CN107421562A - Calibration Method based on face battle array earth sensor semi-physical simulation earth simulator for earth - Google Patents
Calibration Method based on face battle array earth sensor semi-physical simulation earth simulator for earth Download PDFInfo
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- CN107421562A CN107421562A CN201611077902.0A CN201611077902A CN107421562A CN 107421562 A CN107421562 A CN 107421562A CN 201611077902 A CN201611077902 A CN 201611077902A CN 107421562 A CN107421562 A CN 107421562A
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- earth
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Classifications
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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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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Navigation (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The invention discloses a kind of Calibration Method based on face battle array earth sensor semi-physical simulation earth simulator for earth.The position for changing cold stop hole is set by system control unit first, obtain multigroup offset and corresponding angle, secondly by using polynomial fitting method, the function met between the offset of system requirements and corresponding angle change is established, completes calibration work.The invention has the advantages that：Pass through simple calibration so that simulator is more accurate and has stronger maintainability.
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 Calibration Method of ball sensor semi-physical simulation.
Background technology
Earth sensor, pitch attitude angle and roll attitude angle of the satellite relative to the earth are commonly used to measure, is satellite
Posture is sensitive and one of crucial unit of control subsystem, and it passes through 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 measurement accuracy and reliability is directly connected to the attitude of satellite accurate
Stably.
Ground checkout equipment of the earth simulator for earth as earth sensor, performance test and precision are provided for earth sensor
Demarcation.Earth simulator for earth is mainly made up of earth infra-red radiation analogue unit, attitude-simulating unit, system control unit etc., is used
According to different characteristic orbit altitude being provided with different apertures on the cold drawing of simulation earth infra-red radiation, the infrared spoke of hot plate
The thermal target by cold stop, formed under cold drawing background is penetrated, cold stop (thermal target i.e. on cold drawing) is positioned over 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 earth is quick
For sensor by being detected to the earth and the cold and hot border that space is formed, base area flat round position signalling determines the pitching of satellite
Whether attitude angle and roll attitude angle, the posture of satellite correctly determine whether the track of satellite transit is correct, especially satellite
In emission process and excessive CloseTrack process.Therefore, earth simulator for earth Calibration Method of the research suitable for static earth sensor
For accurately realizing that the performance test of earth sensor is significant.
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 Calibration Method of ball simulator.
The earth simulator for earth includes infra-red radiation analogue unit 1, attitude-simulating unit 2 and system control unit 3.Pass through
System control unit 3 controls attitude-simulating unit 2 to drive earth infra-red radiation analogue unit 1 to be translated, and completes calibration work.
It is characterized in that：Described Calibration Method step is as follows：
(1) attitude-simulating unit 2 is controlled by system control unit 3, drives earth infra-red radiation analogue unit 1 to be put down
Moving, so as to change the position in cold stop hole in infra-red radiation analogue unit 1 so that it produces certain skew L relative to optical axis,
The infra-red radiation of cold stop is caused to produce certain angle change after optical system, i.e., infrared earth sensor is relative to ground
The attitudes vibration that ball occurs, it is θ to record this angle change.
(2) repetitive process (1) p times, change skew L, obtains p+1 group offsets L1, L2..., LP+1Become with corresponding angle
Change θ1, θ2..., θP+1。
(3) fitting of a polynomial algorithm is used, is met between the offset of system requirements and corresponding angle change
Calculation formula is：
L=a0+a1θ+a2θ2+a3θ,
Wherein a0, a1, a2, a3Respectively displacement calibration constant term parameter, first order parameter, quadratic term parameter, cubic term ginseng
Number.
The invention has the advantages that：Pass through simple calibration so that simulator is more accurate and has stronger maintainability.
Brief description of the drawings
Fig. 1 is the structure chart of earth simulator for earth of the present invention.
Fig. 2 is Calibration Method flow chart of the present invention.
Fig. 3 is the offset of the posture control unit translation in specific implementation process and corresponding angle change matched curve
Figure.
Embodiment
Below by embodiment and accompanying drawing, the present invention is described in further detail.
Wherein one master for being used to determine the angle change at pitch attitude angle or roll attitude angle is found by ZEMAX softwares
Light, obtained by repeated multiple times data.Using fitting of a polynomial algorithm, by repeatedly fitting, the following parameter is obtained.
a0=-4.74135E-9, a1=1.61328,
a2=4.0848E-5, a3=7.77599E-6
For embodiment as described above only for the technological thought of the explanation present invention, its object is to make the common skill of this area
Art personnel can understand present disclosure and implement according to this, and the scope of this patent is not limited merely to above-mentioned specific embodiment,
I.e. all equal changes or modification made according to disclosed spirit, still cover in protection scope of the present invention.
Claims (1)
1. a kind of Calibration 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), attitude-simulating unit (2) is controlled to drive earth infra-red radiation analogue unit (1) to be put down by system control unit (3)
Move, complete calibration work；It is characterized in that：Described Calibration Method step is as follows：
1) attitude-simulating unit (2) is controlled by system control unit (3), drives earth infra-red radiation analogue unit (1) to carry out
Translation, so as to change the home position in cold stop hole in infra-red radiation analogue unit (1) so that it produces certain relative to optical axis
Skew L, cause the infra-red radiation of cold stop to produce certain angle change, i.e. infrared earth sensor after optical system
The attitudes vibration occurred relative to the earth, it is θ to record this angle change；
2) repeat step 1) p times, change skew L, obtain p+1 group offsets L1, L2..., LP+1With corresponding angle change θ1,
θ2..., θP+1；
3) fitting of a polynomial algorithm is used, the calculating being met between the offset of system requirements and corresponding angle change is public
Formula is：
L=a0+a1θ+a2θ2+a3θ,
Wherein a0, a1, a2, a3Respectively displacement calibration constant term parameter, first order parameter, quadratic term parameter, cubic term parameter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611077902.0A CN107421562A (en) | 2016-11-30 | 2016-11-30 | Calibration Method based on face battle array earth sensor semi-physical simulation earth simulator for earth |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611077902.0A CN107421562A (en) | 2016-11-30 | 2016-11-30 | Calibration Method based on face battle array earth sensor semi-physical simulation earth simulator for earth |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107421562A true CN107421562A (en) | 2017-12-01 |
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ID=60422919
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611077902.0A Pending CN107421562A (en) | 2016-11-30 | 2016-11-30 | Calibration Method based on face battle array earth sensor semi-physical simulation earth simulator for earth |
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| CN (1) | CN107421562A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111459049A (en) * | 2020-03-13 | 2020-07-28 | 北京仿真中心 | Semi-physical simulation method and system |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
-
2016
- 2016-11-30 CN CN201611077902.0A patent/CN107421562A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 (6)
| Title |
|---|
| 付东辉等: "地球模拟器中热地球温度分析", 《光机电信息》 * |
| 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）》 * |
| 张振等: "红外焦平面静态地平仪用地球模拟器光机系统设计", 《中国光学与应用光学》 * |
| 徐熙平等: "小型地球模拟器温度控制系统研究", 《电子测量技术》 * |
| 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）》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111459049A (en) * | 2020-03-13 | 2020-07-28 | 北京仿真中心 | Semi-physical simulation method and system |
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Application publication date: 20171201 |