CN103983251A - Low-power consumption, light, small and multifunctional space camera for deep space detection and implementation method thereof - Google Patents

Low-power consumption, light, small and multifunctional space camera for deep space detection and implementation method thereof Download PDF

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Publication number
CN103983251A
CN103983251A CN201410234228.7A CN201410234228A CN103983251A CN 103983251 A CN103983251 A CN 103983251A CN 201410234228 A CN201410234228 A CN 201410234228A CN 103983251 A CN103983251 A CN 103983251A
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camera
space camera
aps
described space
detector
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CN103983251B (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 low-power consumption, light, small and multifunctional space camera for deep space detection. The space camera comprises a lens hood, an optics lens, an auxiliary propulsion system (APS) plate, a camera control plate and a camera supporting structure. The key is to introduce a lens hood lightweight optimization design technology, an optical system optimization design technology, a camera supporting structure lightweight design technology and electronic system optimization design to the space camera using an APS image sensor, so that the space camera is low in power consumption, light and small, and multifunctional; meanwhile, the space camera has the advantages of high imaging quality and strong environmental suitability; a demand of deep space detection on the low-power consumption, light, small and multifunctional space camera is met.

Description

A kind of low-power consumption for survey of deep space, small-sized, multi purpose space camera and its implementation
Technical field
The invention belongs to survey of deep space technical field of photoelectric detection, relate to a kind of low-power consumption for survey of deep space, small-sized, multi purpose space camera and its implementation.
Background technology
Development and survey of deep space mission requirements along with survey of deep space technology, the development trend of doing as the useful load (space camera) of survey of deep space indispensability is: along with technology is constantly progressive, the performance of space camera is more and more higher, the effect of bringing into play in survey of deep space is more and more important, and the entrained space camera of deep space probe also gets more and more; The scientific goal that space camera is born from single to diversification, from simple to complexity; That survey of deep space space camera trends towards is integrated, miniaturization and multifunction, alleviating quality, be lowered into wood, fuel saving, prolongation deep space probe life-span.One of gordian technique that low-power consumption thus, small-sized, multi-functional space camera Development Techniques are survey of deep space technical developments.
Survey of deep space task two aspects of demand main manifestations to low-power consumption, small-sized, multi-functional space camera, the demand of process monitoring on the one hand, in order to monitor more truly, more in real time the situation of key operations and the long-term state at supervision some position of detector of survey of deep space activity, grasp deep space probe critical component, can low-power consumption, small-sized, multi purpose space camera be installed at the different parts of detector, pass in time the image obtaining back ground; Be the demand of useful load on the other hand, this is a very important aspect.Develop a deep space probe, its final purpose is to survey a certain celestial body, obtains required information, realizes scientific goal, just needs configuration can meet the useful load of target requirement.Although useful load has plurality of classes, take optical imagery as basic load be all important and necessary all the time.
Summary of the invention
In view of this, fundamental purpose of the present invention is to provide a kind of low-power consumption for survey of deep space, small-sized, multi purpose space camera and its implementation.
In order to achieve the above object, technical scheme of the present invention is achieved in that
The invention provides a kind of low-power consumption for survey of deep space, small-sized, multi purpose space camera, comprise light shield, optical lens, APS plate, crimp type mother daughter board connector, camera control plate and camera supporting construction; Wherein, light shield, optical lens, APS plate, crimp type mother daughter board connector, camera control plate are placed successively,
Light shield, at the front end of described optical lens, for subduing the parasitic light outside visual field;
Optical lens, between light shield and APS plate, for collecting objective optics signal to be imaged, and is imaged on APS imageing sensor;
APS plate, between optical lens and camera control plate, collects optical signalling by optical lens and converts electrical signal to, realizes difference LVDS signal simultaneously and transfers single-ended signal and secondary power supply translation function to;
Crimp type mother daughter board connector, between APS plate and camera control plate, for connecting APS plate and camera control plate, realizes the signal transmission of two circuit boards;
Camera control plate, in space camera rear end, for control signal, collection image, output image, the serial communication of APS chip;
Camera supporting construction, for fixed optics camera lens, APS plate and camera control plate and realize external mechanical interface, guarantees the adaptation of space camera space radiation environment and the adaptation of mechanical environment.
In such scheme, the light hole of described light shield is rectangle light shield, and rectangular long limit is corresponding with the long limit of APS imageing sensor, and rectangular minor face is corresponding with the minor face of APS imageing sensor.22.9 ° * 16.9 ° field angle of rectangle light hole and described space camera adapt.
In such scheme, the APS imageing sensor on described APS plate is IA-G3 color detector, and pixel number is 2352 * 1728, imageing sensor 2352 corresponding with the long limit of light shield light hole, imageing sensor 1728 corresponding with the minor face of light shield light hole.
In such scheme, space flight level 4 row's mother daughter board connectors that described crimp type mother daughter board connector is Airborn.
In such scheme, the camera control FPGA on described camera control plate is the anti-molten formula FPGA of space flight level.
In such scheme, described camera control FPGA, comprise APS driver module, mode of operation control module, SRAM control module, serial communication module, exposure control module and and turn string module; Wherein,
APS driver module, for controlling the sequential of IA-G3 color image sensor;
Mode of operation control module, for according to the order of serial communication interface mode of operation, realizes standby, and static state is taken pictures, dynamically shooting sampling and the dynamically switching of four kinds of mode of operations of shooting windowing, thereby the output of control chart picture;
SRAM control module, operates required sequential for generation of memory read/write, realizes image buffer storage, column direction windowing and image sampling function;
Serial communication module, injects and engineering parameter query manipulation for completing external command;
Exposure control module, for realizing two kinds of patterns of automatic exposure and Manual exposure;
And turn string module, for 8 bit image data-switching after sram cache are become to 1 bit serial data.
In such scheme, the visual field of described space camera is 22.9 ° * 16.9 °, focal length is 43mm, F number is 8, normal imaging distance: 5m～∞, weight is 460g, power consumption is 3.52W, envelope is of a size of: 118.9mm * 110mm * 92mm, function is that coloured image obtains, with an automatic light meter, parasitic light suppresses, static state is taken pictures, dynamically shooting.
The implementation method of a kind of low-power consumption for survey of deep space provided by the invention, small-sized, multi purpose space camera, described space camera comprises light shield, optical lens, APS plate, crimp type mother daughter board connector, camera control plate and camera supporting construction; The visual field of described space camera is 22.9 ° * 16.9 °, focal length is 43mm, F number is 8, normal imaging distance: 5m～∞, weight is 460g, power consumption is 3.52W, and envelope is of a size of: 118.9mm * 110mm * 92mm, and function is that coloured image obtains, with an automatic light meter, parasitic light suppresses, static state is taken pictures, dynamically shooting; Described implementation method is:
1) implementation method of the low-power consumption of described space camera is:
1. select IA-G3APS detector to realize the low-power consumption of described space camera;
Detector for space industry mainly comprises CCD and the large class of APS detector two, although ccd detector technology maturation cannot realize low-power consumption.The integrated level of APS detector is high, low in energy consumption, Radiation hardness is strong, and its performance and image quality are improved largely, the IA-G3APS detector that described space camera adopts integrates the functions such as correlated-double-sampling, AD, AGC, has reduced volume, weight, power consumption.So select the colored APS detector of IA-G3, realize the low-power consumption of described space camera.
2. select the A54SX72A-CQ208B type FPGA device of Actel company to realize the low-power consumption of described space camera.
The APS that described space camera adopts the A54SX72A-CQ208B type FPGA device of the Actel company that integrated level is high to realize space camera drives and controls, mode of operation is controlled, SRAM controls, serial communication is controlled, exposure is controlled and and turn string and control, simplify hardware circuit, reduced power consumption.So select the A54SX72A-CQ208B type FPGA device of Actel company, realize the low-power consumption of described space camera.
2) the small-sized implementation method of described space camera is:
1. select IA-G3APS detector to realize the small-sized of described space camera;
Detector for space industry mainly comprises CCD and the large class of AP S detector two, although ccd detector technology maturation cannot realize small-sized.The integrated level of APS detector is high, low in energy consumption, Radiation hardness is strong, and its performance and image quality are improved largely, the IA-G3APS detector that described space camera adopts integrates the functions such as correlated-double-sampling, AD, AGC, has reduced volume, weight, power consumption.So select the colored APS detector of IA-G3, realize the small-sized of described space camera.
2. select the FPGA device of the A54SX72A-CQ208B of Actel company to realize the small-sized of described space camera;
The APS that described space camera adopts the A54SX72A-CQ208B type FPGA device of the Actel company that integrated level is high to realize space camera drives and controls, mode of operation is controlled, SRAM controls, serial communication is controlled, exposure is controlled and and turn string and control, simplified hardware circuit, reduce circuit board size, thereby alleviated the volume of described space camera.So select the A54SX72A-CQ208B type FPGA device of Actel company, realize the small-sized of described space camera.
3. select space flight level 4 row's mother daughter board connectors (RC442-052-351-4400) of Airborn to realize the small-sized of described space camera;
Described space camera, proportion is less in the weight of whole camera for its electronic system (pcb board, all kinds of devices etc.), camera supporting construction (guaranteeing the adaptability such as mechanical environment, radiation environment, thermal environment of camera) is the topmost quality of whole camera weight source, so reduce the weight of camera supporting construction, is the most effective loss of weight measure.Reduce the weight of camera supporting construction, wherein effective measures reduce camera volume exactly.For small-sized space camera, camera volume is directly limited to the size of pcb board of electronic system and the distance between pcb board.By the optimal design to electronic system, what affect pcb board size and pcb board spacing is the connector between pcb board.Traditional connector construction size between pcb board is larger, has not only increased the size of pcb board, and has increased the distance between pcb board, thereby increased the weight of whole camera.In described space camera, adopt space flight level 4 row's mother daughter board connectors (RC442-052-351-4400) of Airborn, this high density mother daughter board connector not only reduces pcb board size, and reduced the distance between pcb board, thereby reduced the volume and weight of whole camera.So, select space flight level 4 row's mother daughter board connectors (RC442-052-351-4400) of Airborn to realize the small-sized of described space camera.
4. the Shape optimization designs of the clear aperture by light shield realizes the small-sized of described space camera;
As shown in Figure 2, described space camera is according to optical system parameter, optical design and structural design have been carried out, traditional light shield adopts circular, and in the present invention, the square light shield that has added certain length in the place ahead of optical lens, has alleviated the weight of light shield, thereby has alleviated volume, the weight of described space camera.So the Shape optimization designs of the clear aperture by light shield has realized the small-sized of described space camera;
5. by optimizing optical systematic parameter, realize the small-sized of described space camera.
Accomplish small light, except claimed structure is partly used proportion try one's best little material and optimal design, and require electronic system as far as possible simple and use outside the device of high integration, must focus on the optimization of optical parametric.The simple structure form of optical system is the basis of realizing small light, and the optical parametric of described optical lens is determined by following formula.
S image = Φ 0 · ρ · τ · cos θ s · cos θ 0 4 · F 2 · B s · η · κ · t
Wherein, S imagefor accumulating electron number in single pixel, Φ 0for solar photon number density, ρ is diffuse-reflection factor; τ is transmissivity of optical system; θ sfor imaging surface method is vowed and sun angle, θ ofor the angle of imaging surface method arrow with observer, the F number that F is camera, B sfor the area of single pixel, η is quantum efficiency, and κ is fill factor, curve factor, and t is the time shutter;
The optical parametric of described optical lens is that wavelength band is 420～700nm, and visual field is 22.9 ° * 16.9 °, and focal length is 43mm, and F number is 8, and normal imaging distance is 5m～∞, and transport function MTF is for being greater than 0.45.
After the version of optical system is determined, the lightweight index that described optical lens finally can reach is also just substantially definite.The design result of described optical lens is that optical lens maximum caliber is Ф 44mm, and optical lens overall length is 54.5mm, and optical lens (containing light shield) weight is 58g, so realize the small-sized of described space camera by optimizing optical systematic parameter.
3) the multi-functional implementation method of described space camera is:
1. the colour of selecting the colored APS detector of IA-G3 to realize described space camera obtains function;
The IA-G3APS detector that described space camera adopts, IA-G3APS detector is the colour plane battle array CMOS based on Bayer filtering, pixel surface increases red (R), green (G) or blue (B) optical filter according to Bayer rule, and each pixel can responsive a kind of gradation.For the coloured image based on RGB, each pixel all needs to have R, G and B gray-scale value.So the colour of selecting the colored APS detector of IA-G3 to realize described space camera obtains function.
2. by Baffle design and the inner veiling glare braking measure of optical lens, realize the parasitic light inhibit feature of described space camera;
As shown in Figure 2, described space camera is according to optical system parameter, carried out optical design and structural design, and taked a series of veiling glare braking measure: in the place ahead of optical lens, added the square light shield of certain length, stopped most of veiling glare outside visual field and enter; All optical elements of optical system all will plate multi-layered antireflection coating; On the non-working surface of optical element, be coated with delustring paint, make veiling glare large high attenuation in route of transmission; At body tube, picture frame inwall, processed delustring tooth.So realize the parasitic light inhibit feature of described space camera by Baffle design and the inner veiling glare braking measure of optical lens
3. select the FPGA device of the A54SX72A-CQ208B of Actel company to realize the functions such as automatic exposure, standby mode, static exposal model, dynamic sampling image pickup mode and dynamic windowing image pickup mode of described space camera.
The APS that described space camera adopts the A54SX72A-CQ208B type FPGA device of the Actel company that integrated level is high to realize space camera drives and controls, mode of operation is controlled, SRAM controls, serial communication is controlled, exposure is controlled and and turn string and control.So select the A54SX72A-CQ208B type FPGA device of Actel company, realize the multi-functional of described space camera.
Compared with prior art, the advantage that the present invention has is: adopted IA-G3 color detector, high integration FPGA, space flight level 4 row's mother daughter board connectors of Airborn have carried out the light shield lightweight optimal design of space camera, the optimal design of optical system, camera supporting construction light-weight design and electronic system optimal design, having realized space camera power consumption is 3.52W, weight is 460g, volume is 118.9mm * 110mm * 92mm, function is that coloured image obtains, with an automatic light meter, parasitic light suppresses, static state is taken pictures, sampling is dynamically made a video recording and is windowed and dynamically makes a video recording.
Accompanying drawing explanation
Fig. 1 is that the system of space camera of the present invention forms schematic diagram;
In its figure, be labeled as: 11-light shield, 12-optical lens, 13-APS plate, 14-crimp type mother daughter board connector, 15-camera control plate, 16-camera supporting construction;
Fig. 2 is light shield and the optical lens schematic diagram of space camera of the present invention;
Fig. 3 is the camera control FPGA functional block diagram of space camera of the present invention;
In its figure, be labeled as: 21-APS driver module, 22-mode of operation control module, 23-SRAM control module, 24-serial communication module, 25-exposure control module, 26-also turn string module;
Fig. 4 is the specific embodiment of the space camera of space camera of the present invention.
Embodiment
Below in conjunction with drawings and the specific embodiments, the present invention is further described in more detail.
The index of the specific implementation of space camera provided by the invention is:
1) visual field: 22.9 ° * 16.9 °;
2) focal length: 43mm;
3) F number: 8;
4) normal imaging distance: 5m～∞;
5) weight: 460g;
6) power consumption: 3.52W;
7) envelope size: 118.9mm * 110mm * 92mm.
The function of the specific implementation of space camera provided by the invention is:
1) coloured image obtains function;
2) automatic dimming function;
3) parasitic light inhibit feature;
4) static camera function;
5) the dynamic camera function of sampling;
6) the dynamic camera function of windowing.
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, described space camera comprises light shield 11, optical lens 12, APS plate 13, crimp type mother daughter board connector 14, camera control plate 15 and camera supporting construction 16; Wherein,
Light shield 11, at the front end of described optical lens 12, for subduing the parasitic light outside visual field;
Optical lens 12, between light shield 11 and APS plate, for collecting objective optics signal to be imaged, and is imaged on APS imageing sensor;
APS plate 13, between optical lens 12 and camera control plate, collects optical signalling by optical lens 12 and converts electrical signal to, realizes difference LVDS signal simultaneously and transfers single-ended signal and secondary power supply translation function to;
Crimp type mother daughter board connector 14, between APS plate 13 and camera control plate 15, for connecting APS plate 13 and camera control plate 15, realizes the signal transmission of two circuit boards;
Camera control plate 15, in space camera rear end, for control signal, collection image, output image, the serial communication of APS chip;
Camera supporting construction 16, for fixed optics camera lens 12, APS plate 13 and camera control plate 14 and realize external mechanical interface, guarantees the adaptation of space camera space radiation environment and the adaptation of mechanical environment, as shown in 4.
As shown in Figure 2, the light hole of described light shield 11 is rectangle light shield, and rectangular long limit is corresponding with the long limit of APS imageing sensor, and rectangular minor face is corresponding with the minor face of APS imageing sensor.22.9 ° * 16.9 ° field angle of rectangle light hole and described space camera adapt.
APS imageing sensor on described APS plate 13 is IA-G3 color detector, and pixel number is 2352 * 1728, imageing sensor 2352 corresponding with the long limit of light shield light hole, imageing sensor 1728 corresponding with the minor face of light shield light hole.
Space flight level 4 row's mother daughter board connectors that described crimp type mother daughter board connector 14 is Airborn.
Camera control FPGA on described camera control plate 15 is the anti-molten formula FPGA of space flight level.
As shown in Figure 3, described camera control FPGA, comprise APS driver module 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 driver module 21, for controlling the sequential of IA-G3 color image sensor;
Mode of operation control module 22, for according to the order of serial communication interface mode of operation, realizes standby, and static state is taken pictures, dynamically shooting sampling and the dynamically switching of four kinds of mode of operations of shooting windowing, thereby the output of control chart picture;
SRAM control module 23, operates required sequential for generation of memory read/write, realizes image buffer storage, column direction windowing and image sampling function;
Serial communication module 24, injects and engineering parameter query manipulation for completing external command;
Exposure control module 25, for realizing two kinds of patterns of automatic exposure and Manual exposure;
And turn string module 26, for 8 bit image data-switching after sram cache are become to 1 bit serial data.
The visual field of described space camera is 22.9 ° * 16.9 °, focal length is 43mm, F number is 8, normal imaging distance: 5m～∞, weight is 460g, power consumption is 3.52W, and envelope is of a size of: 118.9mm * 110mm * 92mm, function is that coloured image obtains, with an automatic light meter, parasitic light suppresses, static state is taken pictures, dynamically shooting.
The implementation method of a kind of low-power consumption for survey of deep space provided by the invention, small-sized, multi purpose space camera, described space camera comprises light shield 11, optical lens 12, APS plate 13, crimp type mother daughter board connector 14, camera control plate 15 and camera supporting construction 16; The visual field of described space camera is 22.9 ° * 16.9 °, focal length is 43mm, F number is 8, normal imaging distance: 5m～∞, weight is 460g, power consumption is 3.52W, and envelope is of a size of: 118.9mm * 110mm * 92mm, and function is that coloured image obtains, with an automatic light meter, parasitic light suppresses, static state is taken pictures, dynamically shooting; Described implementation method is:
1) implementation method of the low-power consumption of described space camera is:
1. select IA-G3APS detector to realize the low-power consumption of described space camera;
Detector for space industry mainly comprises CCD and the large class of APS detector two, although ccd detector technology maturation cannot realize low-power consumption.The integrated level of APS detector is high, low in energy consumption, Radiation hardness is strong, and its performance and image quality are improved largely, the IA-G3APS detector that described space camera adopts integrates the functions such as correlated-double-sampling, AD, AGC, has reduced volume, weight, power consumption.So select the colored APS detector of IA-G3, realize the low-power consumption of described space camera.
2. select the A54SX72A-CQ208B type FPGA device of Actel company to realize the low-power consumption of described space camera.
The APS that described space camera adopts the A54SX72A-CQ208B type FPGA device of the Actel company that integrated level is high to realize space camera drives and controls, mode of operation is controlled, SRAM controls, serial communication is controlled, exposure is controlled and and turn string and control, simplify hardware circuit, reduced power consumption.So select the A54SX72A-CQ208B type FPGA device of Actel company, realize the low-power consumption of described space camera.
2) the small-sized implementation method of described space camera is:
1. select IA-G3APS detector to realize the small-sized of described space camera;
Detector for space industry mainly comprises CCD and the large class of APS detector two, although ccd detector technology maturation cannot realize small-sized.The integrated level of APS detector is high, low in energy consumption, Radiation hardness is strong, and its performance and image quality are improved largely, the IA-G3APS detector that described space camera adopts integrates the functions such as correlated-double-sampling, AD, AGC, has reduced volume, weight, power consumption.So select the colored APS detector of IA-G3, realize the small-sized of described space camera.
2. select the FPGA device of the A54SX72A-CQ208B of Actel company to realize the small-sized of described space camera;
The APS that described space camera adopts the A54SX72A-CQ208B type FPGA device of the Actel company that integrated level is high to realize space camera drives and controls, mode of operation is controlled, SRAM controls, serial communication is controlled, exposure is controlled and and turn string and control, simplified hardware circuit, reduce circuit board size, thereby alleviated the volume of described space camera.So select the A54SX72A-CQ208B type FPGA device of Actel company, realize the small-sized of described space camera.
3. select space flight level 4 row's mother daughter board connectors (RC442-052-351-4400) of Airborn to realize the small-sized of described space camera;
Described space camera, proportion is less in the weight of whole camera for its electronic system (pcb board, all kinds of devices etc.), camera supporting construction (guaranteeing the adaptability such as mechanical environment, radiation environment, thermal environment of camera) is the topmost quality of whole camera weight source, so reduce the weight of camera supporting construction, is the most effective loss of weight measure.Reduce the weight of camera supporting construction, wherein effective measures reduce camera volume exactly.For small-sized space camera, camera volume is directly limited to the size of pcb board of electronic system and the distance between pcb board.By the optimal design to electronic system, what affect pcb board size and pcb board spacing is the connector between pcb board.Traditional connector construction size between pcb board is larger, has not only increased the size of pcb board, and has increased the distance between pcb board, thereby increased the weight of whole camera.In described space camera, adopt space flight level 4 row's mother daughter board connectors (RC442-052-351-4400) of Airborn, this high density mother daughter board connector not only reduces pcb board size, and reduced the distance between pcb board, thereby reduced the volume and weight of whole camera.So, select space flight level 4 row's mother daughter board connectors (RC442-052-351-4400) of Airborn to realize the small-sized of described space camera.
4. the Shape optimization designs of the clear aperture by light shield realizes the small-sized of described space camera;
As shown in Figure 2, described space camera is according to optical system parameter, optical design and structural design have been carried out, traditional light shield adopts circular, and in the present invention, the square light shield that has added certain length in the place ahead of optical lens, has alleviated the weight of light shield, thereby has alleviated volume, the weight of described space camera.So the Shape optimization designs of the clear aperture by light shield has realized the small-sized of described space camera;
5. by optimizing optical systematic parameter, realize the small-sized of described space camera.
Accomplish small light, except claimed structure is partly used proportion try one's best little material and optimal design, and require electronic system as far as possible simple and use outside the device of high integration, must focus on the optimization of optical parametric.The simple structure form of optical system is the basis of realizing small light, and the optical parametric of described optical lens is determined by following formula.
S image = Φ 0 · ρ · τ · cos θ s · cos θ 0 4 · F 2 · B s · η · κ · t
Wherein, S imagefor accumulating electron number in single pixel, Φ 0for solar photon number density, ρ is diffuse-reflection factor; τ is transmissivity of optical system; θ sfor imaging surface method is vowed and sun angle, θ ofor the angle of imaging surface method arrow with observer, the F number that F is camera, B sfor the area of single pixel, η is quantum efficiency, and κ is fill factor, curve factor, and t is the time shutter;
The optical parametric of described optical lens is that wavelength band is 420～700nm, and visual field is 22.9 ° * 16.9 °, and focal length is 43mm, and F number is 8, and normal imaging distance is 5m～∞, and transport function MTF is for being greater than 0.45.
After the version of optical system is determined, the lightweight index that described optical lens finally can reach is also just substantially definite.The design result of described optical lens is that optical lens maximum caliber is Ф 44mm, and optical lens overall length is 54.5mm, and optical lens (containing light shield) weight is 58g, so realize the small-sized of described space camera by optimizing optical systematic parameter.
3) the multi-functional implementation method of described space camera is:
1. the colour of selecting the colored APS detector of IA-G3 to realize described space camera obtains function;
The IA-G3APS detector that described space camera adopts, IA-G3APS detector is the colour plane battle array CMOS based on Bayer filtering, pixel surface increases red (R), green (G) or blue (B) optical filter according to Bayer rule, and each pixel can responsive a kind of gradation.For the coloured image based on RGB, each pixel all needs to have R, G and B gray-scale value.So the colour of selecting the colored APS detector of IA-G3 to realize described space camera obtains function.
2. by Baffle design and the inner veiling glare braking measure of optical lens, realize the parasitic light inhibit feature of described space camera;
As shown in Figure 2, described space camera is according to optical system parameter, carried out optical design and structural design, and taked a series of veiling glare braking measure: in the place ahead of optical lens, added the square light shield of certain length, stopped most of veiling glare outside visual field and enter; All optical elements of optical system all will plate multi-layered antireflection coating; On the non-working surface of optical element, be coated with delustring paint, make veiling glare large high attenuation in route of transmission; At body tube, picture frame inwall, processed delustring tooth.So realize the parasitic light inhibit feature of described space camera by Baffle design and the inner veiling glare braking measure of optical lens
3. select the FPGA device of the A54SX72A-CQ208B of Actel company to realize the functions such as automatic exposure, standby mode, static exposal model, dynamic sampling image pickup mode and dynamic windowing image pickup mode of described space camera.
The APS that described space camera adopts the A54SX72A-CQ208B type FPGA device of the Actel company that integrated level is high to realize space camera drives and controls, mode of operation is controlled, SRAM controls, serial communication is controlled, exposure is controlled and and turn string and control.So select the A54SX72A-CQ208B type FPGA device of Actel company, realize the multi-functional of described space camera.

Claims (9)

1. the low-power consumption for survey of deep space, small-sized, multi purpose space camera, it is characterized in that, this space camera comprises light shield (11), optical lens (12), APS plate (13), crimp type mother daughter board connector (14), camera control plate (15) and camera supporting construction (16); Wherein, light shield (11), optical lens (12), APS plate (13), crimp type mother daughter board connector (14), camera control plate (15) are placed successively,
Light shield (11), for subduing the parasitic light outside visual field;
Optical lens (12), for by target imaging to be imaged at APS imageing sensor;
APS plate (13), for opto-electronic conversion, difference LVDS signal transfers single-ended signal to, secondary power supply conversion;
Crimp type mother daughter board connector (14), for connecting APS plate (13) and camera control plate (15), carries out signal transmission;
Camera control plate (15), for control signal, collection image, output image, the serial communication of APS chip;
Camera supporting construction (16), for fixed optics camera lens (12), APS plate (13) and camera control plate (14) and realize external mechanical interface.
2. space camera according to claim 1, it is characterized in that, the light hole of described light shield (11) is rectangle light shield, and rectangular long limit is corresponding with the long limit of APS imageing sensor, and rectangular minor face is corresponding with the minor face of APS imageing sensor; 22.9 ° * 16.9 ° field angle of rectangle light hole and described space camera adapt.
3. space camera according to claim 1, it is characterized in that, APS imageing sensor on described APS plate (13) is IA-G3 color detector, pixel number is 2352 * 1728, the long limit that detector pixel number is 2352 is corresponding with the long limit of light shield light hole, and the minor face that detector pixel number is 1728 is corresponding with the minor face of light shield light hole.
4. space camera according to claim 1, is characterized in that, space flight level 4 row's mother daughter board connectors that described crimp type mother daughter board connector (14) is Airborn.
5. space camera according to claim 1, is characterized in that, the camera control FPGA on described camera control plate (15) is the anti-molten formula FPGA of space flight level.
6. space camera according to claim 1 or 5, it is characterized in that, described camera control FPGA, comprise APS driver module (21), mode of operation control module (22), SRAM control module (23), serial communication module (24), exposure control module (25) and and turn and go here and there module (26); Wherein,
APS driver module (21), for controlling the sequential of APS imageing sensor;
Mode of operation control module (22), for according to the order of serial communication interface mode of operation, realizes standby, and static state is taken pictures, dynamically shooting sampling and the dynamically switching of four kinds of mode of operations of shooting windowing, thereby the output of control chart picture;
SRAM control module (23), operates required sequential for generation of memory read/write, realizes image buffer storage, column direction windowing and image sampling function;
Serial communication module (24), injects and engineering parameter query manipulation for completing external command;
Exposure control module (25), for realizing two kinds of patterns of automatic exposure and Manual exposure;
And turn string module (26), for 8 bit image data-switching after sram cache are become to 1 bit serial data.
7. space camera according to claim 1, it is characterized in that, the visual field of described space camera is 22.9 ° * 16.9 °, focal length is 43mm, and F number is 8, normal imaging distance: 5m～∞, weight is 460g, power consumption is 3.52W, and envelope is of a size of: 118.9mm * 110mm * 92mm, the function having is that coloured image obtains, with an automatic light meter, parasitic light suppresses, static state is taken pictures, dynamically shooting.
8. the implementation method of the low-power consumption for survey of deep space, small-sized, multi purpose space camera, it is characterized in that, described space camera comprises light shield (11), optical lens (12), APS plate (13), crimp type mother daughter board connector (14), camera control plate (15) and camera supporting construction (16); The visual field of described space camera is 22.9 ° * 16.9 °, focal length is 43mm, F number is 8, normal imaging distance: 5m～∞, weight is 460g, power consumption is 3.52W, and envelope is of a size of: 118.9mm * 110mm * 92mm, and the function having is that coloured image obtains, with an automatic light meter, parasitic light suppresses, static state is taken pictures, dynamically shooting; Described implementation method is:
1) implementation method of the low-power consumption of described space camera is:
1. select IA-G3APS detector to realize the low-power consumption of described space camera;
Detector for space industry mainly comprises CCD and the large class of APS detector two, although ccd detector technology maturation cannot realize low-power consumption; The integrated level of APS detector is high, low in energy consumption, Radiation hardness is strong, and its performance and image quality are improved largely, the IA-G3APS detector that described space camera adopts integrates correlated-double-sampling, AD, AGC function, has reduced volume, weight, power consumption; So select the colored APS detector of IA-G3, realize the low-power consumption of described space camera;
2. select the A54SX72A-CQ208B type FPGA device of Actel company to realize the low-power consumption of described space camera;
The APS that described space camera adopts the A54SX72A-CQ208B type FPGA device of the Actel company that integrated level is high to realize space camera drives and controls, mode of operation is controlled, SRAM controls, serial communication is controlled, exposure is controlled and and turn string and control, simplify hardware circuit, reduced power consumption; So select the A54SX72A-CQ208B type FPGA device of Actel company, realize the low-power consumption of described space camera;
2) the small-sized implementation method of described space camera is:
1. select IA-G3APS detector to realize the small-sized of described space camera;
Detector for space industry mainly comprises CCD and the large class of APS detector two, although ccd detector technology maturation cannot realize small-sized; The integrated level of APS detector is high, low in energy consumption, Radiation hardness is strong, and its performance and image quality are improved largely, the IA-G3APS detector that described space camera adopts integrates correlated-double-sampling, AD, AGC function, has reduced volume, weight, power consumption; So select the colored APS detector of IA-G3, realize the small-sized of described space camera;
2. select the FPGA device of the A54SX72A-CQ208B of Actel company to realize the small-sized of described space camera;
The APS that described space camera adopts the A54SX72A-CQ208B type FPGA device of the Actel company that integrated level is high to realize space camera drives and controls, mode of operation is controlled, SRAM controls, serial communication is controlled, exposure is controlled and and turn string and control, simplified hardware circuit, reduce circuit board size, thereby alleviated the volume of described space camera; So select the A54SX72A-CQ208B type FPGA device of Actel company, realize the small-sized of described space camera;
3. select space flight level 4 row's mother daughter board connectors of Airborn to realize the small-sized of described space camera;
Described space camera, its electronic system proportion in the weight of whole camera is less, and camera supporting construction is the topmost quality of whole camera weight source, so reduce the weight of camera supporting construction, is the most effective loss of weight measure; Reduce the weight of camera supporting construction, wherein effective measures reduce camera volume exactly; For small-sized space camera, camera volume is directly limited to the size of pcb board of electronic system and the distance between pcb board; By the optimal design to electronic system, what affect pcb board size and pcb board spacing is the connector between pcb board; Traditional connector construction size between pcb board is larger, has not only increased the size of pcb board, and has increased the distance between pcb board, thereby increased the weight of whole camera; The space flight level 4 row's mother daughter board connectors that adopt Airborn in described space camera, this high density mother daughter board connector not only reduces pcb board size, and has reduced the distance between pcb board, thereby has reduced the volume and weight of whole camera; So, select space flight level 4 row's mother daughter board connectors of Airborn to realize the small-sized of described space camera;
4. the Shape optimization designs of the clear aperture by light shield realizes the small-sized of described space camera;
Described space camera has added the square light shield of certain length in the place ahead of optical lens, alleviated the weight of light shield, thereby has alleviated volume, the weight of described space camera; So the Shape optimization designs of the clear aperture by light shield has realized the small-sized of described space camera;
5. by optimizing optical systematic parameter, realize the small-sized of described space camera;
Accomplish small light, except claimed structure is partly used proportion try one's best little material and optimal design, and require electronic system try one's best simple and use outside the device of high integration, must focus on the optimization of optical parametric, the simple structure form of optical system is the basis of realizing small light, and the optical parametric of described optical lens is determined by following formula:
S image = Φ 0 · ρ · τ · cos θ s · cos θ 0 4 · F 2 · B s · η · κ · t
Wherein, S imagefor accumulating electron number in single pixel, Φ 0for solar photon number density, ρ is diffuse-reflection factor; τ is transmissivity of optical system; θ sfor imaging surface method is vowed and sun angle, θ ofor the angle of imaging surface method arrow with observer, the F number that F is camera, B sfor the area of single pixel, η is quantum efficiency, and κ is fill factor, curve factor, and t is the time shutter;
The optical parametric of described optical lens is that wavelength band is 420～700nm, and visual field is 22.9 ° * 16.9 °, and focal length is 43mm, and F number is 8, and normal imaging distance is 5m～∞, and transport function MTF is for being greater than 0.45;
After the version of optical system is determined, the lightweight index that described optical lens finally can reach is also just substantially definite.The design result of described optical lens is that optical lens maximum caliber is Ф 44mm, and optical lens overall length is 54.5mm, and optical lens is 58g containing light shield weight, so realize the small-sized of described space camera by optimizing optical systematic parameter;
3) the multi-functional implementation method of described space camera is:
1. the colour of selecting the colored APS detector of IA-G3 to realize described space camera obtains function;
The IA-G3APS detector that described space camera adopts, IA-G3APS detector is the colour plane battle array CMOS based on Bayer filtering, pixel surface increases red (R), green (G) or blue (B) optical filter according to Bayer rule, and each pixel can responsive a kind of gradation; For the coloured image based on RGB, each pixel all needs to have R, G and B gray-scale value; So the colour of selecting the colored APS detector of IA-G3 to realize described space camera obtains function;
2. by Baffle design and the inner veiling glare braking measure of optical lens, realize the parasitic light inhibit feature of described space camera;
Described space camera has added the square light shield of certain length in the place ahead of optical lens, stop most of veiling glare outside visual field and enter; All optical elements of optical system all will plate multi-layered antireflection coating; On the non-working surface of optical element, be coated with delustring paint, make veiling glare large high attenuation in route of transmission; At body tube, picture frame inwall, processed delustring tooth; So realize the parasitic light inhibit feature of described space camera by Baffle design and the inner veiling glare braking measure of optical lens;
3. select FPGA device to realize the automatic exposure of described space camera, standby mode, static exposal model, dynamic sampling image pickup mode and dynamic windowing image pickup mode function;
The APS that described space camera adopts FPGA device to realize space camera drives and controls, mode of operation is controlled, SRAM controls, serial communication is controlled, exposure is controlled and and turn string and control.
9. implementation method according to claim 8, is characterized in that, so select the A54SX72A-CQ208B type FPGA device of the Actel company that integrated level is high to realize the multi-functional of described space camera.
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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104184958A (en) * 2014-09-17 2014-12-03 中国科学院光电技术研究所 Automatic exposure control method and device based on FPGA and suitable for space exploration imaging
CN104864854A (en) * 2015-06-01 2015-08-26 中国科学院光电技术研究所 Monocular vision pose measurement method based on weighting and constraining of side, interior angle and shape factor of triangle
CN107112695A (en) * 2014-10-21 2017-08-29 康诺特电子有限公司 Camera and motor vehicles for motor vehicles
CN107831628A (en) * 2017-11-07 2018-03-23 中国科学院西安光学精密机械研究所 optical, mechanical and electronic integration space camera
CN109343297A (en) * 2018-10-25 2019-02-15 中国科学院西安光学精密机械研究所 A kind of passive thermal control type lunar surface camera and imaging method
CN109660706A (en) * 2018-12-18 2019-04-19 青岛小鸟看看科技有限公司 A kind of depth camera
CN111854696A (en) * 2020-07-02 2020-10-30 中国科学院光电技术研究所 High-reliability step-by-step picture type staring three-dimensional imaging space camera and implementation method thereof
CN113660403A (en) * 2021-08-23 2021-11-16 长春理工大学 Satellite-borne ultra-miniature monitoring camera

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1875544A (en) * 2003-07-14 2006-12-06 罗切斯特大学 Multiplexed-input-separated sigma-delta analog-to-digital converter design for pixel-level analog-to-digital conversion
CN201345029Y (en) * 2009-01-19 2009-11-11 浙江悍马光电设备有限公司 Stereoscopic camera with single lens
US20120182467A1 (en) * 2008-09-10 2012-07-19 Panasonic Corporation Camera body and imaging device

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1875544A (en) * 2003-07-14 2006-12-06 罗切斯特大学 Multiplexed-input-separated sigma-delta analog-to-digital converter design for pixel-level analog-to-digital conversion
US20120182467A1 (en) * 2008-09-10 2012-07-19 Panasonic Corporation Camera body and imaging device
CN201345029Y (en) * 2009-01-19 2009-11-11 浙江悍马光电设备有限公司 Stereoscopic camera with single lens

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
唐承佩等: "基于FPGA 的多传感器融合单元的设计研究", 《传感技术学报》 *
张彬彬等: "航天器电子产品用板间电连接器典型失效模式研究", 《电子工艺技术》 *
范铁道等: "基于FPGA 的CMOS图像感器IA_G3 驱动电路的研究", 《电子器件》 *

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104184958A (en) * 2014-09-17 2014-12-03 中国科学院光电技术研究所 Automatic exposure control method and device based on FPGA and suitable for space exploration imaging
CN104184958B (en) * 2014-09-17 2017-07-11 中国科学院光电技术研究所 A kind of automatic exposure control method and its device based on FPGA suitable for space exploration imaging
CN107112695A (en) * 2014-10-21 2017-08-29 康诺特电子有限公司 Camera and motor vehicles for motor vehicles
CN104864854A (en) * 2015-06-01 2015-08-26 中国科学院光电技术研究所 Monocular vision pose measurement method based on weighting and constraining of side, interior angle and shape factor of triangle
CN104864854B (en) * 2015-06-01 2017-09-22 中国科学院光电技术研究所 It is a kind of based on the triangle length of side, interior angle, form factor Weighted Constraint monocular vision pose measuring method
CN107831628A (en) * 2017-11-07 2018-03-23 中国科学院西安光学精密机械研究所 optical, mechanical and electronic integration space camera
CN109343297A (en) * 2018-10-25 2019-02-15 中国科学院西安光学精密机械研究所 A kind of passive thermal control type lunar surface camera and imaging method
CN109660706A (en) * 2018-12-18 2019-04-19 青岛小鸟看看科技有限公司 A kind of depth camera
CN111854696A (en) * 2020-07-02 2020-10-30 中国科学院光电技术研究所 High-reliability step-by-step picture type staring three-dimensional imaging space camera and implementation method thereof
CN113660403A (en) * 2021-08-23 2021-11-16 长春理工大学 Satellite-borne ultra-miniature monitoring camera

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