CN103809473B - It is applied to the space high-voltage relay array of electric propulsion system - Google Patents
It is applied to the space high-voltage relay array of electric propulsion system Download PDFInfo
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- CN103809473B CN103809473B CN201310724790.3A CN201310724790A CN103809473B CN 103809473 B CN103809473 B CN 103809473B CN 201310724790 A CN201310724790 A CN 201310724790A CN 103809473 B CN103809473 B CN 103809473B
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Abstract
The present invention provides a kind of space high-voltage relay array being applied to electric propulsion system, to solve the safety problem of electric propulsion system power switching.A kind of space high-voltage relay array being applied to electric propulsion system, including: instruction input interface, isolated drive circuit, isolation telemetric circuit, remote measurement output interface, power input, high-voltage relay group, earth resistance network and the power output interface being positioned in array cabinet；Instruction input interface is connected with isolated drive circuit and isolation telemetric circuit respectively；Isolated drive circuit is connected with instruction input interface and high-voltage relay group respectively；High-voltage relay group is connected with isolated drive circuit, isolation telemetric circuit, power input and power output interface respectively；Isolation telemetric circuit is connected with instruction input interface, high-voltage relay group and remote measurement output interface respectively；Earth resistance network is connected with array cabinet.The present invention can improve the safety of electric propulsion system power switching.
Description
Technical field
The present invention relates to power switching technical field, particularly to a kind of electric propulsion system that is applied to
Space high-voltage relay array.
Background technology
For a long time, domestic ion-conductance propulsion system develop be absorbed in the unit such as thruster, power supply and
The research of single cover system integrated technology, does not carries out this system multiple stage in-orbit, the application technology of set deeply
Enter research.When long-life telecommunication satellite platform or this system of survey of deep space task application, multiple stage pushes away
Power device needs to carry out reliably power switching.
Such as complete at telecommunication satellite, in position, north and south guarantor's task of 10～15 years, separate unit power supply to be realized
The processing unit operation to two thruster power switchings, this switching need to be come by high-voltage relay array
Realize, the domestic technical research not yet carrying out this equipment, therefore for adapting to electric propulsion system in communication
Satellite and survey of deep space advance the demand of task, it is necessary to develop a kind of electric propulsion system for TURP
Change special high-voltage relay array apparatus.
Summary of the invention
Brief overview about the present invention given below, in order to provide about some of the present invention
The basic comprehension of aspect.Should be appreciated that this general introduction is not that the exhaustive about the present invention is summarized.
It is not intended to determine the key of the present invention or pith, is not the intended limitation present invention
Scope.Its purpose is only to provide some concept in simplified form, in this, as discuss after a while
Preamble in greater detail.
The present invention provides a kind of space high-voltage relay array being applied to electric propulsion system, to solve
The safety problem of electric propulsion system power switching.
The invention provides a kind of space high-voltage relay array being applied to electric propulsion system, bag
Include: the instruction input interface that is positioned in array cabinet, isolated drive circuit, isolation telemetric circuit,
Remote measurement output interface, power input, high-voltage relay group, earth resistance network and power are defeated
Outgoing interface；
Described instruction input interface respectively with described isolated drive circuit and described isolation telemetric circuit
It is connected, for powering for described isolated drive circuit and described isolation telemetric circuit, and will receive
The power switching instruction that sends of electric propulsion control unit send to described isolated drive circuit；
Described isolated drive circuit respectively with described instruction input interface and described high-voltage relay group
It is connected, for receiving the power switching instruction that described instruction input interface sends, and by described power supply
Switching command is converted to driving instruction and sends to described high-voltage relay group；
Described high-voltage relay group respectively with described isolated drive circuit, described isolation telemetric circuit,
Described power input is connected with described power output interface, for entering according to described driving instruction
Row power switching, and the relay status indication signal of reaction power switching result is sent to described
Isolation telemetric circuit；
Described isolation telemetric circuit respectively with described instruction input interface, described high-voltage relay group and
Described remote measurement output interface is connected, for receiving the described relay that described high-voltage relay group sends
Condition indicative signal, and it is single that described relay status indication signal feeds back to described electric propulsion control
Unit；
Described earth resistance network is connected with described array cabinet.
Compared with prior art, the present invention includes advantages below:
The space high-voltage relay array being applied to electric propulsion system that the present invention provides, selects high pressure
Relay group realizes in electric propulsion system separate unit power supply processing unit to cutting that two thrusters are powered
Change, owing to isolated drive circuit can be by the coil power supply power supply of switching command Yu high-voltage relay group
Keeping apart, isolation telemetric circuit can be by relay status indication signal and relay auxiliary contact
Keep apart, and the on off operating mode of thruster can be taken remote measurement, it is simple to electric propulsion system
Carry out fault diagnosis.Therefore the present invention possesses insulation blocking function, can be in a certain branch road electricity thrust
When device breaks down, isolated fault thruster, simultaneously protection power satellite bus.Therefore the present invention
The safety and reliability of electric propulsion system power switching can be improved, optimize whole star resource and join
Put.
Accompanying drawing explanation
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will
The accompanying drawing used required in embodiment or description of the prior art is briefly described, it is clear that
Ground, the accompanying drawing in describing below is only some embodiments of the present invention, skill common for this area
From the point of view of art personnel, on the premise of not paying creative work, it is also possible to obtain according to these accompanying drawings
Other accompanying drawing.
A kind of space high-voltage being applied to electric propulsion system that Fig. 1 provides for the embodiment of the present invention continues
The composition schematic diagram of electrical equipment array；
The high-voltage relay array that Fig. 2 provides for the embodiment of the present invention and electric propulsion power supply process single
The annexation figure of unit；
Two groups of contacts of relay that Fig. 3 provides for the embodiment of the present invention and power supply processing unit middle-jiao yang, function of the spleen and stomach
Pole power supply output plus terminal, the annexation figure of earth resistance network；
Insurance instruction that Fig. 4 provides for the embodiment of the present invention and the sequential chart of switching command.
Reference:
1-instructs input interface；2-isolated drive circuit；3-isolates telemetric circuit；4-remote measurement exports
Interface；5-power input；6-high-voltage relay group；7-earth resistance network；8-power is defeated
Outgoing interface；9-array cabinet.
Detailed description of the invention
For making the purpose of the embodiment of the present invention, technical scheme and advantage clearer, below in conjunction with
Accompanying drawing in the embodiment of the present invention, carries out clear, complete to the technical scheme in the embodiment of the present invention
Ground describes, it is clear that described embodiment is a part of embodiment of the present invention rather than whole
Embodiment.Element and feature described in the accompanying drawing of the present invention or a kind of embodiment are permissible
Combine with the element shown in one or more other accompanying drawing or embodiment and feature.Should
Note, for purposes of clarity, accompanying drawing and explanation eliminate unrelated to the invention, this area
Parts known to those of ordinary skill and the expression of process and description.Based on the enforcement in the present invention
Example, it is all that those of ordinary skill in the art are obtained on the premise of not paying creative work
Other embodiments, broadly fall into the scope of protection of the invention.
With reference to Fig. 1, it it is a kind of space height being applied to electric propulsion system that the embodiment of the present invention provides
The composition schematic diagram of potential relay array, is applied to the space of electric propulsion system described in the present embodiment
High-voltage relay array, specifically may include that be positioned in array cabinet 9 instruction input interface 1,
Isolated drive circuit 2, isolation telemetric circuit 3, remote measurement output interface 4, power input 5,
High-voltage relay group 6, earth resistance network 7 and power output interface 8.
Described instruction input interface 1 is electric with described isolated drive circuit 2 and described isolation remote measurement respectively
Road 3 is connected, for powering for described isolated drive circuit 2 and described isolation telemetric circuit 3, and
The power switching instruction electric propulsion control unit received sent sends to described isolation drive
Circuit 2.
It should be noted that electric propulsion system includes that electric propulsion control unit, electric propulsion power supply process
Unit and high-voltage relay array.High-voltage relay array by instruction input interface 1 receive from
The power switching instruction of electric propulsion control unit, for guaranteeing relay action message and Fault Isolation,
In one preferred embodiment of the invention, the instruction of described power switching can through optocoupler or magnetic coupling every
Being loaded into after from the coil of high-voltage relay group 6, light-coupled isolation pressure voltage is that direct current 3500V (surveys
Examination time 60S).
Described isolated drive circuit 2 respectively with described instruction input interface 1 and described high-voltage relay
Group 6 is connected, for receiving the power switching instruction that described instruction input interface 1 sends, and by institute
State power switching instruction and be converted to driving instruction transmission to described high-voltage relay group 6.
It should be noted that the instruction of described power switching includes: insurance instruction and switching command.Institute
State isolated drive circuit 2 for, according to described insurance instruction connect to described high-voltage relay group supply
Electricity power supply, drives described high-voltage relay group to switch over operation according to described switching command.Therefore
Isolated drive circuit 2 can be by the coil power supply isolated from power of switching command Yu high-voltage relay group 6
Come, improve safety when space high-voltage relay array is applied to electric propulsion system and reliable
Property.In one preferred embodiment of the invention, time a length of 100ms of described insurance instruction
-300ms, time a length of 120ms-280ms of described switching command, the duration of described insurance instruction
Duration more than described switching command.In one preferred embodiment of the invention, described insurance refers to
Time a length of 200ms, time a length of 120ms of described switching command of order.Excellent in the one of the present invention
Selecting in embodiment, described isolated drive circuit 2 can select optocoupler to isolate, optocoupler every
It is direct current 3500V from pressure voltage.In one preferred embodiment of the invention, described isolation drive
Circuit 2 connects the+28V power supply powered to high-voltage relay group.Isolated drive circuit 2 is all right
Magnetic coupling device is selected to isolate.
Described high-voltage relay group 6 respectively with described isolated drive circuit 2, described isolation remote measurement electricity
Road 3, described power input 5 are connected with described power output interface 8, for according to described
Driving instruction is powered switching, and by the relay status indication signal of reaction power switching result
It is sent to described isolation telemetric circuit 3.
Described isolation telemetric circuit 3 respectively with described instruction input interface 1, described high-voltage relay
Group 6 is connected with described remote measurement output interface 4, for receiving what described high-voltage relay group 6 sent
Relay status indication signal, and described relay status indication signal is fed back to described electric propulsion
Control unit.It should be noted that in one preferred embodiment of the invention, described isolation is distant
Slowdown monitoring circuit 3 can select optocoupler to isolate, at the another kind of preferred embodiment of the present invention
In, light-coupled isolation pressure voltage is direct current 3500V, and isolation telemetric circuit 3 can also select magnetic coupling device
Part is isolated.And described relay status indication signal continuing by described high-voltage relay group 6
Electrical equipment auxiliary contact are transmitted, and isolation telemetric circuit 3 can be by described relay status instruction letter
Number isolate with relay auxiliary contact, improve space high-voltage relay array and be applied to electricity and push away
Enter safety and reliability during system.It should be noted that arrange in high-voltage relay array
Isolation telemetric circuit 3, can take remote measurement to the on off operating mode of thruster, it is simple to electric propulsion system
System carries out fault diagnosis.
Described earth resistance network 7 is connected with described array cabinet 9.Preferred in the one of the present invention
In embodiment, described earth resistance network 7 can select the resistance of 100K Ω.
The space high-voltage relay array being applied to electric propulsion system that the present invention provides, selects high pressure
Relay group 6 realizes what two thrusters were powered by separate unit power supply processing unit in electric propulsion system
Switching, owing to isolated drive circuit 2 can be by the coil power supply of switching command Yu high-voltage relay group
Isolated from power comes, and isolation telemetric circuit 3 can be auxiliary with relay by relay status indication signal
Help contact to keep apart, and the on off operating mode of thruster can be taken remote measurement, it is simple to electricity is pushed away
Enter system and carry out fault diagnosis.Therefore the present invention possesses insulation blocking function, can be at a certain branch road
When electric thruster breaks down, isolated fault thruster, simultaneously protection power satellite bus.Therefore
The present invention can improve the safety and reliability of electric propulsion system power switching, optimizes whole star money
Source configures.
It should be noted that multiple stage thruster can be controlled by a high-voltage relay array,
The present embodiment illustrates as a example by two thrusters of high-voltage relay antenna array control, high-voltage relay
Group 6 connection has the first working thrust device and the second working thrust device.Described high-voltage relay group 6 is wrapped
Including multiple magnetic latching relay, described high-voltage relay group includes: common, A group contact,
B group contact and auxiliary contact.One end of described common is by described power input and electricity
Power supply processing unit is advanced to be connected；Described A group contact is connected with the electrode of the first working thrust device；
Described B group contact is connected with the electrode of the second working thrust device；Auxiliary contact are by the electricity of auxiliary contact
Level state is sent to described isolation telemetric circuit as power switching result.Described power switching instructs
Instruction is switched to the first working thrust device or the second working thrust device；When described power switching refers to
Show when being switched to the first working thrust device, the other end of described common and described A group contact
It is connected；Auxiliary contact are by the level of the auxiliary contact of place, described A group contact magnetic latching relay
State is sent to described isolation telemetric circuit as power switching result.Preferred in the one of the present invention
In embodiment, when the instruction instruction of described power switching is switched to the first working thrust device, described B
Group contact is connected with the shell of array cabinet 9 by described earth resistance network 7.
Above-mentioned common, A group contact, B group contact and auxiliary contact can be understood in conjunction with Fig. 2.
With reference to Fig. 2, the high-voltage relay array provided for the embodiment of the present invention and electric propulsion power supply process single
The annexation figure of unit.Wherein, power supply processing unit 10 includes 9 road power supplys, and power supply processes single
The power supply output of unit 10 is connected with relay array 20, concrete and relay array mesohigh relay
8 common of device group are connected, i.e. anode supply in figure repeat circuit array, negative electrode heating
Power supply, negative electrode touch hold power supply, negative electrode priming supply, screen loop line, accelerating power source, in add thermoelectricity
Source and in touch hold power supply.High-voltage relay group includes that No. 8 relays, every road relay can enter
Row North-South Road switches.Power switching instruction can indicate to switch to which electric propulsion device, and such as instruction is cut
Shifting to the first electric propulsion device, the contact being now connected with the first electric propulsion is exactly A group contact, does not has
The contact chosen is B group contact, the most non-powered branch road.Non-powered branch road connects high resistant with picking shell,
I.e. B group contact is connected with the shell of array cabinet 9 by described earth resistance network 7.The present invention
The space high-voltage relay array being applied to electric propulsion system provided, can receive electric propulsion control
The power switching instruction of unit, realizes touching of corresponding magnetic latching relay according to power switching instruction
Point switching, makes the feeder ear (relay common) of electric propulsion power supply processing unit switch to choosing
The electrode (relay A group contact) of middle thruster, electrode (the relay B of unselected thruster
Group contact) connect high resistant and be connected with the shell of array cabinet, relay auxiliary contact will be switched simultaneously
Level state feed back to electric propulsion control unit, in order to system operators identification respectively switches relay
The contacting state of device.
In one preferred embodiment of the invention, the common of above-mentioned high-voltage relay group, A
Silicone rubber is used to carry out at vacuum encapsulation at the wire that group contact, B group contact and auxiliary contact are drawn
Reason.
With reference to Fig. 3, the two groups of contacts of relay provided for the embodiment of the present invention and power supply processing unit
Anodic power supply output plus terminal, the annexation figure of earth resistance network.Two groups of contact (A of relay
Group contact and B group contact) in A1 with B2 in parallel, A2 with B1 is in parallel, when power branch road cut
Change to North Road thruster anode+time (anode supply+be connected with C1), the anode of South Road thruster+
It is connected with C2, is i.e. connected through high resistant with array casing.
Reference Fig. 4, the insurance instruction provided for the embodiment of the present invention and the sequential chart of switching command,
Owing to when thruster works, there is high pressure, high-power signal between relay contact, for keeping away
Exempt from maloperation and the short circuit of+28V auxiliary power supply bus that driving malfunction causes, it is ensured that relay
Safe and reliable switching, in addition to carrying out anti-misoperation design in electric propulsion control unit side,
Relay array side also answers anti-misoperation to design, and the mode that the present embodiment uses is to each road
When relay carries out North-South Road switching, it is simultaneously emitted by two operational orders, and insurance instruction
(Arming) and switching command, and to the pulse widths of two instructions constraint is made.Carry out
During handover operation, electric propulsion control unit first sends insurance instruction and connects 28V power supply buses, with
I.e. sending switching command pulse, make relay line bag 28V driving voltage connect, handover operation is complete
Cheng Hou, 28V bussed supply is released, it is to avoid as affected when short trouble occurs in relay side
The normal work of other equipment on 28V bus.Instruction sequencing is as shown in Figure 4.In the present invention one
Planting in preferred embodiment, electric propulsion control unit first sends one when relay switches over operation
The insurance instruction of bar 200mS duration connects the+28V power supply powered to relay line bag, when this
Between be simultaneously emitted by the driving instruction of a treaty 120ms in window to drive magnetic latching relay, this
Sample, after handover operation completes ,+28V power supply buses is timely released.
The space high-voltage relay array being applied to electric propulsion system that the embodiment of the present invention provides, adopts
By the discrete layout designs of high and low pressure circuit.Instruction input interface 1, isolated drive circuit 2, every
It is low pressure low-power circuit from telemetric circuit 3, remote measurement output interface 4, power input 5,
High-voltage relay group 6, power output interface 8 are high-power power supply circuits, and discrete layout sets
Meter refers to, by the two discrete layouts of class circuit, independent cabling, spatially guarantee that two class signal distances exist
More than 300mm, low pressure low-power circuit is on independent printed circuit board, and high-power supplies
The signal of telecommunication is the most defeated with power input 5 and power through individually lead-in wire by high-voltage relay group 6
Outgoing interface 8 connects.The most described instruction input interface 1, isolated drive circuit 2, isolation remote measurement electricity
Road 3 and remote measurement output interface 4 are arranged on printed circuit board；Described instruction input interface 1 passes through
On described printed circuit board cover copper conductor respectively with described isolated drive circuit 2 and described isolation
Telemetric circuit 3 is connected, and described isolated drive circuit 2 is led by the copper that covers on described printed circuit board
Line is connected with described instruction input interface 1, and described isolation telemetric circuit 3 is by described printed circuit
On plate cover copper conductor respectively with described instruction input interface 1 and described remote measurement output interface 4 phase
Even；Described high-voltage relay group 6 by lead-in wire respectively with described isolated drive circuit 2, described every
It is connected with described power output interface 8 from telemetric circuit 3, described power input 5.
Because high-voltage relay array has High voltage output characteristic, and array cabinet 9 sets for non-tight
Meter, so in order to array cabinet inside has good Gas Escaping Property under vacuum conditions, it is to avoid high pressure
The generation of electric discharge, in one preferred embodiment of the invention, the biside plate top of array cabinet 9,
It is provided with the steam vent of gas in discharging described array cabinet, preferred at the another kind of the present invention
In embodiment, the diameter of described steam vent can be 2mm.Can be in the both sides of array cabinet 9
Plate top, makes a call to the steam vent of 200 a diameter of 2mm altogether.Experiment proves that, described steam vent
In thermal vacuum test, can effectively reach to discharge the purpose of gas in array cabinet, it is ensured that array computer
The pressure identical with environment is reached at short notice, it is to avoid put under hypobaric inside case
Electricity, the most described steam vent does not affect the mechanical performance of array cabinet.
In one preferred embodiment of the invention, described lead-in wire installs insulated sleeve additional.To array computer
Device pin exposed in case and lead-in wire carry out insulating protection process, install insulated sleeve additional, can in case
Only high voltage circuit generation corona and arcing problem.
In one preferred embodiment of the invention, described high-voltage relay group 6 uses silicon casting glue
Carry out vacuum encapsulation, deployed silicon casting glue is specifically filled high-voltage relay by the present embodiment
Group, carries out vacuum degassing, afterwards after putting into vacuum tank and standing under the pressure of 300Pa-100Pa
2h-3h is solidified in 60 DEG C of-70 DEG C of baking ovens.Through above-mentioned process, the voltage endurance capability of Embedding Material
10kV/1mm can be reached.
In the various embodiments described above of the present invention, sequence number and/or the sequencing of embodiment are merely convenient of
Describe, do not represent the quality of embodiment.Description to each embodiment all emphasizes particularly on different fields, and certain is real
Execute the part not having to describe in detail in example, may refer to the associated description of other embodiments.
One of ordinary skill in the art will appreciate that: realize all or part of of said method embodiment
Step can be completed by the hardware that programmed instruction is relevant, and aforesaid program can be stored in a meter
In calculation machine read/write memory medium, this program upon execution, performs to include said method embodiment
Step；And aforesaid storage medium includes: read only memory (Read-Only Memory, letter
Claim ROM), random access memory (Random Access Memory, be called for short RAM),
The various medium that can store program code such as magnetic disc or CD.
In the embodiments such as apparatus and method of the present invention, it is clear that each parts or each step are permissible
Decompose, combine and/or decompose after reconfigure.These decompose and/or reconfigure and should be regarded as this
The equivalents of invention.Meanwhile, in description to the specific embodiment of the invention above, for one
Kind of embodiment describes and/or the feature that illustrates can in same or similar mode at one or more
Other embodiments multiple use, combined with the feature in other embodiment, or substitute it
Feature in its embodiment.
It should be emphasized that term " includes/comprises " referring to when using feature, key element, step herein
Or the existence of assembly, but it is not precluded from one or more further feature, key element, step or assembly
Existence or additional.
Although last it is noted that the present invention and advantage thereof have been described in detail above, but
It is to be understood that without departing from the spirit and scope of the present invention being defined by the claims appended hereto
In the case of can carry out various change, substitute and convert.And, the scope of the present invention is not limited only to
Process described by description, equipment, means, the specific embodiment of method and steps.This area
Interior those of ordinary skill will readily appreciate that from the disclosure, can make according to the present invention
With performing the function essentially identical to corresponding embodiment described herein or obtaining phase basic with it
Same result, existing and the most to be developed process, equipment, means, method or step.
Therefore, appended claim is directed in the range of them including such process, equipment, hands
Section, method or step.
Claims (10)
1. the space high-voltage relay array being applied to electric propulsion system, it is characterised in that bag
Include: the instruction input interface that is positioned in array cabinet, isolated drive circuit, isolation telemetric circuit, distant
Survey output interface, power input, high-voltage relay group, earth resistance network and power output to connect
Mouthful；
Described instruction input interface respectively with described isolated drive circuit and described isolation telemetric circuit phase
Even, for powering for described isolated drive circuit and described isolation telemetric circuit, and the electricity that will receive
The power switching instruction that Solid rocket engine unit sends sends to described isolated drive circuit；
Described isolated drive circuit respectively with described instruction input interface and described high-voltage relay group phase
Even, for receiving the power switching instruction that described instruction input interface sends, and by described power switching
Instruction is converted to driving instruction and sends to described high-voltage relay group；
Described high-voltage relay group respectively with described isolated drive circuit, described isolation telemetric circuit, institute
State power input to be connected with described power output interface, for supplying according to described driving instruction
TURP changes, and it is distant that the relay status indication signal of reaction power switching result is sent to described isolation
Slowdown monitoring circuit；
Described isolation telemetric circuit respectively with described instruction input interface, described high-voltage relay group and institute
State remote measurement output interface to be connected, for receiving the described relay status that described high-voltage relay group sends
Indication signal, and described relay status indication signal is fed back to described electric propulsion control unit；
Described earth resistance network is connected with described array cabinet.
The space high-voltage relay array being applied to electric propulsion system the most according to claim 1,
It is characterized in that:
Described high-voltage relay group connects the first working thrust device and the second working thrust device；
Described high-voltage relay group includes that multiple magnetic latching relay, described high-voltage relay group include:
Common, A group contact, B group contact and auxiliary contact；
One end of described common is by described power input and electric propulsion power supply processing unit
It is connected；Described A group contact is connected with the electrode of the first working thrust device；Described B group contact and the
The electrode of two working thrust devices is connected；Auxiliary contact using the level state of auxiliary contact as power switching
Result is sent to described isolation telemetric circuit；
The instruction instruction of described power switching is switched to the first working thrust device or the second working thrust device；When
When the instruction instruction of described power switching is switched to the first working thrust device, the other end of described common
It is connected with described A group contact；Auxiliary contact are auxiliary by place, described A group contact magnetic latching relay
The level state helping contact is sent to described isolation telemetric circuit as power switching result.
The space high-voltage relay array being applied to electric propulsion system the most according to claim 2,
It is characterized in that:
When the instruction instruction of described power switching is switched to the first working thrust device, described B group contact
It is connected with the shell of array cabinet by described earth resistance network.
The space high-voltage relay array being applied to electric propulsion system the most according to claim 1,
It is characterized in that:
The instruction of described power switching includes: insurance instruction and switching command；
Described isolated drive circuit is used for, and connects to described high-voltage relay group according to described insurance instruction
The power supply of power supply, drives described high-voltage relay group to switch over operation according to described switching command.
The space high-voltage relay array being applied to electric propulsion system the most according to claim 4,
It is characterized in that:
Time a length of 100ms-300ms of described insurance instruction, described switching command time a length of 120
Ms-280ms, the duration of described insurance instruction is more than the duration of described switching command.
The space high-voltage relay array being applied to electric propulsion system the most according to claim 1,
It is characterized in that:
Described isolated drive circuit and isolation telemetric circuit select optocoupler to isolate.
The space high-voltage relay array being applied to electric propulsion system the most according to claim 1,
It is characterized in that:
The biside plate top of array cabinet, is provided with the aerofluxus of gas in discharging described array cabinet
Hole.
The space high-voltage relay array being applied to electric propulsion system the most according to claim 1,
It is characterized in that:
Described instruction input interface, isolated drive circuit, isolation telemetric circuit and remote measurement output interface set
It is placed on printed circuit board；Described instruction input interface is by covering copper conductor on described printed circuit board
Being connected with described isolated drive circuit and described isolation telemetric circuit respectively, described isolated drive circuit leads to
The copper conductor that covers crossed on described printed circuit board is connected with described instruction input interface, described isolation remote measurement
Circuit by described printed circuit board cover copper conductor respectively with described instruction input interface and described
Remote measurement output interface is connected；
Described high-voltage relay group by lead-in wire respectively with described isolated drive circuit, described isolation remote measurement
Circuit, described power input are connected with described power output interface.
The space high-voltage relay array being applied to electric propulsion system the most according to claim 8,
It is characterized in that:
Described lead-in wire installs insulated sleeve additional.
The space high-voltage relay battle array being applied to electric propulsion system the most according to claim 2
Row, it is characterised in that:
What the common of high-voltage relay group, A group contact, B group contact and auxiliary contact were drawn leads
Silicone rubber is used to carry out vacuum encapsulation process at line.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310724790.3A CN103809473B (en) | 2013-12-24 | 2013-12-24 | It is applied to the space high-voltage relay array of electric propulsion system |
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| CN201310724790.3A CN103809473B (en) | 2013-12-24 | 2013-12-24 | It is applied to the space high-voltage relay array of electric propulsion system |
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| CN103809473B true CN103809473B (en) | 2016-08-17 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104330661B (en) * | 2014-10-23 | 2017-02-01 | 兰州空间技术物理研究所 | Device and method for simulating load characteristics of kaufmann ion thruster |
| CN105114275B (en) * | 2015-07-14 | 2017-11-03 | 兰州空间技术物理研究所 | A kind of ion thruster power supply-distribution system |
| JP2020150787A (en) * | 2019-02-28 | 2020-09-17 | ソーラーエッジ テクノロジーズ リミテッド | Relay array for grid connection |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101539483A (en) * | 2009-04-29 | 2009-09-23 | 北京航空航天大学 | Electric propulsion testing platform measurement control device |
| CN201359690Y (en) * | 2008-12-31 | 2009-12-09 | 浙江通普特种车有限公司 | General-purpose multiplex relay control system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6304040B1 (en) * | 1999-07-12 | 2001-10-16 | Hughes Electronics Corporation | Starter circuit for an ion engine |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201359690Y (en) * | 2008-12-31 | 2009-12-09 | 浙江通普特种车有限公司 | General-purpose multiplex relay control system |
| CN101539483A (en) * | 2009-04-29 | 2009-09-23 | 北京航空航天大学 | Electric propulsion testing platform measurement control device |
Non-Patent Citations (2)
| Title |
|---|
| 深空探测使命中电推进应用综述;张天平 等;《中国宇航学会深空探测技术专业委员会第九届学术年会论文集(中册)》;20121017;1-10 * |
| 离子电推进在小行星探测器上的应用研究;杨福全 等;《中国宇航学会深空探测技术专业委员会第九届学术年会论文集(中册)》;20121017;856-862 * |
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| Publication number | Publication date |
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| CN103809473A (en) | 2014-05-21 |
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