CN108225372A - A kind of electric propulsion plume is to star sensor light interference test system - Google Patents
A kind of electric propulsion plume is to star sensor light interference test system Download PDFInfo
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- CN108225372A CN108225372A CN201711387840.8A CN201711387840A CN108225372A CN 108225372 A CN108225372 A CN 108225372A CN 201711387840 A CN201711387840 A CN 201711387840A CN 108225372 A CN108225372 A CN 108225372A
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- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C25/00—Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass
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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
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Abstract
The invention discloses a kind of electric propulsion plumes to star sensor light interference test system, including：The quick simulator of star sensor, star, electric thruster and plume collection device；Pass through layout designs of the star sensor with respect to the position of the spout of electric thruster, with reference to the quick simulator of star, it can be in the case where electric propulsion space plume shadow be rung, realize the test of the quick disturbed situation of visual field to star, it solves the light disturbed test quantification problem of plasma plume, design considerations is provided for satellite sensor visual field layout.
Description
Technical field
The invention belongs to plasma technical field of measurement and test more particularly to a kind of electric propulsion plume to interfere star sensor light
Pilot system.
Background technology
Electric propulsion is a kind of novel space power system, has the outstanding advantage of high specific impulse, is advanced in the world at this stage
One of significant technology of spacecraft.At home, the Oriental Red III B in exploitation, Dongfanghong four be enhanced, Dongfanghong five
Common platforms is waited to be required to realize the demand of bearing capacity promotion using electric propulsion.
Electric propulsion application is a double-edged sword, and advantage is notable, but technical sophistication, application risk are high.Electric propulsion plume is with passing
The chemical propulsion plume of uniting is different, other than hypersonic flow problem or a plasma stream for including a large amount of charged particles
Dynamic problem, spacecraft power caused by the meeting of electric propulsion plume, the effect of heat aspect, can generate perturbed force (torque) or cause spacecraft
Surface temperature increases and material damage, can also cause the charging and discharging effects on spacecraft surface, in averager failure or degree of neutralization
The possibility that not enough will all increase electrion；Leakage path is provided for solar battery array, parasite current loss is formed, causes too
The decline of the positive power of battery, the luminous effect of plume in itself are also possible to influence the light sensitive device normal work outside spacecraft.
For this reason, it is necessary to carry out the basic research of every problem in science for electric propulsion plume.
Invention content
The technology of the present invention solves the problems, such as：A kind of electric propulsion plume is overcome the deficiencies of the prior art and provide to star sensor
Light interference test system, to realize the analysis of the ground validation of whole star plume light disturbing effect and experimental design.
In order to solve the above-mentioned technical problem, the invention discloses a kind of propulsion plume to star sensor light interference test system
System, including：The quick simulator of star sensor, star, electric thruster and plume collection device；Wherein, the quick simulator of star sensor, star,
Electric thruster and plume collection device are arranged in vacuum tank；In star sensor field of view center axis and the quick simulator optical axis of star
The heart coincides；Plume collection device is arranged on the distal end of the spout of electric thruster；
Electric thruster, for generating stabilized plasma plume；
Plume collection device, for absorbing the plasma plume of electric thruster injection；
The quick simulator of star for simulating the radiation feature of fixed star and geometric properties, provides the brightness of fixed star, the spectrum of fixed star
With fixed star sound state star chart；
Star sensor, for the position deviation and attitude misalignment of the fixed star that the quick simulator of sensitive star is simulated.
In above-mentioned electric propulsion plume in star sensor light interference test system, further including：Mounting bracket；
Star sensor is installed and fixed with the quick simulator of star by the mounting bracket；Wherein, cloth in the mounting bracket
Positioning pin is equipped with, to ensure star sensor field of view center axis with the concentricity of the quick simulator optical axis of star as 0.1mm.
In above-mentioned electric propulsion plume in star sensor light interference test system,
The collection surface of plume collection device perpendicular to electric thruster spout axis, and, the collection surface of plume collection device
Area envelope electric thruster spout 30 ° of plume full-shape area.
In above-mentioned electric propulsion plume in star sensor light interference test system, further including：Power supply air feed equipment；
Electric thruster generates stabilized plasma plume under the action of air feed equipment of powering, so that electric thruster is operated in volume
When determining operating point, output stability is better than 5%.
In above-mentioned electric propulsion plume in star sensor light interference test system, further including：Processor is used for：
Around asterism 50 × 50 range is chosen in the quick simulator acquired image of star as operating range, described in calculating
The mean value and variance yields of image in operating range, obtain image result of calculation；
Described image result of calculation is filtered using u- σ Image filter arithmetics, obtains filtering process result；
According to the filtering process as a result, using asterism recognizer, resolving obtains asterism position and asterism gross energy；
To star, quick simulator acquired image is traversed, resolves to obtain the corresponding asterism position of each image and asterism is total
Energy；
To star, quick simulator acquired image counts, and determines the corresponding gross energy average value of each experimental stage and peak
It is worth energy；
According to average energy and the decline percentage of peak energy, influence degree of the plume to asterism energy is determined.
The present invention has the following advantages：
(1) star sensor light interference test system is laid out special with reference to satellite the invention discloses a kind of electric propulsion plume
Point formulates the combined authentication method based on star sensor and the quick simulator of star, has stronger engineering application value, has ensured work
The validity of journey assessment, has obtained effective identification to asterism change in location, asterism energy variation and veiling glare situation, has effectively realized
Assessment to the interference of plume light, and then realize ground validation analysis and the experimental design of whole star plume light disturbing effect.
(2) star sensor phase is passed through to star sensor light interference test system the invention discloses a kind of electric propulsion plume
To the layout designs of electric thruster nozzle exit area, with reference to the quick simulator of star, situation about can be rung in electric propulsion space plume shadow
Under, realize the test of the quick disturbed situation of visual field to star, the light disturbed test quantification problem for solving plasma plume is satellite
Sensor visual field layout provides design considerations.
(3) electric propulsion plumage is overcome to star sensor light interference test system the invention discloses a kind of electric propulsion plume
Streamer disturbing effect measures difficult point, overcomes the test of star sensitive equipment vacuum environment and protection difficult point, realizes electric propulsion plume
To star sensor light interference test and assessment, the electric propulsion system of high rail telecommunication satellite is can be applied to, is endangered for plume light pollution
Evil assessment and protection provide design improve foundation, and can according to verification experimental verification and assessment improvement effect, directiveness propose rationally,
Effective means of defence.
Description of the drawings
Fig. 1 is that a kind of electric propulsion plume illustrates the layout of star sensor light interference test system in the embodiment of the present invention
Figure；
Fig. 2 is that another electric propulsion plume illustrates the layout of star sensor light interference test system in the embodiment of the present invention
Figure；
Fig. 3 be in the embodiment of the present invention a kind of electric propulsion plume to the structure diagram of star sensor light interference test system.
Specific embodiment
To make the object, technical solutions and advantages of the present invention clearer, it is public to the present invention below in conjunction with attached drawing
Embodiment is described in further detail.
The invention discloses a kind of electric propulsion plume to star sensor light interference test system, by the layout envelope design of whole star
The quick visual field of star visual field area opposite with electric thruster plume ensures that electric propulsion plume can apply star sensor light interference assessment result
In all high rail telecommunication satellite platforms.Of the invention to combine Practical Project problem, novelty proposes that the layout designs of experiment, guarantee are set
The data processing method of meter, the flow scheme design of experiment and experiment, by data processing, is realized to different electric propulsion ignition phases
The changing rules such as asterism position, asterism energy and the veiling glare energy of middle star sensor gathered data are analyzed, to obtain difference
The quick precision variation range of star of position.Can be follow-up in addition, by detailed electric propulsion plume light interference test flow scheme design
The assessment of electric propulsion engineer application provides total solution.
With reference to Fig. 1, show that a kind of electric propulsion plume is to star sensor light interference test system in the embodiment of the present invention
Schematic layout pattern.In the present embodiment, the electric propulsion plume is to star sensor light interference test system, including：Star sensor,
The quick simulator of star, electric thruster and plume collection device.Wherein, the quick simulator of star sensor, star, electric thruster and plume are collected
Device is arranged in vacuum tank；Star sensor field of view center axis coincides with the quick simulator optical axis center of star；Plume is collected
Device is arranged on the distal end of the spout of electric thruster.
In the present embodiment, the relative placement between star sensor and electric thruster should be covered in the range of practical implementation
All operating modes：(1) relative placement between star sensor and electric thruster can determine according to satellite practical layout position, such as
Shown in Fig. 1.(2) limit layout (most severe layout), i.e., the quick visual field of star passes completely through the influence test of plume, as limit value index
Satellite master-plan teacher, such as Fig. 2 are supplied to, shows that another electric propulsion plume does star sensor light in the embodiment of the present invention
Disturb the schematic layout pattern of pilot system.
In the present embodiment, electric thruster, for generating stabilized plasma plume.Plume collection device, for absorbing electricity
The plasma plume of thruster injection.The quick simulator of star, for simulating the radiation feature of fixed star and geometric properties, provides fixed star
Brightness, the spectrum of fixed star and fixed star sound state star chart, so as to verify the work(such as the fixed star recognition capability of star sensor, posture, polarity
It can index.Star sensor, for the position deviation and attitude misalignment of the fixed star that the quick simulator of sensitive star is simulated.
Preferably, the collection surface of plume collection device perpendicular to electric thruster spout axis, and, plume collection device
The area of 30 ° of the plume full-shape of the spout of the area envelope electric thruster of collection surface.
In the preferred embodiment of the present invention, with reference to Fig. 3, a kind of electric propulsion plume pair in the embodiment of the present invention is shown
The structure diagram of star sensor light interference test system.
Such as Fig. 3, electric propulsion plume can also include star sensor light interference test system：Mounting bracket.Preferably,
Star sensor is installed and fixed with the quick simulator of star by the mounting bracket.Wherein, it is disposed with positioning in the mounting bracket
Pin, to ensure star sensor field of view center axis with the concentricity of the quick simulator optical axis of star as 0.1mm.
Such as Fig. 3, electric propulsion plume can also include star sensor light interference test system：Power supply air feed equipment.It is preferred that
, electric thruster generates stabilized plasma plume under the action of air feed equipment of powering, so that electric thruster is operated in specified work
When putting, output stability is better than 5%.Wherein, electric thruster is operated in rated operation point, can specifically refer to：Electric thruster
It is operated in rated operation point under vacuum conditions.And electrical parameter and Supplying gas condition meet technical target of the product requirement.
Such as Fig. 3, electric propulsion plume can also include star sensor light interference test system：Processor.Preferably, institute
Processor is stated, can be used for：50 × 50 range is chosen in the quick simulator acquired image of star around asterism as operation model
It encloses, calculates the mean value and variance yields of the image in the operating range, obtain image result of calculation；It is calculated using u- σ image filterings
Method is filtered described image result of calculation, obtains filtering process result；According to the filtering process as a result, using star
Point recognizer, resolving obtain asterism position and asterism gross energy；To star, quick simulator acquired image is traversed, is resolved
Obtain the corresponding asterism position of each image and asterism gross energy；To star, quick simulator acquired image counts, and determines each
The corresponding gross energy average value of experimental stage and peak energy；According to average energy and the decline percentage of peak energy, really
Determine influence degree of the plume to asterism energy.
Wherein, it should be noted that in embodiments of the present invention, vacuum bulkhead face in star sensor field range, anti-
The body surfaces such as sputtering target and mounting bracket coat black carburizing black film material, and pass through test calibration acquisition data before experiment
The reference data of analysis realizes star mould test noise reduction.Further, in star sensor, star simulator and corresponding vacuum chamber
Cable carries out aluminium film Anti-splash cladding (the quick hood entrance of star and star simulator light-emitting window are without cladding).
Based on above-described embodiment, illustrated by taking a concrete application scene as an example below.
(1) prepare before experiment：The installation of star sensor and the quick simulator of star is fixed, the installation and debugging of vaccum-pumping equipment, is applied
Black carburizing black film etc..
(2) installation and debugging of power supply air feed equipment：Gas supply prepares (supply air line, pipe interface, crossing cabin flange, flowmeter
With the installation and debugging of valve etc.), pipeline leak detection, xenon bottle prepares, and power supply prepares (installation of electric thruster supply line, crossing cabin inspection
Leakage and Insulation test etc.).
(3) carry out the experiment joint debugging before closing cabin：Electric thruster, storage connect for equipment electrostatic such as unit, PPU and control simulators
Mouthful and insulation check, star is quick and the installation of star mould after data acquisition equipment joint debugging, splashproof shoots at the target installation and debugging, and the star closed before cabin is quick
Rating test.
(4) ready work is tested.
(5) operating condition of test design and implementation, the quick performance of star is surveyed before and after specifically including the quick initial alignment of vacuum star, vacuum environment
Examination is compared, the quick Image Acquisition of star of electric propulsion pretreatment, electric propulsion cathode is lighted a fire and the quick Image Acquisition of star, electric propulsion averager point
Fire and the quick Image Acquisition of star, electric propulsion line is drawn and the quick Image Acquisition of star, the quick data prediction of star；It is finally that result of the test is commented
Valency is with summarizing.
In embodiments of the present invention, under each electric propulsion operating mode to the position of asterism in collected star sensor image,
The performance changes such as asterism energy and veiling glare energy are analyzed.Around asterism 50 × 50 range is obtained in acquisition image first,
Then the mean value and threshold value of image are calculated；Secondly, image is filtered using u- σ Image filter arithmetics, then using asterism
Recognizer calculates the data such as asterism position, asterism gross energy and preserves；Finally, all acquisition images are counted, sublevel
Section obtains gross energy average value and gross energy variance.Location information unit is pixel, according to Star-Sensor Design principle, a picture
The Space Angle resolution setting of element is 70 ".Gross energy and peak energy unit are gray scale.It can be obtained by counting location information
The asterism change in location influence degree quick to star is changed by counting asterism gross energy, can obtain asterism energy variation by plumage
Flow the decline percentage influenced.
This test assessment conclusion is that on star, quick precision influence is generally not to be exceeded 10 to electric propulsion plume ", gross energy variation should
No more than 12%, attitude control accuracy requirement is subjected to for error assignment item shared by 0.05 degree or so of telecommunication satellite in this way.
In conclusion the invention discloses a kind of electric propulsion plume to star sensor light interference test system, with reference to satellite
Layout characteristics formulate the combined authentication method based on star sensor and the quick simulator of star, have stronger engineering application value, protect
The validity of engineering evaluation is hindered, effective identification has been obtained to asterism change in location, asterism energy variation and veiling glare situation, effectively
The assessment interfered plume light is realized, and then realizes ground validation analysis and the experimental design of whole star plume light disturbing effect.
Secondly, the present invention is by layout designs of the star sensor with respect to electric thruster nozzle exit area, with reference to the quick simulator of star,
It can realize the test of the quick disturbed situation of visual field to star in the case where electric propulsion space plume shadow is rung, solve plasma
The light disturbed test quantification problem of body feathers stream provides design considerations for satellite sensor visual field layout.
In addition, the present invention overcomes electric propulsion plume light disturbing effects to measure difficult point, star sensitive equipment vacuum ring is overcome
Border is tested and protection difficult point, realizes electric propulsion plume to star sensor light interference test and assessment, can be applied to high rail and lead to
Believe the electric propulsion system of satellite, design is provided and improves foundation, and can be according to experiment for plume light pollution hazard evaluation and protection
Verification and assessment improvement effect, directiveness propose reasonable, effective means of defence.
Each embodiment in this explanation is described by the way of progressive, the highlights of each of the examples are with its
The difference of his embodiment, just to refer each other for identical similar part between each embodiment.
The above, best specific embodiment only of the invention, but protection scope of the present invention is not limited thereto,
Any one skilled in the art in the technical scope disclosed by the present invention, the change or replacement that can be readily occurred in,
It should be covered by the protection scope of the present invention.
The content not being described in detail in description of the invention belongs to the known technology of professional and technical personnel in the field.
Claims (5)
1. a kind of electric propulsion plume is to star sensor light interference test system, which is characterized in that including：The quick mould of star sensor, star
Intend device, electric thruster and plume collection device；Wherein, the quick simulator of star sensor, star, electric thruster and plume collection device are set
It puts in vacuum tank；Star sensor field of view center axis coincides with the quick simulator optical axis center of star；Plume collection device is set
It puts in the distal end of the spout of electric thruster；
Electric thruster, for generating stabilized plasma plume；
Plume collection device, for absorbing the plasma plume of electric thruster injection；
The quick simulator of star for simulating the radiation feature of fixed star and geometric properties, provides the brightness of fixed star, the spectrum of fixed star and perseverance
Star sound state star chart；
Star sensor, for the position deviation and attitude misalignment of the fixed star that the quick simulator of sensitive star is simulated.
2. electric propulsion plume according to claim 1 is to star sensor light interference test system, which is characterized in that also wraps
It includes：Mounting bracket；
Star sensor is installed and fixed with the quick simulator of star by the mounting bracket；Wherein, it is disposed in the mounting bracket
Positioning pin, to ensure star sensor field of view center axis with the concentricity of the quick simulator optical axis of star as 0.1mm.
3. electric propulsion plume according to claim 1 is to star sensor light interference test system, which is characterized in that
The collection surface of plume collection device perpendicular to electric thruster spout axis, and, the face of the collection surface of plume collection device
The area of 30 ° of the plume full-shape of the spout of product envelope electric thruster.
4. electric propulsion plume according to claim 1 is to star sensor light interference test system, which is characterized in that also wraps
It includes：Power supply air feed equipment；
Electric thruster generates stabilized plasma plume under the action of air feed equipment of powering, so that electric thruster is operated in specified work
When putting, output stability is better than 5%.
5. electric propulsion plume according to claim 1 is to star sensor light interference test system, which is characterized in that also wraps
It includes：Processor is used for：
50 × 50 range as operating range, calculates the operation around asterism in the selection quick simulator acquired image of star
In the range of image mean value and variance yields, obtain image result of calculation；
Described image result of calculation is filtered using u- σ Image filter arithmetics, obtains filtering process result；
According to the filtering process as a result, using asterism recognizer, resolving obtains asterism position and asterism gross energy；
To star, quick simulator acquired image is traversed, resolves to obtain the corresponding asterism position of each image and asterism total energy
Amount；
To star, quick simulator acquired image counts, and determines the corresponding gross energy average value of each experimental stage and peak value energy
Amount；
According to average energy and the decline percentage of peak energy, influence degree of the plume to asterism energy is determined.
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| CN111027159A (en) * | 2019-10-31 | 2020-04-17 | 中国空间技术研究院 | Star sensor space layout method based on logic tracing |
| CN113553752A (en) * | 2021-07-23 | 2021-10-26 | 中国电子科技集团公司第十八研究所 | Research method for influence of electric propulsion plume on solar cell array |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109855792A (en) * | 2019-01-21 | 2019-06-07 | 北京卫星环境工程研究所 | Electric propulsion test plume particle precipitation protective device and its vacuum test system |
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| CN113553752A (en) * | 2021-07-23 | 2021-10-26 | 中国电子科技集团公司第十八研究所 | Research method for influence of electric propulsion plume on solar cell array |
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