CN104699072A - Residual magnetism control expansion satellite solar wing and test verification method thereof - Google Patents
Residual magnetism control expansion satellite solar wing and test verification method thereof Download PDFInfo
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- CN104699072A CN104699072A CN201510050633.8A CN201510050633A CN104699072A CN 104699072 A CN104699072 A CN 104699072A CN 201510050633 A CN201510050633 A CN 201510050633A CN 104699072 A CN104699072 A CN 104699072A
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- 238000012360 testing method Methods 0.000 title claims abstract description 64
- 230000005389 magnetism Effects 0.000 title claims abstract description 48
- 238000000034 method Methods 0.000 title claims abstract description 11
- 238000012795 verification Methods 0.000 title claims abstract description 10
- 238000004088 simulation Methods 0.000 claims abstract description 40
- 238000013461 design Methods 0.000 claims description 19
- 239000004744 fabric Substances 0.000 claims description 9
- 239000000758 substrate Substances 0.000 claims description 7
- 238000005286 illumination Methods 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 239000000203 mixture Substances 0.000 claims description 3
- 230000006835 compression Effects 0.000 claims description 2
- 238000007906 compression Methods 0.000 claims description 2
- 230000006698 induction Effects 0.000 abstract description 8
- 230000005611 electricity Effects 0.000 abstract description 2
- 238000013507 mapping Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 7
- 239000004020 conductor Substances 0.000 description 4
- 238000010998 test method Methods 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000003749 cleanliness Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 229920001721 polyimide Polymers 0.000 description 1
- 238000012216 screening Methods 0.000 description 1
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0218—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterised by the fault detection method dealing with either existing or incipient faults
- G05B23/0224—Process history based detection method, e.g. whereby history implies the availability of large amounts of data
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02S—GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRARED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, e.g. USING PHOTOVOLTAIC [PV] MODULES
- H02S40/00—Components or accessories in combination with PV modules, not provided for in groups H02S10/00 - H02S30/00
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- 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
Abstract
The invention discloses a residual magnetism control expansion satellite solar wing and a test verification method thereof. The residual magnetism control expansion satellite solar wing comprises a solar battery power supply circuit including a solar wing frontage, a connection cable connected with a solar wing backside and an electric connector; serial-connection solar battery unit circuits are configured into a figure '8' structure, every four serial-connection solar battery unit circuits form a mapping unit with double mirror surfaces, and a current-dividing circuit formed by in parallel connecting multiple serial-connection solar battery unit circuits is symmetric about upper and lower parts of the solar wing frontage; positive and negative wires of each solar battery unit circuit are led out from the same point and paired contacts of positive and negative wires led out from the same current-dividing circuit are adjacently arranged on the electric connector on the solar wing backside. Test simulation specimens are manufactured, wherein the surface current of the serial-connection solar battery unit circuit is simulated by the line current of the lead and each lead is in series connected with two resistors with the resistance value of 2omega and the rated power of 1W, so that the current passing through each simulation lead in the same current-dividing circuit is balanced. The test result indicates that the magnetic induction intensity at the position which is 1m far away from the solar wing is about 1nT during electricity generation of the solar wing.
Description
Technical field
The present invention relates to a kind of the expansion satellite sun wing and verification experimental verification method of remanent magnetism control design case, belong to satellite sun wing remanent magnetism control field.
Background technology
Satellite power system is generally made up of solar wing, battery pack, other regulation and control circuit, solar wing is satellite unique generating set in orbit, be load supplying at area of illumination, it is battery charging simultaneously, unnecessary output current order from the 1st level shunt circuit is shunted step by step, wherein 7 level shunt circuit and 8 level shunt circuit are connected on the two ends of battery pack by switching tube as rapid charge battle array, it is directly battery charging when large current charge, large current charge terminates rear disconnection charging, reverts to bussed supply.
General whole star maximum power dissipation regulates the Low earth orbit satellite of bus entirely at about 1000W, 28V, solar wing adopts large parallel-connection structure, and point 8 shunting level circuit, the element circuit that each shunting level circuit is composed in series by solar cell piece composes in parallel.Solar cell Series Sheet unit circuit adopts monolithic size to be about the solar cell of 40mm × 60mm, and monolithic battery best effort point voltage is about 1.78V, and consider that improving reliability stays a slice to backup, an element circuit is made up of 18 solar cells.Best operating point electric current about has 0.38A, and short-circuit current can reach 0.4A, considers the maximum power dissipation of whole more than star 1000W, and whole solar wing generally about has 100 such element circuits to be formed in parallel, and total output current reaches 40A.Solar cell piece is arranged on the substrate of aluminium honeycomb in units of element circuit, is insulated by polyimide film and substrate.
As Fig. 1, the size of current that arc wire passes through is I, in Cartesian coordinates, magnetic fields dB on (x, y, z) point, be that electric current in the conductor element (or solar cell element) owing to being dl causes in length, its relational expression is as follows:
In formula: μ
0represent the magnetoconductivity of vacuum space, r represents the vector put to (x, y, z) from electric current element Idl.Total magnetic moment B can be added by all electric current element Idl and obtain, and it has the component in three directions, i.e. Bx, By, Bz.Current－carrying conductor element does not produce magnetic-field component in the flow direction.Such as: the conductor element parallel with y-axis can produce magnetic-field component Bx, Bz, but along the y-axis direction magnetic-field component (i.e. By=0) is not had on.According to calculating, the solar wing remanent magnetism distance that operationally its electric current produces that output power is about 1100W is about 0.2Am
2, that is the magnetic induction density at distance solar wing 1 meter of is about 40nT.
For the electromagnetic surveillance test satellite having the electromagnetic susceptibility load such as magnetometer, the magnetic field produced in magnetometer position when requiring that solar wing works is within 0.025nT.Magnetometer is supported away from celestial body by boom, at distance celestial body 4.5 meters of, apart from solar wing about 5 meters.That is when solar wing works, should within 2.5nT at the magnetic induction density apart from its 1 meter of, this remanent magnetism to solar wing controls to propose higher requirement.
In order to reach so high requirement, in the control of satellite sun wing remanent magnetism, main also there are the following problems:
(1) mainly consider reliability and security when the solar cell piece in solar wing front arranges, and improve pieces of cloth coefficient, the area of the solar cell piece namely unit area solar wing substrate arranged, the remanent magnetism produced during operation on orbit is larger; (2) cable at the solar wing back side and electrical connector design also only consider reliability and security, and the remanent magnetism produced during operation on orbit is larger; (3) in the past in model, owing to not having very high requirement to the magnetic cleanliness factor of whole star, also due to the restriction of cost and test condition, the magnetic test of solar wing actual products can not be carried out, the remanent magnetism of expansion solar wing is apart from only carrying out theory calculate, but theory calculate can not represent actual value.
Summary of the invention
The technical matters that the present invention solves is: overcome prior art deficiency, a kind of the expansion satellite sun wing and verification experimental verification method of remanent magnetism control design case are proposed, optimize the design of existing solar wing, comprise the solar cell feed circuit in solar wing front, the stube cable at the solar wing back side and electric connector, the remanent magnetism distance that solar wing after optimizing produces in theory is zero, the maximum magnetic induction that this test method can produce when can record solar wing operation on orbit, verifies with this validity that solar wing remanent magnetism control and optimize designs.
The technical scheme that the present invention solves is: a kind of expansion satellite sun wing of remanent magnetism control design case, comprise the solar cell feed circuit in solar wing front, the stube cable at the solar wing back side and electric connector, the solar cell feed circuit in solar wing front comprise 8 shunting level circuit, and by multiple solar cell Series Sheet unit's circuit in parallel bus-bar together in shunting level circuit;
8 shunting level circuit are respectively one-level divided circuit, secondary divided circuit, three level shunt circuit, level Four divided circuit, Pyatyi divided circuit, six level shunt circuit, seven level shunt circuit, eight level shunt circuit;
Solar wing is divided into inner panel, middle plate, outside plate, and inner panel, middle plate, outside plate are arranged in order and are connected by mechanism; Inner panel, middle plate, outside plate respectively cloth are equipped with multiple solar cell Series Sheet unit circuit, and multiple solar cell Series Sheet units circuit is symmetrical with the center line on solar wing Width., the solar cell Series Sheet unit circuit quantity of inner panel, middle plate, this three plate of outside plate is identical, layout is identical, is all provided with four respectively and compresses point in inner panel, middle plate and outside plate, and the size of a solar cell Series Sheet unit circuit is vacated in the position of each compression point;
8 shunting level circuit, in solar wing front, are arranged symmetrically with up and down with the center line on solar wing Width, and seven level shunt circuit and eight level shunt circuit are arranged on the left of inner panel symmetrical with the center line on solar wing Width near celestial body; Pyatyi divided circuit be arranged in middle plate, outside plate top near solar wing edge, six level shunt circuit arrangement are in the bottom of middle plate, outside plate near solar wing edge, and six level shunt circuit and Pyatyi divided circuit are symmetrical with the center line on solar wing Width; One-level divided circuit is arranged in the centre position of top near middle plate and the right upper portion of inner panel of middle plate, three level shunt circuit arrangement are in the centre position of the bottom of middle plate near middle plate and the lower right side of inner panel, symmetrical with the center line on solar wing Width with one-level divided circuit; The top that secondary divided circuit is arranged in outside plate is middle top near the right side of the centre position of outside plate and middle plate, the bottom that level Four divided circuit is arranged in outside plate is middle on the lower near the right side of the centre position of outside plate and middle plate, symmetrical with the center line on solar wing Width with secondary divided circuit.
Between the solar cell Series Sheet unit circuit of inner panel, middle plate and outside plate, the direction of current of any horizontal and vertical two adjacent solar cell Series Sheet unit circuit is contrary, forms two mirror image; Single solar cell Series Sheet unit circuit comprises two current loops, and the direction of current of two current loops is contrary, i.e. " 8 " word pieces of cloth, in a solar cell Series Sheet unit circuit, current direction presents " 8 " word, and the positive and negative extension line of single solar cell Series Sheet unit circuit is drawn from same point, forms the closed path loop that both direction is contrary;
The positive negative wire of each solar cell Series Sheet unit circuit leads to bus-bar from same point in pairs, the positive negative wire of multiple solar cell Series Sheet units circuit in parallel in same shunting level circuit is drawn from the solar wing back side after bus-bar confluxes, its positive and negative extension line is drawn from same position in pairs, and it is intrafascicular to be arranged in same cable, symmetrical with the center line on solar wing Width, the cable at the solar wing back side is divided into two bundles, the lead-in wire of the center line top all solar cells Series Sheet unit circuit on solar wing Width is a branch of, the lead-in wire of solar wing center line bottom all solar battery cells circuit is a branch of, bunch of cables takes complete multiple twin unit,
Electric connector is arranged on the both sides of solar wing back side cable, and the distance of core of a cable colligation place pitch electrical connector is less than or equal to 20mm; Electric connector comprises multiple contact, and the arrangement of multiple contact polarity is one group of circulation arrangement according to positive and negative negative just (+--+).
Verify a test method for the expansion satellite sun wing remanent magnetism control effects of remanent magnetism control design case, comprise and set up test simulation part stage and remanent magnetism experimental stage,
It is described that to set up test simulation part stage etch as follows:
(1) by the line current simulation of the surface current wire of solar cell Series Sheet unit circuit, and serial connection two resistance 2 Ω, rated power are the resistance of 1W on every root wire, the electric current that in balanced same shunting level circuit, every root wire passes through, makes current differential that every root analog conducting wire in parallel in same shunting level circuit passes through within 8%; The spacing of analog conducting wire, the size of solar wing, the electric connector at the trend of inner panel, distance between middle plate and outside plate, solar wing back side cable and positive and negative extension line position, the solar wing back side, by the rocker stand of satellite and the stube cable of celestial body, all according to the material object manufacture of solar wing, solar wing substrate and rocker stand plank replace, and namely complete the foundation of test simulation part;
Described remanent magnetism experimental stage step is as follows:
(2) by the test simulation part of step (1) and electronic load, battery pack, power-supply controller of electric and solar battery array simulator composition remanent magnetism pilot system, solar battery array simulator main track is connected with the negative wire of test simulation part, solar battery array simulator negative wire is connected with the negative wire of power-supply controller of electric input end, the main track of test simulation part is connected with the main track of power-supply controller of electric input end, the positive negative wire of electronic load connects the positive negative wire of power-supply controller of electric output terminal respectively, the positive and negative output line of battery pack is connected with the positive negative wire of the battery pack input end of power-supply controller of electric, within the system, test simulation part is equivalent to a section lead and is connected between solar battery array simulator and power-supply controller of electric, and solar battery array simulator output current flows through output current during test simulation part simulated solar wing operation on orbit, electronic load analog satellite in orbit time whole star load, the area of illumination charging in-orbit of battery pack analog satellite, due to SHUNT state and the power supply states of the just different shunting level circuit of the size impact of load current and charging current, so load current and charging current with reality in orbit time size arrange for principle, experimentally need to adjust simultaneously, the maximum current that the output current that solar battery array simulator is often organized can export according to solar wing each shunting level circuit reality is arranged, test simulation part is placed on the testing table that is positioned under zero magnetic environment, electronic load, battery pack, power-supply controller of electric is connected by pair cable with solar battery array simulator, place away from testing table,
Three Magnetic Sensors measuring test simulation part remnant magnetism state are placed on test simulation part normal direction respectively, range simulation part 1 meter, the place of 2 meters, 3 meters;
(3) equipment connection is complete, parameter device is complete, solar battery array simulator exports, remanent magnetism pilot system brings into operation, the magnetic field data of Magnetic Sensor acquisition test simulating piece, after collection, stops solar battery array simulator to export, Magnetic Sensor gathers the magnetic field data of single test simulating piece again, and a front magnetic field data deducts rear Primary field data and is the magnetic field conditions that solar wing is subject to the generation of sunlight generating state in-orbit.
The present invention's advantage is compared with prior art:
(1) in the solar cell feed circuit of solar wing front, solar cell Series Sheet unit circuit adopts the design of " 8 " word pieces of cloth and adjacent four element circuits to adopt two mirror image to arrange, under the prerequisite not reducing product reliability, the remanent magnetism distance that solar wing front-side circuit can be made in theory to produce is zero;
(2) negative leads of each solar cell Series Sheet unit circuit is drawn from same point, the negative leads of multiple solar cell Series Sheet units circuit is drawn out to the solar wing back side from same position after bus-bar confluxes, the positive and negative extension line of multiple shunting level circuit takes complete multiple twin unit at the bunch of cables confluxed in the solar wing back side, the electric connector contact polarity arrangement that back side cable connects is one group of circulation arrangement according to positive and negative negative just (+--+), reduce current path loop area as far as possible, reduce the remanent magnetism distance of back side cable generation during solar wing generating;
(3) the circuit distribution of solar wing front shunting level and back side cable adopt the whole wing to be arranged symmetrically with up and down, make the remanent magnetism distance that can not offset of the inconsistent generation of solar cell Series Sheet unit's circuit, and the remanent magnetism that cable unescapable current path loop area in the back side produces is apart from cancelling out each other in the scope of the whole wing;
(4) the invention allows for one simple, the test method of checking expansion satellite sun wing remnant magnetism state with low cost, its advantage is: in the foundation of test simulation part, by the line current simulation of the surface current wire of solar cell Series Sheet unit circuit, and serial connection two resistance 2 Ω, rated power are the resistance of 1W on every root analog conducting wire, the electric current that in balanced same shunting level circuit, every root analog conducting wire passes through, makes current differential that every root analog conducting wire in parallel in same shunting level circuit passes through within 8%; In the connection of pilot system, test simulation part is equivalent to a section lead and is connected between solar battery array simulator and power-supply controller of electric, and solar battery array simulator output current flows through test simulation part, output current during simulated solar wing operation on orbit; This experimental system can the simulated solar wing operation on orbit time maximum magnetic induction that produces.
Accompanying drawing explanation
Fig. 1 electric current is to space point magnetic fields schematic diagram;
Fig. 2 element circuit of the present invention " 8 " word pieces of cloth schematic diagram;
The two mirror image arrangenent diagram of Fig. 3 four element circuits of the present invention;
Fig. 4 veneer circuit layout of the present invention and current trend figure;
Fig. 5 veneer solar wing of the present invention circuit magnetic moment direction schematic diagram;
Fig. 6 solar wing shunting of the present invention level layout;
Fig. 7 solar wing back side of the present invention Cable layout schematic diagram;
Fig. 8 electric connector of the present invention positive and negative contact arrangement schematic diagram;
Fig. 9 magnetic test facility annexation of the present invention schematic diagram;
Figure 10 solar wing veneer of the present invention pieces of cloth figure.
Embodiment
Basic ideas of the present invention for: with reduce solar wing in-orbit by the current path loop area that produces during sunlight generating for principle, a kind of expansion satellite sun wing of remanent magnetism control design case is provided, the test simulation part of the magnetic field state produced when setting up can simulate its operation on orbit for this solar wing, and design experiment, the remnant magnetism state produced when verifying the expansion satellite sun wing operation on orbit of remanent magnetism control design case meets the demands.
Below in conjunction with the drawings and specific embodiments, the present invention is described in further details.
The expansion satellite sun wing of remanent magnetism control design case:
Due to satellite configuration restriction, satellite-Y need install boom in side, and support the magnetic susceptibility load needed away from satellite body, solar wing is only arranged on+Y the side of satellite body, adopts single-blade configuration.According to satellite whole star load power consumption demand, adopt 96 solar cell Series Sheet unit circuit, gross output is about 1100W, and be arranged in 3 pieces and be of a size of on the carbon fiber aluminum honeycomb sandwich panel of 1600mm × 1200mm, the total area is 5.76m
2, wherein every block plate leaves 4 Φ 32mm and compresses the position of point and the position of 4 40mm × 25mm hinge mounting points.Every block plate is arranged 32 element circuits, and three pieces of plate front-side circuit states are completely the same, as Figure 10.
As Fig. 2, in a solar cell Series Sheet unit circuit, current direction presents " 8 " word, and positive and negative extension line is at one end drawn, and forms the closed path loop that both direction is contrary.If an element circuit adopts 20 solar cell series connection, form two electric current loops of equal and opposite in direction full symmetric, its magnetic moment produced can be offset completely.But consider the busbar voltage of 28V, the element circuit best effort point voltage of 20 series connection is about 35.6V, much larger than busbar voltage, solar cell is operated in constant current section, be equivalent to add unnecessary redundancy backup, solar array area needs to increase, and cost also can increase.So an element circuit adopts 18 solar cell series connection, like this in " 8 " word that an element circuit is formed, an electric current loop is made up of 8 solar cells, another forms by 10, for asymmetric state, the magnetic moment of two current loop generations can not be offset completely, and remanent magnetism is apart from being about 0.912mAm
2, direction is that the current loop of 10 solar cell compositions determines direction according to Ampere's law.
As Fig. 3, on every block plate, the direction of current of any horizontal and vertical two adjacent solar cell Series Sheet unit circuit is contrary, forms two mirror image, makes the magnetic moment can not cancelled out each other in individual unit circuit, cancel out each other in four element circuits.
On one substrate, the layout of solar cell Series Sheet unit circuit and current trend are as Fig. 4, and the current loop of 1 ~ 8 longitudinal expression 9 row, horizontal 1 ~ 9 indicates 9 column unit circuit.On every block plate, the size not pieces of cloth that an element circuit is vacated in some position are compressed at four, can make like this to vacate two mirror image that the adjacent element circuit in position can not form four element circuits therewith, but because the element circuit layout of every block plate is symmetrical up and down about the center line on solar wing Width, its remanent magnetism produced is apart from still cancelling out each other.
According to Ampere's law, the magnetic line of force is parallel with solar wing normal direction, defining solar wing direction just " " is, enter solar wing direction for negative "×", corresponding with Fig. 4, the loop magnetic moment direction that solar wing front-side circuit surrounds as shown in Figure 5, according to current return area and size of current and direction, and the distribution of element circuit is symmetrical up and down about the center line on solar wing Width on every block plate, the magnetic moment that on every block plate, solar battery array front-side circuit produces is cancelled each other, and calculated value is 0.
As Fig. 6,8 shunting level circuit are arranged symmetrically with up and down on a wing, make front solar cell circuit due to the inconsistency of technique, and the aspect of element circuit fails the magnetic moment of cancelling out each other, and the aspect of the whole wing is cancelled out each other.Because the short-circuit current (being about 0.4A) of each element circuit is slightly larger than working current (being about 0.38A), namely each shunting level circuit can slightly larger than the working current of power supply state at the short-circuit current of SHUNT state, and according to shunting the shunting order of level circuit, and the permanent load size (being about 400W) of satellite, 7 level shunt circuit and 8 level shunt circuit only have power supply and charging two duties, namely its output current is working current always, can not be operated in SHUNT state.So the 7 level shunt circuit and 8 level shunt circuit that are in stable state are arranged near celestial body always, other duties can be changed influential shunting level circuit is offset away from celestial body to magnetic moment, reduce solar battery array to the impact of satellite magnetic susceptibility load.Whole solar wing totally 96 element circuits divides 8 to shunt level circuit, and 1 ~ 4 shunting level circuit is made up of 10 element circuits, and 5 ~ 8 shunting level circuit are made up of 14 element circuits.
As Fig. 7, the positive negative wire of multiple solar cell Series Sheet units circuit in parallel in same shunting level circuit is drawn from the solar wing back side after bus-bar confluxes, leading point in the same horizontal line, upper and lower symmetry, and positive and negative extension line is in pairs on same position, reduce the distance of negative leads exit, wherein 1 ~ 4 shunting level circuit and 7,8 shunting level circuit draw three groups of positive negative wires, and 5,6 shunting level circuit draw four groups of positive negative wires; It is intrafascicular that the negative leads of same shunting level circuit is arranged in same cable, and bunch of cables takes complete multiple twin unit, and namely conflux wire harness rotating 360 degrees when extending forward at the solar wing back side; Wire harness colligation place pitch electrical connector is no more than 20mm, reduces the current return area that between plate, electrical connector cable opening is formed as far as possible; Bunch of cables after confluxing is connected in star by rocker stand; Back side whole cable layout is symmetrical up and down, and the magnetic moment making it produce is cancelled out each other in the aspect of the whole wing.
As Fig. 8, in model in the past, in order to improve reliability, reduce the difficulty of process implementing, the electric connector positive-negative polarity contact that solar wing back side cable connects is arrangement separately, and the wire harness that so positive negative wire twists together, through electric connector, forms larger aperture area between positive negative wire.Solar battery array is when the duty that output current is maximum, and on whole solar wing, the aperture area of six place's electric connectors can produce the magnetic induction density being about 1nT at 1 meter of in distance solar wing plane normal direction.For reducing the current path loop area that positive negative wire produces on electrical connectors, the arrangement of electric connector positive-negative polarity contact is one group of circulation arrangement according to positive and negative negative just (+--+), positive negative wire is arranged in pairs, reduce the magnetic moment because positive and negative contact distance produces, and adopt the arrangement of such Mirror Symmetry, the magnetic moment produced due to positive and negative contact distance can be made to cancel out each other.
The foundation of test simulation part:
In the foundation of test simulation part, front-side circuit adopts line current falseface electric current, namely with wire simulation solar battery cell circuit, analog conducting wire is positioned at the centre position of solar cell piece series unit circuit, and in the same shunting level circuit on same plate, the bus-bar in parallel of element circuit is also simulated by wire.Completely the same owing to can not accomplish the conductive line resistance values of each root simulated solar cell array element circuit in technique, can there is larger difference in the electric current passed through after conductor in parallel.On every root wire, be connected in series the resistance of two resistance 2 Ω, rated power 1W for this reason, the difference ratio of resistance between analog conducting wire is made to control within 8%, when then each shunting level circuit leads to certain electric current, the current differential that every root analog conducting wire in same shunting level circuit passes through within 8%, slightly larger than through screening after solar cell Series Sheet unit circuit actual output current difference.
The spacing of analog conducting wire, the size of solar wing, the electric connector at the trend of inner panel, distance between middle plate and outside plate, solar wing back side cable and positive and negative extension line position, the solar wing back side, by the rocker stand of satellite and the stube cable of celestial body, all according to the material object manufacture of solar wing, solar wing substrate and rocker stand plank replace, this model do not comprise solar wing other structure and mechanism section.
Remanent magnetism test design and test findings:
In process of the test, testing equipment annexation is as Fig. 9, and form remanent magnetism pilot system by electronic load, battery pack, power-supply controller of electric and solar battery array simulator, solar battery array simulator has 8 groups, 8 shunting level circuit of corresponding solar wing.Electronic load analog satellite in orbit time whole star load, the area of illumination charging in-orbit of battery pack analog satellite, due to SHUNT state and the power supply states of the just different shunting level circuit of the size impact of load current and charging current, so load current and charging current with reality in orbit time size arrange for principle, experimentally need to adjust simultaneously.Solar battery array simulator output current flows through test simulation part simulated solar wing output current in-orbit, according to Biot-Savart law, the magnetic field that steady current produces is directly proportional to size of current, so arranging solar battery array simulator output current is the maximal value that solar wing estimates output current in-orbit, each element circuit best operating point electric current is pressed 0.38A and is arranged, short-circuit current is pressed 0.4A and is arranged, namely 1 ~ 4 shunting level circuit best operating point electric current composed in parallel by 10 element circuits is arranged by 3.8A, short-circuit current is pressed 4A and is arranged, 5 ~ 8 shunting level circuit best operating point electric currents composed in parallel by 14 element circuits are arranged by 5.32A, short-circuit current is pressed 5.6A and is arranged.
Test simulation part is placed on the testing table that is positioned under zero magnetic environment, and other equipment are connected by pair cable, place away from testing table, in order to avoid form impact to test findings.Three Magnetic Sensors measuring test simulation part remnant magnetism state are placed on test simulation part normal direction respectively, distance test (DT) simulating piece 1 meter, the place of 2 meters, 3 meters, according to Biot-Savart law, circular coil electric current cube being inversely proportional to of the magnetic field and the distance that produce of somewhere in the axial direction thereof, the magnetic field data of 2 meters and 3 meters Magnetic Sensor surveys as a control group.
During test, electronic load, power-supply controller of electric state and solar battery array simulator state are first set, system brings into operation, Magnetic Sensor starts to gather magnetic field data, after collection, stop solar battery array simulator to export, Magnetic Sensor gathers Primary field data again, and a front magnetic field data deducts rear Primary field data and is the magnetic field conditions that solar wing is subject to sunlight generating state in-orbit.
Considering that different shunting level circuit is in adjusts wide state may have an impact to solar wing remanent magnetism situation, again according to satellite in orbit time whole star load power consumption situation of change, and battery charging and solar wing are by according to situation, point 6 kinds of mode of operations are tested respectively.One of them mode of operation as a control group, arranging solar battery array simulator output current is the half of maximum current, namely 1 ~ 4 shunting level circuit best operating point electric current presses 1.9A setting, short-circuit current by 2A setting, and 5 ~ 8 shunting level circuit best operating point electric currents press 2.66A setting, short-circuit current is arranged by 2.8A.Test mode of operation arrange and test findings as shown in table 1.
Table 1 remanent magnetism experiment work pattern and test findings
According to test findings and control group data, the magnetic field that test figure meets steady current generation is directly proportional to size of current, and the circular coil electric current magnetic field of somewhere generation and cube Biot-Savart law be inversely proportional to of distance in the axial direction thereof, illustrate that test figure is credible.Test findings shows, the solar wing through remanent magnetism control design case is subject to the magnetic induction density produced during electricity approved for distribution much smaller than the solar wing without remanent magnetism control design case.During solar wing generating, the magnetic induction density at distance solar wing 1 meter of is about 1nT, meets the index request that magnetic susceptibility load proposes solar wing, demonstrates the validity of design.
Non-elaborated part of the present invention belongs to techniques well known.
Claims (2)
1. the expansion satellite sun wing of a remanent magnetism control design case, comprise the solar cell feed circuit in solar wing front, the stube cable at the solar wing back side and electric connector, the solar cell feed circuit in solar wing front comprise 8 shunting level circuit, and by multiple solar cell Series Sheet unit's circuit in parallel bus-bar together in shunting level circuit;
8 shunting level circuit are respectively one-level divided circuit, secondary divided circuit, three level shunt circuit, level Four divided circuit, Pyatyi divided circuit, six level shunt circuit, seven level shunt circuit, eight level shunt circuit;
Solar wing is divided into inner panel, middle plate, outside plate, and inner panel, middle plate, outside plate are arranged in order and are connected by mechanism; Inner panel, middle plate, outside plate respectively cloth are equipped with multiple solar cell Series Sheet unit circuit, multiple solar cell Series Sheet units circuit is symmetrical with the center line on solar wing Width, the solar cell Series Sheet unit circuit quantity of inner panel, middle plate, this three plate of outside plate is identical, layout is identical, all be provided with four in inner panel, middle plate and outside plate respectively and compress point, the size of a solar cell Series Sheet unit circuit is vacated in the position of each compression point;
8 shunting level circuit, in solar wing front, are arranged symmetrically with up and down with the center line on solar wing Width, and seven level shunt circuit and eight level shunt circuit are arranged on the left of inner panel symmetrical with the center line on solar wing Width near celestial body; Pyatyi divided circuit be arranged in middle plate, outside plate top near solar wing edge, six level shunt circuit arrangement are in the bottom of middle plate, outside plate near solar wing edge, and six level shunt circuit and Pyatyi divided circuit are symmetrical with the center line on solar wing Width; One-level divided circuit is arranged in the centre position of top near middle plate and the right upper portion of inner panel of middle plate, three level shunt circuit arrangement are in the centre position of the bottom of middle plate near middle plate and the lower right side of inner panel, symmetrical with the center line on solar wing Width with one-level divided circuit; The top that secondary divided circuit is arranged in outside plate is middle top near the right side of the centre position of outside plate and middle plate, the bottom that level Four divided circuit is arranged in outside plate is middle on the lower near the right side of the centre position of outside plate and middle plate, symmetrical with the center line on solar wing Width with secondary divided circuit;
Between the solar cell Series Sheet unit circuit of inner panel, middle plate and outside plate, the direction of current of any horizontal and vertical two adjacent solar cell Series Sheet unit circuit is contrary, forms two mirror image; Single solar cell Series Sheet unit circuit comprises two current loops, and the direction of current of two current loops is contrary, i.e. " 8 " word pieces of cloth, in a solar cell Series Sheet unit circuit, current direction presents " 8 " word, and the positive and negative extension line of single solar cell Series Sheet unit circuit is drawn from same point, forms the closed path loop that both direction is contrary;
The positive negative wire of each solar cell Series Sheet unit circuit leads to bus-bar from same point in pairs, the positive negative wire of multiple solar cell Series Sheet units circuit in parallel in same shunting level circuit is drawn from the solar wing back side after bus-bar confluxes, its positive and negative extension line is drawn from same position in pairs, and it is intrafascicular to be arranged in same cable, symmetrical with the center line on solar wing Width, the cable at the solar wing back side is divided into two bundles, the lead-in wire of the center line top all solar cells Series Sheet unit circuit on solar wing Width is a branch of, the lead-in wire of solar wing center line bottom all solar battery cells circuit is a branch of, bunch of cables takes complete multiple twin unit,
Electric connector is arranged on the both sides of solar wing back side cable, and the distance of core of a cable colligation place pitch electrical connector is less than or equal to 20mm; Electric connector comprises multiple contact, and multiple contact polarity arrangement is being just one group of circulation arrangement according to positive and negative bearing.
2. verify a verification experimental verification method for the expansion satellite sun wing of remanent magnetism control design case, it is characterized in that comprising and set up test simulation part stage and remanent magnetism experimental stage,
It is described that to set up test simulation part stage etch as follows:
(1) by the line current simulation of the surface current wire of solar cell Series Sheet unit circuit, and serial connection two resistance 2 Ω, rated power are the resistance of 1W on every root wire, the electric current that in balanced same shunting level circuit, every root wire passes through, makes current differential that every root analog conducting wire in parallel in same shunting level circuit passes through within 8%; The spacing of analog conducting wire, the size of solar wing, the electric connector at the trend of inner panel, distance between middle plate and outside plate, solar wing back side cable and positive and negative extension line position, the solar wing back side, by the rocker stand of satellite and the stube cable of celestial body, all according to the material object manufacture of solar wing, solar wing substrate and rocker stand plank replace, and namely complete the foundation of test simulation part;
Described remanent magnetism experimental stage step is as follows:
(2) by the test simulation part of step (1) and electronic load, battery pack, power-supply controller of electric and solar battery array simulator composition remanent magnetism pilot system, solar battery array simulator main track is connected with the negative wire of test simulation part, solar battery array simulator negative wire is connected with the negative wire of power-supply controller of electric input end, the main track of test simulation part is connected with the main track of power-supply controller of electric input end, the positive negative wire of electronic load connects the positive negative wire of power-supply controller of electric output terminal respectively, the positive and negative output line of battery pack is connected with the positive negative wire of the battery pack input end of power-supply controller of electric, within the system, test simulation part is equivalent to a section lead and is connected between solar battery array simulator and power-supply controller of electric, and solar battery array simulator output current flows through output current during test simulation part simulated solar wing operation on orbit, electronic load analog satellite in orbit time whole star load, the area of illumination charging in-orbit of battery pack analog satellite, due to SHUNT state and the power supply states of the just different shunting level circuit of the size impact of load current and charging current, so load current and charging current with reality in orbit time size arrange for principle, experimentally need to adjust simultaneously, the maximum current that the output current that solar battery array simulator is often organized can export according to solar wing each shunting level circuit reality is arranged, test simulation part is placed on the testing table that is positioned under zero magnetic environment, electronic load, battery pack, power-supply controller of electric is connected by pair cable with solar battery array simulator, place away from testing table,
Three Magnetic Sensors measuring test simulation part remnant magnetism state are placed on test simulation part normal direction respectively, range simulation part 1 meter, the place of 2 meters, 3 meters;
(3) equipment connection is complete, parameter device is complete, solar battery array simulator exports, remanent magnetism pilot system brings into operation, the magnetic field data of Magnetic Sensor acquisition test simulating piece, after collection, stops solar battery array simulator to export, Magnetic Sensor gathers the magnetic field data of single test simulating piece again, and a front magnetic field data deducts rear Primary field data and is the magnetic field conditions that solar wing is subject to sunlight generating state in-orbit.
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