CN206410713U - Earth simulator for earth for face battle array earth sensor semi-physical simulation - Google Patents
Earth simulator for earth for face battle array earth sensor semi-physical simulation Download PDFInfo
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- CN206410713U CN206410713U CN201621297487.5U CN201621297487U CN206410713U CN 206410713 U CN206410713 U CN 206410713U CN 201621297487 U CN201621297487 U CN 201621297487U CN 206410713 U CN206410713 U CN 206410713U
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Abstract
This patent discloses a kind of earth simulator for earth for face battle array earth sensor semi-physical simulation, the equipment includes earth infra-red radiation analogue unit, attitude-simulating unit, heat radiation control unit and system control unit composition.Which is mainly characterized in that：Earth infra-red radiation analogue unit is simulated by adjusting the infra-red radiation difference of hot plate and cold stop；And by changing the change of different pore size cold stop analog orbit height；Attitude-simulating unit provides simulation test means by driving the translation of earth infra-red radiation analogue unit to carry out the simulation of attitude angle change, and then carrying out new infrared earth sensor ground semi-physical simulation for rail control subsystem.This patent advantage is：Simulator highly versatile, stability are good, and compact is light.
Description
Technical field
This patent is related to the ground checkout equipment of spaceborne infrared earth sensor, and in particular to it is static that one kind is applied to face battle array
Infrared earth sensor semi-physical simulation equipment.
Background technology
A kind of infrared earth sensor is to measure spacecraft relative to local vertical using the infra-red radiation of the earth itself
Or the attitude sensor in local Horizon orientation, also referred to as horizon instrument.Current infrared earth sensor mainly has 3 kinds of forms：Horizon
Pass through formula, frontier tracing formula and radiation thermal balance type.Linear array static state infrared earth sensor is that a kind of typical radiant heat is put down
Weighing apparatus formula earth sensor, because without moving component, volume and quality are smaller, low in energy consumption, is particularly suitable for long-life aerial mission,
Be widely used in absolute orientation detective, meteorological, communication, provide etc. on artificial satellite.
Linear array static state infrared earth sensor (hereinafter referred to as earth sensor) typically has at equal intervals symmetrical 4
Individual optical system.Each optical system receives the infra-red radiation from earth different piece respectively, by each optical system
The different infrared energies received are analyzed and draw spacecraft attitude.For example earth sensor works as all optical systems
When reception energy is equal, represent that spacecraft attitude angle is zero.When former and later two optical systems reception energy is unequal, boat is represented
Its device has attitude misalignment in pitch axis；Similarly, when the visual field reception energy of left and right two is unequal, expression has appearance in the axis of rolling
State deviation.
The performance and precision of the earth sensor working condition in orbit by satellite is directly affected.In order to sensitive to the earth
Device carries out performance test and precision calibration, it is necessary to develop a set of special performance test apparatus, i.e. earth mould on the ground for it
Intend device, simulate the earth infrared image seen when earth sensor is run under different tracks, different postures, realize that the earth is quick
The ground test of sensor performance indications is assessed.
The content of the invention
The purpose of this patent is to provide a kind of earth simulator for earth for face battle array earth sensor semi-physical simulation certainly.
A kind of earth simulator for earth for face battle array earth sensor semi-physical simulation includes earth infra-red radiation analogue unit
1st, attitude-simulating unit 2 and system control unit 3.Wherein：
Heat film 1-5 in the earth infra-red radiation analogue unit to be pasted onto on hot plate 1-1, heating film heat-insulating plate 1-
6 are covered on heating film 1-5 and are connected by screw with hot plate 1-1, and hot plate 1-1 and cold stop 1-3 pass through four hot plates
Heat-insulating bracket 1-2 is attached fixation, and infrared collimating mirror (1-4) is connected by screw with framework side plate 1-7, passes through control
The temperature difference simulation earth infra-red radiation of hot plate (1-1) and cold stop 1-3 in earth infra-red radiation analogue unit (1), cold light
Different apertures are provided with according to feature orbit altitude on late 1-3 and simulate multiple orbital attitudes earth infra-red radiation；
The two-dimension translational platform 2-1 in attitude-simulating unit 2 is controlled to drive earth infra-red radiation mould by system control unit 3
Quasi-simple member 1 is translated, and simulates the angle change of different postures.So as to realize in face battle array infrared earth sensor dress star post-simulation
The change of satellite load attitude angle, carries out the test of attitude angle.
This patent advantage is：Simulator highly versatile, stability are good, and compact is light.
Brief description of the drawings
, below will be to embodiment or existing for clearer explanation this patent embodiment or technical scheme of the prior art
There is the accompanying drawing used required in technology description to be briefly described, it is therefore apparent that drawings in the following description are the one of this patent
A little embodiments, for those of ordinary skill in the art, on the premise of not paying creative work, can also be according to these
Accompanying drawing obtains other accompanying drawings.
Fig. 1 is the composition figure of this patent earth simulator for earth；
In figure：1- earth infra-red radiation analogue units；2- attitude-simulating units；3- system control units；
Fig. 2 is the structure chart of this patent earth simulator for earth.
In figure：The heat-insulated post of 1-1- hot plates, 1-2-, 1-3- cold stops, the infrared collimating mirrors of 1-4-, 1-5- heating films and 1-6-
Heat film heat-insulating plate, 1-7- frameworks side plate and 2-1- two-dimension translational platforms.
Embodiment
The preferable embodiment of this patent one is provided below according to Fig. 1-Fig. 2, and is described in detail, so as to be better understood by
The architectural feature and functional characteristics of this patent, it is noted that given embodiment is in order to illustrate this patent, rather than to use
To limit the scope of this patent.
As shown in Fig. 1 Fig. 2, the earth infra-red radiation analogue unit includes：Earth infra-red radiation analogue unit 1, posture
Analogue unit 2 and system control unit 3.Wherein by controlling earth infra-red radiation analogue unit 1 to produce infrared radiation signal, appearance
State analogue unit 2 drives earth infra-red radiation analogue unit 1 to be translated, the control earth infra-red radiation mould of system control unit 3
The temperature difference of quasi-simple member 1 and the translation parameters of attitude-simulating unit 2 are simulated (0 ° of roll angle, 5 ° of the angle of pitch), (5 ° of roll angle, bowed
0 ° of the elevation angle) (0 ° of roll angle, -5 ° of the angle of pitch) and (- 5 ° of roll angle, 0 ° of the angle of pitch) four attitude angle earth infra-red radiations, face battle array
Infrared earth sensor obtains corresponding attitude angle by collection, processing and calculating to be changed, with translation earth simulator for earth simulation
Attitude angle is corresponded to, and ground experiment and discriminating test are carried out after carrying out opposite battle array infrared earth sensor dress star.
It is pasted onto as Fig. 2 wherein heats film 1-5 on hot plate 1-1, heating film heat-insulating plate 1-6 is covered in heating film 1-
It is connected on 5 by screw with hot plate 1-1, hot plate 1-1 and cold stop 1-3 is connected by four hot plate heat-insulating bracket 1-2
Fixation is connect, infrared collimating mirror 1-4 is connected by screw with framework side plate 1-7, by controlling the simulation of earth infra-red radiation single
According to feature orbit altitude on the temperature difference simulation earth infra-red radiation of hot plate 1-1 and cold stop 1-3 in member 1, cold stop 1-3
It is provided with different aperture simulation multiple orbital attitudes earth infra-red radiations；Attitude-simulating is controlled by system control unit (3)
Two-dimension translational platform (2-1) in unit (2) drives earth infra-red radiation analogue unit (1) to be translated, and simulates different postures
Angle change.So as to realize the change that star post-simulation satellite load attitude angle is filled in face battle array infrared earth sensor, posture is carried out
The test at angle.Wherein infrared collimating mirror 1-4 clear aperture is 70mm, and focal length is 93.24mm, cold stop 1-3 diaphragms, hot plate 1-
The equal black anodizing processing in 1 surface, emission ratio εh≥0.85。
Claims (1)
1. a kind of earth simulator for earth for face battle array earth sensor semi-physical simulation, including earth infra-red radiation analogue unit
(1), attitude-simulating unit (2) and system control unit (3), it is characterised in that：
Heating film (1-5) is pasted onto on hot plate (1-1) in the earth infra-red radiation analogue unit (1), heats film heat-insulating
Plate (1-6) is covered on heating film (1-5) and is connected by screw with hot plate (1-1), hot plate (1-1) and cold stop (1-
3) fixation is attached by four hot plate heat-insulating brackets (1-2), infrared collimating mirror (1-4) passes through screw and framework side plate (1-
7) it is connected, by the temperature difference for controlling hot plate (1-1) and cold stop (1-3) in earth infra-red radiation analogue unit (1)
Different apertures are provided with according to feature orbit altitude on simulation earth infra-red radiation, cold stop (1-3) and simulate different tracks height
Spend earth infra-red radiation；
The two-dimension translational platform (2-1) in attitude-simulating unit (2) is controlled to drive earth infra-red radiation by system control unit (3)
Analogue unit (1) is translated, and simulates the angle change of different postures, so as to realize after the battle array infrared earth sensor dress star of face
The change of satellite load attitude angle is emulated, the test of attitude angle is carried out.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621297487.5U CN206410713U (en) | 2016-11-30 | 2016-11-30 | Earth simulator for earth for face battle array earth sensor semi-physical simulation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621297487.5U CN206410713U (en) | 2016-11-30 | 2016-11-30 | Earth simulator for earth for face battle array earth sensor semi-physical simulation |
Publications (1)
| Publication Number | Publication Date |
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| CN206410713U true CN206410713U (en) | 2017-08-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201621297487.5U Active CN206410713U (en) | 2016-11-30 | 2016-11-30 | Earth simulator for earth for face battle array earth sensor semi-physical simulation |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106643794A (en) * | 2016-11-30 | 2017-05-10 | 中国科学院上海技术物理研究所 | Earth simulator for semi-physical simulation of area array earth sensor |
-
2016
- 2016-11-30 CN CN201621297487.5U patent/CN206410713U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106643794A (en) * | 2016-11-30 | 2017-05-10 | 中国科学院上海技术物理研究所 | Earth simulator for semi-physical simulation of area array earth sensor |
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