CN109974859A - The in-orbit automatic marking method of visible short infrared camera - Google Patents
The in-orbit automatic marking method of visible short infrared camera Download PDFInfo
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- CN109974859A CN109974859A CN201910125865.3A CN201910125865A CN109974859A CN 109974859 A CN109974859 A CN 109974859A CN 201910125865 A CN201910125865 A CN 201910125865A CN 109974859 A CN109974859 A CN 109974859A
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- G—PHYSICS
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- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
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Abstract
The present invention relates to a kind of in-orbit automatic marking methods of visible short infrared camera of In-flight calibration technical field, this method comprises: step 1, after satellite launch is entered the orbit, the broadcast message of " shade out ", " into shade " that the reception of visible short infrared camera is sent with rail Satellite, computational shadowgraph area duration；Step 2, satellite sends in-orbit scaling instruction to visible short infrared camera, visible short infrared camera is received again " into shade " after broadcast message, it is seen that short-wave infrared camera starts shadow region duration countdown, and is transferred to dark background measurement and internal calibration mode；Step 3, it is seen that short-wave infrared camera completes the sun before shade end of extent and calibrate preparation according to shadow region duration countdown；Step 4 completes solar radiation calibration within the sun direct irradiation satellite period, enters standby mode after the completion in the sun through solar spectrum calibration is completed in the atmosphere irradiation satellite period.The present invention can obtain accurate calibration data.
Description
Technical field
The present invention relates to In-flight calibration technical field, in particular to a kind of in-orbit auto-scaling side of visible short infrared camera
Method.
Background technique
After satellite launch is entered the orbit, the work order that camera needs to receive satellite transmission could open corresponding function.Camera
In-flight calibration is generally divided into dark background measurement, internal light source calibration, sun calibration (including solar spectrum calibration and radiation calibration)
Etc. links, in order to avoid introducing the influence of the sun or ground vapour stray light, dark background measurement, internal light source calibration need in shadow region
It carries out；When satellite has just gone out shade, sunray is incident on inside visible short infrared camera through atmosphere, can carry out sunlight
Spectrum calibration；In orbit with satellite, sunray switchs to inside directly incident visible short infrared camera, solar radiation energy
Not by Atmospheric components inhalation effects, solar radiation calibration can be carried out.Therefore, it needs to complete sun calibration beam worker before shade out
Make, is otherwise likely to miss effective sun calibration period.In order to orderly, be timely completed camera In-flight calibration, need earth station point
Triggered time and the dependent instruction of each link are not calculated, and upper note arrives satellite number pipe computer in advance.The triggered time of each link
Calculating deviation is larger or dependent instruction sends mistake, will lead to In-flight calibration mission failure；If satellite has " key " starting phase
Machine In-flight calibration function, can quickly, zero defect complete each calibration link, and on time, accurately obtain calibration data.
Through the literature search of existing technologies, Chinese invention patent 201611192370.5 discloses following content:
The in-orbit geometry calibration of satellite is the key link that Optical remote satellite realizes high-precision geometry location, directly affects satellite image
Inside and outside geometric accuracy.Although satellite can all carry out stringent Laboratory Calibration before transmission, due in emission process
Vibration, material outgassing, in orbit when image-forming condition change and device the factors such as aging influence so that satellite geometry
Imaging parameters change, and the calibration value on ground is not able to satisfy the needs of high-precision geometric manipulations, it is therefore desirable to carry out to satellite
In-orbit calibration.In order to guarantee to provide a user external positioning accuracy, Internal Geometric Accuracy, the fusion accuracy, wave band of audio and video products
Registration accuracy, it would be highly desirable to solve in-orbit this technical problem of geometry calibration of high rail level array camera high-precision.But it is visible for utilizing
The in-orbit automatic marking method of short-wave infrared camera, the prior art are not given to corresponding technology and disclose.
Summary of the invention
For the defects in the prior art, it is in-orbit automatic fixed that the object of the present invention is to provide a kind of visible short infrared cameras
Mark method, method of the invention can realize one-key start camera In-flight calibration function on satellite.
The present invention is realized by following technical solution, and it is in-orbit certainly that the present invention relates to a kind of visible short infrared cameras
Dynamic calibrating method, comprising the following steps:
Step 1, after satellite launch is entered the orbit, it is seen that short-wave infrared camera receive " shade out " sent with rail Satellite,
The broadcast message of " into shade ", computational shadowgraph area duration；
Step 2, satellite send in-orbit scaling instruction to visible short infrared camera, it is seen that short-wave infrared camera connects again
It receives " into shade " after broadcast message, it is seen that short-wave infrared camera starts shadow region duration countdown, and is transferred to dark background measurement
And internal calibration mode, enter standby mode after the completion；
Step 3, it is seen that it is fixed to complete the sun according to shadow region duration countdown before shade end of extent for short-wave infrared camera
Mark preparation；
Step 4, when shadow region duration countdown is zero, i.e. shade moment out, it is seen that short-wave infrared camera is automatically into too
Sun calibration process, and start area of illumination timing, in the sun through completion solar spectrum calibration in the atmosphere irradiation satellite period；?
Solar radiation calibration is completed in the sun direct irradiation satellite period, enters standby mode after the completion.
Preferably, in step 1, the shadow region duration, each rail need to carry out calculating and iteration.
Preferably, in step 2, the shadow region duration countdown, since the shadow region duration of adjacent two rail is differed several
Within the scope of millisecond to a few tens of milliseconds, error is negligible, and the shadow region duration that should choose a rail carries out countdown.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, the present invention provides a kind of completely new visible short infrared camera In-flight calibration methods；
2, in method of the invention, satellite only sends " visible short infrared camera In-flight calibration " instruction, it is seen that shortwave is red
Outer camera can execute entire calibration process automatically, and significantly visible short infrared camera is according to shadow region countdown,
It accurately calculates satellite and goes out shade moment, the preparation before carrying out out shade in advance, and be transferred to sun calibration process automatically, obtain
Take accurate calibration data.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is the in-orbit auto-scaling flow diagram of visible short infrared camera；
Fig. 2 is visible short infrared camera In-flight calibration crucial moment schematic diagram.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.
Embodiment
In the present embodiment, the in-orbit automatic marking method of visible short infrared camera of the present invention, comprising the following steps:
After satellite launch is entered the orbit, it is seen that the broadcast that short-wave infrared camera receives " shade out ", " into shade " that send with rail Satellite is believed
Breath, computational shadowgraph area duration；Satellite sends in-orbit scaling instruction to visible short infrared camera, it is seen that short-wave infrared camera is again
It receives " into shade " after broadcast message, it is seen that short-wave infrared camera starts shadow region duration countdown, and is transferred to dark background survey
Amount and internal calibration mode, enter standby mode after the completion；Visible short infrared camera is according to shadow region duration countdown, in yin
Sun calibration preparation is completed before terminating in shadow zone；When shadow region duration countdown is zero, i.e. shade moment out, it is seen that shortwave is red
Outer camera calibrates process automatically into the sun, and starts area of illumination timing, in the sun through complete in the atmosphere irradiation satellite period
It is calibrated at solar spectrum；Solar radiation calibration is completed within the sun direct irradiation satellite period, enters standby mode after the completion.
Present pre-ferred embodiments are provided with reference to the accompanying drawing, in order to explain the technical scheme of the invention in detail.Such as Fig. 1 institute
Show, the in-orbit automatic marking method of visible short infrared camera of the invention the following steps are included:
Step 1, after satellite launch is entered the orbit, it is seen that short-wave infrared camera receive " shade out " sent with rail Satellite,
" into shade " broadcast message, computational shadowgraph area duration；
Step 2, satellite send in-orbit scaling instruction to visible short infrared camera, it is seen that short-wave infrared camera connects again
It receives " into shade " after broadcast message, it is seen that short-wave infrared camera starts shadow region duration countdown, and is transferred to dark background measurement
And internal calibration mode, enter standby mode after the completion；
Step 3, it is seen that it is fixed to complete the sun according to shadow region duration countdown before shade end of extent for short-wave infrared camera
Mark preparation；
Step 4, when shadow region duration countdown is zero, i.e. shade moment out, it is seen that short-wave infrared camera is automatically into too
Sun calibration process, and start area of illumination timing, in the sun through completion solar spectrum calibration in the atmosphere irradiation satellite period；?
Solar radiation calibration is completed in the sun direct irradiation satellite period, enters standby mode after the completion.
Preferably, shadow region duration in the step 1, each rail need to carry out calculating and iteration.
Preferably, the shadow region duration countdown in the step 2, since the shadow region duration difference of adjacent two rail exists
Several milliseconds within the scope of a few tens of milliseconds, error is negligible, the shadow region duration progress countdown after should choosing a rail iteration.
With reference to the accompanying drawing, the present embodiment is further described, the present embodiment realizes that satellite can one-key start visible short
Infrared camera In-flight calibration function.
As shown in Fig. 2, for satellite number pipe computer according to entry/exit shadow state, every rail is red to visible short after satellier injection
Outer camera sends " into shade ", " shade out " broadcast message.Receiving " into shade " the broadcast message moment is labeled as T0, it is seen that short
Wave infrared camera internal timer 1 resets and starts timing；T1, inside meter are labeled as when receiving " shade out " broadcast message
When device 1 stop timing, it is assumed that internal timer 1 amounts to duration △ T0, shows a length of △ T0 when the shadow region of rail.Work as sunlight
Line is cut labeled as T2 when atmosphere is irradiated to satellite, and T1~T2 period can carry out solar spectrum calibration, it is assumed that satellite T1~
Solar radiation calibration can be carried out after T2 sections of operations used time △ T0 ', T2.
When needing to be implemented visible short infrared camera In-flight calibration task, it is in-orbit that satellite sends visible short infrared camera
Scaling instruction, after visible short infrared camera receives the broadcast message " into shade ", internal timer 2 is counted by △ T0
When, it is seen that different imaging parameters (time of integration, gain etc.) are arranged respectively to dark background in the power-up of short-wave infrared camera imaging circuit
Imaging；Scaling light source inside visible short infrared camera is opened after the completion, and using calibration mechanism, internal scaling light source is cut into light
Lu Zhong is arranged different imaging parameters and internal scaling light source is imaged respectively, and visible short infrared camera enters standby mould after the completion
Formula；Assuming that the sun calibrates preparation time-consuming △ T1, and when internal timer 2 becomes △ T1 from △ T0, imaging circuit power-up, if
Different imaging parameters are set dark background is imaged respectively；Stop visible short infrared camera remote sensing data transmission after the completion, using calmly
It marks mechanism to cut diffusing reflection plate in optical path, completes the sun and calibrate preparation；When 2 countdown of internal timer is 0, open
Visible short infrared camera remote sensing data transmission, it is seen that short-wave infrared camera enters solar spectrum calibration, meanwhile, internal timer
2 timing by 0.Assuming that solar spectrum calibrates used time △ T2, solar spectrum calibrates used time △ T3, when 2 timing of internal timer
Solar spectrum calibration is completed when to △ T2, stops visible short infrared camera remote sensing data transmission；When 2 timing of internal timer is arrived
Visible short infrared camera enters solar radiation calibration when △ T0 ', opens visible short infrared camera remote sensing data transmission；It is internal
2 timing of timer completes solar radiation calibration to (△ T0 '+△ T3), it is seen that short-wave infrared camera enters standby mode, completes
Rail calibrates task.
In conclusion the present invention provides a kind of completely new visible short infrared camera In-flight calibration methods；Of the invention
In method, satellite only sends " visible short infrared camera In-flight calibration " instruction, it is seen that short-wave infrared camera can execute automatically
Entire calibration process, significantly visible short infrared camera accurately calculates satellite and goes out yin according to shadow region countdown
The shadow moment, the preparation before carrying out out shade in advance, and it is transferred to sun calibration process automatically, obtain accurate calibration data.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring substantive content of the invention.
Claims (3)
1. a kind of in-orbit automatic marking method of visible short infrared camera, which comprises the following steps:
Step 1, after satellite launch is entered the orbit, it is seen that short-wave infrared camera receives " shade out " sent with rail Satellite, " into yin
The broadcast message of shadow ", computational shadowgraph area duration；
Step 2, satellite send in-orbit scaling instruction to visible short infrared camera, it is seen that short-wave infrared camera receives again
After " into shade " broadcast message, it is seen that short-wave infrared camera starts shadow region duration countdown, and be transferred to dark background measurement and it is interior
Portion's calibration mode enters standby mode after the completion；
Step 3, it is seen that it is quasi- to complete sun calibration according to shadow region duration countdown before shade end of extent for short-wave infrared camera
Standby work；
Step 4, when shadow region duration countdown is zero, i.e. shade moment out, it is seen that short-wave infrared camera is fixed automatically into the sun
Process is marked, and starts area of illumination timing, in the sun through completion solar spectrum calibration in the atmosphere irradiation satellite period；In the sun
Solar radiation calibration is completed in the direct irradiation satellite period, enters standby mode after the completion.
2. the in-orbit automatic marking method of visible short infrared camera as described in claim 1, which is characterized in that in step 1,
The shadow region duration, each rail need to carry out calculating and iteration.
3. the in-orbit automatic marking method of visible short infrared camera as described in claim 1, which is characterized in that in step 2,
The shadow region duration countdown, since the shadow region duration of adjacent two rail differs within the scope of several milliseconds to a few tens of milliseconds, accidentally
Difference is negligible, and the shadow region duration that should choose a rail carries out countdown.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112284535A (en) * | 2020-09-15 | 2021-01-29 | 中国科学院上海技术物理研究所 | Dark background removing method for progressive on-orbit push-scan type medium-short wave infrared imaging spectrometer |
| CN116907547A (en) * | 2023-09-12 | 2023-10-20 | 北京控制工程研究所 | On-orbit dynamic calibration method, device, equipment and medium for aircraft gyroscope |
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| JP4102575B2 (en) * | 2002-03-05 | 2008-06-18 | Ｎｅｃ東芝スペースシステム株式会社 | Spacecraft attitude change control device and attitude change control method |
| CN102436394A (en) * | 2011-11-15 | 2012-05-02 | 北京空间飞行器总体设计部 | Satellite entry-exit independent telemetry processing control method |
| CN105928525A (en) * | 2016-04-25 | 2016-09-07 | 航天东方红卫星有限公司 | Attitude determination method for satellite in calibration relative to moon |
| CN107315182A (en) * | 2017-05-17 | 2017-11-03 | 上海卫星工程研究所 | Passive location excitation equivalence aptitude tests method based on semi-physical simulation |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4102575B2 (en) * | 2002-03-05 | 2008-06-18 | Ｎｅｃ東芝スペースシステム株式会社 | Spacecraft attitude change control device and attitude change control method |
| CN102436394A (en) * | 2011-11-15 | 2012-05-02 | 北京空间飞行器总体设计部 | Satellite entry-exit independent telemetry processing control method |
| CN105928525A (en) * | 2016-04-25 | 2016-09-07 | 航天东方红卫星有限公司 | Attitude determination method for satellite in calibration relative to moon |
| CN107315182A (en) * | 2017-05-17 | 2017-11-03 | 上海卫星工程研究所 | Passive location excitation equivalence aptitude tests method based on semi-physical simulation |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112284535A (en) * | 2020-09-15 | 2021-01-29 | 中国科学院上海技术物理研究所 | Dark background removing method for progressive on-orbit push-scan type medium-short wave infrared imaging spectrometer |
| CN116907547A (en) * | 2023-09-12 | 2023-10-20 | 北京控制工程研究所 | On-orbit dynamic calibration method, device, equipment and medium for aircraft gyroscope |
| CN116907547B (en) * | 2023-09-12 | 2023-11-17 | 北京控制工程研究所 | On-orbit dynamic calibration method, device, equipment and medium for aircraft gyroscope |
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