CN109037981A - A kind of earthing or grounding means for satellite sensor - Google Patents
A kind of earthing or grounding means for satellite sensor Download PDFInfo
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- CN109037981A CN109037981A CN201810729512.XA CN201810729512A CN109037981A CN 109037981 A CN109037981 A CN 109037981A CN 201810729512 A CN201810729512 A CN 201810729512A CN 109037981 A CN109037981 A CN 109037981A
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- ground
- satellite sensor
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- satellite
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/21—Interference related issues ; Issues related to cross-correlation, spoofing or other methods of denial of service
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/015—Arrangements for jamming, spoofing or other methods of denial of service of such systems
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R4/00—Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation
- H01R4/58—Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation characterised by the form or material of the contacting members
- H01R4/64—Connections between or with conductive parts having primarily a non-electric function, e.g. frame, casing, rail
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R4/00—Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation
- H01R4/58—Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation characterised by the form or material of the contacting members
- H01R4/66—Connections with the terrestrial mass, e.g. earth plate, earth pin
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- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Computer Networks & Wireless Communication (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measurement Of Radiation (AREA)
- Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
Abstract
The present invention relates to a kind of earthing or grounding means for satellite sensor, include multiple ground lines, are used to connect with multiple signal loop lines of satellite sensor, wherein the length of the ground line is identical；And ground structure, it is used for all ground connections.Moreover, it relates to a kind of method for satellite sensor to be grounded.By the invention it is possible to greatly reduce on star single machine at work to the electromagnetic interference of satellite sensor, while preventing interference of the satellite sensor to other equipment.
Description
Technical field
The present invention relates to satellite signal transit and electromagnetic shielding field, in particular to a kind of for satellite sensor
Earthing or grounding means.Moreover, it relates to a kind of method for satellite sensor to be grounded.
Background technique
Spacecraft EMC Design accounts for epochmaking status in Project R&D, is on the one hand because electronics is set on star
Standby, especially high-power radiation signal source can more or less generate electromagnetic interference energy, and on the other hand, satellite is in orbit
When, it inevitably will receive the influence of solar ultraviolet and external charged particle.Good EMC Design can reduce, very
To avoid substantially electromagnetic interference to the adverse effect of satellite.
Spacecraft electromagnetic Compatibility Design mainly includes grounding design and overlap joint design etc..Good ground connection can inhibit electricity
Magnetic noise simultaneously improves immunity to interference, moreover it is possible to avoid or reduce the arc discharge between satellite different parts, keep satellite dry from electromagnetism
The influence disturbed.For the low frequency signal transmitted, good grounding design is mostly used to reduce interference source to transmitted signal
It influences.
The ground of spacecraft is broadly divided into power ground, signal ground and structure benchmark, and earthing mode mainly has single-point grounding, more
Point ground connection and mixing ground connection.Ground connection principle mainly has the following:
Whole star power return is arranged in pairs with main track, returns to power supply and distribution unit, and power return is isolated with single machine casing, by
Power subsystem single machine is connected to satellite main structure on the ground by single-point grounding mode.
Signal transmission between single machine, which should all use, back and forth connects line, for whole star, low frequency signal is not provided,
Telemetered signal loop line and remote control execute pulse transmission loop line and return to secondary power supply module, by secondary power supply module single-point grounding.
Spaceborne high frequency single machine and component are all made of the mode of multipoint earthing.Circuit should be taken with regard to proximity when every ground connection
Ground, and the length of earth lead is less than the 1/20 of operating signal wavelengths.
Each device signal loop line and control loop line on star is forbidden to be directly connected to structurally, otherwise set nearby by mounting surface
There can be public power supply loop line on standby mutual interface circuit, form " ground loop " as shown in Figure 1, ground loop can emit
The circuit that Electromagnetic Interference nearby works normally is highly prone to the interference of external electromagnetic wave again.
The principle of overlap joint design is mainly: the direct current contact resistance between single machine casing and mounting plate should be less than 10m Ω；Heat
The overlap joint for controlling multilayer and spacecraft benchmark is not more than 1 Ω；Metal component and whole star of all areas greater than 1cm2 on spacecraft
The overlap resistance of benchmark is not more than 1K Ω.
The measuring signal of certain spacecraft scientific exploration device outputs is skin coulomb magnitude, even flies coulomb magnitude.Acquisition
The chip front end of the small-signal is all made of charge amplifier, is easy to be influenced by external interference, therefore detector
It is very important for earthing mode.
In order to which weak signal to be grounded, prior art is, the output signal main track and loop line of detector is pairs of
Transmission, in load data manager end grounding, is specifically illustrating referring to figure after acquisition signal flows back into load data manager
2.In prior art shielding method is generally only taken to the shielding of small-signal from transmission cable, such as uses multiple twin or screen
Cable is covered to transmit small-signal, but the measure is unsatisfactory to the shield effectiveness of signal, can not thoroughly solve detector
Be disturbed problem, having on star single machine generate larger electromagnetic interference when can still disturb to detector.
Summary of the invention
From the prior art, the task of the present invention is provide a kind of earthing or grounding means and one kind for satellite sensor
Method for satellite sensor to be grounded can greatly reduce on star single machine at work by the device or this method
To the electromagnetic interference of satellite sensor (or abbreviation detector), while preventing interference of the satellite sensor to other equipment.
In the first aspect of the present invention, foregoing task is solved by a kind of earthing or grounding means for satellite sensor,
It includes
Multiple ground lines are used to connect with multiple signal loop lines of satellite sensor, wherein the length of the ground line
It is identical；And
Ground structure is used for all ground connections.
It is provided in a preferred embodiment of the invention, the ground structure is as close possible to satellite sensor itself.It is logical
Ground wire length can be reduced as much as possible by crossing the program, to further decrease single machine to the electromagnetic interference and spy of detector
Device is surveyed to the electromagnetic interference of other equipment.
It provides in another preferred embodiment of the invention, the length of the ground line is 10cm to 30cm.
It provides in another preferred embodiment of the invention, the multiple ground line includes four grounded line.
It is provided in an expansion scheme of the invention, the measurement letter transmitted in the signal loop line of the satellite sensor
Number the quantity of electric charge be skin coulomb magnitude or winged coulomb magnitude.It should be noted here that although the present invention is to the electromagnetism of weak signal
Shield effectiveness is especially good, but technical solution of the present invention also can be applied to the higher other signals source of signal strength.
In the second aspect of the present invention, foregoing task by a kind of method for satellite sensor to be grounded, including under
Column step:
The signal loop line of satellite sensor and multiple ground lines are connected, wherein the length of the ground line is identical；And
The ground line is connect with same satellite sensor at a distance of mounting structure plate as close as possible, makes ground line as far as possible
It is short.
The present invention at least have it is following the utility model has the advantages that
(1) common and preferably nearest ground connection can guarantee that the signal circuit of detector is as short as possible and (such as be grounded wire length
Degree is only about 20cm), therefore signal circuit length is effectively reduced compared to traditional grounding scheme, reduce single machine pair on star
The interference strength of faint output signal also reduces the interference to other equipment；
(2) due to the same length of multiple ground lines of multiple signal loop lines of detector output signal and their companies
It is connected to common ground, therefore the interference signal being mingled in multiple faint output signals in these signal loop lines is also close, divided
The interference signal in these faint output signals can be filtered out when analysing the faint output signal of detector together at low cost, simultaneously
It can guarantee the integrality of signal to the greatest extent；
(3) due to only having the signal loop line of detector to use scheme that is common and being preferably grounded nearby, and detector
Output signal it is very faint, therefore at the different grounding points on ground, such as structural slab formed voltage difference very little, can be effective
The signal strength for avoiding loop as shown in Figure 1 avoids and introduces new interference source.
Detailed description of the invention
With reference to specific embodiment, the present invention is further explained with reference to the accompanying drawing.
Fig. 1 shows the schematic diagram of ground loop according to prior art；
Fig. 2 shows the schematic diagrames of satellite sensor earthing mode according to prior art；
Fig. 3 shows the perspective view of satellite sensor earthing mode according to the present invention；And
Fig. 4 shows the top view of satellite sensor earthing mode according to the present invention.
Specific embodiment
It should be pointed out that each component in each attached drawing may be shown in which be exaggerated in order to illustrate, and it is not necessarily ratio
Example is correctly.In the drawings, identical appended drawing reference is equipped with to the identical component of identical or function.
In the present invention, unless otherwise indicated, " on being arranged in ... ", " being arranged in ... top " and " on being arranged in ... "
Do not exclude the case where there are intermediaries therebetween.
In the present invention, each embodiment is intended only to illustrate the solution of the present invention, and is understood not to restrictive.
In the present invention, unless otherwise indicated, quantifier "one", " one " and the scene for not excluding element.
It is also noted herein that in an embodiment of the present invention, for it is clear, for the sake of simplicity, might show only one
Sub-unit or component, but those skilled in the art are it is understood that under the teachings of the present invention, it can be according to concrete scene
Need to add required component or component.
It should furthermore be mentioned that in the present invention, the wording such as " identical ", " same ", " being equal to " are not meant to the two absolutely
To equal, but allow certain reasonable error, that is to say, that above-mentioned wording also covers " substantially the same ", " substantially same
Sample ", " being substantially equal to " etc..
For prior art grounding scheme, the present inventor has insight into originally: finding from actual test result existing
Earthing mode has the following problems: on the one hand, the output signal of detector is very faint, generates to electronic equipments other on star
Electromagnetic interference is very sensitive, and for example, about 1.3m of the signal circuit in original earthing mode, signal circuit is too long, not only increases signal
The voltage difference generated on circuit, causes original signal to be submerged, and signal circuit is too long is also easier to by electromagnetic interference；Separately
On the one hand, detector is larger, and for length and width in 1m or so, detector surrounding has signal wire output, and each signal wire flows back into
The same single machine of spacecraft, causes current return circuit length different, and the degree being disturbed is also different, thus be difficult by
Different interference signals all filter out, and the loss of original signal is likely to result in the filtering of disturbance signal.
Solution proposed by the present invention solves problem of the prior art, to the electricity of detector when single machine works on star
Magnetic disturbance: when certain single machine works on star, multiple probe access noises are significantly increased, certain probe access noise rises from 6
To 17 or so；Baseline noise reaches about 9.
Based on problem above, the purpose of the present invention is reduce single machine on star to make each spy to the electromagnetic interference of scientific exploration device
It surveys device channel noise and maintains normal range (NR) (lower than 5), guarantee the normal execution of spacecraft scientific exploration task.
Transmitting for the power supply mentioned in prior art arrangement with signal all should be using the scheme connected back and forth to line, from survey
It to this spacecraft and is not suitable for from test result, therefore the invention proposes new earthing modes.In conjunction with the knot of this spacecraft
The faint output signal of detector is realized better shield effectiveness using the principle being grounded nearby by structure feature, the present invention.
Technical solution of the present invention is elaborated combined with specific embodiments below.
Fig. 3 and Fig. 4 respectively illustrates the perspective view and top view of satellite sensor earthing mode according to the present invention.
As shown in Figure 3 and Figure 4, the output signal of satellite sensor 106 is small-signal, and the quantity of electric charge of signal is, for example,
Several skin coulombs.It should be understood that this is only exemplary, the solution of the present invention is also applied for having other output signals
Other detectors of charge magnitude.Such faint output signal is easy by electromagnetic interference, it is therefore desirable to is electromagnetically shielded.Satellite
Detector 106 for example has there are four signal wire (not shown) and four corresponding signal loop line (not shown).But it should refer to
Out, the signal wire of other numbers and signal loop line are also conceivable.The mounting structure plate 105 of satellite is arranged in satellite sensor
Near 106.The equipment that single machine 107 will e.g. be docked with satellite sensor 106 or the equipment with other equipment interconnections, wherein
Single machine may generate electromagnetic interference to detector 106 in other cases.It should be noted here that in this application, term is " single
Machine " refers to the individual equipment on satellite." satellite sensor " refers to the detecting devices on satellite.
Four signal loop lines of satellite sensor 106 pass through respectively equal length, be for example 30cm such as four (its
The ground line of its number is also conceivable) ground line, i.e., first the 101, second ground line 102 of ground line, third ground line 103
It is connect with the 4th ground line 104 with same ground structure, i.e. the connection of the mounting structure plate 105 of satellite.It should be noted here that ground connection
Structure can also be other devices, the metal shell of such as single machine 107 or mounting plate, some installation part etc..In addition, should refer to
Out, the number of the signal loop line of satellite sensor 106 both can be corresponding with the number of ground line, can not also correspond to；Not
In corresponding situation, multiple signal loop lines can be passed through into multiple ground connection by same ground connection or same signal loop line
Line ground connection.In the present embodiment, since detector 106 has in total there are four electronic module, and there is each module output to believe
Number, therefore earthing or grounding means of the invention correspondingly has four grounded line.That is, in practice, it can be according to detector
The number of 106 electronic module determines the number of ground line.
The present invention at least have it is following the utility model has the advantages that
(1) common and preferably nearest ground connection can guarantee that the signal circuit of detector is as short as possible and (such as be grounded wire length
Degree is only about 20cm), therefore signal circuit length is effectively reduced compared to traditional grounding scheme, reduce single machine pair on star
The interference strength of faint output signal also reduces the interference to other equipment；
(2) due to the same length of multiple ground lines of multiple signal loop lines of detector output signal and their companies
It is connected to common ground, therefore the interference signal being mingled in multiple faint output signals in these signal loop lines is also close, divided
The interference signal in these faint output signals can be filtered out when analysing the faint output signal of detector together at low cost, simultaneously
It can guarantee the integrality of signal to the greatest extent；
(3) due to only having the signal loop line of detector to use scheme that is common and being preferably grounded nearby, and detector
Output signal is very faint, therefore the voltage difference very little formed at the different grounding points on ground, such as structural slab, can effectively keep away
The signal strength for exempting from loop as shown in Figure 1 avoids and introduces new interference source.
Although some embodiments of the present invention are described in present specification, to art technology
Personnel are it is readily apparent that these embodiments are merely possible to shown in example.It may occur to persons skilled in the art that numerous
Variant schemes, alternative solution and improvement project without beyond the scope of this invention.The appended claims are intended to limit this hair
Bright range, and cover the method and structure in the range of these claims itself and its equivalents whereby.
Claims (6)
1. a kind of earthing or grounding means for satellite sensor, includes
Multiple ground lines are used to connect with multiple signal loop lines of satellite sensor, wherein the length of the ground line is identical；
And
Ground structure is used for all ground connections.
2. the apparatus according to claim 1, wherein the ground structure is as close possible to satellite sensor itself.
3. the apparatus according to claim 1, wherein the length of the ground line is 10cm to 30cm.
4. the apparatus according to claim 1, wherein the multiple ground line includes four grounded line.
5. the apparatus according to claim 1, wherein the measuring signal transmitted in the signal loop line of the satellite sensor
The quantity of electric charge be skin coulomb magnitude or winged coulomb magnitude.
6. a kind of method for satellite sensor to be grounded, including the following steps:
The signal loop line of satellite sensor and multiple ground lines are connected, wherein the length of the ground line is identical；And
The ground line is connect with same satellite sensor at a distance of mounting structure plate as close as possible.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810729512.XA CN109037981B (en) | 2018-07-05 | 2018-07-05 | A kind of earthing or grounding means for satellite sensor |
| CN201910992332.5A CN110727001B (en) | 2018-07-05 | 2018-07-05 | Signal source grounding device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810729512.XA CN109037981B (en) | 2018-07-05 | 2018-07-05 | A kind of earthing or grounding means for satellite sensor |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910992332.5A Division CN110727001B (en) | 2018-07-05 | 2018-07-05 | Signal source grounding device |
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| Publication Number | Publication Date |
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| CN109037981A true CN109037981A (en) | 2018-12-18 |
| CN109037981B CN109037981B (en) | 2019-10-01 |
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| CN201910992332.5A Active CN110727001B (en) | 2018-07-05 | 2018-07-05 | Signal source grounding device |
| CN201810729512.XA Active CN109037981B (en) | 2018-07-05 | 2018-07-05 | A kind of earthing or grounding means for satellite sensor |
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| Application Number | Title | Priority Date | Filing Date |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110727001A (en) * | 2018-07-05 | 2020-01-24 | 上海微小卫星工程中心 | Signal source grounding device |
| CN111383795A (en) * | 2020-03-09 | 2020-07-07 | 西安联飞智能装备研究院有限责任公司 | Unmanned aerial vehicle shielding cable grounding point determining method and device, cable and unmanned aerial vehicle |
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| CN103253381A (en) * | 2013-05-17 | 2013-08-21 | 北京空间飞行器总体设计部 | Grounding design method of multi-cabin combined type spacecraft |
| CN105883011A (en) * | 2015-01-23 | 2016-08-24 | 北京空间飞行器总体设计部 | Platform interface system for parallel running double-platform spacecraft |
| US20170142824A1 (en) * | 2015-11-18 | 2017-05-18 | Raytheon Company | Eggcrate Radio Frequency Interposer |
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| US6855003B1 (en) * | 2003-10-14 | 2005-02-15 | Brunswick Corporation | Multiple use connector for a GPS system on a marine vessel |
| CN203377382U (en) * | 2013-07-25 | 2014-01-01 | 国家电网公司 | Connection structure of grounding wires and grounding lead wire |
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| CN104868228B (en) * | 2014-02-25 | 2018-05-11 | 华为技术有限公司 | Dual polarized antenna and aerial array |
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| CN110727001B (en) * | 2018-07-05 | 2022-01-07 | 上海微小卫星工程中心 | Signal source grounding device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103253381A (en) * | 2013-05-17 | 2013-08-21 | 北京空间飞行器总体设计部 | Grounding design method of multi-cabin combined type spacecraft |
| CN105883011A (en) * | 2015-01-23 | 2016-08-24 | 北京空间飞行器总体设计部 | Platform interface system for parallel running double-platform spacecraft |
| US20170142824A1 (en) * | 2015-11-18 | 2017-05-18 | Raytheon Company | Eggcrate Radio Frequency Interposer |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110727001A (en) * | 2018-07-05 | 2020-01-24 | 上海微小卫星工程中心 | Signal source grounding device |
| CN111383795A (en) * | 2020-03-09 | 2020-07-07 | 西安联飞智能装备研究院有限责任公司 | Unmanned aerial vehicle shielding cable grounding point determining method and device, cable and unmanned aerial vehicle |
| CN111383795B (en) * | 2020-03-09 | 2021-11-19 | 西安联飞智能装备研究院有限责任公司 | Unmanned aerial vehicle shielding cable grounding point determining method and device, cable and unmanned aerial vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110727001B (en) | 2022-01-07 |
| CN109037981B (en) | 2019-10-01 |
| CN110727001A (en) | 2020-01-24 |
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