CN104316046A - Intensity-correlation star sensor - Google Patents
Intensity-correlation star sensor Download PDFInfo
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- CN104316046A CN104316046A CN201410532389.4A CN201410532389A CN104316046A CN 104316046 A CN104316046 A CN 104316046A CN 201410532389 A CN201410532389 A CN 201410532389A CN 104316046 A CN104316046 A CN 104316046A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
- G01C21/02—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by astronomical means
- G01C21/025—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by astronomical means with the use of startrackers
Abstract
The invention provides an intensity-correlation star sensor which comprises a first lens hood, a second lens hood, a first optical telescope, a second optical telescope, a scanning type sensor, a single photon sensor, electronics read-out equipment, video processing equipment, a satellite-borne time-frequency device, satellite-borne data processing equipment and an interface. By using detection signals of two paths of optical detection systems, the obtained two paths of electric signals are subjected to time synchronization by using the satellite-borne time-frequency device, and are subjected to intensity-correlation signal processing in the satellite-borne data processing equipment. Therefore, on the basis of keeping an integral appearance shape of an optical system of an original star sensor unchangeable, an internal structure is locally regulated, and the engineering realization is easy. The starry sky is imaged by using an intensity-correlation method in a quantum imaging technology, and is searched by using the scanning type sensor; the single photon is used in the other path, relatively dark star bodies are relatively easily detected, and the detection sensitivity is greatly improved.
Description
Technical field
The present invention relates to a kind of star sensor based on quantum imaging technology, belong to star sensor field.
Background technology
Star sensor is succeeded in developing as far back as eighties of last century the fifties, is mainly used in aircraft and missile guidance.So far live through the development of three phases, be widely used in the space flight and aviation devices such as guided missile, aircraft, spaceship, satellite, related to multiple fields of measurement.More several conventional sensor, star sensor have precision high, lightweight, low in energy consumption, without drift and the advantage such as working method is many.Early stage star sensor uses image dissector as sensitive detection parts, and this constructing apparatus is comparatively simple, is mainly used in the surface instrumentation such as large-scale astronomical telescope and missile guidance, but due to the restriction of image dissector self simulation stability, can not meet high-precision requirement.
1974, the U.S. jet laboratory (JPL) starts to develop second generation star sensor------CCD star sensor, compared with the star sensor of first stage, CCD star sensor has high resolving power, radiation resistance, the geometrical optics linearly advantage such as strong, but its relative visual field is little, although single star measuring accuracy is high, single star identification and Attitude Calculation too complex, simultaneously the quality of star sensor and volume also larger; To the nineties in last century, in order to meet the strict demand of space flight device, based on increasing substantially of optics, precision optical machinery, electronics and computer technology, second generation CCD star sensor starts to occur, the star sensor of a new generation has the advantages such as visual field is large, star catalogue is little, more has the function of independent navigation.Current Domestic applies more or CCD star sensor in the world, but the no matter first generation or second generation star sensor, CCD star sensor, all based on the development level of CCD camera, is limited to the parameters such as the pixel number of CCD.
Summary of the invention
The technical problem to be solved in the present invention is, for the deficiencies in the prior art, provides a kind of intensity correlation star sensor.The present invention is based on this brand-new optical field detection mode of quantum imaging, propose a kind of novel intensity correlation star sensor.This scheme, again can the development and application overall navigation of forming into columns to many stars by two cover Electro-Optical Sensor Set imagings of single star.Relatively now conventional CCD star sensor, intensity star association sensor breaches the restriction of diffraction imaging, and detection faint star ability is high, and using degree association algorithm and suitable signal processing algorithm can greatly Background suppression noises simultaneously, have broad application prospects.
The object of the invention is to be achieved through the following technical solutions:
A kind of intensity correlation star sensor, comprise the first light shield, the second light shield, the first optical telescope, the second optical telescope, scan-type sensor, single photon sensor, electronics readout equipment, video processing equipment, spaceborne time-frequency device, data processing onboard equipment and gesture stability interface, wherein, before first light shield, the second light shield are arranged on the first optical telescope, the second optical telescope respectively, for blocking the parasitic light from non-targeted celestial bodies such as the sun, the moon, the earth, significantly to reduce the noise entering optical telescope; First optical telescope and the second optical telescope, for converging the light from target celestial body, complete the optical imagery of starry sky, are imaged on by starry sky on self optical focal plane; Scan-type sensor and single photon sensor are placed on the optical focal plane of the first optical telescope and the second optical telescope respectively, respectively the first optical telescope and the second optical telescope being converged the starry sky image obtained is that electric signal exports through opto-electronic conversion, wherein, the first electric signal exported by scan-type sensor sends into video processing equipment, reads this first electric signal by video processing equipment; The second electric signal exported by single photon sensor sends into electronics readout equipment, reads this second electric signal by this electronics readout equipment; Spaceborne time-frequency device provides absolute time standard for video processing equipment and electronics readout equipment, carries out time synchronized to video processing equipment and electronics readout equipment simultaneously; Data processing onboard equipment carries out to the first electric signal from video processing equipment and the second electric signal from electronics readout equipment the image that second order intensity correlation algorithm obtains target celestial body, and extracted by asterism and the accurate location of star identification acquisition target celestial body in starry sky, again through Attitude Calculation, obtain the posture position information of satellite; The attitude of satellite positional information obtained by data processing onboard device processes is transferred to the control system in downstream by gesture stability interface.
Further, video processing equipment and electronics readout equipment also carry out noise reduction pre-service to the first electric signal and the second electric signal respectively, record the time of arrival of two electric signal respectively, by spaceborne time-frequency device, mark is carried out to two electric signal afterwards, obtain photon sequence information time of arrival.
Further, spaceborne time-frequency device comprises satellite atomic clock, GPS and time synchronism equipment, wherein, satellite atomic clock and GPS are used for providing absolute time standard for video processing equipment and electronics readout equipment, and time synchronism equipment is used for carrying out time synchronized to video processing equipment and electronics readout equipment.
Compared with prior art, comprise according to the advantage of intensity correlation star sensor of the present invention:
1, in Project Realization than being easier to
The present invention improves on the basis of existing CCD star sensor, wherein make use of the detectable signal of two-way optical detection system, by spaceborne time-frequency device, time synchronized is carried out to the two path signal obtained, and in data processing onboard equipment, intensity correlation signal transacting has been carried out to two path signal.Therefore on the basis keeping the optical system of former star sensor, overall appearance shape invariance, the local directed complete set of inner structure is carried out, than being easier in Project Realization.
2, detection sensitivity is higher
The present invention utilizes the intensity correlation method in quantum imaging technique to carry out imaging to starry sky, and use scan-type sensor to search for starry sky, another road uses single photon sensor simultaneously, and therefore more easily detect darker celestial body, detection sensitivity improves greatly.
3, speed of detection is very fast
Significantly improve because the detectivity of the present invention to faint star has had, therefore only need scan narrower visual field and just can obtain the celestial body number that can be used for navigating, therefore speed of detection is improved.
Accompanying drawing explanation
Fig. 1 is the one-piece construction schematic diagram of star sensor of the present invention;
Fig. 2 is the workflow diagram of star sensor of the present invention.
Embodiment
Below in conjunction with the drawings and specific embodiments, intensity correlation star sensor according to the present invention is further described in detail.
As shown in Figure 1, intensity correlation star sensor according to the present invention comprises the first light shield, the second light shield, the first optical telescope, the second optical telescope, scan-type sensor, single photon sensor, electronics readout equipment, video processing equipment, spaceborne time-frequency device, data processing onboard equipment and gesture stability interface.
Before first light shield, the second light shield are arranged on the first optical telescope, the second optical telescope respectively, for blocking from non-targeted celestial body (such as, the sun, the moon, the earth) parasitic light, significantly to reduce the noise entering optical telescope; First optical telescope and the second optical telescope, for converging the light from target celestial body, complete the optical imagery of starry sky, are imaged on by starry sky on self optical focal plane.First optical telescope and the second optical telescope are by optical lens group and machinery mount composition.The design of its concrete structure can adjust according to actual conditions.
Scan-type sensor and single photon sensor are placed on the optical focal plane of the first optical telescope and the second optical telescope respectively, respectively the first optical telescope and the second optical telescope being converged the starry sky image obtained is that electric signal exports through opto-electronic conversion, wherein, the first electric signal exported by scan-type sensor sends into video processing equipment, reads this first electric signal by video processing equipment; The second electric signal exported by single photon sensor sends into electronics readout equipment, reads this second electric signal by this electronics readout equipment.Usually, scan-type sensor and single photon sensor can be equipped with driving circuit and cooling device, obtain optical telescope in real time converge the image obtained for enabling scan-type sensor and single photon sensor.
Video processing equipment and electronics readout equipment also carry out noise reduction pre-service to the first electric signal and the second electric signal respectively, record the time of arrival of two electric signal respectively, by spaceborne time-frequency device, mark is carried out to two electric signal afterwards, obtain photon sequence information time of arrival.
Spaceborne time-frequency device provides absolute time standard for video processing equipment and electronics readout equipment, carries out time synchronized to video processing equipment and electronics readout equipment simultaneously.Spaceborne time-frequency device comprises satellite atomic clock, GPS and time synchronism equipment, wherein, satellite atomic clock and GPS are used for providing absolute time standard for video processing equipment and electronics readout equipment, and time synchronism equipment is used for carrying out time synchronized to video processing equipment and electronics readout equipment.Particularly, time synchronism equipment can adopt time synchronized control circuit to realize.
Data processing onboard equipment adopts second order intensity correlation algorithm to calculate to the first electric signal from video processing equipment and the second electric signal from electronics readout equipment, the image of target celestial body can be obtained, and extracted by asterism and the accurate location of star identification acquisition target celestial body in starry sky, again through Attitude Calculation, obtain the posture position information of satellite; The attitude of satellite positional information obtained by data processing onboard device processes is transferred to the control system in downstream by gesture stability interface.
As shown in Figure 2, the specific works flow process of star sensor of the present invention is:
(1) utilize the star sensor of redundancy on spacecraft, arrange two coplanar star sensor unit, and connected by link by these two unit, the structure according to star sensor of the present invention carries out structural adjustment to it;
(2) adjust the attitude of two light shields and optical telescope, make them aim at the nautical star in district on the same day simultaneously;
(3) by light shield and optical telescope, the visible ray in visual field is converged on focal plane, realize the optical imagery of starry sky;
(4) utilize scan-type sensor and the optical imagery of single photon sensor to starry sky to scan, and light signal is converted to electric signal output;
(5) video processing equipment carries out noise reduction process, biased, gain-adjusted to electric signal, finally carries out A/D conversion, exports starry sky digital picture and carries out cross correlation process to data processing onboard equipment;
(6) single photon sensor utilizes photon counter to detect the visible light signal of astronomical radiation, and visible light signal is converted into electric signal, exports data processing onboard equipment to and carries out cross correlation process;
(7) spaceborne time-frequency device carries out mark to two electric signal, obtains photon sequence information time of arrival, exports data processing onboard equipment to and carries out cross correlation process;
(8) data processing onboard equipment utilization second order intensity correlation algorithm, nautical star recognizer and attitude filtering algorithm etc., carry out sentencing star, single star location, star identification, star sensor attitude angle and the computing of spacecraft attitude angle; Determine the sensing of star sensor optical axis relative to inertial coordinates system, provide attitude four element of spacecraft under inertial coordinates system;
(9) export spacecraft attitude angle information to spacecraft attitude control system by gesture stability interface, carry out gesture stability.
At this, it should be noted that, the content do not described in detail in this instructions, be that those skilled in the art can be realized by the description in this instructions and prior art, therefore, do not repeat.
The foregoing is only the preferred embodiments of the present invention, be not used for limiting the scope of the invention.For a person skilled in the art, under the prerequisite not paying creative work, can make some amendments and replacement to the present invention, all such modifications and replacement all should be encompassed within protection scope of the present invention.
Claims (3)
1. an intensity correlation star sensor, it is characterized in that, comprise the first light shield, the second light shield, the first optical telescope, the second optical telescope, scan-type sensor, single photon sensor, electronics readout equipment, video processing equipment, spaceborne time-frequency device, data processing onboard equipment and gesture stability interface, before wherein the first light shield, the second light shield are arranged on the first optical telescope, the second optical telescope respectively, for blocking the parasitic light from non-targeted celestial body, significantly to reduce the noise entering optical telescope; First optical telescope and the second optical telescope, for converging the light from target celestial body, complete the optical imagery of starry sky, are imaged on by starry sky on self optical focal plane;
Scan-type sensor and single photon sensor are placed on the optical focal plane of the first optical telescope and the second optical telescope respectively, respectively the first optical telescope and the second optical telescope being converged the starry sky image obtained is that electric signal exports through opto-electronic conversion, wherein, the first electric signal exported by scan-type sensor sends into video processing equipment, reads this first electric signal by video processing equipment; The second electric signal exported by single photon sensor sends into electronics readout equipment, reads this second electric signal by this electronics readout equipment;
Spaceborne time-frequency device provides absolute time standard for video processing equipment and electronics readout equipment, carries out time synchronized to video processing equipment and electronics readout equipment simultaneously;
Data processing onboard equipment carries out to the first electric signal from video processing equipment and the second electric signal from electronics readout equipment the image that second order intensity correlation algorithm obtains target celestial body, and extracted by asterism and the accurate location of star identification acquisition target celestial body in starry sky, again through Attitude Calculation, obtain the posture position information of satellite; The attitude of satellite positional information obtained by data processing onboard device processes is transferred to the control system in downstream by gesture stability interface.
2. intensity correlation star sensor according to claim 1, is characterized in that,
Video processing equipment and electronics readout equipment also carry out noise reduction pre-service to the first electric signal and the second electric signal respectively, record the time of arrival of two electric signal respectively; By spaceborne time-frequency device, mark is carried out to two electric signal afterwards, obtain photon sequence information time of arrival.
3. intensity correlation star sensor according to claim 1, it is characterized in that, spaceborne time-frequency device comprises satellite atomic clock, GPS and time synchronism equipment, wherein, satellite atomic clock and GPS are used for providing absolute time standard for video processing equipment and electronics readout equipment, and time synchronism equipment is used for carrying out time synchronized to video processing equipment and electronics readout equipment.
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| CN109375336A (en) * | 2018-11-30 | 2019-02-22 | 中国航空工业集团公司洛阳电光设备研究所 | A kind of continuous focusing star sensor |
| CN109506644A (en) * | 2018-10-17 | 2019-03-22 | 中国航空工业集团公司洛阳电光设备研究所 | The highly sensitive star sensor of round-the-clock |
| CN112325874A (en) * | 2020-10-21 | 2021-02-05 | 中国科学院上海光学精密机械研究所 | System and method for measuring strength correlation of star angular position based on snake-shaped light path |
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| CN104567870A (en) * | 2015-01-30 | 2015-04-29 | 北京航天控制仪器研究所 | Single-pixel star sensor and target star sky detection method thereof |
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| CN109375336B (en) * | 2018-11-30 | 2020-11-24 | 中国航空工业集团公司洛阳电光设备研究所 | Continuous focusing star sensor |
| CN112325874A (en) * | 2020-10-21 | 2021-02-05 | 中国科学院上海光学精密机械研究所 | System and method for measuring strength correlation of star angular position based on snake-shaped light path |
| CN112325874B (en) * | 2020-10-21 | 2023-02-14 | 中国科学院上海光学精密机械研究所 | System and method for measuring strength correlation of star angular position based on snake-shaped light path |
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