CN101915924A - Normal-temperature infrared inner satellite imaging detector - Google Patents
Normal-temperature infrared inner satellite imaging detector Download PDFInfo
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- CN101915924A CN101915924A CN 201010146278 CN201010146278A CN101915924A CN 101915924 A CN101915924 A CN 101915924A CN 201010146278 CN201010146278 CN 201010146278 CN 201010146278 A CN201010146278 A CN 201010146278A CN 101915924 A CN101915924 A CN 101915924A
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Abstract
The invention discloses a normal-temperature infrared inner satellite imaging detector, suitable for detecting an inner satellite and belonging to the technical fields of spacecraft systems and measuring instruments. For detecting an inner satellite in a closed small-size space, the invention provides a far-infrared wave band-based infrared imaging detector system which comprises a short-focus lens, an infrared focal plane array of a non-refrigeration type, a data acquisition circuit and an image data processing unit, wherein the short-focus lens is suitable for imaging an object at a distance of 100-500 mm in a waveband of 8-12 mu m, and the infrared focal plane array of the non-refrigeration type working in the far-infrared waveband can induce a hot source at a normal temperature. Under the conditions of being independent of a light source and a temperature reference chip, the invention can realize the infrared imaging of a movable object under a satellite-borne small-size closed environment.
Description
Technical field
The invention belongs to Space Vehicle System and Infrared survey technical field, relate in particular to a kind of detector of the far infrared radiation imaging that satellite is launched naturally in the utilization under normal temperature environment.
Background technology
Interior formation satellite system is a kind of mode that gravity field is measured, and the relative position of satellite in wherein with outer satellite carried out accurately measuring in real time, is one of key that realizes interior formation task.
The Infrared survey method is a kind of feasible means of relative position measurement.The DeHoff R L of Stanford University proposes to adopt ultraviolet ray excited checking quality (proofmass in 1975 PhD dissertation " Minimum thrusters control of a spinning drag-free satellite; including the design of a largecavity optical sensor (spin non-resistance satellite low thrust control---the big cavity optical sensor design of the opinion of holding concurrently) ", aforementioned in satellite also be a kind of checking quality) on phosphor coating, thereby and receive the position that the infrared ray emit is measured the checking quality with the fence diode, precision reaches the mm level.The infrared ray that this method is used is in short infrared band.Interior formation system works is under normal temperature (300K), and the infrared ray of emission mainly is distributed in the far infrared band of 8～12 μ m, and above-mentioned detection means is inapplicable.
Infrared detection system comprises weather satellite, environment exploration, military surveillance, astronomical sight etc. in spaceborne application, " current situation of space flight infrared eye and progress " that Gong Haimei delivered on " infrared and laser engineering " in 2008 summed up this, point out that present space flight infrared eye uses the cryogenic cooling design mostly, working temperature is at 70～200K.Because the radiometer effect that the big temperature difference is brought in interior formation task need be avoided, so refrigeration type detector is inapplicable.The detector of non-refrigeration type is very rare in spaceborne application, and its operation wavelength is the above very long wave wave band of 15 μ m.In addition, interior formation task comprises the requirement of infrared acquisition: with great visual angle, flash is dark, and detector is realized fixing signal to noise ratio (S/N ratio) in less dynamic range; This and space flight infrared eye commonly used to neglect rink corner, the long depth of field, great dynamic range and change signal to noise ratio (S/N ratio) be totally different.
Though the universal thermal imaging system product that is operated in long infrared band at present is comparative maturity, because its versatility causes volume, power consumption and weight all bigger than normal, the formation task is to the demand of embedded design in can not satisfying far away.
Summary of the invention
Thereby the object of the present invention is to provide satellite is launched under normal temperature condition naturally in a kind of can the utilization far infrared radiation imaging detect in the normal-temperature infrared inner satellite imaging detector of satellite relative position.
To achieve these goals, the technical solution used in the present invention is as follows:
Normal-temperature infrared inner satellite imaging detector of the present invention, comprise nearly burnt far infrared camera lens, far infrared band focal plane arrays (FPA) and image data samples circuit, described nearly burnt far infrared camera lens and the far infrared band focal plane arrays (FPA) formation camera lens-focal plane array column unit that is connected, described image data samples circuit is connected with image data processing unit and constitutes circuit unit, and the image data samples circuit in the described circuit unit is connected by cable with far infrared band focal plane arrays (FPA) in camera lens-focal plane array column unit.
Preferably, described camera lens and focal plane array column unit are installed in the shell, the aluminum metal sealing that described shell is all handled through blackout with inside surface except that the cable interface of rear end.
Preferably, be connected with Aviation Connector between described far infrared band focal plane arrays (FPA) and the cable, adopt the silica gel sealing around the described Aviation Connector 4, silica gel degree of depth L is greater than 3 times of opening size D.
Preferably, described nearly burnt far infrared camera lens adopts that field angle 90 degree are above, the depth of field is the tight shot of 100～500mm, and fixes with described far infrared band focal plane arrays (FPA) relative distance.
Preferably, it is characterized in that: described far infrared band focal plane array is classified the non-refrigeration type infrared focal plane array that is operated in far infrared band as.
Preferably, described image data samples circuit is made up of sequential generating unit, AD sampling unit, reference voltage array, described CPLD produces described far infrared band focal plane array image-forming and the required sequential of difference input AD sampling unit, described reference voltage array produces required reference voltage of described far infrared band focal plane arrays (FPA) and required common mode voltage and the reference voltage of described difference input AD sampling unit, and described AD sampling unit is connected to described far infrared band focal plane arrays (FPA).
Preferred, described sequential generating unit adopts the CPLD below 300,000, and described reference voltage array floats linear power supply chip connection precision resister by low temperature and forms.Described low temperature floats the linear power supply chip and floats the regulated power supply chip that is not more than 100ppm/ ℃ for temperature, and described precision resister is the resistance of 1% precision.
Preferred, between the analog signal output of described infrared focal plane array and AD sampling unit, be connected with signal conditioning circuit, described signal conditioning circuit has fixed gain and fixed voltage biasing.The gain of described common mode voltage and signal conditioning circuit is selected as follows: the amplitude range of effective output signal of described normal-temperature infrared inner satellite imaging detector and the input range of AD sampling unit are complementary.
Beneficial effect of the present invention is as follows:
Normal-temperature infrared inner satellite imaging detector of the present invention, at prospect in the interior satellite sounding technology and the low situation of the background temperature difference, by the accurate setting of resistance value, realized the coordination of imaging tonal range and sampling extreme value window, promoted image contrast to greatest extent, realized clear detection, and detector of the present invention does not need focus adjusting mechanism, has simplified the system complexity of detector, and focal plane arrays (FPA) and circuit link by cable, there is distance to cut apart, helps suppressing the forward direction electromagnetic radiation.
Description of drawings
Fig. 1 is the structural representation of normal-temperature infrared inner satellite imaging detector of the present invention;
Fig. 2 is the functional block diagram of image data samples circuit in the normal-temperature infrared inner satellite imaging detector of the present invention.
Embodiment
Below in conjunction with example and accompanying drawing normal-temperature infrared inner satellite imaging detector of the present invention is described further.Fig. 1 has provided the structural representation of normal-temperature infrared inner satellite imaging detector of the present invention, and Fig. 2 has provided the functional block diagram of image data samples circuit of the present invention.
Referring to accompanying drawing 1, near burnt far infrared camera lens 1 and far infrared band focal plane arrays (FPA) 2 in the normal-temperature infrared inner satellite imaging detector of the present invention are combined formation camera lens-focal plane array column unit, be connected with Aviation Connector 4 on described far infrared band focal plane arrays (FPA) 2, Aviation Connector 4 is connected to image data samples circuit 3 by cable 5.
Described nearly burnt far infrared camera lens 1 is for focusing wide-angle lens, the F1 aperture, and focal length 3.6mm, the field angle scope is greater than 90 degree, germanite glass technology, the band anti-reflection film, the band distortion correction, aberration rate is less than 30%.The depth of field 100～500mm adopts aluminium matter lens barrel, and the inwall blackout is handled, and emissivity is greater than 95%.
Described far infrared band focal plane arrays (FPA) 2 is for being operated in the non-refrigeration type infrared focal plane array of long infrared band, and resolution is more than 320 * 240, and the NETD value is better than 0.2K, nominal operation temperature 300K, operating temperature range-50～800C.
Adopt the silica gel sealing around the described Aviation Connector 4, silica gel degree of depth L can prevent electromagnetic leakage greater than 3 times of opening size D.
Described connection cable 5 is for being no less than the shielding line of 19 cores, and simulating signals such as the reference voltage of digital signal such as sequential and focal plane and video output are distinguished, and the secondary shielding line is set respectively.
Referring to accompanying drawing 2, sequential in the described image data samples circuit 3 take place CPLD by below 300,000, the compatible model CPLD of aerospace level realizes; The reference voltage array floats resistance generation required reference voltage of focal plane arrays (FPA) and required common mode voltage and the reference voltage of difference input AD sampling that the power supply fiducial chip that is not more than 100ppm/ ℃ cooperates 1% precision by temperature, and all reference voltages form stable voltage reference through electric source filter circuit; The sampling resolution of AD sampling unit is selected more than 12; The front end signalization conditioning unit of AD sampling unit adopts fixed voltage biasing and fixed gain, and voltage gain wherein equates with the common mode voltage of AD sampling.
The gain of common mode voltage and signal conditioning circuit is selected according to following rule: the amplitude range of the effective output signal of detector and the input range of AD sampling are complementary, to reach best sampling resolution.
The present invention is applicable to the detection of mobile object in normal temperature small size (being not more than 1m) the sealing isoperibol.
Claims (10)
1. normal-temperature infrared inner satellite imaging detector, it is characterized in that: comprise nearly burnt far infrared camera lens, far infrared band focal plane arrays (FPA) and image data samples circuit, described nearly burnt far infrared camera lens and the far infrared band focal plane arrays (FPA) formation camera lens-focal plane array column unit that is connected, described image data samples circuit is connected with image data processing unit and constitutes circuit unit, and the image data samples circuit in the described circuit unit is connected by cable with far infrared band focal plane arrays (FPA) in camera lens-focal plane array column unit.
2. normal-temperature infrared inner satellite imaging detector according to claim 1, it is characterized in that: described camera lens and focal plane array column unit are installed in the shell, the aluminum metal sealing that described shell is all handled through blackout with inside surface except that the cable interface of rear end.
3. normal-temperature infrared inner satellite imaging detector according to claim 1, it is characterized in that: be connected with Aviation Connector between described far infrared band focal plane arrays (FPA) and the cable, adopt the silica gel sealing around the described Aviation Connector 4, silica gel degree of depth L is greater than 3 times of opening size D.
4. normal-temperature infrared inner satellite imaging detector according to claim 1, it is characterized in that: described nearly burnt far infrared camera lens adopts more than field angle 90 degree, the depth of field is the tight shot of 100～500mm, and fixes with described far infrared band focal plane arrays (FPA) relative distance.
5. normal-temperature infrared inner satellite imaging detector according to claim 1 is characterized in that: described far infrared band focal plane array is classified the non-refrigeration type infrared focal plane array that is operated in far infrared band as.
6. normal-temperature infrared inner satellite imaging detector according to claim 1, it is characterized in that: described image data samples circuit is by the sequential generating unit, the AD sampling unit, the reference voltage array is formed, described CPLD produces described far infrared band focal plane array image-forming and the required sequential of difference input AD sampling unit, described reference voltage array produces required reference voltage of described far infrared band focal plane arrays (FPA) and required common mode voltage and the reference voltage of described difference input AD sampling unit, and described AD sampling unit is connected to described far infrared band focal plane arrays (FPA).
7. normal-temperature infrared inner satellite imaging detector according to claim 6 is characterized in that: described sequential generating unit adopts the CPLD below 300,000, and described reference voltage array floats linear power supply chip connection precision resister by low temperature and forms.
8. normal-temperature infrared inner satellite imaging detector according to claim 7 is characterized in that: described low temperature floats the linear power supply chip and floats the regulated power supply chip that is not more than 100ppm/ ℃ for temperature, and described precision resister is the resistance of 1% precision.
9. normal-temperature infrared inner satellite imaging detector according to claim 6, it is characterized in that: be connected with signal conditioning circuit between the analog signal output of described infrared focal plane array and AD sampling unit, described signal conditioning circuit has fixed gain and fixed voltage biasing.
10. normal-temperature infrared inner satellite imaging detector according to claim 9 is characterized in that: the gain of described common mode voltage and signal conditioning circuit is selected as follows: the amplitude range of effective output signal of described normal-temperature infrared inner satellite imaging detector and the input range of AD sampling unit are complementary.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2010101462781A CN101915924B (en) | 2010-04-14 | 2010-04-14 | Normal-temperature infrared inner satellite imaging detector |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2010101462781A CN101915924B (en) | 2010-04-14 | 2010-04-14 | Normal-temperature infrared inner satellite imaging detector |
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| CN101915924A true CN101915924A (en) | 2010-12-15 |
| CN101915924B CN101915924B (en) | 2012-03-07 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102288297A (en) * | 2011-08-22 | 2011-12-21 | 电子科技大学 | Uncooled far infrared thermal imaging system |
| WO2013053335A1 (en) * | 2011-10-14 | 2013-04-18 | Wu Shiming | Panoramic thermal infrared imager and infrared detection system having same |
| CN106441392A (en) * | 2016-10-18 | 2017-02-22 | 周末 | Satellite detector |
| CN111179334A (en) * | 2019-11-14 | 2020-05-19 | 青岛理工大学 | Sea surface small-area oil spilling area detection system and detection method based on multi-sensor fusion |
Citations (5)
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| US20060180765A1 (en) * | 2005-02-15 | 2006-08-17 | Wolske Jeff S | Infrared imaging system with ellipsoid reflective warm baffle and method |
| CN1900740A (en) * | 2005-11-18 | 2007-01-24 | 北京航空航天大学 | High spectrum full polarization imaging remote sensing system |
| CN101241028A (en) * | 2007-02-07 | 2008-08-13 | 南京理工大学 | Infrared focal plane array image-forming demonstration system |
| CN101275842A (en) * | 2007-03-29 | 2008-10-01 | 北京控制工程研究所 | Near infrared light imaging type autonomous navigation sensor system of middle and high orbit spacecraft |
| CN101470026A (en) * | 2007-12-24 | 2009-07-01 | 南京理工大学 | Ununiformity emendation real-time calibration apparatus for staring type thermal imaging system |
-
2010
- 2010-04-14 CN CN2010101462781A patent/CN101915924B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060180765A1 (en) * | 2005-02-15 | 2006-08-17 | Wolske Jeff S | Infrared imaging system with ellipsoid reflective warm baffle and method |
| CN1900740A (en) * | 2005-11-18 | 2007-01-24 | 北京航空航天大学 | High spectrum full polarization imaging remote sensing system |
| CN101241028A (en) * | 2007-02-07 | 2008-08-13 | 南京理工大学 | Infrared focal plane array image-forming demonstration system |
| CN101275842A (en) * | 2007-03-29 | 2008-10-01 | 北京控制工程研究所 | Near infrared light imaging type autonomous navigation sensor system of middle and high orbit spacecraft |
| CN101470026A (en) * | 2007-12-24 | 2009-07-01 | 南京理工大学 | Ununiformity emendation real-time calibration apparatus for staring type thermal imaging system |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102288297A (en) * | 2011-08-22 | 2011-12-21 | 电子科技大学 | Uncooled far infrared thermal imaging system |
| CN102288297B (en) * | 2011-08-22 | 2012-11-07 | 电子科技大学 | Uncooled far infrared thermal imaging system |
| WO2013053335A1 (en) * | 2011-10-14 | 2013-04-18 | Wu Shiming | Panoramic thermal infrared imager and infrared detection system having same |
| CN106441392A (en) * | 2016-10-18 | 2017-02-22 | 周末 | Satellite detector |
| CN111179334A (en) * | 2019-11-14 | 2020-05-19 | 青岛理工大学 | Sea surface small-area oil spilling area detection system and detection method based on multi-sensor fusion |
| CN111179334B (en) * | 2019-11-14 | 2024-03-19 | 青岛理工大学 | Sea surface small-area oil spill area detection system and detection method based on multi-sensor fusion |
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| Publication number | Publication date |
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| CN101915924B (en) | 2012-03-07 |
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