wherein the control center is an integrated chip.
3. The integrated on-board optical sensor system of claim 1, wherein the detector is a CMOS detector.
4. The integrated on-board optical sensor system of claim 1, wherein the optical photon system further comprises a first optical path unit located between the common optical path unit and the detector, the first optical path unit configured to focus visible light entering via the common optical path unit onto a target surface of the detector.
5. The integrated on-board optical sensor system of claim 1, wherein the optical photon system employs staring imaging mode.
6. The integrated satellite-borne 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 a modulated communication signal transmitted by a counterpart communication terminal;
the communication transmitting device modulates and codes information to be transmitted to form communication light; and
the calibration device calibrates the direction consistency of the transmitting channel and the receiving channel to make the direction consistency consistent.
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| CN113483699B (en) * | 2021-09-08 | 2021-12-28 | 南京英田光学工程股份有限公司 | Ground laser terminal multi-optical-axis parallel calibration method based on star sensor |
| FR3126827A1 (en) * | 2021-09-08 | 2023-03-10 | Airbus Defence And Space Sas | Method for transmitting data by a spacecraft comprising a laser emission module |
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