CN108833749B - Micro-engineering monitoring device mounted on spacecraft solar wing - Google Patents
Micro-engineering monitoring device mounted on spacecraft solar wing Download PDFInfo
- Publication number
- CN108833749B CN108833749B CN201810620303.1A CN201810620303A CN108833749B CN 108833749 B CN108833749 B CN 108833749B CN 201810620303 A CN201810620303 A CN 201810620303A CN 108833749 B CN108833749 B CN 108833749B
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- solar wing
- monitoring device
- structural shell
- spacecraft
- engineering monitoring
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N23/00—Cameras or camera modules comprising electronic image sensors; Control thereof
- H04N23/50—Constructional details
- H04N23/55—Optical parts specially adapted for electronic image sensors; Mounting thereof
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
- F16M13/00—Other supports for positioning apparatus or articles; Means for steadying hand-held apparatus or articles
- F16M13/02—Other supports for positioning apparatus or articles; Means for steadying hand-held apparatus or articles for supporting on, or attaching to, an object, e.g. tree, gate, window-frame, cycle
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Multimedia (AREA)
- Signal Processing (AREA)
- Closed-Circuit Television Systems (AREA)
- Studio Devices (AREA)
Abstract
The invention discloses an engineering monitoring device installed on a spacecraft solar wing, which comprises an imaging module, a circuit module, an electric connector, a structural shell and an installation lug, wherein the imaging module is arranged on the solar wing; the imaging module is arranged on the front side of the structural shell, comprises an optical lens and an image acquisition and coding assembly and is used for acquiring an optical image; the circuit module is arranged in the structural shell and used for finishing the functions of data storage and data transmission, internal power supply and the like; the electric connector is arranged on the front side of the structural shell, is positioned below the imaging module and is used for connecting a power supply cable and a data interaction cable; the structural shell is fixedly connected with the solar wing through a group of mounting lugs, and the mounting lugs are mounted at the lower bottom end of the structural shell. The invention adopts a micro optical monitoring technology to acquire optical images in real time, can be used for judging the unfolding condition of the solar wing and realizes the engineering state monitoring of the spacecraft after the solar wing is unfolded.
Description
Technical Field
The invention relates to an engineering monitoring device, in particular to a monitoring device which is arranged on a spacecraft solar wing and is used for monitoring the engineering state of a spacecraft.
Background
The optical imaging technology is widely applied to various monitoring fields due to intuitive effect. At present, most of the on-orbit operation states of the spacecraft are judged by remote measurement of analog quantity, temperature quantity, digital quantity and the like of each device on the spacecraft, the working conditions of key parts inside the devices on the spacecraft can be effectively judged by the judging methods, but key actions on the spacecraft, such as the execution processes and conditions of firework unlocking, driving mechanisms and the like, cannot be intuitively reflected. The optical imaging monitoring is carried out on the key actions and key equipment of the spacecraft by utilizing the engineering monitoring device, so that the requirement can be effectively solved.
Disclosure of Invention
The invention aims to provide an engineering monitoring device arranged on a spacecraft solar wing, which can realize the monitoring of the unfolding state of the solar wing by acquiring an engineering monitoring image in an optical imaging mode and perform imaging monitoring on a spacecraft body after the solar wing is unfolded in place.
The invention solves the technical problems through the following technical scheme: an engineering monitoring device mounted on a spacecraft solar wing comprises an imaging module, a circuit module, an electric connector, a structural shell and a mounting lug; the imaging module is arranged on the front side of the structural shell, comprises an optical lens and an image acquisition and coding assembly and is used for acquiring an optical image; the circuit module is arranged in the structural shell and used for finishing the functions of data storage and data transmission, internal power supply and the like; the electric connector is arranged on the front side of the structural shell, is positioned below the imaging module and is used for connecting a power supply cable and a data interaction cable; the structural shell is fixedly connected with the solar wing through a group of mounting lugs, and the mounting lugs are mounted at the lower bottom end of the structural shell.
Preferably, the size of the mounting lug can be adjusted according to the size of the reserved space on the solar wing, and the distance between the two lugs is adjusted according to the thickness of the solar wing sail plate.
Preferably, two through holes are formed in the mounting lugs, two mounting holes are reserved in the corresponding positions of the solar wing sailboards, and the engineering monitoring device is clamped in the corresponding positions of the solar wing sailboards during mounting and is fixed through two groups of screws and nuts.
Preferably, the engineering monitoring device is powered before the solar wing is unfolded to acquire an image of the solar wing in the unfolding process, so as to judge the unfolding condition of the solar wing.
Preferably, the power supply of the engineering monitoring device is switched on and off by the spacecraft body through the electric connector through the cable.
Preferably, the data interaction between the engineering monitoring device and the spacecraft body, such as the imaging parameter adjustment instruction, the acquired image data and the like, is realized through a cable and an electric connector.
The invention has the following beneficial effects:
1) the invention adopts the miniature imaging module to realize dynamic optical imaging, image data acquisition and encoding, meets the imaging requirement and has the advantages of small volume and low power consumption.
2) Through reasonable optimization of the installation position, the images of the key parts of the spacecraft body can be realized after the solar wings are unfolded in place, and continuous real-time monitoring is carried out on the images.
3) Whether the solar wing is unfolded normally can be reflected through the image change of the monitoring device in the process of unfolding the solar wing.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic diagram of an engineering survey apparatus according to the present invention.
Fig. 2 is a schematic view of the present invention mounted on a solar wing.
Detailed Description
The following provides a detailed description of the preferred embodiments of the present invention with reference to the accompanying drawings. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications can be made by persons skilled in the art without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1, the micro-engineering monitoring device mounted on the solar wing of the spacecraft of the present invention includes a structural shell 1, an imaging module 2, a circuit module, an electrical connector 3, and a mounting lug 4. The structure shell 1 is a bearing structure of an engineering monitoring device and is fixedly connected with the solar wing through a group of mounting lugs; the imaging module 2 is arranged on the front side of the structural shell, comprises an optical lens and an image acquisition and coding assembly and is used for acquiring an optical image; the circuit module is arranged in the structural shell 1 to complete the functions of storage and transmission of image data acquired by the imaging module 2, internal power supply and the like; the electric connector 3 is arranged on the front side of the structural shell, is positioned below the imaging module and is used for connecting the power supply and data interaction cable 6 between the engineering monitoring device and the spacecraft; the same through holes are reserved on the two mounting lugs 4 for mounting the engineering monitoring device.
As shown in fig. 2, the micro-engineering monitoring device installed on the sun wing of the spacecraft is clamped on a sun wing sailboard 5 through an installation lug 4 and is fastened through two groups of screws and nuts 7. And (3) a mounting area is reserved on the proper position of the solar wing sailboard 5 by combining with the specific monitoring requirement design, and a mounting hole is reserved.
As shown in fig. 2, the micro-engineering monitoring device installed on the solar wing of the spacecraft of the invention performs power supply and data interaction with the spacecraft through the electric connector 3 and the cable 6. The power supply and the power supply control of the engineering monitoring device are completed by the spacecraft. Imaging control and working parameter adjustment of the engineering monitoring device are provided to the engineering monitoring device by the spacecraft through the cable 6 and the electric connector 3; the image data and the telemetering data of the engineering monitoring device are transmitted to the spacecraft through the electric connector 3 and the cable 6.
The above embodiments are described in further detail to solve the technical problems, technical solutions and advantages of the present invention, and it should be understood that the above embodiments are only examples of the present invention and are not intended to limit the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (1)
1. The micro-engineering monitoring device is arranged on a spacecraft solar wing and is characterized by comprising an imaging module, a circuit module, an electric connector, a structural shell and a mounting lug; the imaging module is arranged on the front side of the structural shell, comprises an optical lens and an image acquisition and coding assembly and is used for acquiring an optical image; the circuit module is arranged in the structural shell and used for finishing the functions of data storage and data transmission and internal power supply; the electric connector is arranged on the front side of the structural shell, is positioned below the imaging module and is used for connecting a power supply cable and a data interaction cable; the structure shell is fixedly connected with the solar wing through a group of mounting lugs, and the mounting lugs are mounted at the lower bottom end of the structure shell;
the size of the mounting lug can be adjusted according to the size of a reserved space on the solar wing, and the distance between the two lugs is adjusted according to the thickness of the solar wing sail plate;
the mounting lug is provided with two through holes, two mounting holes are reserved at the corresponding positions of the solar wing sailboard, and the engineering monitoring device is clamped at the corresponding positions of the solar wing sailboard during mounting and is fixed through two groups of screws and nuts;
the engineering monitoring device is powered up before the solar wing is unfolded to obtain an image in the unfolding process of the solar wing so as to judge the unfolding condition of the solar wing;
the power supply on-off of the engineering monitoring device is realized by the spacecraft body through a cable and an electric connector;
the data interaction between the engineering monitoring device and the spacecraft body is realized through a cable and an electric connector.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810620303.1A CN108833749B (en) | 2018-06-15 | 2018-06-15 | Micro-engineering monitoring device mounted on spacecraft solar wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810620303.1A CN108833749B (en) | 2018-06-15 | 2018-06-15 | Micro-engineering monitoring device mounted on spacecraft solar wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108833749A CN108833749A (en) | 2018-11-16 |
| CN108833749B true CN108833749B (en) | 2020-11-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810620303.1A Active CN108833749B (en) | 2018-06-15 | 2018-06-15 | Micro-engineering monitoring device mounted on spacecraft solar wing |
Country Status (1)
| Country | Link |
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| CN (1) | CN108833749B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109714507A (en) * | 2018-12-27 | 2019-05-03 | 深圳阜时科技有限公司 | A kind of imaging device and equipment |
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| CN102384832A (en) * | 2011-09-28 | 2012-03-21 | 华南理工大学 | Vibration measurement device of hinged flexible board structure with rotary center and control method thereof |
| CN103699068A (en) * | 2013-12-06 | 2014-04-02 | 上海卫星工程研究所 | Wireless communication node system for monitoring vibration of solar array of satellite |
| CN204795292U (en) * | 2015-07-10 | 2015-11-18 | 六安市科宇专利技术开发服务有限公司 | Cigarette camera is felt in corridor control |
| CN107038310A (en) * | 2017-04-20 | 2017-08-11 | 航天东方红卫星有限公司 | A kind of image-forming module selection method for satellite visual inspection |
| JP2018043617A (en) * | 2016-09-14 | 2018-03-22 | 三菱電機株式会社 | Spacecraft payload monitoring device |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7604198B2 (en) * | 2003-09-25 | 2009-10-20 | Petersen Bruce L | Rotorcraft having coaxial counter-rotating rotors which produce both vertical and horizontal thrust and method of controlled flight in all six degrees of freedom |
| US20090099761A1 (en) * | 2007-10-11 | 2009-04-16 | Genpower, Inc. | Wireless, battery-powered, photovoltaically charged and monitored runway-based aircraft identification system and method |
| US9094592B2 (en) * | 2011-11-15 | 2015-07-28 | Lg Innotek Co., Ltd. | Camera module with foreign objects inhibiting structure |
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2018
- 2018-06-15 CN CN201810620303.1A patent/CN108833749B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102384832A (en) * | 2011-09-28 | 2012-03-21 | 华南理工大学 | Vibration measurement device of hinged flexible board structure with rotary center and control method thereof |
| CN103699068A (en) * | 2013-12-06 | 2014-04-02 | 上海卫星工程研究所 | Wireless communication node system for monitoring vibration of solar array of satellite |
| CN204795292U (en) * | 2015-07-10 | 2015-11-18 | 六安市科宇专利技术开发服务有限公司 | Cigarette camera is felt in corridor control |
| JP2018043617A (en) * | 2016-09-14 | 2018-03-22 | 三菱電機株式会社 | Spacecraft payload monitoring device |
| CN107038310A (en) * | 2017-04-20 | 2017-08-11 | 航天东方红卫星有限公司 | A kind of image-forming module selection method for satellite visual inspection |
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| CN108833749A (en) | 2018-11-16 |
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