CN203053454U - Detection capacity detection system of space optical system - Google Patents

Abstract

The utility model relates to a detection capacity detection system of a space optical system. The detection system comprises a light source system, a collimation system, a star point unit, an optical spectrum collection unit, a main control system, a data processing unit and a display unit, wherein the collimation system and the optical spectrum collection unit are respectively arranged on an emergent light path of the light source; the star point unit is arranged between the light source system and the collimation system and on a focal plane of the light source system; a space optical system to be measured is arranged on the emergent light path passing through the collimation system; the data processing unit is respectively connected with the display unit and the space optical system to be measured; and the main control system is respectively connected with the space optical system to be measured, the light source system and the optical spectrum collection unit. The detection capacity detection system of the space optical system can reliably and accurately obtain the detection data and is convenient to operate.

Description

Space Optical System detectivity detection system

Technical field

The utility model belongs to the optical detection field, relates to a kind of Space Optical System detectivity detection system, relates in particular to a kind of detection system that Space Optical System detection limit and encircled energy two big indexs are tested.

Background technology

Space Optical System is surveyed extraterrestrial target, and its detectivity has determined the practicality of system.In order fully to verify the detectivity of optical system, need carry out full test to its detectivity.The test of detection limit, encircled energy is enough to than more comprehensively the detectivity of optical system being estimated.On the one hand, the test of detection limit can determine that optical system is to the limit response of weak target.On the other hand, the test of encircled energy can be understood the energy distribution of optical system after to target imaging.For space orientations such as star sensor, navigation optical system, encircled energy then directly influences its spatial attitude measuring accuracy.Encircled energy is more high, and detection limit is more high, but attitude measurement accuracy is tending towards reducing; Encircled energy is too low, then can't survey more weak target, and attitude control is not just known where to begin yet.So two indexs of detection limit and encircled energy condition each other, and have only both to work in coordination, and could bring into play the detectivity of optical system to greatest extent.Therefore, to the research of Space Optical System detectivity laboratory context of detection, just seem very necessary.

Domestic now have corresponding visible light and ultraviolet magnitude simulator, but all can't finish the automatic measurement to detection limit and encircled energy.At this a kind of Space Optical System detectivity detection system, the test that can cover these two indexs are proposed.

The utility model content

In order to solve the above-mentioned technical matters that exists in the background technology, the utility model provides a kind of can reliably reaching accurately to obtain the Space Optical System detectivity detection system that detects data and be convenient to operate.

Technical solution of the present utility model is: the utility model provides a kind of Space Optical System detectivity detection system, it is characterized in that: described Space Optical System detectivity detection system comprises light-source system, colimated light system, asterism unit, spectra collection unit, master control system, data processing unit and display unit; Described colimated light system and spectra collection unit are separately positioned on the emitting light path of light source; Described asterism unit is arranged between light-source system and the colimated light system and is on the focal plane of light-source system; Space Optical System to be measured is arranged on the emitting light path behind the colimated light system; Described data processing unit links to each other with display unit and Space Optical System to be measured respectively; Described master control system links to each other with Space Optical System to be measured, light-source system and spectra collection unit respectively.

Above-mentioned colimated light system off-axis reflection optical system; Described off-axis reflection optical system comprises off axis paraboloid mirror primary mirror, first a folding axle mirror, second folding axle mirror and the iris; The described first folding axle mirror, the second folding axle mirror and off axis paraboloid mirror primary mirror are successively set on light-source system on the emitting light path behind the asterism unit; Described Space Optical System to be measured is arranged on the emitting light path after the reflection of off axis paraboloid mirror primary mirror; Described iris is arranged between off axis paraboloid mirror primary mirror and the Space Optical System to be measured; Described iris is the parasitic light diaphragm that disappears; Described off-axis reflection optical system is that bore is that Φ 500mm and focal length are the off-axis reflection optical systems of 5000mm.

Above-mentioned light-source system comprises canonical product bulb separation, halogen tungsten lamp, xenon lamp and adjustable power supply; Described halogen tungsten lamp and xenon lamp are arranged on the inwall of canonical product bulb separation; Described master control system links to each other with halogen tungsten lamp and xenon lamp respectively by adjustable power supply.

Above-mentioned asterism unit is asterism target target plate; Described spectra collection unit is the spectral radiant emittance meter.

The utility model has the advantages that:

The utility model utilizes least square Gauss curve fitting method first, computer memory optical system disc of confusion diameter, and with this encircled energy is estimated.The limitation that surmounts tradition " number pixel " method, the data fitting processing mode with a kind of more reasonable, science has obtained to detect reliably, accurately data.

The utility model uses a kind of new signal to noise ratio (S/N ratio) formula, and the signal to noise ratio (S/N ratio) when the Space Optical System limit is surveyed is calculated, and also belongs to initiative at home.

The utility model is controlled colimated light system light-emitting window spoke brightness value by two kinds of feedback systems.The one, by spectral radiant emittance instrumentation amount colimated light system light-emitting window spoke brightness value, calculate real time data and feed back to the output of master control system control light source power supply power supply.The 2nd, by calculating signal noise ratio (snr) of image, master control system is controlled the output of light source power supply power supply in real time according to the gained snr value.Can obtain two groups of data like this: the one, at the target signal to noise ratio of specifying under the apparent magnitude energy; The 2nd, specifying the limit under the signal to noise ratio (S/N ratio) to survey energy (being apparent magnitude illuminance).

Space Optical System detectivity detection system of the present utility model, light source is selected the integrating sphere light source for use, has improved the stability of test.

Space Optical System detectivity detection system of the present utility model, light source is selected halogen tungsten lamp, xenon lamp reciprocally incorporated lamp for use, can realize the combination of broadband spectral energy proportioning and multiple colour temperature.

Space Optical System detectivity detection system of the present utility model, the asterism unit is selected the standard asterism of higher circularity for use, can improve the precision of test.

Space Optical System detectivity detection system of the present utility model, colimated light system select for use 5000mm from axle three antiparallel light pipes, introduce aberration hardly, improve measuring accuracy greatly.Select this parallel light tube for use, can simulate very faint starlight target (limiting apparent magnitude 16Mv), improved the test specification of native system.

Space Optical System detectivity detection system of the present utility model, the spectra collection unit is selected high precision spectral radiant emittance meter for use, and has carried out the standard transmission by the canonical product bulb separation that NIST traces to the source, and can obtain test result very accurately.

Space Optical System detectivity detection system of the present utility model, the place is equipped with iris at colimated light system outgoing window, can adjust the bore of colimated light system outgoing beam according to the clear aperture size of different spaces camera, to satisfy the needs of different cameral test.

Space Optical System detectivity detection system of the present utility model, the place is equipped with iris at colimated light system outgoing window, can effectively block parasitic light, improves measuring accuracy.

Description of drawings

Fig. 1 is the structural representation of Space Optical System detectivity detection system provided by the utility model;

Fig. 2 is the Gauss curve fitting design sketch;

Wherein:

The 1-light-source system; 2-asterism unit; 3-off axis paraboloid mirror primary mirror; The 4-first folding axle mirror; The 5-second folding axle mirror; The 6-iris; 7-Space Optical System to be measured; 8-spectral radiant emittance meter; The 9-electronic control translation stage; The automatically controlled turntable of 10-; The 11-master control system; The 12-data processing unit; The 13-display unit; The 14-colimated light system.

Embodiment

Referring to Fig. 1, the utility model provides a kind of Space Optical System detectivity detection system, and this Space Optical System detectivity detection system comprises light-source system 1, colimated light system 14, asterism unit 2, spectra collection unit, master control system 11, data processing unit 12 and display unit 13; Colimated light system 14 and spectra collection unit are separately positioned on the emitting light path of light source; Asterism unit 2 is arranged between light-source system 1 and the colimated light system 14 and is on the focal plane of light-source system 1; Space Optical System 7 to be measured is arranged on the emitting light path behind the colimated light system 14; Data processing unit 12 links to each other with display unit 13 and Space Optical System to be measured 7 respectively; Master control system 11 links to each other with Space Optical System 7 to be measured, light-source system 1 and spectra collection unit respectively.

Colimated light system 14 off-axis reflection optical systems; The off-axis reflection optical system comprises off axis paraboloid mirror primary mirror 3, the first folding axle mirror 4, second folding axle mirror 5 and the iris 6; The first folding axle mirror 4, the second folding axle mirror 5 and off axis paraboloid mirror primary mirror 3 are successively set on light-source system 1 on the emitting light path behind the asterism unit 2; Space Optical System 7 to be measured is arranged on the emitting light path after 3 reflections of off axis paraboloid mirror primary mirror; Iris 6 is arranged between off axis paraboloid mirror primary mirror 3 and the Space Optical System to be measured 7; Iris 6 is the parasitic light diaphragms that disappear; The off-axis reflection optical system is that bore is that Φ 500mm and focal length are the off-axis reflection optical systems of 5000mm.

Light-source system 1 comprises canonical product bulb separation, halogen tungsten lamp, xenon lamp and adjustable power supply; Halogen tungsten lamp and xenon lamp are arranged on the inwall of canonical product bulb separation; Master control system 11 links to each other with halogen tungsten lamp and xenon lamp respectively by adjustable power supply.The canonical product bulb separation is emergent light evenly; Halogen tungsten lamp, xenon lamp reciprocally incorporated lamp be proportioning mutually, obtains the simulated solar spectrum of corresponding colour temperature; Adjustable power supply can be by the regulating and controlling light-source brightness of master control system 11.

Asterism unit 2 is asterism target target plates; The spectra collection unit is spectral radiant emittance meter 8.Spectral radiant emittance meter 8 is arranged on colimated light system 14 light-emitting window places, and is carried on the translation stage that control module controls.

Main control unit is power supply controller, automatically controlled turntable 10 controllers and controllor for step-by-step motor, the power supply controller is adjusted light-source brightness, automatically controlled turntable 10 controllers are adjusted light source direction, the 14 light-emitting window places translation stage motion of controllor for step-by-step motor control colimated light system.Automatically controlled turntable 10 carrying integrating sphere light sources rotate, and electronic control translation stage 9 carryings Space Optical System 7 to be measured also can make it to move at colimated light system 14 light-emitting window places.

Data processing unit 12 comprises that receiving spectrum radiancy meter 8 data carry out the software that integral operation, irradiance convert, target signal to noise ratio is calculated and utilizes least square Gauss curve fitting method that the target energy concentration degree is calculated to the apparent magnitude, belong to self-developed software, concrete irradiance integration, irradiance are encapsulated in wherein to apparent magnitude conversion, signal to noise ratio (S/N ratio), disc of confusion diameter (encircled energy) algorithm.

Disc of confusion diameter algorithm is to aim at encircled energy to measure the novel algorithm of developing.

Spoke brightness is to calculate with reference to human eye vision photopic vision function and apparent magnitude definition that CIE issues to the process of changing between the apparent magnitude.

Automatically controlled turntable 10 is via master control system 11 controls, the integrating sphere light source 1 that rotation is carried on the turntable top turns to 8 faces direction of spectral radiant emittance meter, spectral radiant emittance meter 8 is gathered the real-time spoke brightness value in light-emitting window place, and submit to data processing unit 12, after calculating integration spoke brightness value, compare with setting value, and then the output of control integrating sphere light source power supply power supply, when acquisition is identical with setting spoke brightness value, stop the change to power supply; The integrating sphere light source is rotated, its light that sends is radiated on the asterism 2; Asterism 2 is positioned on the focal plane of colimated light system 14, through the light of asterism by 5 dozens in the first folding axle mirror 4 and the second folding axle mirror on the primary mirror 3 of colimated light system, with parallel beam from the colimated light system outgoing; The place is provided with iris 6 at the outgoing window, both can suppress parasitic light, can also be used for the bore of control parallel beam; Master control system 11 moves electronic control translation stage 7 motion, and Space Optical System 7 is moved to colimated light system 14 light-emitting window places, and asterism unit 2 is carried out memory image after the imaging; According to image, utilize respective algorithms, carry out the measurement of detection limit and encircled energy.

Simultaneously, the concrete course of work of the present utility model is:

1) surveys TV star's equivalence of Space Optical System to be measured, and gather the image of TV star's equivalent time;

The specific implementation of step 1) is:

When light source igniting, master control system turns to spectral radiant emittance meter direction with light source earlier, carries out the spectral information collection.Data processing unit carries out corresponding calculating to the spectroscopic data of gathering, and feeds back to master control system.The control flow of master control system by arranging in advance, the power supply output in the ACTIVE CONTROL light-source system, up to reaching desired, stable test condition, TV star's equivalence that obtain by conversion this moment is system's detection limit.The electronic control translation stage of master control system control then moves to parallel light tube light-emitting window place with Space Optical System to be measured and gathers image.Data processing unit calculates obtaining image, obtains target signal to noise ratio, particularly:

1.1.1) light light-source system;

1.1.2) by the spectra collection unit to light-source system spectral information gather;

1.1.3) by data processing unit the spectroscopic data of gathering is carried out corresponding calculating and feeds back to master control system;

1.1.3.1) spectroscopic data that collects is carried out associated quad calculating, obtain spectral irradiance E (λ) value at colimated light system light-emitting window place, its computing formula is:

$E\left(\mathrm{\λ}\right)=\frac{\mathrm{\π}}{4}{g\left(\frac{d}{f^{\′}}\right)}^2\mathrm{gL}\left(\mathrm{\λ}\right)\mathrm{g\τ}$

Wherein:

D is the asterism element diameter;

F ' is the colimated light system focal length;

L (λ) is the spoke brightness value;

τ is the transmitance of colimated light system;

1.1.3.2) with step 1.1.3.1) resulting spectral irradiance E (λ) value calculates the illuminance value E at colimated light system light-emitting window place _Illuminance, its computing formula is:

Wherein:

K _mBe the corresponding photopic vision maximum spectral luminous efficacy of human eye constant, described K _mGet 683lm/W;

V (λ) is human eye photopic vision function;

1.1.4) power supply output in the master control system control light-source system;

1.1.5) calculate the TV star equivalent and with the TV star who calculates equivalent with require TV star's equivalence of index to compare, if meet the requirements index, then carry out step 1.1.6); If undesirable index is then returned step 1.1.4); Described TV star's equivalence is system's detection limit;

With step 1.1.3.1) resulting illuminance value E _IlluminanceCalculate the apparent magnitude m value, its computing formula is:

LgE _Illuminance-lgE ₀=0.4 (m-0)

Wherein:

E ₀Be the illuminance of zero correspondence such as star such as grade, described E ₀Be 2.648 * 10 ^-6Lx;

Described step 1.1.7) computation process is carried out according to following formula:

$\mathrm{SNR}=\frac{S_E}{N_E}=\frac{S_C}{\sqrt{\frac{S_C}{g}+\frac{B_C}{g}+{\mathrm{<figure-callout\; id="2"\; label="N"\; filenames="DEST\_PATH\_HDA00003083699200011.png,DEST\_PATH\_HDA00003083699200012.png"\; state="\{\{state\}\}">N</figure-callout>}}^2}}$

Wherein:

S _CBe the DN value sum of target in 3 * 3 pixels;

S _EIt is the signal of representing with electron number;

B _CBe dark background mean value;

N _EIt is the background signal of representing with electron number;

N is the standard deviation of dark background;

G is the gain of CCD.

1.1.6) Space Optical System to be measured is moved to the light-emitting window place of colimated light system and gathers image;

1.1.7) by data processing unit the image that obtains is calculated, obtain target signal to noise ratio.

In addition, the specific implementation of the mentioned step 1) of the utility model can also be in the following way:

When light source illuminated the asterism target, master control system control electronic control translation stage moved to parallel light tube light-emitting window place with Space Optical System to be measured and gathers image, and data processing unit calculates obtaining image, obtains target signal to noise ratio.Judge the signal to noise ratio (S/N ratio) size and adjust the output of light source power supply power supply with this, reach setting value until signal to noise ratio (S/N ratio).The light source of master control system control then turns to spectral radiant emittance meter direction, gathers spectral information, carries out corresponding data and handles, and obtains system's detection limit value.Gather image this moment, the computing system encircled energy, particularly:

1.2.1) light light-source system;

1.2.2) light-emitting window place that Space Optical System to be measured is moved to colimated light system gathers image;

1.2.3) data processing unit calculates according to following formula obtaining image, obtains target signal to noise ratio;

$\mathrm{SNR}=\frac{S_E}{N_E}=\frac{S_C}{\sqrt{\frac{S_C}{g}+\frac{B_C}{g}+{\mathrm{<figure-callout\; id="2"\; label="N"\; filenames="DEST\_PATH\_HDA00003083699200011.png,DEST\_PATH\_HDA00003083699200012.png"\; state="\{\{state\}\}">N</figure-callout>}}^2}}$

Wherein:

S _CBe the DN value sum of target in 3 * 3 pixels;

S _EIt is the signal of representing with electron number;

B _CBe dark background mean value;

N _EIt is the background signal of representing with electron number;

N is the standard deviation of dark background;

G is the gain of CCD;

1.2.4) judge the signal to noise ratio (S/N ratio) size, the setting value if target signal to noise ratio meets the requirements is then carried out step 1.2.5); If the undesirable setting value of target signal to noise ratio is then adjusted the output of light source power supply power supply, after signal to noise ratio (S/N ratio) reaches setting value, carry out step 1.2.5 again):

The concrete account form of spectral irradiance E (λ) value is:

$E\left(\mathrm{\&lambda;}\right)=\frac{\mathrm{\&pi;}}{4}{g\left(\frac{d}{f^{\&prime;}}\right)}^2\mathrm{gL}\left(\mathrm{\&lambda;}\right)\mathrm{g\&tau;}$

Wherein:

D is the asterism element diameter;

F ' is the colimated light system focal length;

L (λ) is the spoke brightness value;

τ is the transmitance of colimated light system.

1.2.5) gather the spectral information of spectra collection unit, carry out corresponding data and handle, obtain spectral irradiance E (λ) value, described spectral irradiance E (λ) value is system's detection limit value;

1.2.6) image during acquisition system detection limit value.

More than two kinds of control modes can satisfy the different spaces optical system to the needs of detection limit index test.On the one hand, directly instruct master control system to carry out the magnitude simulation with the charter specific targets, by calculating signal to noise ratio (S/N ratio), pass judgment on the optical system limit and survey index at last; On the other hand, by a series of calculating and adjustment, make it possible to record under fixing signal to noise ratio (S/N ratio) the most weak target magnitude that optical system can be surveyed.This dual mode by the cooperation of spectral radiant emittance meter and Space Optical System, has been finished the automatic mensuration of detection limit based on master control system, has improved whole testing efficiency, more comprehensively detection limit is detected.

2) encircled energy of the image calculation Space Optical System to be measured that collects according to step 1).

Select the asterism of suitable diameter d according to the focal distance f of the bore D of optical system and colimated light system, Space Optical System is placed on colimated light system light-emitting window place, regulate light-source brightness, make the asterism picture in image near saturated, gather image, by least square Gauss curve fitting method computing system encircled energy.

The mensuration of encircled energy

Select the asterism of suitable diameter d according to the focal distance f of the bore D of optical system and colimated light system, see formula:

$d\&le;\frac{1.22\mathrm{\&lambda;}}{D}\mathrm{gf}---\left(5\right)$

Space Optical System is placed on colimated light system light-emitting window place, regulates light-source brightness, make the asterism picture in image near saturated, the collection image, calculate according to the following steps:

The asterism figure that takes is gone background, and background value is B:

B=A _pixel+5·σ _pixel （6）

When the disperse unit bright image DN of unit value during greater than this threshold value of B, just can be detected.

A _PixelThe average gray value of signal pattern view picture figure during for the bat star;

σ _PixelBe the dark background noise figure.

Centered by disperse unit gray scale peak, getting 9 * 9 pixels is regional C, is enough to comprise whole energy of disc of confusion in this zone.

In the favored area C of institute, try to achieve the center position (x of disperse unit with centroid method _i, y _i), see formula (7), (8):

$x_0=\frac{\underset{i=1}{\overset{N}{\mathrm{\&Sigma;}}}i\&times;f(i,j)}{\underset{i=1}{\overset{N}{\mathrm{\&Sigma;}}}\underset{j=1}{\overset{N}{\mathrm{\&Sigma;}}}f(i,j)}---\left(7\right)$

${\mathrm{<figure-callout\; id="0"\; label="y"\; filenames="DEST\_PATH\_HDA00003083699200012.png"\; state="\{\{state\}\}">y</figure-callout>}}_0=\frac{\underset{j=1}{\overset{N}{\mathrm{\&Sigma;}}}j\&times;f(i,j)}{\underset{i=1}{\overset{N}{\mathrm{\&Sigma;}}}\underset{j=1}{\overset{N}{\mathrm{\&Sigma;}}}f(i,j)}---\left(8\right)$

(i j) carries out normalized, obtains f to the gray-scale value f of pixel ₁(i, j).

To arriving (x with each pixel in the regional C ₀, y ₀) distance be the x axle, with the gray-scale value f of each pixel ₁(i j) is the y axle, and these values are carried out Gauss curve fitting, and fit equation is

Method therefor is least square Gauss curve fitting method, based on iteration theorem, referring to Fig. 2, is the Gauss curve fitting design sketch.

In the coefficient a in the one dimension Gauss equation of trying to achieve, b substitution two dimension Gauss equation (polar coordinate system),

Be shown below:

$T(\mathrm{\&rho;},\mathrm{\&theta;})=a\&CenterDot;e^{-\frac{{\mathrm{\&rho;}}^2}{b}}---\left(9\right)$

ρ is the utmost point footpath of polar coordinate system;

θ is the polar angle of polar coordinate system.

Utilize equation (4) to calculate,

$\frac{\underset{0}{\overset{2\mathrm{\&pi;}}{\&Integral;}}\underset{0}{\overset{d}{\&Integral;}}T(\mathrm{\&rho;},\mathrm{\&theta;})\&CenterDot;\mathrm{\&rho;d\&rho;d\&theta;}}{\underset{0}{\overset{2\mathrm{\&pi;}}{\&Integral;}}\underset{0}{\overset{\&infin;}{\&Integral;}}T(\mathrm{\&rho;},\mathrm{\&theta;})\&CenterDot;\mathrm{\&rho;d\&rho;d\&theta;}}=0.8---\left(10\right)$

Be that radius is drawn circle with d, account for 80% of whole two-dimentional Gaussian distribution cone volume with the volume of two-dimentional Gaussian distribution circular cone that envelope surrounds, just encircled energy is 80% corresponding bottom surface radius of circle.

The d that calculates is on duty with 2, namely is the disc of confusion diameter, just the encircled energy of asterism target.

Space Optical System detectivity detection system of the present utility model possesses and carries out automatic standard adjustment to setting detection limit, and can pass through another automatic control mode, carries out the mensuration of detection limit to setting signal to noise ratio (S/N ratio).

The method has advantages such as automatic feedback measurement mechanism, automatic light source brightness regulation with respect to the magnitude simulator of traditional sense, saving labour that can be very big, raising testing efficiency.And propose to utilize the setting signal to noise ratio (S/N ratio), directly measure the Space Optical System actual detection limit.Not only can finish the test to the detection limit routine, and can test out the limit detection level of optical system, using for engineering provides important science data.In the calculating of magnitude simulation, introduce human eye photopic vision usefulness function, can calculate the simulation magnitude very accurately.The spectral radiant emittance meter of tracing to the source from NIST can be that whole calculating provides accurately, stable data.By the relative spectral radiant energy flux curve data of the sun, the formula of magnitude simulation is verified, calculate that smoothly obtaining starlight illumination such as internationally recognized zero is 2.65 * 10 ^-6Lx proves that thus this kind method is to stand deliberation fully in theory.

Space Optical System detectivity detection system of the present utility model, can accurately measure the disc of confusion diameter of Space Optical System, the mensuration mode that surmounts tradition " number pixel " with a kind of data processing method of more reasonable, science, is measured this index comparatively accurately.During Space Optical System disc of confusion measuring diameter, only be distributed between 3 * 3 to 5 * 5 pixels mainly due to the disc of confusion energy, the information data of obtaining during test is too rare, if use traditional method, the result of mensuration will be introduced into very big error.And by after the disc of confusion least square Gauss curve fitting method, measuring accuracy can be improved a magnitude.This evaluation for the Space Optical System encircled energy has meaning free from worldly cares, this index will directly influence bearing accuracy, the attitude control of space star sensor, all be widely used on aerospace flight vehicles such as satellite, intercontinental strategic missile, spaceship.

Claims (4)

1. Space Optical System detectivity detection system, it is characterized in that: described Space Optical System detectivity detection system comprises light-source system, colimated light system, asterism unit, spectra collection unit, master control system, data processing unit and display unit; Described colimated light system and spectra collection unit are separately positioned on the emitting light path of light source; Described asterism unit is arranged between light-source system and the colimated light system and is on the focal plane of light-source system; Space Optical System to be measured is arranged on the emitting light path behind the colimated light system; Described data processing unit links to each other with display unit and Space Optical System to be measured respectively; Described master control system links to each other with Space Optical System to be measured, light-source system and spectra collection unit respectively.

2. Space Optical System detectivity detection system according to claim 1, it is characterized in that: described colimated light system is the off-axis reflection optical system; Described off-axis reflection optical system comprises off axis paraboloid mirror primary mirror, first a folding axle mirror, second folding axle mirror and the iris; The described first folding axle mirror, the second folding axle mirror and off axis paraboloid mirror primary mirror are successively set on light-source system on the emitting light path behind the asterism unit; Described Space Optical System to be measured is arranged on the emitting light path after the reflection of off axis paraboloid mirror primary mirror; Described iris is arranged between off axis paraboloid mirror primary mirror and the Space Optical System to be measured; Described iris is the parasitic light diaphragm that disappears; Described off-axis reflection optical system is that bore is that Φ 500mm and focal length are the off-axis reflection optical systems of 5000mm.

3. Space Optical System detectivity detection system according to claim 1 and 2, it is characterized in that: described light-source system comprises canonical product bulb separation, halogen tungsten lamp, xenon lamp and adjustable power supply; Described halogen tungsten lamp and xenon lamp are arranged on the inwall of canonical product bulb separation; Described master control system links to each other with halogen tungsten lamp and xenon lamp respectively by adjustable power supply.

4. Space Optical System detectivity detection system according to claim 3, it is characterized in that: described asterism unit is asterism target target plate; Described spectra collection unit is the spectral radiant emittance meter.

Images