CN207523959U - Become the earth simulator for earth of track polarity measurement for linear array infrared earth sensor - Google Patents
Become the earth simulator for earth of track polarity measurement for linear array infrared earth sensor Download PDFInfo
- Publication number
- CN207523959U CN207523959U CN201720061558.XU CN201720061558U CN207523959U CN 207523959 U CN207523959 U CN 207523959U CN 201720061558 U CN201720061558 U CN 201720061558U CN 207523959 U CN207523959 U CN 207523959U
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- earth
- infra
- infrared
- cold stop
- adapter
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Abstract
This patent discloses the earth simulator for earth for becoming track polarity measurement for linear array infrared earth sensor, including four earth boundary infra-red radiation analogue units and system control unit.Which is mainly characterized in that：The infra-red radiation difference that earth boundary infra-red radiation analogue unit adjusts hot plate and cold stop by system control unit is simulated, multiple orbital attitudes are simulated by translating cold stop position, linear array static state infrared earth sensor is carried out for rail control subsystem, ground test means are provided, and then ensure that infrared earth sensor provides high-precision attitude measurement for satellite.This patent advantage is：Simulator stability is good, and compact is light.
Description
Technical field
This patent is related to the ground checkout equipment of spaceborne infrared earth sensor.It is infrared to be suitable for linear array more particularly to one kind
Earth sensor detection means.
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.Infrared earth sensor mainly has 3 kinds of forms at present：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, are particularly suitable for long-life aerial mission,
Be widely used in absolute orientation detective, meteorological, communication, provide etc. on artificial satellites.
Linear array static state infrared earth sensor (hereinafter referred to as earth sensor) generally has at equal intervals symmetrical 4
A 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 obtain spacecraft attitude.Such as 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, represent there is 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 earth sensitivity
Device carries out polarity test and precision calibration, it is necessary to develop a set of dedicated change track polarity test equipment for it on the ground and become
The earth simulator for earth that track polarity measures.
Invention content
The purpose of this patent is that providing one kind for linear array infrared earth sensor is suitble to carry out the change pole of orbit on ground
Property test earth simulator for earth.
This patent is that a kind of earth simulator for earth for becoming track polarity measurement for linear array infrared earth sensor includes four
Earth boundary infra-red radiation analogue unit 1 and system control unit 2.
The earth boundary infra-red radiation analogue unit includes First Transition ring 1-1, first adapter 1-2, the second transition
Ring 1-3, the second adapter 1-4, infrared collimating mirror 1-5, cold stop fixed frame 1-6, cold stop 1-7, hot plate 1-8, heating film
1-9, heating film thermal insulating plate 1-10 and back cover 1-11.Heating film 1-9 is pasted onto on hot plate 1-8, heating film thermal insulating plate 1-
10 are covered on heating film 1-9 fixation are connect with hot plate 1-8 by screw, heat film thermal insulating plate 1-10 and back cover 1-11 and lead to
It crosses screw connection to fix, cold stop 1-7 is inserted into cold stop fixed frame 1-6, and different tracks, infrared collimating mirror 1-5 are simulated in position
And cold stop fixed frame 1-6 and back cover 1-11 is connected by screw fixation, the second adapter 1-4 passes through with infrared collimating mirror 1-5
Second transition rings 1-3, which is threadedly coupled, to be fixed, and first adapter 1-2 connect fixation with the second adapter 1-4 by screw, and first
Adapter 1-2 is threadedly coupled fixation with infrared earth sensor by First Transition ring 1-1.
System control unit 2 controls the temperature of the hot plate 1-8 and cold stop 1-7 in earth boundary infra-red radiation analogue unit 1
It spends differential mode and intends earth boundary infra-red radiation, translation cold stop 1-7 simulates different tracks in position, and four infra-red radiation analogue units are total to
With composition entire earth boundary infra-red radiation, so as to fulfill in linear array infrared earth sensor ground polarity test and calibration.
This patent advantage is：Simulator stability is good, and compact is light.
Description of the drawings
Fig. 1 is earth simulator for earth composition figure；
In figure：1- earth boundary infra-red radiation analogue unit；2- system control units.
Fig. 2 is earth simulator for earth structure chart；
In figure：1-1- First Transitions ring, 1-2- first adapters, the second transition rings of 1-3-, the second adapters of 1-4-, 1-
The infrared collimating mirrors of 5- and 1-6- cold stops fixed frame, 1-7- cold stops, 1-8- hot plates, 1-9- heating film, 1-10- heat thin
Film thermal insulation board, 1-11- back covers.
Specific embodiment
A preferable embodiment of this patent is provided below according to Fig. 1, Fig. 2, and is described in detail, so as to preferably
Solve the structure feature and functional characteristics of this patent.It should be pointed out that the example provided is in order to illustrate this patent rather than uses
To limit the range of this patent.
This patent as shown in Figure 1 includes four earth boundary infra-red radiation analogue units 1 and system control unit 2；Wherein
The temperature difference of the hot plate 1-8 and cold stop 1-7 in earth boundary infra-red radiation analogue unit 1 are controlled by system control unit 2
Earth boundary infra-red radiation is simulated, four infra-red radiation analogue units collectively constitute entire earth boundary infrared emanation.
Heating film 1-9 is pasted onto on hot plate 1-8 in the earth boundary infra-red radiation analogue unit as shown in Figure 2, is added
Hot film thermal insulating plate 1-10 is covered on heating film 1-9 connect fixation, heating film thermal insulating plate 1- with hot plate 1-8 by screw
10 are connected by screw fixation with back cover 1-11, and infrared collimating mirror 1-5 and cold stop 1-7 and back cover 1-11 are connected by screw
Fixed, the second adapter 1-4 is threadedly coupled fixation, first adapter 1-2 with infrared collimating mirror 1-5 by the second transition rings 1-3
Fixation is connect with the second adapter 1-4 by screw, first adapter 1-2 is sensitive by First Transition ring 1-1 and infrared earth
Device, which is threadedly coupled, to be fixed, and hot plate 1-8 in earth boundary infra-red radiation analogue unit 1 and cold is controlled by system control unit 2
The temperature difference simulation earth boundary infra-red radiation of diaphragm 1-7, four infra-red radiation analogue units collectively constitute entire earth boundary
Infrared emanation, so as to fulfill in linear array infrared earth sensor ground polarity test and calibration.
Wherein infrared collimating mirror 1-6 focal lengths are 15mm, and field angle is 32 °, and cold stop 1-7 materials are 2A12, hot plate 1-8 materials
Expect for T2, cold stop black anodizing processing equal with hotplate surface, emission ratio εh>=0.85, First Transition ring material T2,
It is T2 for the second transition ring material, first adapter material is 2A12, and the second adapter material is polyimides.
Claims (1)
1. a kind of earth simulator for earth for becoming track polarity measurement for linear array infrared earth sensor, red including four earth boundaries
External radiation analogue unit (1) and system control unit (2)；
The earth boundary infra-red radiation analogue unit includes First Transition ring (1-1), first adapter (1-2), the second transition
Ring (1-3), the second adapter (1-4), infrared collimating mirror (1-5), cold stop fixed frame (1-6), cold stop (1-7), hot plate (1-
8), heating film (1-9), heating film thermal insulating plate (1-10) and back cover (1-11)；Heating film (1-9) is pasted onto hot plate (1-
8) on, heating film thermal insulating plate (1-10) is covered on heating film (1-9) and connect fixation with hot plate (1-8) by screw, adds
Hot film thermal insulating plate (1-10) is connected by screw fixation with back cover (1-11), and cold stop (1-7) is inserted into cold stop fixed frame (1-
6) in, position simulates different tracks, infrared collimating mirror (1-5) and cold stop fixed frame (1-6) and passes through screw with back cover (1-11)
Connection is fixed, and the second adapter (1-4) and infrared collimating mirror (1-5) are threadedly coupled fixation by the second transition rings (1-3), and first
Adapter (1-2) connect fixation with the second adapter (1-4) by screw, and first adapter (1-2) passes through First Transition ring (1-
1) fixation is threadedly coupled with infrared earth sensor；
Hot plate (1-8) and cold stop (1-7) in system control unit (2) control earth boundary infra-red radiation analogue unit (1)
Temperature difference simulation earth boundary infra-red radiation, different tracks, four infra-red radiations simulations are simulated in translation cold stop (1-7) position
Unit collectively constitutes entire earth boundary infra-red radiation, so as to fulfill in linear array infrared earth sensor ground polarity test and
Calibration.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621297446 | 2016-11-30 | ||
| CN2016212974466 | 2016-11-30 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207523959U true CN207523959U (en) | 2018-06-22 |
Family
ID=62574836
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720061558.XU Withdrawn - After Issue CN207523959U (en) | 2016-11-30 | 2017-01-19 | Become the earth simulator for earth of track polarity measurement for linear array infrared earth sensor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207523959U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828988A (en) * | 2016-11-30 | 2017-06-13 | 中国科学院上海技术物理研究所 | Become the earth simulator for earth of track polarity measurement for linear array infrared earth sensor |
| CN115009544A (en) * | 2022-05-02 | 2022-09-06 | 军事科学院系统工程研究院网络信息研究所 | Satellite multi-beam direction finding calibration method based on cross amplitude and angle transfer function |
-
2017
- 2017-01-19 CN CN201720061558.XU patent/CN207523959U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828988A (en) * | 2016-11-30 | 2017-06-13 | 中国科学院上海技术物理研究所 | Become the earth simulator for earth of track polarity measurement for linear array infrared earth sensor |
| CN106828988B (en) * | 2016-11-30 | 2023-09-12 | 中国科学院上海技术物理研究所 | Earth simulator for linear array infrared earth sensor orbit-changing polarity measurement |
| CN115009544A (en) * | 2022-05-02 | 2022-09-06 | 军事科学院系统工程研究院网络信息研究所 | Satellite multi-beam direction finding calibration method based on cross amplitude and angle transfer function |
| CN115009544B (en) * | 2022-05-02 | 2022-12-16 | 军事科学院系统工程研究院网络信息研究所 | Satellite multi-beam direction finding calibration method based on cross amplitude and angle transfer function |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20180622 Effective date of abandoning: 20230912 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20180622 Effective date of abandoning: 20230912 |