CN106643795A - Simulation method based on area array earth sensor semi-physical simulation earth simulator - Google Patents
Simulation method based on area array earth sensor semi-physical simulation earth simulator Download PDFInfo
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- CN106643795A CN106643795A CN201611090600.7A CN201611090600A CN106643795A CN 106643795 A CN106643795 A CN 106643795A CN 201611090600 A CN201611090600 A CN 201611090600A CN 106643795 A CN106643795 A CN 106643795A
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- G—PHYSICS
- G01—MEASURING; TESTING
- 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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Abstract
The invention discloses a simulation method based on an area array earth sensor semi-physical simulation earth simulator. According to the method, firstly, cold diaphragm hole diameter is calculated according to the rail height; the earth infrared radiation is obtained through setting the temperature difference T of an earth infrared radiation simulation unit heat plate and the cold diaphragm, so that the infrared radiation of the earth is obtained; then, through the transverse movement of the circle center of the diaphragm hole relative to the X and Y axis direction, the simulation of different postures is realized. The method provided by the invention has the advantages that the universality of the simulator is high; the stability is high; the size is small; the weight is light; convenience is realized.
Description
Technical field
The present invention relates to spaceborne earth sensor ground checkout equipment technology, particularly relates to one kind and is applied to face battle array statically
The earth simulator for earth attitude simulation method of ball sensor semi-physical simulation.
Background technology
Earth sensor, is commonly used to measure pitch attitude angle and roll attitude angle of the satellite relative to the earth, is satellite
One of sensitive and control subsystem crucial unit of attitude, it is by the sensitive for infrared radiation to the earth, there is provided reference signal with
Spacecraft is set to keep the instrument of biaxial stabilization, whether its certainty of measurement and reliability is directly connected to the attitude of satellite accurate
With it is stable.
Earth simulator for earth provides performance test and precision as the ground checkout equipment of earth sensor for earth sensor
Demarcate.Earth simulator for earth is mainly made up of earth infra-red radiation analogue unit, attitude-simulating unit, system control unit etc., is used
Different apertures are provided with according to different characteristic orbit altitude on the cold drawing of simulation earth infra-red radiation, the infrared spoke of hot plate
Penetrate by cold stop, form the thermal target under cold drawing background, cold stop (thermal target i.e. on cold drawing) is positioned over into collimation lens
Focal plane on, every infra-red radiation on thermal target after optical system, formed with certain clear aperature directional light,
So as to reach the purpose of earth infra-red radiation simulation.Earth infra-red radiation analogue unit structure is as shown in Figure 1.And the static state earth is quick
Sensor is detected by the cold and hot border formed to the earth and space, base area flat round position signalling, determines bowing for satellite
Attitude angle and roll attitude angle are faced upward, for satellite gravity anomaly, whether the attitude of satellite correctly determines the track of satellite transit
Whether correct, especially satellite is in emission process and excessive CloseTrack process.Therefore, research is suitable for static earth sensor
Earth simulator for earth attitude simulation method is significant for the performance test of earth sensor.
The content of the invention
The purpose of the present invention is exactly to provide a kind of ground of suitable ground detection for linear array static earth sensor product
The attitude simulation method of ball simulator.
Battle array earth sensor semi-physical simulation earth simulator for earth in face includes infra-red radiation analogue unit (1), attitude-simulating list
First (2) and system control unit (3).Attitude-simulating unit (2) is controlled by system control unit (3) and drives earth infra-red radiation
Analogue unit (1) is translated, the angle change of the different attitudes of simulation, so as to realize after the battle array infrared earth sensor dress star of face
The change of emulation satellite load attitude angle, carries out the test of attitude angle.
It is a kind of based on the attitude simulation method of face battle array earth sensor semi-physical simulation earth simulator for earth its concrete steps such as
Under：
(1) the aperture D in circular cold stop hole during orbit altitude H is calculated,
D=2 × f × tan { arcsin [(6371+40)/(6371+H)] }, for simulating earth infra-red radiation, wherein f is
The focal length of optical system in earth infra-red radiation analogue unit；
(2) temperature difference T of earth infra-red radiation analogue unit hot plate and cold stop is set；
(3) center of circle in cold stop hole is calculated relative to X-direction translation Lx, Y direction translation Ly, Lx=a0+a1p+a2p2
+a3p3, Ly=a0+a1r+a2r2+a3r3, wherein, a0, a1, a2, a3Respectively displacement calibration constant term parameter, first order parameter, two
Secondary item parameter, cubic term parameter, p are the angle of pitch, and r is roll angle.
The invention has the advantages that：Simulator highly versatile, good stability, compact is light.
Description of the drawings
Fig. 1 is the structure chart of earth simulator for earth of the present invention.
Fig. 2 is analogy method flow chart of the present invention.
Specific embodiment
Below by embodiment and accompanying drawing, the present invention is described in further detail.
1st, attitude-simulating is carried out by orbit altitude 15000Km, diaphragm diameter is selected after being computed for the cold light of 56.26mm
The aperture of door screen；
2nd, space earth infra-red radiation is simulated, the cold drawing with circular iris hole is positioned over into the optical system of earth simulator for earth
The focal plane of system, by Electric heating and using temperature controller control earth infra-red radiation analogue unit in hot plate and
The temperature difference of cold drawing is 26 DEG C；
3rd, the attitude-simulating at -5 ° of 5 ° of pitch attitude angle and roll attitude angle is carried out in the present embodiment.For pitch attitude
The simulation that 5 ° of angle, it is that positive direction moves 8.06839mm relative to the movement of optical system that corresponding translation stage drives cold-hot plate, right
In -5 ° of the simulation in roll attitude angle, it is negative direction movement relative to the movement of optical system that corresponding translation stage drives cold-hot plate
8.06635mm.The motion that two-dimension translational platform motor is converted to the attitude angle of pitching will be rolled by this, motor drives tested
Product opposing optical system is moved, the method for causing ground flat round emergent light angle to change, and can be effectively realized ground
Simulation of the ball simulator to attitude.
Embodiment as above its object is to make the common skill of this area only for the technological thought of the explanation present invention
Art personnel will appreciate that present disclosure and implement according to this that the scope of this patent is not limited merely to above-mentioned specific embodiment,
I.e. all equal changes made according to disclosed spirit or modification, still cover in protection scope of the present invention.
Claims (1)
1. a kind of analogy method based on face battle array earth sensor semi-physical simulation earth simulator for earth；Described face position ball is sensitive
Device semi-physical simulation earth simulator for earth includes infra-red radiation analogue unit (1), attitude-simulating unit (2) and system control unit
(3)；Controlling attitude-simulating unit (2) by system control unit (3) drives earth infra-red radiation analogue unit (1) to be put down
Move, the angle change of the different attitudes of simulation, so as to realize in face battle array infrared earth sensor dress star post-simulation satellite load attitude
The change at angle, carries out the test of attitude angle；It is characterized in that described analogy method step is as follows：
1) the aperture D in circular cold stop hole during orbit altitude H is calculated,
D=2 × f × tan { arcsin [(6371+40)/(6371+H)] },
For simulating earth infra-red radiation, wherein f is the focal length of optical system in earth infra-red radiation analogue unit；
2) temperature difference T of earth infra-red radiation analogue unit hot plate and cold stop is set；
3) center of circle in cold stop hole is calculated relative to X-direction translation Lx, Y direction translation Ly,
Lx=a0+a1p+a2p2+a3p3, Ly=a0+a1r+a2r2+a3r3,
Wherein, a0, a1, a2, a3Respectively displacement calibration constant term parameter, first order parameter, quadratic term parameter, cubic term parameter, p
For the angle of pitch, r is roll angle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611090600.7A CN106643795A (en) | 2016-11-30 | 2016-11-30 | Simulation method based on area array earth sensor semi-physical simulation earth simulator |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611090600.7A CN106643795A (en) | 2016-11-30 | 2016-11-30 | Simulation method based on area array earth sensor semi-physical simulation earth simulator |
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| CN106643795A true CN106643795A (en) | 2017-05-10 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1757566A (en) * | 2005-10-11 | 2006-04-12 | 中国科学院上海技术物理研究所 | Be fit to the earth simulator for earth that double cone scanning type infrared horizon instrument ground detection is used |
| CN201808672U (en) * | 2009-12-31 | 2011-04-27 | 北京控制工程研究所 | Portable earth simulator |
| CN102175259A (en) * | 2010-12-31 | 2011-09-07 | 北京控制工程研究所 | Autonomous navigation simulation test system based on earth-sun-moon integrated sensor |
| CN102310953A (en) * | 2010-06-29 | 2012-01-11 | 长春理工大学 | Portable earth simulator |
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2016
- 2016-11-30 CN CN201611090600.7A patent/CN106643795A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1757566A (en) * | 2005-10-11 | 2006-04-12 | 中国科学院上海技术物理研究所 | Be fit to the earth simulator for earth that double cone scanning type infrared horizon instrument ground detection is used |
| CN201808672U (en) * | 2009-12-31 | 2011-04-27 | 北京控制工程研究所 | Portable earth simulator |
| CN102310953A (en) * | 2010-06-29 | 2012-01-11 | 长春理工大学 | Portable earth simulator |
| CN102175259A (en) * | 2010-12-31 | 2011-09-07 | 北京控制工程研究所 | Autonomous navigation simulation test system based on earth-sun-moon integrated sensor |
Non-Patent Citations (7)
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| 付东辉等: "地球模拟器中热地球温度分析", 《光机电信息》 * |
| 何柏年等: "高精度大型地球模拟器及红外标定转台", 《控制工程》 * |
| 吕涛等: "低轨道红外地球模拟器设计", 《长春理工大学学报（自然科学版）》 * |
| 徐熙平等: "小型地球模拟器温度控制***研究", 《电子测量技术》 * |
| 李刚等: "卫星仿真测试用太阳模拟器和地球模拟器设计", 《红外技术》 * |
| 赵剑等: "新型的红外地球敏感器地面测试标定方法", 《红外与激光工程》 * |
| 赵蕊等: "卫星试验用小型地球模拟器研究", 《长春理工大学学报（自然科学版）》 * |
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Application publication date: 20170510 |