CN103983251B - A kind of low-power consumption for survey of deep space, small-sized, multi purpose space camera and its implementation - Google Patents

A kind of low-power consumption for survey of deep space, small-sized, multi purpose space camera and its implementation Download PDF

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Publication number
CN103983251B
CN103983251B CN201410234228.7A CN201410234228A CN103983251B CN 103983251 B CN103983251 B CN 103983251B CN 201410234228 A CN201410234228 A CN 201410234228A CN 103983251 B CN103983251 B CN 103983251B
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camera
space
aps
space camera
sized
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CN103983251A (en
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余国彬
刘恩海
周向东
钟杰
赵汝进
王进
周武林
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Institute of Optics and Electronics of CAS
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Institute of Optics and Electronics of CAS
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C11/00—Photogrammetry or videogrammetry, e.g. stereogrammetry; Photographic surveying
    • G01C11/02—Picture taking arrangements specially adapted for photogrammetry or photographic surveying, e.g. controlling overlapping of pictures

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Abstract

The invention discloses a kind of low-power consumption for survey of deep space, small-sized, multi purpose space camera, including shade, optical lens, APS plates, camera control plate and camera support structure；Which it is critical only that, to having used the space camera of APS imageing sensors, introduce shade lightweight design optimizing, the design optimizing of optical system, the structure lightened designing technique of camera support and electronic system optimization design, achieve the low-power consumption of space camera, small-sized and multi-functional, have image quality high strong with environmental suitability simultaneously, survey of deep space is met to low-power consumption, the demand of small-sized, multi purpose space camera.

Description

A kind of low-power consumption for survey of deep space, small-sized, multi purpose space camera and in fact Existing method
Technical field
The invention belongs to survey of deep space technical field of photoelectric detection, it is related to a kind of low-power consumption for survey of deep space, gently little Type, multi purpose space camera and its implementation.
Background technology
With development and the survey of deep space mission requirements of survey of deep space technology, the payload indispensable as survey of deep space is done The development trend of (space camera) is：As technology constantly improves, the performance more and more higher of space camera is sent out in survey of deep space The effect that waves is more and more important, and the space camera entrained by deep space probe is also more and more；The science undertaken by space camera Target is from single to diversification, from simple to complexity；Survey of deep space space camera is intended to integrated, miniaturization and multi-functional Change, to mitigate quality, reduce into wood, save fuel, extend the deep space probe life-span.Thus low-power consumption, small-sized, multi-functional Space camera Development Techniques are one of key technologies of survey of deep space technology development.
Survey of deep space task mainly shows two aspects to the demand of low-power consumption, small-sized, multi-functional space camera, and one Aspect is the demand of process monitoring, for truer, monitoring survey of deep space activity more in real time, grasps deep space probe key portion The situation of the key operations of part and the long term state at some positions of monitoring detector, can install in the different parts of detector Low-power consumption, small-sized, multi purpose space camera, pass the image of acquisition back ground in time；On the other hand it is payload Demand, this are highly important one side.A deep space probe is developed, its final purpose is a certain celestial body of detection, obtains Required information, realizes scientific goal, it is necessary to which configuration can meet the payload of target requirement.Although payload has multiple Classification, but the load based on optical imagery is all important and necessary all the time.
Content of the invention
In view of this, present invention is primarily targeted at providing a kind of low-power consumption for survey of deep space, small-sized, many work( Can space camera and its implementation.
In order to achieve the above object, the technical scheme is that and to be achieved in that：
The invention provides a kind of low-power consumption for survey of deep space, small-sized, multi purpose space camera, including shading Cover, optical lens, APS plates, crimp type mother daughter board connector, camera control plate and camera support structure；Wherein, shade, light Learn camera lens, APS plates, crimp type mother daughter board connector, camera control plate to be sequentially placed,
Shade, in the front end of the optical lens, for cutting down the veiling glare outside visual field；
Optical lens, between shade and APS plates, for collecting objective opticses signal to be imaged, and are imaged on APS On imageing sensor；
Optical lens collection optical signalling, between optical lens and camera control plate, is converted into electricity letter by APS plates Number, while realizing that difference LVDS signal switchs to single-ended signal and secondary power supply translation function；
Crimp type mother daughter board connector, between APS plates and camera control plate, for connecting APS plates and camera control plate, real The signal transmission of existing two pieces of circuit boards；
Camera control plate, in space camera rear end, for the control signal of APS chips, collection image, output image, string Row communication；
Camera support structure, for fixing optical lens, APS plates and camera control plate and realizing that external machinery connects Mouthful, it is ensured that the adaptation of space camera space radiation environment and the adaptation of mechanical environment.
In such scheme, the light hole of the shade is rectangle shade, rectangular long side and APS image sensings The long side of device is corresponding, and rectangular minor face is corresponding with the minor face of APS imageing sensors.Rectangle light hole and the space camera 22.9 ° × 16.9 ° angles of visual field be adapted.
In such scheme, APS imageing sensors on the APS plates are IA-G3 color detectors, pixel number is 2352 × 1728, the 2352 of imageing sensor is corresponding with the long side of shade light hole, imageing sensor 1728 with shade light hole Minor face corresponding.
In such scheme, space flight level 4 row mother daughter board connector of the crimp type mother daughter board connector for Airborn.
In such scheme, the camera control FPGA on the camera control plate is that space flight level instead melts formula FPGA.
In such scheme, the camera control FPGA, including APS drive modules, mode of operation control module, SRAM controls Module, serial communication module, exposure control module and and turn string module；Wherein,
APS drive modules, for controlling the sequential of IA-G3 color image sensors；
Mode of operation control module, standby for according to serial communication interface mode of operation order, realizing, static state is taken pictures, Dynamic shooting sampling and the switching of dynamic shooting four kinds of mode of operations of windowing, so that control image output；
SRAM control unit, for sequential needed for producing memory read/write operation, realizes image buffer storage, column direction windowing With image sampling function；
Serial communication module, for completing external command injection and engineering parameter inquiry operation；
Exposure control module, for realizing automatic exposure and Manual exposure both of which；
And turn string module, for by 8 bit image data conversions after sram cache into 1 Bits Serial data.
In such scheme, the visual field of the space camera is 22.9 ° × 16.9 °, and focal length is 43mm, and F numbers are 8, normally into Image distance from：5m～∞, weight is 460g, and power consumption is 3.52W, and envelope size is：118.9mm × 110mm × 92mm, function are coloured silk Color image acquisition, Xanthophyll cycle with an automatic light meter, spuious, static state is taken pictures, dynamic is imaged.
A kind of low-power consumption for survey of deep space that the present invention is provided, the small-sized, implementation method of multi purpose space camera, The space camera includes shade, optical lens, APS plates, crimp type mother daughter board connector, camera control plate and camera support Structure；The visual field of the space camera is 22.9 ° × 16.9 °, and focal length is 43mm, and F numbers are 8, normal imaging distance：5m～∞, Weight is 460g, and power consumption is 3.52W, and envelope size is：118.9mm × 110mm × 92mm, function is obtained for coloured image, oneself Move light modulation, spuious Xanthophyll cycle, static state are taken pictures, dynamic is imaged；The implementation method is：
1) implementation method of the low-power consumption of the space camera is：
1. the low-power consumption of the space camera is realized from IA-G3APS detectors；
Detector for space industry mainly includes two big class of CCD and APS detectors, although ccd detector technology into Ripe, but low-power consumption cannot be realized.The integrated level of APS detectors is high, low in energy consumption, Radiation hardness is strong, and its performance and imaging Quality is improved largely, and the IA-G3APS detectors that the space camera is adopted are by the function collection such as correlated-double-sampling, AD, AGC Into, reducing volume, weight, power consumption together.So realizing the space camera from IA-G3 colour APS detectors Low-power consumption.
2. the A54SX72A-CQ208B types FPGA device from Actel companies is realizing the low-power consumption of the space camera.
The space camera using the high Actel companies of integrated level A54SX72A-CQ208B types FPGA device realizing The APS drive controls of space camera, mode of operation control, SRAM controls, serial communication control, spectrum assignment and and turn string and control System, simplifies hardware circuit, reduces power consumption.So the A54SX72A-CQ208B types FPGA device from Actel companies comes in fact The low-power consumption of the existing space camera.
2) the small-sized implementation method of the space camera is：
1. the small-sized of the space camera is realized from IA-G3APS detectors；
Detector for space industry mainly includes two big class of CCD and AP S detectors, although ccd detector technology into Ripe, but cannot realize small-sized.The integrated level of APS detectors is high, low in energy consumption, Radiation hardness is strong, and its performance and imaging Quality is improved largely, and the IA-G3APS detectors that the space camera is adopted are by the function collection such as correlated-double-sampling, AD, AGC Into, reducing volume, weight, power consumption together.So realizing the space camera from IA-G3 colour APS detectors Small-sized.
2. from Actel companies A54SX72A-CQ208B FPGA device realizing the small-sized of the space camera；
The space camera using the high Actel companies of integrated level A54SX72A-CQ208B types FPGA device realizing The APS drive controls of space camera, mode of operation control, SRAM controls, serial communication control, spectrum assignment and and turn string and control System, simplifies hardware circuit, reduces circuit board size, so as to alleviate the volume of the space camera.So selecting Actel The A54SX72A-CQ208B types FPGA device of company is realizing the small-sized of the space camera.
3. the 4 row's mother daughter board connector (RC442-052-351-4400) of space flight level from Airborn is realizing the space Camera small-sized；
Described space camera, its electronic system (pcb board, all kinds of devices etc.) institute's accounting in the weight of whole camera Example is less, and camera support structure (adaptability such as the mechanical environment of guarantee camera, radiation environment, thermal environment) is whole camera weight Topmost quality source, so the weight for reducing camera support structure is maximally effective loss of weight measure.Camera support to be reduced The weight of structure, most effective of which measure are exactly to reduce camera volume.For small-sized space camera, camera volume is straight Acceptance is limited to the distance between the size of the pcb board of electronic system and pcb board.By the optimization design to electronic system, Affect pcb board size and pcb board spacing is the adapter between pcb board.Convention connectors physical dimension ratio between pcb board Larger, the size of pcb board is not only increased, and increases the distance between pcb board, so as to increase the weight of whole camera. 4 row's mother daughter board connector (RC442-052-351-4400) of space flight level of Airborn, this height is adopted in described space camera Density mother daughter board connector not only reduces pcb board size, and reduces the distance between pcb board, so as to reduce whole camera Volume and weight.So, the 4 row's mother daughter board connector (RC442-052-351-4400) of space flight level from Airborn is realizing The space camera small-sized.
4. the small-sized of the space camera is realized by the Shape optimization designs of the clear aperture of shade；
As shown in Fig. 2 described space camera is according to optical system parameter, optical design and structure design is carried out, passed The shade of system is using circle, and in the present invention, has added the square shade of certain length in the front of optical lens, mitigates The weight of shade, so that alleviate volume, the weight of the space camera.So the shape by the clear aperture of shade Shape optimization design is achieving the small-sized of the space camera；
5. the small-sized of the space camera is realized by optimizing optical system parameter.
Small light to be accomplished, except requiring structure division using the as far as possible little material of proportion and optimization design, Yi Jiyao Ask electronic system as far as possible simple and using the device of high integration outside, it is necessary to focus on the optimization of optical parametric.Optical system Simplest structure form is to realize the basis of small light, and the optical parametric of the optical lens is determined by following formula.
Wherein, SimageFor accumulating electron number, Φ in single pixel0For solar photon number density, ρ is diffuse-reflectance coefficient；τ is Transmissivity of optical system；θsFor imaging surface method arrow and sun angle, θoFor imaging surface method arrow and the angle of observer, F is camera F numbers, BsFor the area of single pixel, η is quantum efficiency, and κ is fill factor, curve factor, and t is time of exposure；
It is 420～700nm that the optical parametric of the optical lens is wavelength band, and visual field is 22.9 ° × 16.9 °, focal length For 43mm, F numbers are 8, and normal imaging distance is 5m～∞, and transmission function MTF is more than 0.45.
After the version of optical system determines, the lightweight index that the optical lens can finally reach is also just basic Determine.The design result of the optical lens be optical lens maximum caliber be Ф 44mm, optical lens overall length be 54.5mm, light Camera lens (containing shade) weight is 58g, so realizing the small-sized of the space camera by optimizing optical system parameter.
3) the multi-functional implementation method of the space camera is：
1. realize from IA-G3 colour APS detectors that the colored of the space camera obtains function；
The IA-G3APS detectors that the space camera is adopted, IA-G3APS detectors are the colours filtered based on Bayer Face battle array CMOS, pixel surface increase red (R), green (G) or blue (B) optical filter according to Bayer rules, and each pixel can A kind of sensitive gradation.For the coloured image based on RGB, each pixel is both needed to R, G and B gray value.So selecting IA-G3 colour APS detectors obtain function come the colour for realizing the space camera.
2. the veiling glare of the space camera is realized by veiling glare braking measure inside Baffle design and optical lens Suppress function；
As shown in Fig. 2 the space camera is according to optical system parameter, optical design and structure design is carried out, and has been adopted A series of veiling glare braking measure is taken：The square shade of certain length is added in the front of optical lens, has stopped outside visual field Most of veiling glare is entered；All optical elements of optical system will plate multi-layered antireflection coating；On the non-working surface of optical element Delustring paint is applied, veiling glare is greatly attenuated in route of transmission；Delustring tooth be machined in body tube, picture frame inwall.So by hiding Inside mask set and optical lens, veiling glare braking measure is realizing the spuious Xanthophyll cycle function of the space camera
3. from Actel companies A54SX72A-CQ208B FPGA device realizing the automatic exposure of the space camera The functions such as light, standby mode, static exposal model, dynamic sampling image pickup mode and dynamic windowing image pickup mode.
The space camera using the high Actel companies of integrated level A54SX72A-CQ208B types FPGA device realizing The APS drive controls of space camera, mode of operation control, SRAM controls, serial communication control, spectrum assignment and and turn string and control System.So from Actel companies A54SX72A-CQ208B types FPGA device realizing the multi-functional of the space camera.
Compared with prior art, present invention has the advantage that：Employ IA-G3 color detectors, high integration FPGA, 4 row's mother daughter board connector of space flight level of Airborn carried out the shade lightweight optimization design of space camera, optical system excellent Change design, the structure lightened design of camera support and electronic system optimization design, it is achieved that space camera power consumption is 3.52W, weight is 460g, and volume is 118.9mm × 110mm × 92mm, function be coloured image obtain, with an automatic light meter, spuious Xanthophyll cycle, static state are taken pictures, dynamic of sampling shooting and windowing dynamic are imaged.
Description of the drawings
Fig. 1 is the system composition schematic diagram of the space camera of the present invention；
It is labeled as in its figure：11- shades, 12- optical lens, 13-APS plates, 14- crimp type mother daughter board connectors, 15- phases Machine panel, 16- camera support structures；
Fig. 2 is the shade and optical lens schematic diagram of the space camera of the present invention；
Fig. 3 is the camera control FPGA functional block diagrams of the space camera of the present invention；
It is labeled as in its figure：21-APS drive modules, 22- mode of operation control modules, 23-SRAM control modules, 24- strings Row communication module, 25- exposure control modules, 26- simultaneously turn string module；
Fig. 4 is the specific embodiment of the space camera of the space camera of the present invention.
Specific embodiment
Below in conjunction with the accompanying drawings and specific embodiment the present invention is further described in more detail.
The index for implementing of space camera that the present invention is provided is：
1) visual field：22.9°×16.9°；
2) focal length：43mm；
3) F numbers：8；
4) normal imaging distance：5m～∞；
5) weight：460g；
6) power consumption：3.52W；
7) envelope size：118.9mm×110mm×92mm.
The function of implementing of space camera that the present invention is provided is：
1) coloured image obtains function；
2) automatic dimming function；
3) spuious Xanthophyll cycle function；
4) static camera function；
5) dynamic of sampling camera function；
6) open a window dynamic camera function.
The invention provides a kind of low-power consumption for survey of deep space, small-sized, multi purpose space camera, as shown in figure 1, The space camera include shade 11, optical lens 12, APS plates 13, crimp type mother daughter board connector 14, camera control plate 15 with And camera support structure 16；Wherein,
Shade 11, in the front end of the optical lens 12, for cutting down the veiling glare outside visual field；
Optical lens 12, between shade 11 and APS plates, for collecting objective opticses signal to be imaged, and are imaged On APS imageing sensors；
Optical lens 12, between optical lens 12 and camera control plate, are collected optical signalling and are converted into electricity by APS plates 13 Signal is learned, while realizing that difference LVDS signal switchs to single-ended signal and secondary power supply translation function；
Crimp type mother daughter board connector 14, between APS plates 13 and camera control plate 15, for connecting APS plates 13 and camera Panel 15, realizes the signal transmission of two pieces of circuit boards；
Camera control plate 15, in space camera rear end, for the control signal of APS chips, collection image, output image, Serial communication；
Camera support structure 16, for fixing optical lens 12, APS plates 13 and camera control plate 14 and realizing external Mechanical interface, it is ensured that the adaptation of space camera space radiation environment and the adaptation of mechanical environment, as indicated at 4.
As shown in Fig. 2 the light hole of the shade 11 is rectangle shade, rectangular long side is passed with APS images The long side of sensor is corresponding, and rectangular minor face is corresponding with the minor face of APS imageing sensors.Rectangle light hole and the space phase 22.9 ° of machine × 16.9 ° of angles of visual field are adapted.
APS imageing sensors on the APS plates 13 are IA-G3 color detectors, and pixel number is 2352 × 1728, image The 2352 of sensor are corresponding with the long side of shade light hole, the 1728 of imageing sensor with the minor face pair of shade light hole Should.
Space flight level 4 row mother daughter board connector of the crimp type mother daughter board connector 14 for Airborn.
Camera control FPGA on the camera control plate 15 is that space flight level instead melts formula FPGA.
As shown in figure 3, the camera control FPGA, including APS drive modules 21, mode of operation control module 22, SRAM Control module 23, serial communication module 24, exposure control module 25 and and turn string module 26；Wherein,
APS drive modules 21, for controlling the sequential of IA-G3 color image sensors；
Mode of operation control module 22, static bat standby for according to serial communication interface mode of operation order, realizing According to the switching that dynamic shooting is sampled with dynamic shooting four kinds of mode of operations of windowing, so that control image output；
SRAM control unit 23, for sequential needed for producing memory read/write operation, realizes image buffer storage, column direction windowing Mouth and image sampling function；
Serial communication module 24, for completing external command injection and engineering parameter inquiry operation；
Exposure control module 25, for realizing automatic exposure and Manual exposure both of which；
And turn string module 26, for by 8 bit image data conversions after sram cache into 1 Bits Serial data.
The visual field of the space camera is 22.9 ° × 16.9 °, and focal length is 43mm, and F numbers are 8, normal imaging distance：5m～ ∞, weight is 460g, and power consumption is 3.52W, and envelope size is：118.9mm × 110mm × 92mm, function be coloured image obtain, Xanthophyll cycle with an automatic light meter, spuious, static state are taken pictures, dynamic is imaged.
A kind of low-power consumption for survey of deep space that the present invention is provided, the small-sized, implementation method of multi purpose space camera, The space camera include shade 11, optical lens 12, APS plates 13, crimp type mother daughter board connector 14, camera control plate 15 with And camera support structure 16；The visual field of the space camera is 22.9 ° × 16.9 °, and focal length is 43mm, and F numbers are 8, normal imaging Distance：5m～∞, weight is 460g, and power consumption is 3.52W, and envelope size is：118.9mm × 110mm × 92mm, function are colour Image acquisition, Xanthophyll cycle with an automatic light meter, spuious, static state is taken pictures, dynamic is imaged；The implementation method is：
1) implementation method of the low-power consumption of the space camera is：
1. the low-power consumption of the space camera is realized from IA-G3APS detectors；
Detector for space industry mainly includes two big class of CCD and APS detectors, although ccd detector technology into Ripe, but low-power consumption cannot be realized.The integrated level of APS detectors is high, low in energy consumption, Radiation hardness is strong, and its performance and imaging Quality is improved largely, and the IA-G3APS detectors that the space camera is adopted are by the function collection such as correlated-double-sampling, AD, AGC Into, reducing volume, weight, power consumption together.So realizing the space camera from IA-G3 colour APS detectors Low-power consumption.
2. the A54SX72A-CQ208B types FPGA device from Actel companies is realizing the low-power consumption of the space camera.
The space camera using the high Actel companies of integrated level A54SX72A-CQ208B types FPGA device realizing The APS drive controls of space camera, mode of operation control, SRAM controls, serial communication control, spectrum assignment and and turn string and control System, simplifies hardware circuit, reduces power consumption.So the A54SX72A-CQ208B types FPGA device from Actel companies comes in fact The low-power consumption of the existing space camera.
2) the small-sized implementation method of the space camera is：
1. the small-sized of the space camera is realized from IA-G3APS detectors；
Detector for space industry mainly includes two big class of CCD and APS detectors, although ccd detector technology into Ripe, but cannot realize small-sized.The integrated level of APS detectors is high, low in energy consumption, Radiation hardness is strong, and its performance and imaging Quality is improved largely, and the IA-G3APS detectors that the space camera is adopted are by the function collection such as correlated-double-sampling, AD, AGC Into, reducing volume, weight, power consumption together.So realizing the space camera from IA-G3 colour APS detectors Small-sized.
2. from Actel companies A54SX72A-CQ208B FPGA device realizing the small-sized of the space camera；
The space camera using the high Actel companies of integrated level A54SX72A-CQ208B types FPGA device realizing The APS drive controls of space camera, mode of operation control, SRAM controls, serial communication control, spectrum assignment and and turn string and control System, simplifies hardware circuit, reduces circuit board size, so as to alleviate the volume of the space camera.So selecting Actel The A54SX72A-CQ208B types FPGA device of company is realizing the small-sized of the space camera.
3. the 4 row's mother daughter board connector (RC442-052-351-4400) of space flight level from Airborn is realizing the space Camera small-sized；
Described space camera, its electronic system (pcb board, all kinds of devices etc.) institute's accounting in the weight of whole camera Example is less, and camera support structure (adaptability such as the mechanical environment of guarantee camera, radiation environment, thermal environment) is whole camera weight Topmost quality source, so the weight for reducing camera support structure is maximally effective loss of weight measure.Camera support to be reduced The weight of structure, most effective of which measure are exactly to reduce camera volume.For small-sized space camera, camera volume is straight Acceptance is limited to the distance between the size of the pcb board of electronic system and pcb board.By the optimization design to electronic system, Affect pcb board size and pcb board spacing is the adapter between pcb board.Convention connectors physical dimension ratio between pcb board Larger, the size of pcb board is not only increased, and increases the distance between pcb board, so as to increase the weight of whole camera. 4 row's mother daughter board connector (RC442-052-351-4400) of space flight level of Airborn, this height is adopted in described space camera Density mother daughter board connector not only reduces pcb board size, and reduces the distance between pcb board, so as to reduce whole camera Volume and weight.So, the 4 row's mother daughter board connector (RC442-052-351-4400) of space flight level from Airborn is realizing The space camera small-sized.
4. the small-sized of the space camera is realized by the Shape optimization designs of the clear aperture of shade；
As shown in Fig. 2 described space camera is according to optical system parameter, optical design and structure design is carried out, passed The shade of system is using circle, and in the present invention, has added the square shade of certain length in the front of optical lens, mitigates The weight of shade, so that alleviate volume, the weight of the space camera.So the shape by the clear aperture of shade Shape optimization design is achieving the small-sized of the space camera；
5. the small-sized of the space camera is realized by optimizing optical system parameter.
Small light to be accomplished, except requiring structure division using the as far as possible little material of proportion and optimization design, Yi Jiyao Ask electronic system as far as possible simple and using the device of high integration outside, it is necessary to focus on the optimization of optical parametric.Optical system Simplest structure form is to realize the basis of small light, and the optical parametric of the optical lens is determined by following formula.
Wherein, SimageFor accumulating electron number, Φ in single pixel0For solar photon number density, ρ is diffuse-reflectance coefficient；τ is Transmissivity of optical system；θsFor imaging surface method arrow and sun angle, θoFor imaging surface method arrow and the angle of observer, F is camera F numbers, BsFor the area of single pixel, η is quantum efficiency, and κ is fill factor, curve factor, and t is time of exposure；
It is 420～700nm that the optical parametric of the optical lens is wavelength band, and visual field is 22.9 ° × 16.9 °, focal length For 43mm, F numbers are 8, and normal imaging distance is 5m～∞, and transmission function MTF is more than 0.45.
After the version of optical system determines, the lightweight index that the optical lens can finally reach is also just basic Determine.The design result of the optical lens be optical lens maximum caliber be Ф 44mm, optical lens overall length be 54.5mm, light Camera lens (containing shade) weight is 58g, so realizing the small-sized of the space camera by optimizing optical system parameter.
3) the multi-functional implementation method of the space camera is：
1. realize from IA-G3 colour APS detectors that the colored of the space camera obtains function；
The IA-G3APS detectors that the space camera is adopted, IA-G3APS detectors are the colours filtered based on Bayer Face battle array CMOS, pixel surface increase red (R), green (G) or blue (B) optical filter according to Bayer rules, and each pixel can A kind of sensitive gradation.For the coloured image based on RGB, each pixel is both needed to R, G and B gray value.So selecting IA-G3 colour APS detectors obtain function come the colour for realizing the space camera.
2. the veiling glare of the space camera is realized by veiling glare braking measure inside Baffle design and optical lens Suppress function；
As shown in Fig. 2 the space camera is according to optical system parameter, optical design and structure design is carried out, and has been adopted A series of veiling glare braking measure is taken：The square shade of certain length is added in the front of optical lens, has stopped outside visual field Most of veiling glare is entered；All optical elements of optical system will plate multi-layered antireflection coating；On the non-working surface of optical element Delustring paint is applied, veiling glare is greatly attenuated in route of transmission；Delustring tooth be machined in body tube, picture frame inwall.So by hiding Inside mask set and optical lens, veiling glare braking measure is realizing the spuious Xanthophyll cycle function of the space camera
3. from Actel companies A54SX72A-CQ208B FPGA device realizing the automatic exposure of the space camera The functions such as light, standby mode, static exposal model, dynamic sampling image pickup mode and dynamic windowing image pickup mode.
The space camera using the high Actel companies of integrated level A54SX72A-CQ208B types FPGA device realizing The APS drive controls of space camera, mode of operation control, SRAM controls, serial communication control, spectrum assignment and and turn string and control System.So from Actel companies A54SX72A-CQ208B types FPGA device realizing the multi-functional of the space camera.

Claims (1)

1. a kind of low-power consumption for survey of deep space, small-sized, multi purpose space camera, it is characterised in that the space camera bag Include shade (11), optical lens (12), APS plates (13), crimp type mother daughter board connector (14), camera control plate (15) and phase Machine supporting construction (16)；Wherein, shade (11), optical lens (12), APS plates (13), crimp type mother daughter board connector (14), phase Machine panel (15) is sequentially placed,
Shade (11), for cutting down the veiling glare outside visual field；
Optical lens (12), for by target imaging to be imaged in APS imageing sensors；
APS plates (13), for opto-electronic conversion, difference LVDS signal switchs to single-ended signal, and secondary power supply is changed；
Crimp type mother daughter board connector (14), for connecting APS plates (13) and camera control plate (15), carries out signal transmission；
Camera control plate (15), for the control signal of APS chips, collection image, output image, serial communication；
Camera support structure (16), for fix optical lens (12), APS plates (13) and camera control plate (15) and realize right Outer mechanical interface；
The light hole of shade (11) is rectangle, rectangular long corresponding in long with APS imageing sensors, rectangular The minor face of shape is corresponding with the minor face of APS imageing sensors；22.9 ° × 16.9 ° of rectangle light hole and the space camera are regarded Rink corner is adapted；
APS imageing sensors on APS plates (13) are IA-G3 color detectors, and pixel number is 2352 × 1728, detector Pixel number be 2352 long corresponding in long with shade light hole, detector pixel number is that 1728 minor face is led to shade The minor face of unthreaded hole is corresponding；
The 4 row's mother daughter board connector of space flight level of described crimp type mother daughter board connector (14) for Airborn；
Camera control FPGA on camera control plate (15) is that space flight level instead melts formula FPGA；
The camera control FPGA, including APS drive modules (21), mode of operation control module (22), SRAM control unit (23), serial communication module (24), exposure control module (25) and and turn string module (26)；Wherein,
APS drive modules (21), for controlling the sequential of APS imageing sensors；
Mode of operation control module (22), standby for according to serial communication interface mode of operation order, realizing, static state is taken pictures, Dynamic shooting sampling and the switching of dynamic shooting four kinds of mode of operations of windowing, so that control image output；
SRAM control unit (23), for sequential needed for producing memory read/write operation, realizes image buffer storage, column direction windowing With image sampling function；
Serial communication module (24), for completing external command injection and engineering parameter inquiry operation；
Exposure control module (25), for realizing automatic exposure and Manual exposure both of which；
And turn string module (26), for by 8 bit image data conversions after sram cache into 1 Bits Serial data；
The visual field of the space camera is 22.9 ° × 16.9 °, and focal length is 43mm, and F numbers are 8, normal imaging distance：5m～∞, weight Measure as 460g, power consumption is 3.52W, envelope size is：118.9mm × 110mm × 92mm, the function having are obtained for coloured image Take, Xanthophyll cycle with an automatic light meter, spuious, static state are taken pictures, dynamic is imaged；
The space camera implementation method is：
1) implementation method of the low-power consumption of the space camera is：
1. the low-power consumption of the space camera is realized from IA-G3APS detectors；
Detector for space industry mainly includes two big class of CCD and APS detectors, although ccd detector technology maturation, but Low-power consumption cannot be realized；The integrated level of APS detectors is high, low in energy consumption, Radiation hardness is strong, and its performance and image quality have Increase substantially, correlated-double-sampling, AD, AGC function are integrated by the IA-G3APS detectors that the space camera is adopted, Reduce volume, weight, power consumption；So realizing the low-power consumption of the space camera from IA-G3 colour APS detectors；
2. the A54SX72A-CQ208B types FPGA device from Actel companies is realizing the low-power consumption of the space camera；
The space camera using the high Actel companies of integrated level A54SX72A-CQ208B types FPGA device achieving sky Between camera APS drive controls, mode of operation control, SRAM control, serial communication control, spectrum assignment and and turn string control, Hardware circuit is simplified, power consumption is reduced；So from Actel companies A54SX72A-CQ208B types FPGA device realizing The low-power consumption of the space camera；
2) the small-sized implementation method of the space camera is：
1. the small-sized of the space camera is realized from IA-G3APS detectors；
Detector for space industry mainly includes two big class of CCD and APS detectors, although ccd detector technology maturation, but Cannot realize small-sized；The integrated level of APS detectors is high, low in energy consumption, Radiation hardness is strong, and its performance and image quality have Increase substantially, correlated-double-sampling, AD, AGC function are integrated by the IA-G3APS detectors that the space camera is adopted, Reduce volume, weight, power consumption；So realizing the small-sized of the space camera from IA-G3 colour APS detectors；
2. from Actel companies A54SX72A-CQ208B FPGA device realizing the small-sized of the space camera；
The space camera using the high Actel companies of integrated level A54SX72A-CQ208B types FPGA device achieving sky Between camera APS drive controls, mode of operation control, SRAM control, serial communication control, spectrum assignment and and turn string control, Hardware circuit is simplified, circuit board size is reduced, so as to alleviate the volume of the space camera；So public from Actel The A54SX72A-CQ208B types FPGA device of department is realizing the small-sized of the space camera；
3. the 4 row's mother daughter board connector of space flight level from Airborn is realizing the small-sized of the space camera；
Described space camera, its electronic system proportion in the weight of whole camera are less, and camera support structure is Entirely the topmost quality of camera weight is originated, so the weight for reducing camera support structure is maximally effective loss of weight measure；Will Reduce the weight of camera support structure, most effective of which measure is exactly to reduce camera volume；For small-sized space camera comes Say, camera volume is limited directly by the distance between the size of the pcb board of electronic system and pcb board；By to electronics system The optimization design of system, affect pcb board size and pcb board spacing are the adapters between pcb board；Tradition between pcb board is even Device physical dimension is connect than larger, the size of pcb board is not only increased, and is increased the distance between pcb board, whole so as to increase The weight of individual camera；4 row's mother daughter board connector of space flight level of Airborn, this high-density plate is adopted in described space camera Between adapter not only reduce pcb board size, and reduce the distance between pcb board, so as to reduce the volume of whole camera And weight；So, the 4 row's mother daughter board connector of space flight level from Airborn is realizing the small-sized of the space camera；
4. the small-sized of the space camera is realized by the Shape optimization designs of the clear aperture of shade；
Described space camera has added the square shade of certain length in the front of optical lens, alleviates the weight of shade Amount, so that alleviate volume, the weight of the space camera；So by the Shape optimization designs of the clear aperture of shade come Achieve the small-sized of the space camera；
5. the small-sized of the space camera is realized by optimizing optical system parameter；
Small light to be accomplished, except requiring structure division using the as far as possible little material of proportion and optimization design, and requires electricity Son learn systems attempt simple and using the device of high integration outside, it is necessary to focus on the optimization of optical parametric, optical system most simple Single structure form is to realize the basis of small light, and the optical parametric of the optical lens is determined by following formula：
S i m a g e = Φ 0 · ρ · τ · cosθ s · cosθ 0 4 · F 2 · B s · η · κ · t
Wherein, SimageFor accumulating electron number, Φ in single pixel0For solar photon number density, ρ is diffuse-reflectance coefficient；τ is optics System transmitance；θsFor imaging surface method arrow and sun angle, θoFor imaging surface method arrow and the angle of observer, F is the F numbers of camera, BsFor the area of single pixel, η is quantum efficiency, and κ is fill factor, curve factor, and t is time of exposure；
It is 420～700nm that the optical parametric of the optical lens is wavelength band, and visual field is 22.9 ° × 16.9 °, and focal length is 43mm, F number is 8, and normal imaging distance is 5m～∞, and transmission function MTF is more than 0.45；
After the version of optical system determines, the lightweight index that the optical lens can finally reach is also just substantially true Fixed, it is Ф 44mm that the design result of the optical lens is optical lens maximum caliber, and optical lens overall length is 54.5mm, optics Camera lens weight containing shade is 58g, so realizing the small-sized of the space camera by optimizing optical system parameter；
3) the multi-functional implementation method of the space camera is：
1. realize from IA-G3 colour APS detectors that the colored of the space camera obtains function；
The IA-G3 APS detectors that the space camera is adopted, IA-G3 APS detectors are the colour planes filtered based on Bayer Battle array CMOS, pixel surface increase red (R), green (G) or blue (B) optical filter according to Bayer rules, and each pixel can be quick Feel a kind of gradation；For the coloured image based on RGB, each pixel is both needed to R, G and B gray value；So selecting IA- G3 colour APS detectors obtain function come the colour for realizing the space camera；
2. the spuious Xanthophyll cycle of the space camera is realized by veiling glare braking measure inside Baffle design and optical lens Function；
The space camera has added the square shade of certain length in the front of optical lens, stops most of veiling glare outside visual field Enter；All optical elements of optical system will plate multi-layered antireflection coating；Delustring paint is applied on the non-working surface of optical element, is made Veiling glare is greatly attenuated in route of transmission；Delustring tooth be machined in body tube, picture frame inwall；So by Baffle design and light Veiling glare braking measure is learned inside camera lens realizing the spuious Xanthophyll cycle function of the space camera；
3. the automatic exposure of the space camera, standby mode, static exposal model, dynamic sampling are realized from FPGA device Image pickup mode and dynamic windowing image pickup mode function；
The space camera achieves the APS drive controls of space camera, mode of operation control, SRAM controls using FPGA device System, serial communication control, spectrum assignment and and turn string control；
A54SX72A-CQ208B types FPGA device from the high Actel companies of integrated level is realizing many of the space camera Function；
This is used for the low-power consumption of survey of deep space, small-sized, multi purpose space camera and employs IA-G3 color detectors, highly integrated 4 row's mother daughter board connector of space flight level of degree FPGA, Airborn has carried out the shade lightweight optimization design of space camera, optics The structure lightened design of the optimization design of system, camera support and electronic system optimization design, it is achieved that space camera work( Consume for 3.52W, weight is 460g, volume is 118.9mm × 110mm × 92mm, function be coloured image obtain, with an automatic light meter, Spuious Xanthophyll cycle, static state are taken pictures, dynamic of sampling shooting and windowing dynamic are imaged.
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