CN105186671B - A kind of pair of cabin combined type spacecraft joint electric power system and method - Google Patents
A kind of pair of cabin combined type spacecraft joint electric power system and method Download PDFInfo
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- CN105186671B CN105186671B CN201510677252.2A CN201510677252A CN105186671B CN 105186671 B CN105186671 B CN 105186671B CN 201510677252 A CN201510677252 A CN 201510677252A CN 105186671 B CN105186671 B CN 105186671B
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Abstract
The present invention provides a kind of pair of cabin combined type spacecraft joint electric power system and method, and wherein system includes：Rise cabin power-supply system and landing module power-supply system；Wherein, rising cabin power-supply system includes：First solar battery array, the first charging shunting adjustment module, electric discharge adjustment module and batteries；Landing module power-supply system includes：Second solar battery array and the second charging shunting adjustment module；The supply object of double cabin combined type spacecraft joint electric power systems is each load in spacecraft, and load includes：Rise the full regulation bus load in cabin and do not adjust bus load, and the full regulation bus of landing module loads and not adjusted bus load.The double cabin combined type spacecrafts joint electric power system and method that the present invention is provided can either ensure power demands, power demands when also ensure that cabin independence flight when spacecraft combines flight.
Description
Technical field
The invention belongs to spacecraft power supply systems design area, more particularly to a kind of pair of cabin combined type spacecraft joint power supply
System and method.
Background technology
Double cabin combination spacecrafts are a kind of common forms of spacecraft, in retrievable satellite, airship, moon exploration program
It is widely used.As space exploration goal task becomes increasingly abundant, visited especially using space station as the manned space flight of representative
Survey task, and using moon landing, make an inspection tour exploration, sampling return task as representative survey of deep space task, often using double cabin groups
Conjunction mode completes predetermined detection mission.China's retrievable satellite and the serial airship of Shenzhou typically by orbital module, propelling module and are returned
Return device composition, No. three detectors of the goddess in the moon are made up of lander with rover, No. five detectors of the goddess in the moon by orbiter, orbital vehicle, lander, on
Rise device, the device of recoverable capsule four composition.In addition, generally being visited in the survey of deep space task such as mars exploration by carrying to land around detector
Survey device, such as No. 2 tasks of Mars Express and harrier, both complete the detection to target celestial body jointly.
After conventional spacecraft is entered the orbit via delivery transmitting, combination form change will not typically occur during task, its electricity
Source system is also usually independent electric power supply.Double cabins combine spacecraft different phase during task and complete different task, can go out
The combination form change such as existing cabin separation, spacecrafts rendezvous, and have different power demands also according to task arrangement between each cabin, therefore,
Double cabin combination spacecraft power supply system designs are increasingly complex, it is necessary to carry out targeted design according to task feature.
For independent Spaceflight device, about 95% spacecraft uses solar battery array-batteries power-supply system both at home and abroad,
Illumination period is powered from solar battery array and to battery charging, and the shade phase is powered by batteries, ensures full duty cycle boat
The power demands of its device.
For double cabin combined type spacecrafts, the power supply mode between each cabin needs to be designed according to the task in each cabin.By
Launch cost is directly affected in the weight of spacecraft, it is therefore desirable to which the combined type spacecraft that there is associated working pattern is joined
Power-supply service is closed, the means such as equipment and array signal processing is taken into full account, realizes the purpose of loss of weight.
Double cabin combination spacecraft power supply modes can substantially be divided into 3 classes at present：1) power supply relation is not present between cabin, each cabin is only
Vertical power supply meets respective loading demand；2) unidirectionally powered between cabin, during the combination flight of cabin, a cabin is supplied by other cabin completely
Electricity；3) bidirectional power supply between cabin, bidirectional power supply includes two kinds of situations again, one is the grid-connected power supply that complements one another, second is joint
Power supply.It is exactly that two-way confession is realized by grid-connected power supply between U.S.'s power-supply system and Russian power-supply system in international space station
Electricity, is also to be realized by grid-connected power supply mode by tiangong-1 target between China's tiangong-1 target aircraft and the Shenzhou spacecraft
Aircraft is powered between the Shenzhou spacecraft.
By taking the joint power supply mode of space station power as an example, international space station power-supply system composition frame chart such as Fig. 1 institutes
Show, a set of 28V DC power systems that a set of 120V DC power systems (USOS) comprising U.S.'s construction and Russia build
(FGB).It can be interconnected between 2 sets of power-supply systems and allow mutually to carry out power transmission.2 sets of power-supply systems use solar cell
Battle array-batteries power-supply system, illumination period is powered by solar battery array and carries out charging energy-storing to batteries, and the shade phase is by storing
Battery pack is powered.The power-supply system in the U.S. provides about 78kW power, and Russian power-supply system provides about 29kW power.It is logical
In the case of often, 2 sets of power-supply systems meet respective loading demand respectively.When need progress complement each other power supply when, international space station
In there are two kinds of equipment to realize the transmission of two sets of power-supply system energy of US and Russia and the conversion of bus system.Converted by a voltage-dropping type
Device ARCU (American-to-Russian Converter Unit) realizes that the high pressure from USOS to FGB is changed to low pressure, leads to
A boost converter RACU (Russian-to-American Converter Unit) is crossed to realize by the low of FGB to USOS
It is pressed onto high pressure conversion.
It can be seen that being powered combining between 2 cabins to realize, it is necessary to carry out voltage change by ARCU and RACU
Realization is changed, on the one hand making the power-supply system weight of space station increases, be on the one hand because increase power conversion link is also increased
System heat consumption simultaneously reduces reliability.
The content of the invention
To solve the above problems, the present invention provides a kind of pair of cabin combined type spacecraft joint electric power system and method, can
Enough ensure power demands, power demands when also ensure that cabin independence flight during spacecraft combination flight.
Double cabin combined type spacecrafts joint electric power system of the present invention, it includes：Rise cabin power-supply system and landing module electricity
Source system；Wherein, rising cabin power-supply system includes：First solar battery array, the first charging shunting adjustment module, electric discharge regulation mould
Block and batteries；Landing module power-supply system includes：Second solar battery array and the second charging shunting adjustment module；Double cabin combinations
The supply object of formula spacecraft joint electric power system is each load in spacecraft, wherein load includes：Rise the full regulation in cabin
Bus loads and not adjusted bus load, and the full regulation bus of landing module loads and do not adjusted bus load；
Annexation is：
The anode lead-out wire of first solar battery array is the first full regulation bus, and negative terminal lead-out wire is the first power supply loop line；
The full regulation bus load in the first charging shunting adjustment module and rising cabin is serially connected in the first full regulation bus and first and supplied respectively
Between electric loop line；The anode lead-out wire of batteries does not adjust bus for first, and the negative terminal lead-out wire of batteries and first supply
Electric loop line connection, the bus load that do not adjust for rising cabin is serially connected in first and not adjusted between bus and the first power supply loop line respectively；
Electric discharge adjustment module is serially connected between the first full regulation bus and battery anode, and the first full regulation bus is output to battery
On electric current be adjusted；
The anode lead-out wire of second solar battery array is the second full regulation bus, and negative terminal lead-out wire is the second power supply loop line；
The anode lead-out wire of second charging shunting adjustment module does not adjust bus for second, and negative terminal is connected with the second power supply loop line；Land
The full regulation bus load in cabin is serially connected between the second full regulation bus and the second power supply loop line respectively, and landing module does not adjust mother
Linear load is serially connected in second and not adjusted between bus and the second power supply loop line respectively；
By adjusting bussed supply cable connection entirely between first full regulation bus and the second full regulation bus；First is uncomfortable
Section bus and second is not adjusted between bus by not adjusting bussed supply cable connection entirely；First power supply looping-in cable and second
Connected between power supply looping-in cable by looping-in cable, and full regulation bussed supply cable, full regulation bussed supply cable and
Cable between the cabin of the double cabin combined type spacecrafts of looping-in cable composition；
Wherein, the first charging shunting adjustment module does not adjust many on bus for consuming the first full regulation bus and first
Aftercurrent, all loads to rise cabin, which provide to meet the electric current of load request and provide for batteries, meets charging electric rate
The electric current of demand；
Under work in combination pattern, the second charging shunting adjustment module is used to consume cable, the second full regulation bus between cabin
Unwanted currents on bus are not adjusted with second, are provided for all loads in two cabins and are met the electric current of load request and be batteries
The electric current for meeting charging electric rate demand is provided；
Under the pattern of working independently, the second charging shunting adjustment module is uncomfortable for the full regulation bus of consumption second and second
The unwanted currents on bus are saved, provides for all loads of landing module and meets the electric current of load request.
The present invention also provides a kind of method of supplying power to of the electric power system based on described in claim 1, and it includes：
Step 1, double cabin combined type spacecrafts are from transmitting to lunar surface active section, and the supplier of electricity before lunar surface and the separation of double cabins
Formula is work in combination pattern, and the particular content of the assembly mode of operation is：
1) illumination period：
The first solar battery array for rising cabin does not work, and the second solar battery array of landing module is plus the batteries for rising cabin
Constitute joint powering mode, i.e. the second solar battery array power output and be divided into 2 parts：A part is the full regulation bus of landing module
Load and do not adjust bus load supplying；A part by adjusting bussed supply cable and not adjusting bussed supply cable point entirely entirely
The full regulation bus load in cabin Wei not risen and bus load supplying is not adjusted；
If the second solar battery array power output of landing module is more than all load aggregate demands in two cabins but less than or equal to two
All load aggregate demands in cabin add battery charging power demand, then by electric between cabin while load supplying all for two cabins
Cable is battery charging；If the second solar battery array power output of landing module is more than all load aggregate demands in two cabins and electric power storage
Pond group charge power demand, then it is all load supplyings in two cabins and storage again to be shunted by the second charging after adjustment module is shunted
Battery pack charges；
2) the shade phase：
Second solar battery array of the first solar battery array and landing module that rise cabin does not work, and detector is by rising cabin
Batteries power, i.e., batteries power output is divided into 4 parts：Do not adjust bus load of the part to rise cabin is supplied
Electricity；A part after adjustment module of discharging by rising the full regulation bus load supplying in cabin；A part adjusts female entirely by not
Line cable does not adjust bus load supplying for landing module；A part is female by adjusting the full regulation that bus cable is landing module entirely
Linear load is powered；
Step 2, after the rising cabin of double cabin combined type spacecrafts is separated with landing module, landing module works in lunar surface, on
Rise cabin and leave lunar surface, power supply mode is single nacelle mode of operation, and the particular content of single nacelle mode of operation is：
(1) landing module：
Illumination period, the second solar battery array power output loads for the full regulation bus load of landing module with bus is not adjusted
Power supply；If the second solar battery array power output is more than all load aggregate demands of landing module, pass through the second charging shunt regulating
Module shunted after again for landing module full regulation bus load and do not adjust bus load supplying；
The shade phase, landing module does not work；
(2) rise cabin to run to track designation, the first solar array extending constitutes the first solar battery array and electric power storage
Pond group joint powering mode, specific power supply content is as follows：
Illumination period, the first solar battery array as power supply source, its power output for rise cabin the load of full regulation bus and
Bus load supplying is not adjusted, if solar battery array power output, which is more than, rises cabin load aggregate demand but less than or equal to rising cabin
Load aggregate demand adds battery charging power demand, then is battery charging while load supplying all for rising cabin；
If solar battery array power output, which is more than, rises cabin load aggregate demand and battery charging power demand, pass through the first charging
Shunt regulating module is battery charging while being and rise all load supplyings in cabin again after being shunted；
The shade phase, rise the batteries in cabin as power supply, power output is divided into 2 parts：A part is directly rising cabin
Do not adjust bus load supplying；A part passes through full regulation bus load supplying of the adjustment module for rising cabin that discharge.
Beneficial effect：
A kind of pair of cabin disclosed by the invention combined type spacecraft joint method of supplying power to and system, pass through batteries, electric discharge
Adjustment module time-sharing multiplex realizes assembly joint power supply, can either ensure power demands when spacecraft combines flight, also can
Ensure power demands during the independence flight of cabin, both optimized power system design between spacecraft module, and also reached reduction spacecraft power supply
The purpose of system weight.And spacecraft power supply system can be mitigated by batteries, electric discharge adjustment module time-sharing multiplex
Weight, reaches the purpose for saving Spacecraft Launch cost.
Brief description of the drawings
Fig. 1 is the space station electrical schematic of prior art；
Fig. 2 is double cabin combination spacecraft joint electric power system schematic diagrames；
Fig. 3 is double cabin combination spacecraft illumination period joint electric power system schematic diagrames；
Fig. 4 is double cabin combination spacecraft shade phase joint electric power system schematic diagrames；
Fig. 5 is rising cabin electric power system schematic diagram after the separation of cabin；
Fig. 6 is landing module electric power system schematic diagram after the separation of cabin.
Embodiment
Certain lunar orbiter is main to complete moon surface sample and lunar surface comprising cabin (the first cabin) and landing module (the second cabin) is risen
Take off task.Wherein the first cabin is main cabin, it is desirable under assembly offline mode or solo hop pattern can in illumination and
Worked under the alternate rail conditions of shade, cabin supplemented by the second cabin can be in illumination and the alternate rail of shade under combination bulk-mode
Worked under the conditions of road, only work or do not work in illumination period after being separated in cabin.
The present invention provides a kind of pair of cabin combined type spacecraft joint electric power system, and it includes：Rise cabin (the first cabin) power supply
System and landing module (the second cabin) power-supply system；As shown in Figure 2.Rising cabin (the first cabin) power-supply system includes：First sun electricity
Chi Zhen, the first charging shunting adjustment module, electric discharge adjustment module, batteries.Landing module (the second cabin) power-supply system includes：The
Two solar battery arrays, the second charging shunting adjustment module.Supply object is each load in spacecraft, wherein load includes：On
The full regulation bus load in liter cabin is loaded with bus is not adjusted, and the full regulation bus load of landing module is born with bus is not adjusted
Carry.
The annexation between each element in joint powersupply system is：
The anode lead-out wire of first solar battery array is the first full regulation bus, and negative terminal lead-out wire is the first power supply loop line；
First charging shunting adjustment module and rise the full regulation bus in cabin and load 1~n and be serially connected in first respectively and adjust bus and the entirely
Between one power supply loop line；The anode lead-out wire of batteries is first not adjust bus, the negative terminal lead-out wire of batteries and the
One power supply loop line connection, the bus that do not adjust for rising cabin loads 1~m and is serially connected in first respectively and does not adjust bus and first and powers back
Between line；Electric discharge adjustment module is serially connected between the first full regulation bus and battery anode, is output to first to battery complete
Electric current on regulation bus is adjusted；
The anode lead-out wire of second solar battery array is the second full regulation bus, and negative terminal lead-out wire is the second power supply loop line；
The anode lead-out wire of second charging shunting adjustment module does not adjust bus for second, and negative terminal is connected with the second power supply loop line；Land
Full regulation bus the load 1 '~n ' in cabin is serially connected between the second full regulation bus and the second power supply loop line respectively, and landing module is not
Regulation bus load 1 '~m ' is serially connected in second and not adjusted between bus and the second power supply loop line respectively；
By adjusting bussed supply cable connection entirely between first full regulation bus and the second full regulation bus；First is uncomfortable
Section bus and second is not adjusted between bus by not adjusting bussed supply cable connection entirely；First power supply looping-in cable and second
Connected between power supply looping-in cable by looping-in cable.It is complete to adjust bussed supply cable, do not adjust bussed supply cable, loop line entirely
Cable between cable composition cabin；
Wherein, the first charging shunting adjustment module does not adjust many on bus for consuming the first full regulation bus and first
Aftercurrent, all loads to rise cabin, which provide to meet the electric current of load request and provide for batteries, meets charging electric rate
The electric current of demand；
Under work in combination pattern, the second charging shunting adjustment module is used to consume cable, the second full regulation bus between cabin
Unwanted currents on bus are not adjusted with second, are provided for all loads in two cabins and are met the electric current of load request and be batteries
The electric current for meeting charging electric rate demand is provided；
Under the pattern of working independently, the second charging shunting adjustment module is uncomfortable for the full regulation bus of consumption second and second
The unwanted currents on bus are saved, provides for all loads of landing module and meets the electric current of load request；
Under the pattern of working independently, the electric current that electric discharge adjustment module is output to battery on the first full regulation bus is carried out
Regulation, loads 1~n and provides to rise the full regulation bus in cabin and meet the electric current of load request；
Under work in combination pattern, electric discharge adjustment module battery is output to electric current on the first full regulation bus and
The electric current being output to by adjusting bus cable entirely on the second full regulation bus is adjusted, so that female for the full regulation for rising cabin
Full regulation bus load 1 '~n ' of 1~n of linear load and landing module provides the electric current for meeting load request.
The present invention also provides the method for supplying power to that a kind of pair of cabin combined type spacecraft combines electric power system, including：
Step 1, lunar orbiter is from transmitting to lunar surface active section, and the first solar battery array for rising cabin (the first cabin) is in
Rounding state, it is impossible to be used in generate electricity, the second solar battery array of landing module (the second cabin) is in expansion generating state.The now moon
Detector power by landing module (the second cabin) the second solar battery array and rise the connection that constitutes of batteries in cabin (the first cabin)
Close power supply and electric energy is provided, and joint power supply is realized by being multiplexed batteries and electric discharge adjustment module.
Power supply mode is work in combination pattern, and the particular content of the assembly mode of operation is：
1) illumination period：
Second solar battery array of landing module (the second cabin) combines powering mode plus the batteries for rising cabin (the first cabin),
As shown in Figure 3.Second solar battery array power output of landing module (the second cabin) is divided into 2 parts：A part is landing module (second
Cabin) full regulation bus load 1 '~n ' and do not adjust bus load 1 '~m ' power；A part is rising by cable between cabin
The full regulation bus in cabin (the first cabin) loads 1~n and does not adjust 1~m of bus load and powers；
Such as the second solar battery array power output of landing module (the second cabin) be more than two cabins load aggregate demand but be less than or
In two cabins load aggregate demand add battery charge power demand, then be by cable between cabin while for two cabin load supplyings on
Rise the battery charging in cabin (the first cabin)；Always needed as landing module (the second cabin) solar battery array power output is more than the load of two cabins
Summation battery charging power demand, then it is all loads in two cabins again to be shunted by the second charging after adjustment module is shunted
Power and charged for battery.
2) the shade phase：
Shade phase detector by rise cabin (the first cabin) batteries power, electrical schematic as shown in figure 4,.Electric power storage
Pond group power output is divided into 4 parts：It is a part of directly to be powered to rise the 1~m of bus load that do not adjust in cabin (the first cabin)；One
Divide and powered by discharging adjustment module to rise the 1~n of full regulation bus load in cabin (the first cabin)；A part passes through cable between cabin
Bus load 1 '~m ' power supplies are not adjusted for landing module (the second cabin)；A part passes through cable between cabin after overdischarge adjustment module
For full regulation bus load 1 '~n ' power supplies of landing module (the second cabin).
Step 2, lunar orbiter rises cabin (the first cabin) and passes through cabin with landing module (the second cabin) before lunar surface, cabin separation
Between cable carry out joint power supply, specific power supply content synchronization rapid 2.Lunar orbiter rises in cabin (the first cabin) before lunar surface takes off
Separated with landing module (the second cabin), landing module (the second cabin) works in lunar surface, rise cabin (the first cabin) and leave lunar surface, power
Mode is single nacelle mode of operation.
Landing module (the second cabin), which is only required, after separation (i.e. to be worked in the work of the daytime moon during the second solar battery array generating).
Landing module (the second cabin) electrical schematic is as shown in fig. 6, specifically power supply content is as follows：
1) illumination period, the second solar battery array power output of landing module (the second cabin) is the full tune of landing module (the second cabin)
Section bus loads 1 '~n ' and does not adjust bus load 1 '~m ' power supplies；Always needed as solar battery array power output is more than load
Ask, then by second charging shunt adjustment module shunted after again for landing module (the second cabin) full regulation bus load 1 '~
N ' and do not adjust bus load 1 '~m ' power supply.
2) the shade phase, due to landing module (the second cabin) no storage battery group, landing module (the second cabin) does not work.
Rise after cabin (the first cabin) operation to track designation, rise first solar array extending in cabin (the first cabin), on
Liter cabin (the first cabin) constitutes the solar battery array of itself and combines powering mode with batteries.Rise cabin (the first cabin) power supply signal
Figure is as shown in figure 5, specifically power supply content is as follows：
3) illumination period, rises first solar battery array in cabin (the first cabin) as power supply source, its power output is rising cabin
(the first cabin) adjusts bus 1~n of load and does not adjust 1~m of bus load and power entirely, and such as solar battery array power output, which is more than, to be born
Carry aggregate demand but add battery charge power demand less than or equal to cabin load aggregate demand is risen, be then all loads in rising cabin
It is the battery charging for rising cabin (the first cabin) while power supply；Rise cabin load always as solar battery array power output is more than
Demand and battery charging power demand, then it is again rising cabin (the to be shunted by the first charging after adjustment module is shunted
One cabin) bus 1~n of load is adjusted entirely and 1~m of bus load is not adjusted powers, and be battery charging.
4) the shade phase, the batteries in cabin (the first cabin) are risen as power supply, power output is divided into 2 parts：It is a part of straight
1~the m of bus load that do not adjust for being connected in rising cabin (the first cabin) powers；A part is by discharging adjustment module to rise cabin (the
One cabin) full regulation bus load 1~n power.
Certainly, the present invention can also have other various embodiments, ripe in the case of without departing substantially from spirit of the invention and its essence
Various corresponding changes and deformation, but these corresponding changes and change ought can be made according to the present invention by knowing those skilled in the art
Shape should all belong to the protection domain of appended claims of the invention.
Claims (2)
1. a kind of pair of cabin combined type spacecraft joint electric power system, it is characterised in that including：Rise cabin power-supply system and landing module
Power-supply system；Wherein, rising cabin power-supply system includes：First solar battery array, the first charging shunting adjustment module, electric discharge regulation
Module and batteries；Landing module power-supply system includes：Second solar battery array and the second charging shunting adjustment module；Double cabin groups
The supply object of box-like spacecraft joint electric power system is each load in spacecraft, wherein load includes：Rise the full tune in cabin
Section bus load is loaded with bus is not adjusted, and the full regulation bus of landing module loads and do not adjusted bus load；
Annexation is：
The anode lead-out wire of first solar battery array is the first full regulation bus, and negative terminal lead-out wire is the first power supply loop line；First
The full regulation bus load in charging shunting adjustment module and rising cabin is serially connected in the first full regulation bus and first and powered back respectively
Between line；The anode lead-out wire of batteries does not adjust bus for first, and the negative terminal lead-out wire of batteries and first are powered back
Line connect, rise cabin do not adjust bus load be serially connected in respectively first do not adjust bus and first power supply loop line between；Electric discharge
Adjustment module is serially connected between the first full regulation bus and battery anode, battery is output on the first full regulation bus
Electric current is adjusted；
The anode lead-out wire of second solar battery array is the second full regulation bus, and negative terminal lead-out wire is the second power supply loop line；Second
The anode lead-out wire of charging shunting adjustment module does not adjust bus for second, and negative terminal is connected with the second power supply loop line；Landing module
Full regulation bus load is serially connected between the second full regulation bus and the second power supply loop line respectively, and the bus that do not adjust of landing module is born
Load is serially connected in second and not adjusted between bus and the second power supply loop line respectively；
By adjusting bussed supply cable connection entirely between first full regulation bus and the second full regulation bus；First does not adjust mother
Line and second is not adjusted between bus by not adjusting bussed supply cable connection entirely；First power supply looping-in cable and the second power supply
Connected between looping-in cable by looping-in cable, and adjust bussed supply cable entirely, do not adjust bussed supply cable and loop line entirely
Cable between the cabin of the double cabin combined type spacecrafts of cable composition；
Wherein, the first charging shunting adjustment module does not adjust the unnecessary electricity on bus for the full regulation bus of consumption first and first
Stream, all loads to rise cabin, which provide to meet the electric current of load request and provide for batteries, meets charging electric rate demand
Electric current；
Under work in combination pattern, the second charging shunting adjustment module is used to consuming cable between cabin, the second full regulation bus and the
Two do not adjust the unwanted currents on bus, are provided for all loads in two cabins and meet the electric current of load request and provided for batteries
Meet the electric current of charging electric rate demand；
Under the pattern of working independently, the second charging shunting adjustment module is used for consumption second, and regulation bus and second does not adjust mother entirely
Unwanted currents on line, provide for all loads of landing module and meet the electric current of load request.
2. a kind of method of supplying power to of the electric power system based on described in claim 1, it is characterised in that including：
Step 1, double cabin combined type spacecrafts from transmitting to lunar surface active section, and lunar surface and double cabins separation before power supply mode be
Assembly mode of operation, the particular content of the assembly mode of operation is：
1) illumination period：
The first solar battery array for rising cabin is not worked, and the second solar battery array of landing module is constituted plus the batteries for rising cabin
Joint powering mode, i.e. the second solar battery array power output are divided into 2 parts：A part loads for the full regulation bus of landing module
Bus load supplying is not adjusted；It is a part of to be respectively by adjusting bussed supply cable entirely and not adjusting bussed supply cable entirely
Rise the full regulation bus load in cabin and do not adjust bus load supplying；
If the second solar battery array power output of landing module is more than all load aggregate demands in two cabins but less than or equal to two cabin institutes
There are load aggregate demand plus battery charging power demand, be then by cable between cabin while load supplying all for two cabins
Battery charging；If the second solar battery array power output of landing module is more than all load aggregate demands in two cabins and batteries
Charge power demand, then it is all load supplyings in two cabins and battery again to be shunted by the second charging after adjustment module is shunted
Group charging；
2) the shade phase：
The first solar battery array and the second solar battery array of landing module for rising cabin do not work, and detector is by rising the storage in cabin
Battery-powered, i.e., batteries power output is divided into 4 parts：A part does not adjust bus load supplying for rising cabin；One
Part after adjustment module of discharging by rising the full regulation bus load supplying in cabin；A part by not adjusting bus cable entirely
Bus load supplying is not adjusted for landing module；A part is loaded by adjusting the full regulation bus that bus cable is landing module entirely
Power supply；
Step 2, after the rising cabin of double cabin combined type spacecrafts is separated with landing module, landing module works in lunar surface, rises cabin
Lunar surface is left, power supply mode is single nacelle mode of operation, and the particular content of single nacelle mode of operation is：
(1) landing module：
Illumination period, the second solar battery array power output supplies for the full regulation bus load of landing module with bus load is not adjusted
Electricity；If the second solar battery array power output is more than all load aggregate demands of landing module, pass through the second charging shunt regulating mould
Block shunted after again for landing module full regulation bus load and do not adjust bus load supplying；
The shade phase, landing module does not work；
(2) rise cabin to run to track designation, the first solar array extending constitutes the first solar battery array and batteries
Joint powering mode, specific power supply content is as follows：
Illumination period, the first solar battery array is as power supply source, and its power output is loaded and uncomfortable to rise the full regulation bus in cabin
Bus load supplying is saved, if solar battery array power output, which is more than to rise cabin load aggregate demand but be less than or equal to, rises cabin load
Aggregate demand adds battery charging power demand, then is battery charging while load supplying all for rising cabin；If too
Positive cell array power output, which is more than, rises cabin load aggregate demand and battery charging power demand, then is shunted by the first charging
Adjustment module is battery charging while being and rise all load supplyings in cabin again after being shunted；
The shade phase, rise the batteries in cabin as power supply, power output is divided into 2 parts：A part is directly to rise cabin not
Adjust bus load supplying；A part passes through full regulation bus load supplying of the adjustment module for rising cabin that discharge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510677252.2A CN105186671B (en) | 2015-10-19 | 2015-10-19 | A kind of pair of cabin combined type spacecraft joint electric power system and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510677252.2A CN105186671B (en) | 2015-10-19 | 2015-10-19 | A kind of pair of cabin combined type spacecraft joint electric power system and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105186671A CN105186671A (en) | 2015-12-23 |
| CN105186671B true CN105186671B (en) | 2017-11-03 |
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| CN106410936B (en) * | 2016-08-31 | 2018-08-31 | 航天东方红卫星有限公司 | A kind of large power high efficiency satellite power system based on high-low pressure double-bus |
| CN106787115B (en) * | 2017-01-24 | 2018-11-23 | 上海卫星工程研究所 | The high-power phased array antenna power supply-distribution system design method of polar-orbiting satellite |
| CN107706940B (en) * | 2017-09-30 | 2020-02-18 | 北京空间飞行器总体设计部 | Flexible grid-connected system between bus power supply systems without regulation of spacecraft |
| CN108183513A (en) * | 2017-11-28 | 2018-06-19 | 北京空间技术研制试验中心 | A kind of construction method of spacecraft electric power system |
| CN107968394B (en) * | 2017-12-07 | 2020-07-14 | 北京空间技术研制试验中心 | System construction method for master-slave spacecraft grid-connected power supply |
| CN109038795B (en) * | 2018-07-20 | 2021-06-04 | 上海空间电源研究所 | Power supply separation interlocking protection and soft switching device and method |
| CN109256839B (en) * | 2018-11-01 | 2023-01-06 | 上海埃依斯航天科技有限公司 | Non-attitude stable spacecraft system energy acquisition method |
| CN109787343B (en) * | 2019-02-28 | 2021-03-09 | 中国科学院国家空间科学中心 | Power supply system for active ball falling |
| CN110011297B (en) * | 2019-04-25 | 2021-06-11 | 北京卫星制造厂有限公司 | Two-way dual-mode grid-connected system between spacecrafts |
| CN110854840B (en) * | 2019-11-19 | 2022-06-17 | 北京空间技术研制试验中心 | Grid-connected power supply method of spacecraft grid-connected topological structure based on common bus |
| CN111525545B (en) * | 2020-04-20 | 2021-04-02 | 北京空间飞行器总体设计部 | Two-cabin grid-connected power supply system and method |
| CN111786473B (en) * | 2020-05-22 | 2021-12-07 | 中国空间技术研究院 | Ultrahigh-voltage multi-network hybrid bus power transmission system suitable for space power station |
| CN112027115B (en) * | 2020-07-31 | 2021-10-01 | 北京控制工程研究所 | Landing and ascending spacecraft integrated control system |
| CN112242698B (en) * | 2020-09-25 | 2022-12-09 | 北京空间飞行器总体设计部 | Hundred kilowatt-level spacecraft full-regulation power supply system |
| CN112636444B (en) * | 2020-12-07 | 2022-06-03 | 上海卫星工程研究所 | Double-star combined spacecraft grid-connected power supply and distribution system with fully-regulated unified bus |
| CN113879567B (en) * | 2021-09-06 | 2024-04-02 | 北京空间飞行器总体设计部 | High-reliability composite power supply system applied to Mars landing inspection task |
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| US9356173B2 (en) * | 2012-08-31 | 2016-05-31 | Sandia Corporation | Dynamically reconfigurable photovoltaic system |
| CN102832677A (en) * | 2012-09-29 | 2012-12-19 | 上海空间电源研究所 | Novel current distribution power adjuster for charging satellite power supply system on basis of pulse width modulation |
| CN102946135B (en) * | 2012-12-10 | 2014-12-31 | 上海空间电源研究所 | Joint power-supply control system among detector power subsystems and control method thereof |
| CN103236731B (en) * | 2013-05-03 | 2015-04-29 | 深圳市航天新源科技有限公司 | Power supply controller framework based on separated charge and control method thereof |
| CN103264777B (en) * | 2013-05-24 | 2015-07-08 | 北京空间飞行器总体设计部 | Energy sharing method for two spacecrafts |
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