CN101915924B - Normal-temperature infrared inner satellite imaging detector - Google Patents
Normal-temperature infrared inner satellite imaging detector Download PDFInfo
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- CN101915924B CN101915924B CN2010101462781A CN201010146278A CN101915924B CN 101915924 B CN101915924 B CN 101915924B CN 2010101462781 A CN2010101462781 A CN 2010101462781A CN 201010146278 A CN201010146278 A CN 201010146278A CN 101915924 B CN101915924 B CN 101915924B
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Abstract
The invention discloses a normal-temperature far 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 IR survey technical field, relate in particular to a kind of detector of the far infrared radiation that satellite is launched naturally in the utilization under normal temperature environment imaging.
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 IR 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 (proof mass in 1975 PhD dissertation " Minimum thrusters control of a spinning drag-free satellite; including the design of a large cavity 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.
IRDS 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
The normal temperature far infrared inner satellite imaging detector of satellite relative position in the object of the present invention is to provide satellite in a kind of can the utilization thereby the far infrared radiation imaging of emission detecting naturally under normal temperature condition.
To achieve these goals, the technical scheme of the present invention's employing is following:
Normal temperature far 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 far infrared band focal plane arrays (FPA) are connected and constitute camera lens focal plane array column unit; 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 through 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 said 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 said far infrared band focal plane arrays (FPA) and required common mode voltage and the reference voltage of said 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 said reference voltage array connects precision resister by low temperature drift linear power supply chip and forms.Described low temperature drift linear power supply chip 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 said 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 said common mode voltage and signal conditioning circuit is selected according to following method: amplitude range and the input range of AD sampling unit of effective output signal of said normal temperature far infrared inner satellite imaging detector are complementary.
Beneficial effect of the present invention is following:
Normal temperature far infrared inner satellite imaging detector of the present invention is to prospect in the interior satellite sounding technology and the low situation of the background temperature difference, through the accurate setting of resistance value; Realized of the coordination of imaging tonal range with 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; Simplified the system complexity of detector; Focal plane arrays (FPA) and circuit link through cable, have distance to cut apart, and help suppressing the forward direction electromagnetic radiation.
Description of drawings
Fig. 1 is the structural representation of normal temperature far 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 far infrared inner satellite imaging detector of the present invention.
Embodiment
Below in conjunction with instance and accompanying drawing normal temperature far infrared inner satellite imaging detector of the present invention is further specified.Fig. 1 has provided the structural representation of normal temperature far 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 in the normal temperature far infrared inner satellite imaging detector of the present invention is combined formation camera lens-focal plane array column unit with far infrared band focal plane arrays (FPA) 2; On described far infrared band focal plane arrays (FPA) 2, be connected with Aviation Connector 4, Aviation Connector 4 is connected to image data samples circuit 3 through 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 superior to 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 that detector effectively exports signal and the input range of AD sampling are complementary, to reach the sampling resolution of the best.
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 (9)
1. normal temperature far 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 through cable with far infrared band focal plane arrays (FPA) in camera lens-focal plane array column unit; Described image data samples circuit is made up of sequential generating unit, difference input AD sampling unit, reference voltage array; Described sequential generating unit produces said 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 said far infrared band focal plane arrays (FPA) and required common mode voltage and the reference voltage of said difference input AD sampling unit, and described difference input AD sampling unit is connected to described far infrared band focal plane arrays (FPA).
2. normal temperature far infrared inner satellite imaging detector according to claim 1; It is characterized in that: described camera lens-focal plane array column unit is 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 far 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; Described Aviation Connector (4) adopts the silica gel sealing on every side, and silica gel degree of depth L is greater than 3 times of opening size D.
4. normal temperature far 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 far 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 far infrared band focal plane arrays (FPA) that is operated in far infrared band as.
6. normal temperature far infrared inner satellite imaging detector according to claim 1 is characterized in that: described sequential generating unit adopts the CPLD below 300,000, and said reference voltage array connects precision resister by low temperature drift linear power supply chip and forms.
7. normal temperature far infrared inner satellite imaging detector according to claim 6 is characterized in that: described low temperature drift linear power supply chip floats the regulated power supply chip that is not more than 100ppm/ ℃ for temperature, and described precision resister is the resistance of 1% precision.
8. normal temperature far infrared inner satellite imaging detector according to claim 1; It is characterized in that: between the analog signal output of said far infrared band focal plane arrays (FPA) and difference input AD sampling unit, be connected with signal conditioning circuit, described signal conditioning circuit has fixed gain and setovers with fixed voltage.
9. normal temperature far infrared inner satellite imaging detector according to claim 8 is characterized in that: the gain of said common mode voltage and signal conditioning circuit is selected according to following method: the input range that makes amplitude range and the difference of effective output signal of said normal temperature far infrared inner satellite imaging detector import the AD sampling unit is 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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| CN2010101462781A CN101915924B (en) | 2010-04-14 | 2010-04-14 | Normal-temperature infrared inner satellite imaging detector |
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| CN101915924B true CN101915924B (en) | 2012-03-07 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102288297B (en) * | 2011-08-22 | 2012-11-07 | 电子科技大学 | Uncooled far infrared thermal imaging system |
| CN202270019U (en) * | 2011-10-14 | 2012-06-13 | 吴士明 | Medical far infrared thermal imaging device adopting wide-angle lens |
| CN106441392A (en) * | 2016-10-18 | 2017-02-22 | 周末 | Satellite detector |
| 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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| US7180067B2 (en) * | 2005-02-15 | 2007-02-20 | Raytheon Company | Infrared imaging system with ellipsoid reflective warm baffle and method |
| CN100451677C (en) * | 2005-11-18 | 2009-01-14 | 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 |
| CN101275842B (en) * | 2007-03-29 | 2010-12-15 | 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 |
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