CN104316046B - A kind of intensity correlation star sensor - Google Patents
A kind of intensity correlation star sensor Download PDFInfo
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- CN104316046B CN104316046B CN201410532389.4A CN201410532389A CN104316046B CN 104316046 B CN104316046 B CN 104316046B CN 201410532389 A CN201410532389 A CN 201410532389A CN 104316046 B CN104316046 B CN 104316046B
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- G01C21/02—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by astronomical means
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Abstract
The present invention provides a kind of intensity correlation star sensor, including 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 interface.Using the detectable signal of two-way optical detection system, time synchronized is carried out to the two path signal for obtaining by spaceborne time-frequency device, and intensity correlation signal transacting has been carried out to two path signal in data processing onboard equipment.Therefore the local directed complete set of internal structure is carried out on the basis of the optical system of former star sensor, overall appearance shape invariance is kept, and is easier in Project Realization.Starry sky is imaged using the intensity correlation method in quantum imaging technique, starry sky is scanned for using scan-type sensor, another road uses single photon sensor, it is easier to detect dark celestial body, detectivity is greatly improved.
Description
Technical field
The present invention relates to a kind of star sensor based on quantum imaging technology, belongs to star sensor field.
Background technology
Star sensor is most succeeded in developing early in eighties of last century the fifties, is mainly used in aircraft and missile guidance.So far
The development of three phases is lived through, the space flight and aviation device such as guided missile, aircraft, spaceship, satellite is widely used to, is related to many
Individual fields of measurement.Several conventional sensors of comparison, star sensor have high precision, lightweight, low in energy consumption, without drift and work
The advantages of mode is more.The star sensor of early stage uses image dissector as sensitive detection parts, and this constructing apparatus are relatively simple, mainly should
For ground instruments such as large-scale astronomical telescope and missile guidances, but due to the restriction of image dissector itself simulation stability, it is impossible to
Meet high-precision requirement.
1974, U.S. jet laboratory (JPL) started to develop second generation star sensor --- --- CCD stars sensitivity
Device, compared with the star sensor of first stage, CCD star sensors have high-resolution, radiation resistance, geometric optics linearly strong etc. excellent
Gesture, but its relative visual field is little, although and single star certainty of measurement is high, but, single star is recognized and Attitude Calculation too complex, quick with clock star
The quality and volume of sensor is also than larger；To last century the nineties, in order to meet the strict demand of space flight device, based on light
, precision optical machinery, electronics and computer technology are increased substantially, and second generation CCD star sensor starts to occur, of new generation
Star sensor has the advantages such as visual field is big, star catalogue is little, more has the function of independent navigation.Current Domestic is applied more in the world
Or CCD star sensors, but the no matter first generation or second generation star sensor, CCD star sensors are all based on the development of CCD camera
Level, is limited to the parameters such as the pixel number of CCD.
Content of the invention
The technical problem to be solved in the present invention is, for the deficiencies in the prior art, there is provided a kind of intensity correlation star sensor.
The present invention is based on this brand-new optical field detection mode of quantum imaging, it is proposed that a kind of new intensity correlation star sensor.This
Scheme can pass through two sets Electro-Optical Sensor Sets of single star and be imaged, again can the overall navigation formed into columns to many stars of development and application.Relatively more existing
In conventional CCD star sensors, intensity star association sensor breaches the restriction of diffraction imaging, and detection faint star ability is high, while
Ambient noise can be suppressed greatly using intensity correlation algorithm and appropriate signal processing algorithm, be had broad application prospects.
The purpose of the present invention is achieved through the following technical solutions：
A kind of intensity correlation star sensor, including the first light shield, the second light shield, the first optical telescope, the second light
Learn 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, the first light shield, the second light shield are separately mounted to the first light
Before learning telescope, the second optical telescope, for blocking the veiling glare from the non-targeted celestial body such as the sun, the moon, earth, with big
Width is lowered into the noise of optical telescope；First optical telescope and the second optical telescope are used for converging from target celestial body
Light, complete the optical imagery of starry sky, starry sky be imaged on the optical focal plane of itself；Scan-type sensor and single photon
Sensor is respectively placed on the optical focal plane of the first optical telescope and the second optical telescope, and respectively the first optics is looked in the distance
It is electric signal output through opto-electronic conversion that mirror and the second optical telescope converge the starry sky image for obtaining, and wherein, is sensed by scan-type
First electric signal of device output sends into video processing equipment, reads first electric signal by video processing equipment；Passed by single photon
Second electric signal of sensor output sends into electronics readout equipment, reads second electric signal by the electronics readout equipment；Star
Carry time-frequency device be that video processing equipment and electronics readout equipment provide absolute time standard, while to video processing equipment with
Electronics readout equipment carries out time synchronized；Data processing onboard equipment to the first electric signal from video processing equipment and comes
The image that second order intensity correlation algorithm obtains target celestial body is carried out from the second electric signal of electronics readout equipment, and passes through asterism
Extract and star identification obtains accurate location of the target celestial body in starry sky, then through Attitude Calculation, obtain the posture position of satellite
Information；The attitude of satellite positional information obtained by the process of data processing onboard equipment is transferred to downstream by gesture stability interface
Control system.
Further, video processing equipment and electronics readout equipment also enter to the first electric signal and the second electric signal respectively
Row noise reduction is pre-processed, and is recorded the arrival time of two electric signals respectively, two electric signals is carried out by spaceborne time-frequency device afterwards
Mark, obtains photon arrival time sequence information.
Further, spaceborne time-frequency device includes satellite atomic clock, GPS and time synchronism equipment, wherein, spaceborne
Atomic clock and GPS are used for being that video processing equipment and electronics readout equipment provide absolute time standard, time synchronized
Equipment is used for carrying out time synchronized to video processing equipment and electronics readout equipment.
Compared with prior art, included according to the advantage of the intensity correlation star sensor of the present invention：
1st, it is easier in Project Realization
The present invention is improved on the basis of existing CCD star sensors, wherein make use of two-way optical detection system
Detectable signal, time synchronized has been carried out to the two path signal for obtaining by spaceborne time-frequency device, and in data processing onboard
Intensity correlation signal transacting is carried out to two path signal in equipment.Therefore optical system in the former star sensor of holding, entirety are outer
The local directed complete set of internal structure is carried out on the basis of seeing shape invariance, is easier in Project Realization.
2nd, detectivity is higher
The present invention is imaged to starry sky using the intensity correlation method in quantum imaging technique, using scan-type sensor
Starry sky is scanned for, while another road is using single photon sensor, is therefore easier to detect dark celestial body, is detected sensitive
Degree is greatly improved.
3rd, speed of detection is very fast
Greatly improve as the present invention has to the detectivity of faint star, therefore need to only scan narrower visual field and can just obtain
The celestial body number for navigating must be can be used for, therefore speed of detection is improved.
Description of the drawings
Fig. 1 is the overall structure diagram of the star sensor of the present invention；
Fig. 2 is the workflow diagram of the star sensor of the present invention.
Specific embodiment
Below in conjunction with the drawings and specific embodiments to being done further in detail according to the intensity correlation star sensor of the present invention
Explanation.
As shown in figure 1, according to the present invention intensity correlation star sensor include the first light shield, the second light shield, first
Optical telescope, the second optical telescope, scan-type sensor, single photon sensor, electronics readout equipment, Video processing set
Standby, spaceborne time-frequency device, data processing onboard equipment and gesture stability interface.
Before first light shield, the second light shield are separately mounted to the first optical telescope, the second optical telescope, for hiding
The veiling glare from non-targeted celestial body (for example, the sun, the moon, the earth) is kept off, so that the noise for entering optical telescope is greatly reduced；
First optical telescope and the second optical telescope are used for converging the light from target celestial body, complete the optical imagery of starry sky,
Starry sky is imaged on the optical focal plane of itself.First optical telescope and the second optical telescope by optical lens group and
Machinery mount is constituted.Its concrete structure design can be adjusted according to actual conditions.
Scan-type sensor and single photon sensor are respectively placed in the light of the first optical telescope and the second optical telescope
Learn on focal plane, the first optical telescope and the second optical telescope are converged starry sky image respectively that obtain through opto-electronic conversion is
Electric signal output, wherein, sends into video processing equipment by the first electric signal that scan-type sensor is exported, by video processing equipment
Read first electric signal；Electronics readout equipment is sent into by the second electric signal that single photon sensor is exported, by the electronics
Readout equipment reads second electric signal.Generally, scan-type sensor and single photon sensor can be equipped with drive circuit and cooling
Device, converges the image for obtaining for enabling scan-type sensor and single photon sensor to obtain optical telescope in real time.
It is pre- that video processing equipment and electronics readout equipment also carry out noise reduction to the first electric signal and the second electric signal respectively
Process, record the arrival time of two electric signals respectively, mark is carried out to two electric signals by spaceborne time-frequency device afterwards, is obtained
Photon arrival time sequence information.
Spaceborne time-frequency device is that video processing equipment and electronics readout equipment provide absolute time standard, while to video
Processing equipment and electronics readout equipment carry out time synchronized.Spaceborne time-frequency device include satellite atomic clock, GPS and when
Between synchronizer, wherein, it is that video processing equipment and electronics readout equipment are provided absolutely that satellite atomic clock and GPS are used for
To time standard, time synchronism equipment is used for carrying out time synchronized to video processing equipment and electronics readout equipment.Specifically,
Time synchronism equipment can be realized using time synchronized control circuit.
Data processing onboard equipment is to the first electric signal from video processing equipment and from electronics readout equipment
Second electric signal is calculated using second order intensity correlation algorithm, you can is obtained the image of target celestial body, and is extracted by asterism
Accurate location of the target celestial body in starry sky is obtained with star identification, then through Attitude Calculation, obtains the posture position information of satellite；
The attitude of satellite positional information obtained by the process of data processing onboard equipment is transferred to the control in downstream by gesture stability interface
System.
As shown in Fig. 2 the specific workflow of the star sensor of the present invention is：
(1) using the star sensor of redundancy on spacecraft, two coplanar star sensor units are set, and by the two lists
Unit carries out structural adjustment by link connection, the structure according to the star sensor of the present invention to which；
(2) attitude of two light shields and optical telescope is adjusted, and them is made while being directed at the nautical star in area on the same day；
(3) visible ray in visual field is converged on focal plane by light shield and optical telescope, realizes the light of starry sky
Study picture；
(4) optical imagery of starry sky is scanned using scan-type sensor and single photon sensor, and by optical signal
Be converted to electric signal output；
(5) video processing equipment carries out noise reduction process, biasing, gain-adjusted to electric signal, finally carries out A/D conversions, defeated
Going out starry sky digital picture carries out cross correlation process to data processing onboard equipment；
(6) single photon sensor detects the visible light signal of astronomical radiation, and it will be seen that optical signal using photon counter
Electric signal is converted into, exporting to data processing onboard equipment carries out cross correlation process；
(7) spaceborne time-frequency device carries out mark to two electric signals, obtains photon arrival time sequence information, exports to star
Carrying data processing equipment carries out cross correlation process；
(8) data processing onboard equipment utilization second order intensity correlation algorithm, nautical star recognizer and attitude filtering algorithm
Deng carrying out sentencing star, single star positioning, star identification, star sensor attitude angle and the calculating of spacecraft attitude angle and process；Determine star sensor
Sensing of the optical axis relative to inertial coodinate system, provides attitude four element of the spacecraft under inertial coodinate system；
(9) spacecraft attitude angle information is exported to spacecraft attitude control system by gesture stability interface, carries out appearance
State is controlled.
Here, it should be noted that the content not described in detail in this specification, it is those skilled in the art by this theory
Description and prior art in bright book can be realized, therefore, not repeated.
The preferred embodiments of the present invention are the foregoing is only, is not used for limiting the scope of the invention.For ability
For the technical staff in domain, on the premise of not paying creative work, some modifications and replacement can be made to the present invention,
All such modifications and replacement should all be included within the scope of the present invention.
Claims (3)
1. a kind of intensity correlation star sensor, it is characterised in that look in the distance including the first light shield, the second light shield, the first optics
Mirror, 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 the first light shield, the second light shield are respectively mounted
Before the first optical telescope, the second optical telescope, for blocking the veiling glare from non-targeted celestial body, be greatly reduced into
Enter the noise of optical telescope；First optical telescope and the second optical telescope are used for converging the light from target celestial body,
The optical imagery of starry sky is completed, starry sky is imaged on the optical focal plane of itself；
Scan-type sensor and single photon sensor are respectively placed in the first optical telescope and the optics of the second optical telescope is burnt
In plane, it is telecommunications through opto-electronic conversion that the first optical telescope and the second optical telescope are converged starry sky image respectively that obtain
Number output, wherein, the first electric signal exported by scan-type sensor sends into video processing equipment, is read by video processing equipment
First electric signal；Electronics readout equipment is sent into by the second electric signal that single photon sensor is exported, is read by the electronics
Equipment reads second electric signal；
Spaceborne time-frequency device is that video processing equipment and electronics readout equipment provide absolute time standard, while to Video processing
Equipment and electronics readout equipment carry out time synchronized；
Data processing onboard equipment to the first electric signal from video processing equipment and from electronics readout equipment second
Electric signal carries out the image that second order intensity correlation algorithm obtains target celestial body, and is extracted by asterism and star identification acquisition target satellite
Accurate location of the body in starry sky, then through Attitude Calculation, obtain the posture position information of satellite；By data processing onboard equipment
Process the control system that the attitude of satellite positional information for obtaining is transferred to downstream by gesture stability interface.
2. intensity correlation star sensor according to claim 1, it is characterised in that
Video processing equipment and electronics readout equipment also carry out noise reduction pretreatment to the first electric signal and the second electric signal respectively,
The arrival time of two electric signals is recorded respectively；Mark is carried out to two electric signals by spaceborne time-frequency device afterwards, photon is obtained
Arrival time sequence information.
3. intensity correlation star sensor according to claim 1, it is characterised in that spaceborne time-frequency device includes spaceborne atom
Clock, GPS and time synchronism equipment, wherein, satellite atomic clock and GPS are used for as video processing equipment and electronics
Learn readout equipment and absolute time standard is provided, time synchronism equipment is used for carrying out video processing equipment and electronics readout equipment
Time synchronized.
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Families Citing this family (5)
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| CN104567870B (en) * | 2015-01-30 | 2018-02-09 | 北京航天控制仪器研究所 | A kind of single pixel star sensor and its target starry sky detection method |
| CN109506644B (en) * | 2018-10-17 | 2022-09-02 | 中国航空工业集团公司洛阳电光设备研究所 | All-time high-sensitivity star sensor |
| 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 |
| 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 |
| CN114858183B (en) * | 2022-03-31 | 2024-07-09 | 北京航天控制仪器研究所 | Star sensor fault self-detection method |
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