CN109606752A - For low orbit spacecraft illumination path testing method and system - Google Patents
For low orbit spacecraft illumination path testing method and system Download PDFInfo
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- CN109606752A CN109606752A CN201811518289.0A CN201811518289A CN109606752A CN 109606752 A CN109606752 A CN 109606752A CN 201811518289 A CN201811518289 A CN 201811518289A CN 109606752 A CN109606752 A CN 109606752A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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Abstract
Illumination path testing method and its equipment of the present invention.This method is used to test the power supply of the solar cell wing-driving mechanism-parallel regulator-power manager-spacecraft load of low orbit spacecraft, charge circuit, ground regulated power supply is controlled to loop power supply by main control computer to obtain reference value, then, after control lamp array equipment irradiation needs the solar cell wing to be tested, the test parameter for acquiring charge circuit and current supply circuit compares test parameter and corresponding reference value and judges whether current supply circuit and charge circuit are reliably connected.After docking this method avoid spacecraft ontology with the solar cell wing, in the unacknowledged situation of supply access, to the harmfulness of whole other product facilities of cabin, safety, the operability of ground test are increased.
Description
Technical field
The present invention relates to the testing field of low orbit spacecraft more particularly to low orbit spacecraft illumination path testing method and
Its device judges that spacecraft is entirely powered, charge power is powered back after docking for the low orbit spacecraft solar cell wing with cabin
Whether the connection on road is reliable.
Background technique
With the rapid development of the low rail space technology in China, spacecraft development shows high-power, long-life, highly reliable
Feature.And the power supply source of spacecraft is mainly solar battery array, in order to be able to satisfy the powerful requirement of spacecraft, so that the sun
The battery cloth the piece number of cell wing increases, the area of the whole wing and weight increase, and the volume weight of spacecraft ontology is big, therefore on ground
Test phase considers that the solar cell wing and spacecraft ontology use split type test mode for safety, operability.?
Spacecraft ontology ground test terminates after the completion of testing with the solar cell wing itself, and the two is docked.In order to confirm sun electricity
After Chi Yi installation, it is reliably connected, need to leads to from the solar cell wing out of my cabin to the whole power supply of cabin internal control control equipment, charge power access
Special test method is crossed to be verified.Therefore, the feasible and parameter sampling of illumination path testing test method it is correct for
Being reliably connected for verifying power flow is particularly important.And the realization of illumination test method is mentioned to solar battery array energy reliable power supply
Foundation has been supplied, has been provided the foundation to the in-orbit reliability service of low orbit spacecraft.
Summary of the invention
Problems solved by the invention is after the solar cell wing is installed, out of out of my cabin the solar cell wing to the cabin of spacecraft ontology
Control power supply, the problem of being reliably connected of charge power access of equipment.
To solve the above problems, the present invention provides a kind of illumination path testing system, for testing low orbit spacecraft too
Positive cell wing-driving mechanism-parallel regulator-power manager-power supply of spacecraft load, charge circuit, the illumination access
Test macro includes main control computer, ground regulated power supply, illumination highway device and lamp array equipment, wherein the master control calculates
Machine is equipped with application software, and application software sending first goes code or the first open command is so that ground pressure stabilizing is electric
Source-driving mechanism-parallel regulator-power manager is connected or breaks with charge circuit with the current supply circuit that spacecraft loads
It opens, in the case where connection, which obtains the parameter of current supply circuit and charge circuit to obtain reference value；The master control
Computer application software in the correct situation of the reference value, generate brightness control instruction and transmit the brightness control instruction with
So that the lamp array equipment generates the simulated solar irradiation for irradiating the solar cell wing, the application software generate second go code or
The second open command of person is so that the confession that the solar cell wing-driving mechanism-parallel regulator-power manager and spacecraft load
Electrical circuit and charge circuit connect or disconnect, and in the case, the application software acquires the current supply circuit and charge circuit
Parameter to obtain test parameter；The more corresponding test parameter of main control computer and corresponding reference value, are being surveyed
Parameter is tried no more than in the case where reference value, determines that the connection in the circuit is reliable, is greater than corresponding reference value in test parameter
In the case of, determine that the circuit connection is unreliable.
In further scheme, the lamp array equipment includes sun optical analog lamp array, lamp array power controling box and lamp array liter
Vehicle drops, wherein sun optical analog lamp array uses the air-cooled xenon lamp forming array of long arc, the lamp array power controling box and day sun
The connection of optical analog lamp array, including several lamp array brightness regulating buttons, the regulation button controlled by the brightness control instruction so that
The corresponding cold xenon lamp obtained in the lamp array shines.
In further scheme, the lamp array equipment further includes lamp array lift truck, and the lamp array lift truck includes lifting dress
It sets and control device, the sun optical analog lamp array connects the lifting device；The control device receives the climb command
And control the lifting device and rise so that sun optical analog lamp array rises, the reception decline instructs and controls the lifting
Device decline is so that the sun optical analog lamp array declines.
Another aspect of the present invention is to provide a kind of testing solar battery wing-driving mechanism-parallel regulator-power management
The method that charging and current supply circuit are reliably connected between the load of device-spacecraft, this method comprises the following steps: S1, by the survey
Test system and the solar cell wing, driving mechanism, parallel regulator, power manager and spacecraft load connect, wherein sunlight
Simulation lamp array is placed in solar cell lamina lateralis processus pterygoidei to be illuminated and posts 0.5m~1.5m in front of the one side of cell piece, lamp array face and drive
Motivation structure axis is parallel；S2, the power supply of ground source of stable pressure is opened, the application software of the main control computer of test macro issues first and connects
Logical instruction takes off the supply access that slotting-power manager-spacecraft loads to connect ground regulated power supply-；S3, unlatching ground are steady
Voltage source, so that ground regulated power supply gives spacecraft load supplying by de- slotting-power manager, the application on main control computer
The parameter of the software collection current supply circuit is to obtain reference value；S4, main control computer application software in the correct feelings of reference value
Under condition, after one side 2s~5s that cell piece is posted with the solar cell lamina lateralis processus pterygoidei that sun optical analog lamp array is irradiated, main control computer
Acquire the current supply circuit and charge circuit of the solar cell wing-driving mechanism-parallel regulator-power manager and spacecraft load
Test parameter, compare the test parameter of the current supply circuit and corresponding reference value, in the correct situation of parameter, described in judgement
Current supply circuit is reliably connected and enters step S5, conversely, continuing step S4；Meanwhile it closing ground regulated power supply and making 100V steady
Power on the supply access of the de- slotting-power manager-spacecraft load of voltage source-illumination access device-is closed；S5, continuation
After illumination 10s~25s, application software acquires the test parameter of the charge circuit, judge charge circuit test parameter whether
Correctly, in the correct situation of the parameter of charge circuit, judge that the charge circuit is reliably connected.
In further scheme, the method also includes following steps: S6, the power supply of ground source of stable pressure is opened, so that 100V
Regulated power supply gives spacecraft load supplying by the de- slotting-power manager of illumination access device-；Lamp is closed by lamp array operator
Battle array, so that the solar cell piece on left wing's outside plate is loaded by driving mechanism-parallel regulator-power manager to spacecraft
Supply access is closed；S7,100V pressure stabilizing power supply is closed, so that 100V regulated power supply inserts-power tube by the way that illumination access device-is de-
Device is managed to close to spacecraft load supplying power；S8, the power supply of 28V source of stable pressure is opened, main control computer passes through illumination highway device
Power manager sends pressure stabilizing supply relay open command on spacecraft, disconnects 100V regulated power supply-illumination access device-
The supply access of de- slotting-power manager-spacecraft load；S9, terminate test, remove and receive illumination path testing equipment.
In further scheme, the test macro include main control computer, ground regulated power supply, illumination highway device and
Lamp array equipment, wherein the main control computer is equipped with application software, which issues first and go code or first
Open command is so that the power supply of ground regulated power supply-driving mechanism-parallel regulator-power manager and spacecraft load is returned
Road and charge circuit connect or disconnect, and in the case where connection, which obtains the ginseng of current supply circuit and charge circuit
Number is to obtain reference value；The application software of the main control computer generates brightness control and refers in the correct situation of the reference value
It enables and transmits the brightness control instruction so that the lamp array equipment generates the simulated solar irradiation for irradiating the solar cell wing, this is answered
It is gone code with software generation second or the second open command is so that the solar cell wing-driving mechanism-parallel regulator-function
The current supply circuit and charge circuit of rate manager and spacecraft load connect or disconnect, in the case, the application software
The parameter of the current supply circuit and charge circuit is acquired to obtain test parameter；The more corresponding test parameter of main control computer
Determine that the connection in the circuit is reliable in the case where test parameter is not more than reference value with corresponding reference value, surveying
It is unreliable greater than in the case where corresponding reference value, determining that the circuit connects to try parameter.
In further scheme, the lamp array equipment includes sun optical analog lamp array, lamp array power controling box and lamp array liter
Vehicle drops, wherein sun optical analog lamp array uses the air-cooled xenon lamp forming array of long arc, the lamp array power controling box and day sun
The connection of optical analog lamp array, including several lamp array brightness regulating buttons, the regulation button controlled by the brightness control instruction so that
The corresponding cold xenon lamp obtained in the lamp array shines.
In further scheme, the lamp array equipment further includes lamp array lift truck, and the lamp array lift truck includes lifting dress
It sets and control device, the sun optical analog lamp array connects the lifting device；The control device receives the climb command
And control the lifting device and rise so that sun optical analog lamp array rises, the reception decline instructs and controls the lifting
Device decline is so that the sun optical analog lamp array declines.
Compared with prior art, the present invention has at least the following advantages:
1, a kind of low orbit spacecraft illumination path testing method is provided, spacecraft ontology and the solar cell wing pair are avoided
After connecing, in the unacknowledged situation of supply access, to the harmfulness of whole other product facilities of cabin, the safety of ground test is increased
Property, operability.
2, the present invention is easy to implement, increases the flexibility of test opportunity and test phase.
Detailed description of the invention
Fig. 1 is schematic diagram of the low orbit spacecraft illumination highway device of the present invention for test；
Fig. 2 is a kind of power supply of spacecraft ontology of low orbit spacecraft illumination path testing system testing of the present invention, fills
Electrical circuit schematic diagram；
Fig. 3 is each equipment connection schematic diagram of illumination path testing system.
Specific embodiment
By the technology contents that the present invention will be described in detail, construction feature, reached purpose and efficacy, below in conjunction with embodiment
And attached drawing is cooperated to be described in detail.
It please refers to Fig.1 to Fig.3, to facilitate the understanding of the present invention, first introduces measurand and the object and this test macro
Connection it is as follows: after illumination path testing system of the present invention is installed on spacecraft cabin for testing solar battery battle array, test
The power supply of spacecraft, the equipment that is reliably connected of charge circuit, including main control computer, ground regulated power supply and lamp array equipment.
Main control computer is equipped with application software, and the application software is for controlling measurand, the parameter on acquisition circuit and judging to connect
It whether reliable connects.The ground regulated power supply is as reference power source, in the case where the power supply power supply, acquires charge circuit and confession
The parameter of electrical circuit using as reference value, for it is subsequent powered with the solar cell wing in the case where, test parameter and the phase of acquisition
The reference value answered compares, and in turn, judges whether circuit connection is reliable.The lamp array equipment includes sun optical analog lamp array, lamp array
Power controling box and lamp array lift truck, wherein sun optical analog lamp array uses the air-cooled xenon lamp forming array of long arc, the lamp array electricity
Source control cabinet is connected to the sun optical analog lamp array, including several lamp array brightness regulating buttons, and the regulation button is by described bright
Control instruction control is spent so that the corresponding cold xenon lamp in the lamp array shines.The lamp array equipment further includes lamp array lifting
Vehicle, the lamp array lift truck include lifting device and control device, and the sun optical analog lamp array connects the lifting device；Institute
Control device is stated to receive the climb command and control the lifting device and rise so that the rising of sun optical analog lamp array, receives
The decline instructs and controls the lifting device decline so that the sun optical analog lamp array declines.In Fig. 1 and Fig. 3,
Illumination path testing equipment, which need to have, provides the interface of ground power supply access, provides parameter measurement channel and instruction simulation channel.
Please refer to Fig. 2 and Fig. 3, the equipment on a kind of supply access of the spacecraft cabin of measurand includes power
Manager, parallel regulator and driving mechanism (are fixed on the medium in cabin for the solar cell wing, are used for solar cell
The medium of power signal transmissions between the wing and parallel regulator).Spacecraft solar battery array corresponding with the spacecraft cabin is adopted
With dividing configuration to design, wherein power supply battle array is used for powering load, charging battle array is used to charge to energy-storage battery.Wherein solar battery array
It is divided into left and right both wings, 3 blocks of plates of every wing, respectively inner panel, middle plate and outside plate, battle array that 8 tunnels power supply battle array is arranged in left wing, 12 tunnels are charged is right
Battle array that 9 tunnels power supply battle array is arranged in the wing, 9 tunnels are charged.
Parameter used in illumination path testing method: busbar voltage is that power supply power supply access is exported to the primary mother of load
Line voltage；Secondary power supply voltage is voltage of the busbar voltage after DCDC block transforms；A unit charging battle array voltage is A
Charge voltage of the battle array after parallel regulator collects on unit 7 tunnel；B unit charging battle array voltage is that 7 tunnel of B unit charging battle array is shunting tune
Save the voltage after device collects；Single channel charging battle array voltage is the voltage of the 5th tunnel of C unit charging battle array；Single service battle array voltage be it is left too
The voltage telemeering of positive the 7th tunnel of cell wing power supply battle array.
Output power circuit: 8 tunnel of left wing battle array of powering passes through cable between plate and equipment room cable connection to left driving mechanism X1
Electric connector is sent to left driving mechanism X4 electric connector by the slip ring of left driving mechanism, is then connected to by equipment room cable
The X13 electric connector of equipment parallel regulator, exports through X12 electric connector to power manager after converging in parallel regulator
X1 electric connector, to supply electricity to below deck equipment by the electric connector of the X6 of power manager.According to point of spacecraft
Throttle regulator design point can acquire busbar voltage, secondary power supply voltage, single service battle array electricity by illumination test access equipment
Electric connector inserting state on the parameter testings accesses such as pressure, to confirm being reliably connected for current supply circuit.
9 tunnel of right flank power supply battle array, to right driving mechanism X1 electric connector, is passed through by cable between plate and equipment room cable connection
The slip ring of right driving mechanism is sent to right driving mechanism X4 electric connector, is then connected to equipment parallel regulator by equipment room cable
X11 electric connector, exported through X12 electric connector to the electrical connection of the X1 of power manager after converging in parallel regulator
Device, to supply electricity to below deck equipment by the electric connector of the X6 of power manager.It is designed according to the parallel regulator of spacecraft
State, the electric connector that can be acquired on the parameter testings accesses such as busbar voltage, secondary power supply voltage by illumination highway device are inserted
State is connect, to confirm being reliably connected for current supply circuit.
Charge battle array loop of power circuit: tri- units of left wing A, B, C the 1st, 3,5,7 tunnels charging battle array pass through cable and equipment between plate
Between cable connection to left driving mechanism X2, sent by the slip ring of left driving mechanism to left driving mechanism X5 electric connector, A unit
1st, 3,5,7 tunnels charging battle array through left driving mechanism X5 electric connector be connected to parallel regulator X1 electric connector, and in shunt regulating
Device is converged, so that the X3 electric connector by parallel regulator charges to energy-storage battery A；B unit the 1st, 3,5,7 tunnels fill
Electric battle array is connected to parallel regulator X4 electric connector through left driving mechanism X5 electric connector, and is converged in parallel regulator, from
And it is charged by the X6 electric connector of parallel regulator to energy-storage battery B；C unit the 1st, 3,5,7 tunnels charging battle array through left driving
Mechanism X5 electric connector is connected to parallel regulator X7 electric connector, and is converged in parallel regulator, to be adjusted by shunting
The X9 electric connector for saving device charges to energy-storage battery C.According to the parallel regulator design point of spacecraft, can be tested by illumination
Highway device acquires A unit charging battle array voltage, B unit charging battle array voltage, single channel and charges on three parameter testing accesses of battle array voltage
Electric connector inserting state, to confirm the reliable of charge circuit.
Tri- units of right flank A, B, C the 2nd, 4,6 tunnels charging battle array pass through cable between plate and equipment room cable connection to right drive
Motivation structure X2 is sent by the slip ring of right driving mechanism to right driving mechanism X5 electric connector, A unit the 2nd, 4,6 tunnels charge battle array
It is connected to parallel regulator X1 electric connector through right driving mechanism X5 electric connector, and is converged in parallel regulator, thus logical
The X3 electric connector for crossing parallel regulator charges to energy-storage battery A；B unit the 2nd, 4,6 tunnels charging battle array through right driving mechanism X5
Electric connector is connected to parallel regulator X4 electric connector, and is converged in parallel regulator, to pass through parallel regulator
X9 electric connector charges to energy-storage battery B；According to the parallel regulator design point of spacecraft, can be set by illumination test access
Electric connector inserting state on standby acquisition A unit charging battle array voltage, B unit charging three parameter testing accesses of battle array voltage, from
And confirm the reliable of charge circuit.
Please continue to refer to Fig. 1 to Fig. 3, steps are as follows for the test method of illumination path testing system of the present invention:
In place according to Fig. 3 connection by test equipment, by taking left wing's outside plate test in the case of expansion as an example, specific test is provided
Process, right flank test implement.The lower progress outside plate test of solar cell wing impaction state, operating procedure is also referring to holding
Row.Specific testing process is as follows:
Step 1: putting test equipment in place according to attached drawing 2, and position is connected devices in conjunction with Fig. 3, wherein lamp array is put
It is placed on left solar cell lamina lateralis processus pterygoidei and posts 0.5-1.5m in front of the one side of cell piece, lamp array face is parallel with driving mechanism axis；?
It in the step, is illustrated by taking left solar cell lamina lateralis processus pterygoidei as an example, for any one solar cell wing to be measured, the lamp array is put
The 0.5-1.5m in front of the one side that device posts cell piece.
Step 2: opening equipment power supply (such as 28V source of stable pressure) to driving mechanism, parallel regulator, power management
Each device power of the meeting road of device and spacecraft load, in the case where powering on, the application software of main control computer issues the
One goes code to connect ground regulated power supply (such as 100V) and connect the de- slotting-power of ground regulated power supply-illumination access device-
Manager-spacecraft load supply access；
Step 3: ground regulated power supply (such as 100V source of stable pressure) is opened, so that ground regulated power supply (100V pressure stabilizing electricity
Source) by illumination access device-it is de- insert-power manager gives spacecraft load supplying, the application software on main control computer is adopted
Collect the parameter of the current supply circuit to obtain reference value, required parameter such as " parameter used in illumination path testing method " portion
Described in point；
Step 4: when parameter is correct, with sun optical analog lamp array, (brightness regulation of lamp array is by lamp array electricity after checking
Source control cabinet is controlled such that corresponding cold xenon lamp shines) the solar cell lamina lateralis processus pterygoidei of irradiation posts the one side 2s of cell piece
After~5s, main control computer acquire the solar cell wing-driving mechanism-parallel regulator-power manager and spacecraft load
The test parameter of current supply circuit and charge circuit in the correct situation of parameter, is sentenced by the parameter compared with corresponding reference value
It is set to the current supply circuit connection reliably and enters step 5, meanwhile, it closes ground regulated power supply and makes 100V regulated power supply-light
It is closed according to the power on the supply access of the de- slotting-power manager-spacecraft load of access device-；
Step 5: after continuing illumination 10s~25s, the test parameter of the application software acquisition charge circuit of main control computer,
The test parameter is judged whether the test parameter of charge circuit is correct compared with corresponding reference value, in the survey of charge circuit
It tries in the correct situation of parameter, then shows the load of left wing's outside plate-driving mechanism-parallel regulator-power manager-spacecraft
Power supply, charging path have been reliably connected.
Step 6: ground regulated power supply (such as the ground 100V regulated power supply) power supply is opened, so that ground regulated power supply (ratio
Such as 100V regulated power supply) by illumination access device-it is de- insert-power manager gives spacecraft load supplying；By lamp array operator
Member closes lamp array, and the solar cell piece of the solar cell wing to be illuminated is made to pass through driving mechanism-parallel regulator-power manager
It is closed to the supply access that spacecraft loads；
Step 7: ground regulated power supply (100V regulated power supply) power supply is closed, so that ground regulated power supply (100V pressure stabilizing electricity
Source) by illumination access device-it is de- insert-power manager closes to spacecraft load supplying power；
Step 8: opening equipment power supply (such as 28V source of stable pressure) power supply, main control computer passes through illumination highway device
The power manager transmission pressure stabilizing supply relay open command on spacecraft, disconnection ground regulated power supply (such as 100V pressure stabilizing
Power supply) the de- supply access for inserting the load of-power manager-spacecraft of-illumination access device-；
Step 9: terminating test, removes and receive illumination path testing system.
Claims (8)
1. illumination path testing system, for testing the solar cell wing-driving mechanism-parallel regulator-function of low orbit spacecraft
Rate manager-power supply of spacecraft load, charge circuit, which includes main control computer, ground pressure stabilizing
Power supply and lamp array equipment, wherein
The main control computer is equipped with application software, the application software issue first go code or the first open command with
So that ground regulated power supply-driving mechanism-parallel regulator-power manager and spacecraft load current supply circuit and charge back
Road connects or disconnects, and in the case where connection, which obtains the parameter of current supply circuit and charge circuit to be joined
Examine value；
The application software of the main control computer generates brightness control instruction and to transmit this bright in the correct situation of the reference value
Spend control instruction so that the lamp array equipment generates the simulated solar irradiation for irradiating the solar cell wing, which generates the
Two go code or the second open command is so that the solar cell wing-driving mechanism-parallel regulator-power manager and boat
The current supply circuit and charge circuit of its device load connect or disconnect, and in the case, the application software acquires the power supply and returns
The parameter of road and charge circuit is to obtain test parameter；
The more corresponding test parameter of main control computer and corresponding reference value are not more than reference value in test parameter
In the case where, determine that the connection in the circuit is reliable, in the case where test parameter is greater than corresponding reference value, determines the circuit
It is unreliable to connect.
2. illumination path testing system as described in claim 1, which is characterized in that the lamp array equipment includes sun optical analog
Lamp array and lamp array power controling box, wherein sun optical analog lamp array uses the air-cooled xenon lamp forming array of long arc, the lamp array power supply
Control cabinet is connected to day sunlight simulation lamp array, including several lamp array brightness regulating buttons, and the regulation button is by the brightness
Control instruction control is so that the corresponding cold xenon lamp in the lamp array shines.
3. illumination path testing system as claimed in claim 2, which is characterized in that the lamp array equipment further includes lamp array lifting
Vehicle, the lamp array lift truck include lifting device and control device, and the sun optical analog lamp array connects the lifting device；Institute
Control device is stated to receive the climb command and control the lifting device and rise so that the rising of sun optical analog lamp array, receives
The decline instructs and controls the lifting device decline so that the sun optical analog lamp array declines.
4. charging and powering between the load of the testing solar battery wing-driving mechanism-parallel regulator-power manager-spacecraft
The method that circuit is reliably connected, characterized in that this method comprises the following steps:
S1, the test macro and the solar cell wing, driving mechanism, parallel regulator, power manager and spacecraft are loaded
Connection, wherein sun optical analog lamp array is placed in solar cell lamina lateralis processus pterygoidei to be illuminated and posts 0.5- in front of the one side of cell piece
1.5m, lamp array face are parallel with driving mechanism axis；
S2, it is powered by equipment power supply so that time that driving mechanism, parallel regulator, power manager and spacecraft load
Each device power of road, in the case where powering on, the application software of the main control computer of test macro, which issues first and connects, to be referred to
It enables to connect the supply access of the de- slotting-power manager-spacecraft load of ground regulated power supply-, the application of main control computer
Software send the first open command with disconnect the current supply circuit of the de- slotting power manager of ground regulated power supply-and spacecraft load and
Charge circuit；
S3, ground regulated power supply is opened, so that ground regulated power supply gives spacecraft load supplying by de- slotting-power manager,
Application software on main control computer acquires the parameter of the current supply circuit to obtain reference value；
S4, main control computer application software provide reference range, with sun optical analog lamp array irradiate the solar cell wing outside
After plate posts one side 2s~5s of cell piece, main control computer acquires the solar cell wing-driving mechanism-parallel regulator-power
The test parameter of the current supply circuit and charge circuit of manager and spacecraft load, compares the test parameter and phase of the current supply circuit
The reference value answered determines that the current supply circuit is reliably connected and enters step S5 in the correct situation of parameter, conversely, continuing
Step S4；Meanwhile it closing ground regulated power supply and making 100V regulated power supply-illumination access device-is de- to insert-power manager-boat
Power on the supply access of its device load is closed；
After S5, continuation illumination 10s~25s, application software acquires the solar cell wing-driving mechanism-parallel regulator-power management
Device and spacecraft load current supply circuit and charge circuit test parameter, by the test parameter compared with corresponding reference value and
Judge whether the test parameter of charge circuit is correct, in the correct situation of parameter of charge circuit, judges the charge circuit
It is reliably connected.
5. the testing solar battery wing-driving mechanism-parallel regulator-power manager-spacecraft according to claim 4
Charge the method being reliably connected with current supply circuit between load, characterized in that the method also includes following steps:
S6, the power supply of ground regulated power supply is opened, so that ground regulated power supply inserts-power manager by the way that illumination access device-is de-
Give spacecraft load supplying；Lamp array is closed by lamp array operator, so that the solar cell piece of the solar cell wing to be illuminated is logical
Mechanism-parallel regulator-power manager of overdriving is closed to the supply access that spacecraft loads；
S7, the power supply of ground regulated power supply is closed, so that ground regulated power supply inserts-power manager by the way that illumination access device-is de-
It is closed to spacecraft load supplying power；
S8, the power supply of ground source of stable pressure is opened, the application software of main control computer is sent first and disconnected by illumination test equipment to be referred to
It enables to disconnect the current supply circuit of ground regulated power supply-driving mechanism-parallel regulator-power manager and spacecraft load and fill
Electrical circuit；
S9, terminate test, remove and receive illumination path testing system.
6. the testing solar battery wing-driving mechanism-parallel regulator-power manager-boat according to claim 4 or 5
Charging and the method that is reliably connected of current supply circuit between the load of its device, characterized in that the test macro include main control computer,
Ground regulated power supply, illumination highway device and lamp array equipment, wherein
The main control computer is equipped with application software, the application software issue first go code or the first open command with
So that the de- slotting-power manager of ground regulated power supply-and the current supply circuit and charge circuit of spacecraft load connect or disconnect,
In the case where connection, which obtains the parameter of current supply circuit and charge circuit to obtain reference value；
The application software of the main control computer is generated by lamp array equipment under the reference range and irradiates the solar cell
The simulated solar irradiation of the wing, the application software acquisition solar cell wing-driving mechanism-parallel regulator-power manager and boat
The current supply circuit of its device load and the parameter of charge circuit, to obtain test parameter；
The more corresponding test parameter of main control computer and corresponding reference range, test parameter is in reference value model
When enclosing interior, determine that the connection in the circuit is reliable, when test parameter exceeds corresponding reference range, determines the circuit connection not
Reliably.
7. illumination path testing system as claimed in claim 6, which is characterized in that the lamp array equipment includes sun optical analog
Lamp array, lamp array power controling box and lamp array lift truck, wherein sun optical analog lamp array uses the air-cooled xenon lamp forming array of long arc,
The lamp array power controling box is connected to day sunlight simulation lamp array, including several lamp array brightness regulating buttons, the adjusting are pressed
Button is controlled by the brightness control instruction so that the corresponding cold xenon lamp in the lamp array shines.
8. illumination path testing system as claimed in claim 7, which is characterized in that the lamp array equipment further includes lamp array lifting
Vehicle, the lamp array lift truck include lifting device and control device, and the sun optical analog lamp array connects the lifting device；Institute
Control device is stated to receive the climb command and control the lifting device and rise so that the rising of sun optical analog lamp array, receives
The decline instructs and controls the lifting device decline so that the sun optical analog lamp array declines.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811518289.0A CN109606752B (en) | 2018-12-12 | 2018-12-12 | Method and system for testing illumination path of low-orbit spacecraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811518289.0A CN109606752B (en) | 2018-12-12 | 2018-12-12 | Method and system for testing illumination path of low-orbit spacecraft |
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| CN109606752A true CN109606752A (en) | 2019-04-12 |
| CN109606752B CN109606752B (en) | 2021-12-21 |
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Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08244699A (en) * | 1995-03-08 | 1996-09-24 | Toshiba Corp | Space navigation body |
| CN101950002A (en) * | 2010-08-13 | 2011-01-19 | 航天东方红卫星有限公司 | Comprehensive test method of small satellite power subsystem |
| US7965049B2 (en) * | 2008-06-23 | 2011-06-21 | King Enertech Systems Corp. | Electric energy control circuit for solar power illumination system |
| CN103279077A (en) * | 2013-04-25 | 2013-09-04 | 上海卫星工程研究所 | Ground power supply intelligent control system for satellite electrical test |
| CN103841736A (en) * | 2013-11-27 | 2014-06-04 | 北京卫星环境工程研究所 | Automatic control system and method of multiple solar irradiation xenon lamps in simulation space environment |
| CN104375502A (en) * | 2014-11-13 | 2015-02-25 | 中国科学院光电研究院 | Ground testing system suitable for power source controller of stratospheric airship |
| CN104503421A (en) * | 2014-10-30 | 2015-04-08 | 航天东方红卫星有限公司 | Test system used for satellite power supply and distribution system |
| CN105577117A (en) * | 2015-12-08 | 2016-05-11 | 上海空间电源研究所 | Solar cell array illumination test device and method |
| CN106569147A (en) * | 2016-10-31 | 2017-04-19 | 航天东方红卫星有限公司 | Moonlet power supply sub-system test method based on lithium ion storage battery pack |
| CN107140233A (en) * | 2017-04-07 | 2017-09-08 | 中国人民解放军国防科学技术大学 | Ground simulation satellite and the rocket integrated multi-functional structural aircraft |
| CN107294496A (en) * | 2017-05-16 | 2017-10-24 | 上海卫星工程研究所 | Solar battery array lighting test method on satellite |
| US9815573B2 (en) * | 2014-09-01 | 2017-11-14 | James Joshua Woods | Solar energy conversion and transmission system and method |
| CN108649896A (en) * | 2018-05-16 | 2018-10-12 | 中国科学院光电研究院 | A kind of test system of stratospheric airship photovoltaic cycle energy system |
-
2018
- 2018-12-12 CN CN201811518289.0A patent/CN109606752B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08244699A (en) * | 1995-03-08 | 1996-09-24 | Toshiba Corp | Space navigation body |
| US7965049B2 (en) * | 2008-06-23 | 2011-06-21 | King Enertech Systems Corp. | Electric energy control circuit for solar power illumination system |
| CN101950002A (en) * | 2010-08-13 | 2011-01-19 | 航天东方红卫星有限公司 | Comprehensive test method of small satellite power subsystem |
| CN103279077A (en) * | 2013-04-25 | 2013-09-04 | 上海卫星工程研究所 | Ground power supply intelligent control system for satellite electrical test |
| CN103841736A (en) * | 2013-11-27 | 2014-06-04 | 北京卫星环境工程研究所 | Automatic control system and method of multiple solar irradiation xenon lamps in simulation space environment |
| US9815573B2 (en) * | 2014-09-01 | 2017-11-14 | James Joshua Woods | Solar energy conversion and transmission system and method |
| CN104503421A (en) * | 2014-10-30 | 2015-04-08 | 航天东方红卫星有限公司 | Test system used for satellite power supply and distribution system |
| CN104375502A (en) * | 2014-11-13 | 2015-02-25 | 中国科学院光电研究院 | Ground testing system suitable for power source controller of stratospheric airship |
| CN105577117A (en) * | 2015-12-08 | 2016-05-11 | 上海空间电源研究所 | Solar cell array illumination test device and method |
| CN106569147A (en) * | 2016-10-31 | 2017-04-19 | 航天东方红卫星有限公司 | Moonlet power supply sub-system test method based on lithium ion storage battery pack |
| CN107140233A (en) * | 2017-04-07 | 2017-09-08 | 中国人民解放军国防科学技术大学 | Ground simulation satellite and the rocket integrated multi-functional structural aircraft |
| CN107294496A (en) * | 2017-05-16 | 2017-10-24 | 上海卫星工程研究所 | Solar battery array lighting test method on satellite |
| CN108649896A (en) * | 2018-05-16 | 2018-10-12 | 中国科学院光电研究院 | A kind of test system of stratospheric airship photovoltaic cycle energy system |
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