CN108288874A - The grid-connected power supply region method of more spacecrafts of different voltages system - Google Patents
The grid-connected power supply region method of more spacecrafts of different voltages system Download PDFInfo
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- CN108288874A CN108288874A CN201810147367.4A CN201810147367A CN108288874A CN 108288874 A CN108288874 A CN 108288874A CN 201810147367 A CN201810147367 A CN 201810147367A CN 108288874 A CN108288874 A CN 108288874A
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- 238000000034 method Methods 0.000 title claims abstract description 29
- 238000013461 design Methods 0.000 claims abstract description 44
- 230000004224 protection Effects 0.000 claims description 15
- 229910052793 cadmium Inorganic materials 0.000 claims description 13
- 239000000725 suspension Substances 0.000 claims description 12
- OJIJEKBXJYRIBZ-UHFFFAOYSA-N cadmium nickel Chemical compound [Ni].[Cd] OJIJEKBXJYRIBZ-UHFFFAOYSA-N 0.000 claims description 10
- 230000003068 static effect Effects 0.000 claims description 5
- 238000010586 diagram Methods 0.000 claims description 4
- 238000003032 molecular docking Methods 0.000 claims description 4
- 230000008569 process Effects 0.000 claims description 4
- 238000006243 chemical reaction Methods 0.000 claims description 3
- 238000012790 confirmation Methods 0.000 claims description 3
- 238000007667 floating Methods 0.000 claims description 3
- 230000007246 mechanism Effects 0.000 claims description 3
- 238000012544 monitoring process Methods 0.000 claims description 3
- 238000010248 power generation Methods 0.000 claims description 3
- 230000000087 stabilizing effect Effects 0.000 claims description 3
- 238000007599 discharging Methods 0.000 claims description 2
- 238000002955 isolation Methods 0.000 claims description 2
- 230000005611 electricity Effects 0.000 description 6
- 230000007774 longterm Effects 0.000 description 4
- 230000009466 transformation Effects 0.000 description 3
- 239000002775 capsule Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000006855 networking Effects 0.000 description 2
- 230000000284 resting effect Effects 0.000 description 2
- 238000000844 transformation Methods 0.000 description 2
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 description 1
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000005856 abnormality Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000000686 essence Substances 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
- H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
-
- H02J3/383—
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M1/00—Details of apparatus for conversion
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
- Y02E10/56—Power conversion systems, e.g. maximum power point trackers
Abstract
The present invention relates to a kind of grid-connected power supply region methods of more spacecrafts of different voltages system, which is characterized in that including：The demand of the grid-connected power supply of assembly of analysis visiting spacecraft and passive space vehicle；Design the topological structure of the grid-connected power supply of the assembly；Design the scheme that grid-connected electric controller realizes power supply；Design the safety of the grid-connected power supply of the assembly；Analyze the grid-connected output power of the assembly；Design the assembly powered operation pattern.The grid-connected power supply region method of more spacecrafts of different voltages system according to the present invention may be implemented to be that the more spacecraft power supplies in space station are grid-connected for a long time.
Description
Technical field
The present invention relates to the grid-connected confessions of more spacecrafts of spacecraft energy resource system field more particularly to a kind of different voltages system
Electric system design method.
Background technology
According to the requirement of task development, after visiting spacecraft is docked with passive space vehicle, the assembly of composition is navigated by target
Its device is controlled, and visiting spacecraft is in resting state.During stop, spacecraft of coming to visit is realized with passive space vehicle for Electricity Federation
Net.
Currently, the grid-connected method of supplying power to of existing voltage system is not suitable for spacecraft, it can not realize that space station is more
The long-term in-orbit power supply of spacecraft.Therefore, in-orbit power supply long-term to the more spacecrafts in space station is urgently to be resolved hurrily in the world at present
Problem.
Invention content
It is an object of the invention to solve the above problems, it can be that the more spacecraft power supplies in space station are grid-connected for a long time to provide one kind
Different voltages system the grid-connected power supply region method of more spacecrafts.
To achieve the above object, the present invention provides a kind of grid-connected power supply region side of more spacecrafts of different voltages system
Method, including：
The demand of the grid-connected power supply of assembly of analysis visiting spacecraft and passive space vehicle；
Design the topological structure of the grid-connected power supply of the assembly；
Design the scheme that grid-connected electric controller realizes power supply；
Design the safety of the grid-connected power supply of the assembly；
Analyze the grid-connected output power of the assembly；
Design the assembly powered operation pattern.
According to an aspect of the present invention, the passive space vehicle provides the electricity of 500W or more to the visiting spacecraft
Energy.
According to an aspect of the present invention, the demand of the grid-connected power supply of the assembly includes：
The passive space vehicle uses 100V High Voltage Power Supply systems, and the visiting spacecraft is using 28V power supply systems；
The voltage conversion that a net-connected controller carries out 100V to 28V is arranged in the passive space vehicle；
Power supply process is equipped with the distance that control switchs and keeps the visiting spacecraft and the passive space vehicle；
The both ends of the passive space vehicle and the visiting spacecraft are respectively provided with power control switch.
According to an aspect of the present invention, the topological structure of the grid-connected power supply of the assembly includes：
The energy of the visiting spacecraft power supply system includes solar array, net-connected controller and cadmium-nickel accumulator；
The output voltage section of the solar array, the net-connected controller and the cadmium-nickel accumulator+electric discharge adjuster
Realize power supply.
According to an aspect of the present invention, the solar array, the net-connected controller and the cadmium-nickel accumulator are in institute
It states in a charging-discharging cycle of assembly, the course of work is the following four stage：
A. when the assembly is in shadow region, by the net-connected controller and the visiting spacecraft ickel-cadmium cell+
Electric discharge adjuster is completed to power jointly, and the net-connected controller provides 500W power outputs, the ickel-cadmium cell+electric discharge adjuster
300W power outputs are provided；
B. when the assembly enter the areas Yang Zhao solar incident angle it is larger when, the solar array output power is less than
300W is powered jointly by the solar array, the net-connected controller and the ickel-cadmium cell+electric discharge adjuster, the sun
Windsurfing output power progressively increases to 300W from 0W, and the net-connected controller keeps the output of 500W rated power, the cadmium nickel electricity
Pond+electric discharge adjuster output power constantly reduces, and 0 is reduced to always from 300W；
C. common by the solar array and the net-connected controller when the solar array output power is more than 300W
It completes to load supplying is stopped, the solar array output power is gradually increased from 300W, the net-connected controller output power
It is gradually reduced from 500W；
D. when the assembly is in the areas Yang Zhao, when the solar array output power be more than 800W when, by it is described too
Positive windsurfing provides required power to load is stopped, and is in SHUNT state；Or at this time by the solar array and described and network control
Device processed provides power needed for stop load jointly, should ensure that the solar array provides the output of minimum 400W bearing powers at this time.
According to an aspect of the present invention, the grid-connected electric controller realizes that the scheme of power supply includes：
The net-connected controller uses voltage source, is exported for voltage stabilizing when load is not up to full load, is when reaching full load
Constant current output；
In the net-connected controller output end and the visiting spacecraft energy source output terminal, isolating diode is set；
100V is converted the DC/DC converter module parallel connections of 28V using 3 by the passive space vehicle, wherein 1 module is made
It is used for cold standby；
An isolating diode is arranged in each DC/DC converter modules, and energy module voltage sample point is placed on isolation
Before diode；
Net-connected controller output voltage≤the 30V.
According to an aspect of the present invention, the safety of the grid-connected power supply of the assembly includes：
The net-connected controller has 2 grades of output over-voltage protections, and converter can be operated in output over-voltage protection by the 1st grade
Maximum output voltage when state controls within 32V, the overvoltage that the 2nd grade of output over-voltage protection is output voltage when being more than 40V
Protection；
The input terminal of the grid-connected power supply output end of the passive space vehicle and the orbital module distributor of the visiting spacecraft
It is respectively provided with control switch, when grid-connected power supply, by monitoring objective spacecraft electric network state and the visiting spacecraft electric network state,
Open and close by controlling switch realizes grid-connected power supply and suspension.
According to an aspect of the present invention, the grid-connected output power of the assembly includes：
According to the power supply system block diagram of the visiting spacecraft, the resistance of the length, thickness of service cable for service cable
Value is calculated, and the static models of the power supply system of the visiting spacecraft are built；
Pass through the passive space vehicle crossing cabin from the net-connected controller to the orbital module distributor of the visiting spacecraft
The floating disconnection device of electric connector, the orbital module crossing cabin electric connector of the visiting spacecraft, docking mechanism；
The visiting spacecraft energy resource system is 28.5V in shadow region output ceiling voltage；
Passive space vehicle net-connected controller output power ability described in shadow region is not less than 500W；
The output power of visiting spacecraft solar array described in the areas Yang Zhao is not less than 400W.
According to an aspect of the present invention, the assembly powered operation pattern includes grid-connected normal workflow and suspension
Normal workflow；
The grid-connected normal workflow includes：
(1) the net-connected controller input 100V of the passive space vehicle is connected；
(2) the net-connected controller output loop line is connected with main track；
(3) the visiting spacecraft confirms orbital module grid-connected voltage parameter；
(4) the grid-connected switch of the visiting spacecraft orbit cabin distributor is connected, body power supply link connection is realize combination；
(5) confirm the visiting spacecraft power supply system stability；
(6) the visiting spacecraft windsurfing zero；
The suspension normal workflow includes：
(1) windsurfing of the visiting spacecraft starts to control；
(2) state confirmation is carried out, the solar array opens control normally, and power generation is normal；
(3) the grid-connected switch of orbital module distributor of the visiting spacecraft is disconnected；
(4) the net-connected controller output main track and loop line are disconnected；
(5) the net-connected controller input 100V of the passive space vehicle is disconnected.
A scheme according to the present invention, for Electricity Federation when may be implemented to constitute assembly after multiple Spacecraft Rendezvous are docked
Net, it is ensured that the energy balance of assembly aircraft.
The long-term in-orbit grid-connected power supply of the more spacecrafts in space station may be implemented in a scheme according to the present invention.
A scheme according to the present invention so that the structure letter of the grid-connected power supply system of more spacecrafts of different voltages system
It is single, it is easy to implement, and have enough safeties and operation stability.
Description of the drawings
It in order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the present invention
Example, for those of ordinary skill in the art, without creative efforts, can also obtain according to these attached drawings
Obtain other attached drawings.
Fig. 1 schematically shows the grid-connected power supply region method of more spacecrafts of different voltages system according to the present invention
Flow chart；
Fig. 2 schematically shows a kind of grid-connected output power distribution of the power supply system energy of embodiment according to the present invention
Figure；
Fig. 3 schematically shows a kind of grid-connected power supply composed structure arrangement of more spacecrafts of embodiment according to the present invention
Figure；
Fig. 4 schematically shows the structure chart that a kind of each connector of embodiment according to the present invention passes through cable connection；
Fig. 5 schematically shows that above-mentioned design method according to the present invention realizes the grid-connected flow chart with suspension of power supply.
Specific implementation mode
The description of this specification embodiment should be combined with corresponding attached drawing, and attached drawing should be used as the one of complete specification
Part.In the accompanying drawings, the shape of embodiment or thickness can expand, and to simplify or facilitate mark.Furthermore it is respectively tied in attached drawing
The part of structure will be to describe to illustrate respectively, it is notable that attached to be not shown in figure or do not illustrated by word
Element is the form known to a person of ordinary skill in the art in technical field.
The description of embodiments herein, any reference in relation to direction and orientation are merely for convenience of describing, and cannot manage
Solution is any restrictions to the scope of the present invention.It can be related to the combination of feature below for the explanation of preferred embodiment,
These features may be individually present or combine presence, and the present invention is not defined in preferred embodiment particularly.The present invention
Range be defined by the claims.
Fig. 1 schematically shows the grid-connected power supply region method of more spacecrafts of different voltages system according to the present invention
Flow chart.As shown in Figure 1, the grid-connected power supply region method of more spacecrafts of different voltages system according to the present invention includes：
The demand of the grid-connected power supply of assembly of analysis visiting spacecraft and passive space vehicle；
Design the topological structure of the grid-connected power supply of the assembly；
Design the scheme that grid-connected electric controller realizes power supply；
Design the safety of the grid-connected power supply of the assembly；
Analyze the grid-connected output power of the assembly；
Design the assembly powered operation pattern.
A kind of embodiment according to the present invention, after visiting spacecraft docks composition assembly with passive space vehicle, combination
Body is controlled by passive space vehicle.Assembly after docking, visiting spacecraft are in resting state, assembly during flight,
Visiting spacecraft realizes that power supply networking, passive space vehicle provide the electricity not less than 500W to visiting spacecraft with passive space vehicle
Can, passive space vehicle has grid-connected power supply output function, and visiting spacecraft has solar panel, ickel-cadmium cell and passive space vehicle and supplies
Electric three kinds of grid-connected functions of the energy.
A kind of embodiment according to the present invention, to realize that grid-connected system designs, the demand of the grid-connected power supply of assembly includes：
Passive space vehicle uses 100V high voltage supply systems, and spacecraft of coming to visit is using 28V power supply systems.Passive space vehicle exists
When being conveyed to the grid-connected power supply of visiting spacecraft, the voltage conversion for carrying out 100V to 28V is needed.Passive space vehicle setting one is grid-connected
Controller realizes this function.
Consider that Supply Security, power supply process need switch control and design quarantine measures, ensure passive space vehicle
100V voltages will not go here and there onto the primary energy busbar of visiting spacecraft, while prevent visiting spacecraft reversely to passive space vehicle
Power supply.Avoid or reduce the possibility of the two unstable generations of spacecraft busbar voltage.
Considering power supply reliability, it is desirable that passive space vehicle and visiting spacecraft both ends are respectively provided with power switch control measure,
With the measure for stopping the grid-connected power supply of assembly in the case of grid-connected abnormal electrical power supply, ensure that the failure of a spacecraft does not interfere with separately
An outer spacecraft.
A kind of embodiment according to the present invention, by the grid-connected power demands analysis result of assembly, to realize combination
The grid-connected function of supplying power of body, passive space vehicle should configure net-connected controller, and the dispatching for undertaking 100V/28V voltage transformations and the energy is appointed
Business.Visiting spacecraft be responsible for powering it is grid-connected after internal power source control and management, configuration cutting-in control switch.So visiting boat
The power supply system of its device includes that three kinds of energy are powered, respectively solar array power supply battle array, Cd Ni battery and passive space vehicle
Net-connected controller.In the present embodiment, the priority of the visiting spacecraft power supply system energy is solar array ＞ target space flight
The net-connected controller ＞ Cadmium Nickel Batteries of device.Arrangement above is the realization grid-connected system according to one embodiment of the present invention
The topological structure of the grid-connected power supply of the assembly of design.
In the present embodiment, the charge and discharge week of solar array, net-connected controller and cadmium-nickel accumulator in assembly
In phase, the course of work is the following four stage：
A. it when assembly is in shadow region, is total to by net-connected controller and visiting spacecraft ickel-cadmium cell+electric discharge adjuster
With power supply is completed, net-connected controller provides 500W power outputs, and ickel-cadmium cell+electric discharge adjuster provides 300W power outputs；
B. when assembly enter the areas Yang Zhao solar incident angle it is larger when, solar array output power be less than 300W, by the sun
Windsurfing, net-connected controller and ickel-cadmium cell+electric discharge adjuster are powered jointly, and solar array output power is progressively increased to from 0W
300W, net-connected controller keep the output of 500W rated power, ickel-cadmium cell+electric discharge adjuster output power constantly to reduce, from
300W is reduced to always 0；
C. it when solar array output power is more than 300W, is completed jointly from solar array and net-connected controller negative to stopping
Power supply is carried, solar array output power is gradually increased from 300W, and net-connected controller output power is gradually reduced from 500W；
D. when assembly is in the areas Yang Zhao, when solar array output power is more than 800W, from solar array to stop
Load provides required power, and is in SHUNT state；Or provide stop load jointly by solar array and net-connected controller at this time
Required power should ensure that solar array provides the output of minimum 400W bearing powers at this time.
By determining solar array, net-connected controller and Cadmium Nickel Battery+electric discharge regulator output voltage section, realize
Above-mentioned power supply priority.The setting of the voltage of net-connected controller is related to the output power in shadow region and the areas Yang Zhao, and voltage is higher
More be conducive to shadow region output power but simultaneously the areas Yang Zhao output power also increase bring solar array output power reduce.
Fig. 2 schematically shows the grid-connected output power distribution diagram of the power supply system energy according to the present invention.As shown in Figure 2, and
In net power supply process, the output power of solar energy sailboard is significantly greater than the output power of net-connected controller, the confession of Cd Ni battery
Electrical power is minimum.
A kind of embodiment according to the present invention, to realize that power supply is realized in grid-connected system design, grid-connected electric controller
Scheme include：
Net-connected controller uses voltage source, is exported for voltage stabilizing when load is not up to full load, is constant current when reaching full load
Output.
In the present embodiment, the characteristic of net-connected controller should meet the following conditions：
A. since passive space vehicle uses 100V high voltage supply systems, therefore, it is necessary to be visiting boat by 100V voltage transformations
Its device 28V busbar voltages, while meeting spacecraft busbar quality requirements of coming to visit.
When b. in order to ensure the grid-connected power supply of assembly, mutual power supply will not be formed between net-connected controller and the visiting spacecraft energy
Therefore isolating diode is arranged in net-connected controller output end and visiting spacecraft energy source output terminal in state.
In the present embodiment, it is contemplated that the DC/DC converters of the available 100V transformation 28V of passive space vehicle only have
The module of 200W ensures the output of 500W by output current limiting therefore, it is necessary to use 3 wired in parallel.It is reliable to ensure
Property, it is used using 1 module cold standby.
Due to being exported using 3 wired in parallel, to ensure that the consistency of output voltage, energy module voltage sample point are placed on
Before isolating diode.The equal properties of flow of multiple modules is realized by each module isolating diode, that is, passes through isolating diode
The external characteristics gradient for adjusting converter achievees the purpose that parallel current-sharing.It is direct by isolating diode for multiple energy modules
Parallel connection is carried out, actually automatically adjusts converter output impedance using diode forward characteristic so that the outer spy of module
Property tilt it is approximate consistent；When an output current in parallel module increases, diode forward pressure drop increases so that the module
Output voltage declines, i.e., external characteristics tilts down, and close to the external characteristics of other modules, other module output currents is made to increase, real
Existing approximation flows.
In the present embodiment, the selection of net-connected controller output voltage needs to defer to assembly visiting aircraft power supply system
The sequence for energy power supply priority of uniting.In the case of visiting spacecraft solo hop, solar wing Direct to the sun, energy resource system work
Make state (visiting aircraft energy resource system busbar voltage range) such as the following table 1：
Table 1
As shown in Table 1, solar array shunting is influenced in order to ensure the areas Yang Zhao not, so net-connected controller output voltage cannot
More than 30V.When in order to ensure that shadow region net-connected controller and ickel-cadmium cell are powered together, net-connected controller exports more power,
It it requires that net-connected controller output voltage is as high as possible.In view of net-connected controller exports diode of having connected, diode pressure
Drop increases as electric current increases, and it requires that net-connected controller output voltage cannot be below 29.4V before fully loaded.
With the increase that visiting spacecraft loads, after net-connected controller reaches current-limiting points, constant current state, output will be entered
Voltage will be consistent with visiting spacecraft busbar voltage.In view of the design point for spacecraft energy resource system of coming to visit：Shade
Between area's busbar voltage ranging from 27.8-28.5V.So can also export 500W after making net-connected controller constant current, need to be arranged
Current-limiting points are：500/27.8=18A.So it is 18A to choose net-connected controller output current limiting point.
Fig. 3 schematically shows a kind of grid-connected power supply composed structure arrangement of more spacecrafts of embodiment according to the present invention
Figure.As shown in figure 3, the grid-connected power supply system of more spacecrafts according to the present invention combined by passive space vehicle and visiting spacecraft and
At.Passive space vehicle includes passive space vehicle power subsystem, busbar control unit and net-connected controller.Wherein target space flight
Device power subsystem is made of solar array power supply battle array and Cd Ni battery+electric discharge adjuster.Visiting spacecraft includes orbital module
Distributor, return capsule distributor, propelling module distributor and visiting spacecraft power supply subsystem.Wherein visiting spacecraft power supply, which divides, is
System is made of solar array power supply battle array, Cd Ni battery+electric discharge adjuster and emergency power supply.
A kind of embodiment according to the present invention, to realize that grid-connected system design, the safety of the grid-connected power supply of assembly are set
Meter includes：Anti- strong design and failure effect analysis (FEA) and design.
In the present embodiment, anti-strong design is：
Net-connected controller uses safety Design measure, guarantee not to have high pressure and enter spacecraft of coming to visit.Net-connected controller
With 2 grades of output over-voltage protections, the 1st grade is the output over-voltage protection inside 4 converters, and output over-voltage protection point is no more than volume
Converter can be actually operated in maximum output voltage control when output over-voltage protection state by determine output voltage 1.2 times
Within 32V.
The overvoltage protection that 2nd grade of output over-voltage protection is output voltage when being more than 40V.It is more than when voltage occurs in output end
When the case where 40V, net-connected controller controls input relay by detection circuit and disconnects.
In the present embodiment, failure effect analysis (FEA) and respective design are：
Passive space vehicle and visiting spacecraft all have the function of stopping the grid-connected power supply of assembly, are likely to occur to cope with
Failure.Ensure that the failure of a spacecraft does not interfere with another spacecraft.
The setting of power control switch：
In view of the safety of power supply, the input of net-connected controller power supply output end and visiting spacecraft orbit cabin distributor
End is respectively provided with switch.When grid-connected power supply, it is in just by monitoring objective spacecraft electric network state and visiting spacecraft electric network state
When normal state, switch is closed and realizes grid-connected power supply.When abnormality occurs in any spacecraft power grid, it can pass through and disconnect switch
It realizes not grid-connected.
Failure between two spacecrafts influences：
If visiting spacecraft breaks down, net-connected controller exports terminal shortcircuit, defeated due to the cut-off current characteristics of net-connected controller
It is constant current to go out electric current, and voltage is very low.Total power consumption is much smaller than 500W, is not influenced on input terminal.Passive space vehicle, which can be sent, to be referred to
Order makes output disconnect.
If passive space vehicle generates failure, net-connected controller inputs terminal shortcircuit, then net-connected controller is for spacecraft of coming to visit
For be equivalent to a load.Since output end has the presence of diode, theoretically net-connected controller is relative to visiting spacecraft
For resistance be infinitely great.It is defeated under net-connected controller output end relay closed state but due to the influence of telemetric circuit
It is 5K ohms to go out impedance.Such state will not cause short circuit to visiting spacecraft, and can send instruction makes orbital module distribution
The grid-connected switch of device disconnects.
A kind of embodiment according to the present invention, to realize grid-connected system design, the grid-connected output power analysis bag of assembly
It includes：Static electric charge model is established and power analysis.
In the present embodiment, static electric charge model, which is established, includes：
A. according to spacecraft power supply system block diagram of coming to visit, the parameters such as length, thickness of service cable are for service cable
Resistance value is calculated, and the static models of visiting spacecraft power supply system are built.
B. it according to current cable design state of the art, is needed from net-connected controller to orbital module distributor by target space flight
The floating disconnection device of device crossing cabin electric connector, visiting spacecraft orbit cabin crossing cabin electric connector and docking mechanism, it is each to connect
Device, cable length are as shown in Figure 4.
In the present embodiment, supply lines use twisted-pair feeder, it is positive and negative for electric contact respectively be 26.It is chatted about No. 55 using auspicious
22AWG conducting wires.
It is 13.45m from net-connected controller to orbital module distributor length of cable, by calculating cable electricity in main track/negative wire
Resistance is about：24.3mΩ.
In the present embodiment, power analysis includes：
A. shadow region
According to visiting aircraft busbar voltage range, visiting aircraft energy resource system takes its highest in shadow region output voltage
Value 28.5V.
Shadow region the different loads energy output power distribution condition emulation such as the following table 2：
Table 2
By analysis, cloudy under visiting aircraft 627W loads (propelling module 230W, return capsule 217W, orbital module 180W)
Shadow zone output power is about 409W；1100W or more is loaded in visiting aircraft, net-connected controller output power can reach
500W。
B. the areas Yang Zhao
Choose the visiting aircraft minimum 30V of windsurfing voltage in the areas Yang Zhao, the situation of net-connected controller output power maximum.By
Emulation, it is as a result as follows：
The areas Yang Zhao the different loads energy output power distribution condition emulation such as the following table 3：
Table 3
By upper table 3 it can be seen that the power confessed in the areas Yang Zhao net-connected controller accounts for small part, windsurfing is stopping minimum
When loading 627W or more, output power is not less than 400W.
A kind of embodiment according to the present invention, to realize that grid-connected system design, assembly powered operation pattern include simultaneously
Net normal workflow and suspension normal workflow.In the present embodiment, the grid-connected in-orbit experiment of power supply carries out, can be in the moon
Shadow zone is accessed the access of the areas Huo Yangzhao and is disconnected, and considers safety to greatest extent, it is desirable to which grid-connected and suspension opportunity selection avoids
The areas Yang Zhao turn out cloudy shadow zone or the shadow region areas Zhuan Yangzhao at the time of.Grid-connected/suspension needs in ground observing and controlling or relays covering
Region carries out.
In the present embodiment, grid-connected normal workflow includes：
(1) the net-connected controller input 100V of passive space vehicle is connected；
(2) net-connected controller output loop line is connected with main track；
(3) spacecraft of coming to visit confirms orbital module grid-connected voltage parameter；
(4) the grid-connected switch of spacecraft orbit cabin distributor of coming to visit is connected, body power supply link connection is realize combination；
(5) confirm spacecraft power supply system stability of coming to visit；
(6) spacecraft windsurfing of coming to visit is zeroed；
In the present embodiment, suspension normal workflow includes：
(1) windsurfing of visiting spacecraft starts to control；
(2) state confirmation is carried out, windsurfing opens control normally, and power generation is normal；
(3) the grid-connected switch of orbital module distributor for spacecraft of coming to visit is disconnected；
(4) net-connected controller output main track and loop line are disconnected；
(5) the net-connected controller input 100V of passive space vehicle is disconnected.
Fig. 5 schematically shows that above-mentioned design method according to the present invention realizes the grid-connected flow chart with suspension of power supply.
Above-mentioned design method according to the present invention may be implemented to power when constituting assembly after multiple Spacecraft Rendezvous are docked
Networking, it is ensured that the energy balance of assembly aircraft.
The long-term in-orbit grid-connected power supply of the more spacecrafts in space station may be implemented in above-mentioned design method according to the present invention.
Above-mentioned design method according to the present invention so that the structure of the grid-connected power supply system of more spacecrafts of different voltages system
Simply, easy to implement, and have enough safeties and operation stability.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention
With within principle, any modification, equivalent replacement, improvement and so on should all be included in the protection scope of the present invention god.
Claims (9)
1. a kind of grid-connected power supply region method of more spacecrafts of different voltages system, which is characterized in that including：
The demand of the grid-connected power supply of assembly of analysis visiting spacecraft and passive space vehicle；
Design the topological structure of the grid-connected power supply of the assembly；
Design the scheme that grid-connected electric controller realizes power supply；
Design the safety of the grid-connected power supply of the assembly；
Analyze the grid-connected output power of the assembly；
Design the assembly powered operation pattern.
2. design method according to claim 1, which is characterized in that the passive space vehicle is carried to the visiting spacecraft
For the electric energy of 500W or more.
3. design method according to claim 1, which is characterized in that the demand of the grid-connected power supply of assembly includes：
The passive space vehicle uses 100V High Voltage Power Supply systems, and the visiting spacecraft is using 28V power supply systems；
The voltage conversion that a net-connected controller carries out 100V to 28V is arranged in the passive space vehicle；
Power supply process is equipped with the distance that control switchs and keeps the visiting spacecraft and the passive space vehicle；
The both ends of the passive space vehicle and the visiting spacecraft are respectively provided with power control switch.
4. design method according to claim 1, which is characterized in that the topological structure packet of the grid-connected power supply of the assembly
It includes：
The energy of the visiting spacecraft power supply system includes solar array, net-connected controller and cadmium-nickel accumulator；
It realizes in the output voltage section of the solar array, the net-connected controller and the cadmium-nickel accumulator+electric discharge adjuster
Power supply.
5. design method according to claim 4, which is characterized in that the solar array, the net-connected controller and institute
Cadmium-nickel accumulator is stated in a charging-discharging cycle of the assembly, the course of work is the following four stage：
A. when the assembly is in shadow region, by the net-connected controller and the visiting spacecraft ickel-cadmium cell+electric discharge
Adjuster is completed to power jointly, and the net-connected controller provides 500W power outputs, and the ickel-cadmium cell+electric discharge adjuster provides
300W power outputs；
B. when the assembly enter the areas Yang Zhao solar incident angle it is larger when, the solar array output power be less than 300W, by
The solar array, the net-connected controller and the ickel-cadmium cell+electric discharge adjuster are powered jointly, the solar array output
Power progressively increases to 300W from 0W, and the net-connected controller keeps the output of 500W rated power, the ickel-cadmium cell+electric discharge tune
Section device output power constantly reduces, and 0 is reduced to always from 300W；
C. it when the solar array output power is more than 300W, is completed jointly by the solar array and the net-connected controller
To load supplying is stopped, the solar array output power gradually increases from 300W, the net-connected controller output power from
500W is gradually reduced；
D. when the assembly is in the areas Yang Zhao, when the solar array output power is more than 800W, by the solar sail
Plate provides required power to load is stopped, and is in SHUNT state；Or at this time by the solar array and the net-connected controller
Common provide stops power needed for load, should ensure that the solar array provides the output of minimum 400W bearing powers at this time.
6. design method according to claim 4, which is characterized in that the grid-connected electric controller realizes the side of power supply
Case includes：
The net-connected controller uses voltage source, is exported for voltage stabilizing when load is not up to full load, is constant current when reaching full load
Output；
In the net-connected controller output end and the visiting spacecraft energy source output terminal, isolating diode is set；
100V is converted the DC/DC converter module parallel connections of 28V using 3 by the passive space vehicle, wherein 1 module is as cold
Backup uses；
An isolating diode is arranged in each DC/DC converter modules, and energy module voltage sample point is placed on two poles of isolation
Before pipe；
Net-connected controller output voltage≤the 30V.
7. design method according to claim 4, which is characterized in that the safety of the grid-connected power supply of assembly includes：
The net-connected controller has 2 grades of output over-voltage protections, and the 1st grade can be operated in converter output over-voltage protection state
When maximum output voltage control within 32V, the overvoltage protection that the 2nd grade of output over-voltage protection is output voltage when being more than 40V；
The input terminal of the grid-connected power supply output end of the passive space vehicle and the orbital module distributor of the visiting spacecraft is all provided with
Control switch is set, when grid-connected power supply, by monitoring objective spacecraft electric network state and the visiting spacecraft electric network state, is passed through
The open and close of control switch realizes grid-connected power supply and suspension.
8. design method according to claim 4, which is characterized in that the grid-connected output power of assembly includes：
According to the power supply system block diagram of the visiting spacecraft, the length of service cable, thickness for service cable resistance value into
Row calculates, and builds the static models of the power supply system of the visiting spacecraft；
It is electrically connected by the passive space vehicle crossing cabin from the net-connected controller to the orbital module distributor of the visiting spacecraft
Connect the floating disconnection device of device, the orbital module crossing cabin electric connector of the visiting spacecraft, docking mechanism；
The visiting spacecraft energy resource system is 28.5V in shadow region output ceiling voltage；
Passive space vehicle net-connected controller output power ability described in shadow region is not less than 500W；
The output power of visiting spacecraft solar array described in the areas Yang Zhao is not less than 400W.
9. the design method according to one of claim 4 to 8, which is characterized in that the assembly powered operation pattern packet
Include grid-connected normal workflow and suspension normal workflow；
The grid-connected normal workflow includes：
(1) the net-connected controller input 100V of the passive space vehicle is connected；
(2) the net-connected controller output loop line is connected with main track；
(3) the visiting spacecraft confirms orbital module grid-connected voltage parameter；
(4) the grid-connected switch of the visiting spacecraft orbit cabin distributor is connected, body power supply link connection is realize combination；
(5) confirm the visiting spacecraft power supply system stability；
(6) the visiting spacecraft windsurfing zero；
The suspension normal workflow includes：
(1) windsurfing of the visiting spacecraft starts to control；
(2) state confirmation is carried out, the solar array opens control normally, and power generation is normal；
(3) the grid-connected switch of orbital module distributor of the visiting spacecraft is disconnected；
(4) the net-connected controller output main track and loop line are disconnected；
(5) the net-connected controller input 100V of the passive space vehicle is disconnected.
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Application publication date: 20180717 |