CN110224456A - A kind of satellite low-power consumption starting power supply system - Google Patents
A kind of satellite low-power consumption starting power supply system Download PDFInfo
- Publication number
- CN110224456A CN110224456A CN201910424926.6A CN201910424926A CN110224456A CN 110224456 A CN110224456 A CN 110224456A CN 201910424926 A CN201910424926 A CN 201910424926A CN 110224456 A CN110224456 A CN 110224456A
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- satellite
- battery
- relay
- rocket
- shunt regulating
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- 230000001105 regulatory effect Effects 0.000 claims abstract description 39
- 239000004065 semiconductor Substances 0.000 claims description 12
- 238000000926 separation method Methods 0.000 claims description 12
- 238000005286 illumination Methods 0.000 claims description 4
- 238000002347 injection Methods 0.000 claims description 4
- 239000007924 injection Substances 0.000 claims description 4
- 230000006641 stabilisation Effects 0.000 claims description 3
- 238000011105 stabilization Methods 0.000 claims description 3
- 230000005611 electricity Effects 0.000 claims description 2
- 238000004146 energy storage Methods 0.000 abstract description 8
- 238000010586 diagram Methods 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 1
- 238000004870 electrical engineering Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0063—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with circuits adapted for supplying loads from the battery
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
- H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells
-
- H02J2007/0067—
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
- Photovoltaic Devices (AREA)
Abstract
The present invention provides a kind of satellite low-power consumption starting power supply system, utilize satellite and the rocket separating switch S1, the switching switch whether relay K1 and battery discharge control module are connected as battery switch module, it whether is simultaneously that the switching that shunt regulating control circuit is powered switchs using relay K2 and K3 as battery, to realize that satellite separates preceding shunt regulating control circuit unpowered with carrier rocket, and satellite separates the function that rear shunt regulating control circuit has normal power supply with carrier rocket, and then reduce its decaying of shunt regulating control circuit quiescent dissipation to energy storage battery before satellite is separated with carrier rocket；It can be seen that one aspect of the present invention improves the reliability of power satellite, on the other hand reduce the demand to satellite energy storage battery capacity, to reduce satellite weight.
Description
Technical field
The invention belongs to electrical engineering field technical field of energy management more particularly to a kind of satellite low-power consumption starting power supplies
System.
Background technique
In order to guarantee that the normal operation of power satellite control circuit, the shunt regulating control circuit of satellite are powered usually by defending
Star energy storage battery provides.Before satellite injection, a few days may be stored in carrier rocket.If taking no action to,
Shunt regulating control circuit is direct and continues to be powered by energy storage battery, and the quiescent dissipation of shunt regulating control circuit may be led
It causes energy storage in battery to be greatly reduced, or even is reduced to zero, this will seriously affect satellite normal operation.
Summary of the invention
To solve the above problems, the present invention provides a kind of satellite low-power consumption starting power supply system, satellite and carrier rocket point
There is normal power supply after separating from preceding control circuit unpowered, satellite with carrier rocket, and then reduces satellite and separated with carrier rocket
Its preceding decaying of shunt regulating control circuit quiescent dissipation to energy storage battery.
A kind of satellite starting power supply system, including battery, battery switch module, satellite and the rocket separating switch S1, battery
Control of discharge module, relay K1~K3, shunt regulating control circuit, shunt regulating main circuit and photovoltaic array；
The battery is used in the conducting of battery switch module, to bussed supply of external satellite；
The satellite and the rocket separating switch S1 is the interface switch of satellite and carrier rocket, and before satellite and the rocket separation, the satellite and the rocket are separated
It closes S1 to be in an off state, after satellite and the rocket separation, satellite and the rocket separating switch S1 is in closed state, then when satellite and the rocket separating switch S1 is closed
It closes, and when relay K1 is connected with battery control of discharge module one of both, battery switch module is connected；
The battery is also used to power when relay K2 or K3 are connected to shunt regulating control circuit；Wherein, relay
The turn-on condition of device K2 and K3 are as follows: the provisioning instruction that external spaceborne computer issues is received after satellite and the rocket separation；
The photovoltaic array is used for when satellite is in area of illumination to bussed supply of external satellite；
The shunt regulating control circuit is used to detect the voltage of bus of external satellite, when bus of external satellite
Voltage when being higher than given threshold, shunt regulating main circuit defends outside for shunting the voltage that photovoltaic array exports
The voltage stabilization of bus of star is in setting range.
Further, the battery switch module includes P-channel metal-oxide-semiconductor Q1, resistance R1~R3, the electric power storage tank discharge
Control module includes triode Q2, resistance R4~R6；
The anode of the source electrode connection battery of the P-channel metal-oxide-semiconductor Q1, drain electrode connection bus of external satellite；Resistance
The one end R3 connects the stationary contact of relay K1 and the collector of triode Q2 simultaneously, and the other end passes through resistance R1 connection P ditch respectively
The source electrode of road metal-oxide-semiconductor Q1 passes through the grid of resistance R2 connection P-channel metal-oxide-semiconductor Q1；The movable contact of relay K1 is separated by the satellite and the rocket
Switch S1 ground connection, and the stationary contact of relay K1 and movable contact default are in attached state；
The emitter of the triode Q2 is grounded, and the both ends of resistance R4 are separately connected the base stage and emitter of triode Q2,
The base stage of the one end resistance R5 connecting triode Q2, upper movable contact of the other end in addition to being directly connected to relay K2, also passes through series connection
The upper movable contact of relay K3 is connected after resistance R6, meanwhile, the lower movable contact of relay K2 and K3 are all connected with the anode of battery；
When satellite and the rocket separation and after satellier injection, external spaceborne computer sends provisioning instruction to relay K2 and K3, then after
The lower movable contact of electric appliance K2 and K3 are respectively with corresponding for connecting the stationary contact of the feeder ear of shunt regulating control circuit
Connection, upper movable contact connect with corresponding stationary contact for receiving the control instruction that external spaceborne computer issues respectively
It connects, then battery is powered to shunt regulating control circuit, and the control instruction controls triode Q2 turn-on and turn-off.
The utility model has the advantages that
The present invention provides a kind of satellite low-power consumption starting power supply system, using satellite and the rocket separating switch S1, relay K1 and
The switching switch whether battery discharge control module is connected as battery switch module, at the same using relay K2 and K3 as
Whether battery is the switching switch of shunt regulating control circuit power supply, shunts tune before satellite is separated with carrier rocket to realize
Save control circuit unpowered and satellite separates the function that rear shunt regulating control circuit has normal power supply with carrier rocket, in turn
Reduce its decaying of shunt regulating control circuit quiescent dissipation to energy storage battery before satellite is separated with carrier rocket；Thus may be used
See, one aspect of the present invention improves the reliability of power satellite, on the other hand reduces the need to satellite energy storage battery capacity
It asks, to reduce satellite weight.
Detailed description of the invention
Fig. 1 is the schematic diagram that a kind of satellite low-power consumption provided by the invention starts power supply system.
Specific embodiment
In order to make those skilled in the art more fully understand application scheme, below in conjunction in the embodiment of the present application
Attached drawing, the technical scheme in the embodiment of the application is clearly and completely described.
Referring to Fig. 1, which is a kind of schematic diagram of satellite low-power consumption starting power supply system provided in this embodiment.One kind is defended
Star low-power consumption starts power supply system, which is characterized in that including battery, battery switch module, satellite and the rocket separating switch S1, electric power storage
Tank discharge control module, relay K1~K3, shunt regulating control circuit, shunt regulating main circuit and photovoltaic array.
The battery is used in the conducting of battery switch module, to bussed supply of external satellite.
The satellite and the rocket separating switch S1, relay K1 and battery control of discharge module are for controlling battery switch mould
The conducting of block；Wherein, the satellite and the rocket separating switch S1 is the interface switch of satellite and carrier rocket, and before satellite and the rocket separation, the satellite and the rocket
Separating switch S1 is in an off state, and after satellite and the rocket separation, satellite and the rocket separating switch S1 is in closed state, then when satellite and the rocket separating switch
S1 closure, and when relay K1 is connected with battery control of discharge module one of both, battery switch module is connected.
The battery is also used to power when relay K2 or K3 are connected to shunt regulating control circuit；Wherein, relay
The turn-on condition of device K2 and K3 are as follows: the provisioning instruction that external spaceborne computer issues is received after satellite and the rocket separation.
The photovoltaic array is used for when satellite is in area of illumination to bussed supply of external satellite.
The shunt regulating control circuit is used to detect the voltage of bus of external satellite, when bus of external satellite
Voltage when being higher than given threshold, shunt regulating main circuit is used for the voltage that exports photovoltaic array to bus of external satellite
It is shunted, makes the voltage stabilization of bus of external satellite in setting range.
It should be noted that shunt regulating main circuit and shunt regulating control circuit collectively form satellite power supply controller,
And satellite power supply controller is the key equipment in satellite power system, for by solar battery array, i.e. photovoltaic array to be unstable
Output voltage be converted to a stable busbar voltage of satellite platform, and charge and discharge control is carried out to battery group.Wherein, divide
Stream adjusts main circuit for realizing the flow-dividing control to photovoltaic array, when photovoltaic array output voltage is higher than a busbar voltage
When, shunt regulating main circuit is controlled by shunt regulating control circuit and carries out by-pass shunt, is set until a busbar voltage is lower than
When definite value, shunt regulating main circuit by-pass shunt is forbidden.Therefore, the reliability service and reliable power supply of shunt regulating control circuit are straight
The reliability service for influencing satellite power supply controller and entire satellite power system is connect, and then influences the success or failure of satellite task.
A kind of particular circuit configurations of battery switch module Yu battery control of discharge module are given below, and combine two
The particular circuit configurations of person, conducting to battery switch module, battery control of discharge module and relay K1~K3 and
Shutdown is described further.Wherein, as shown in Figure 1, the battery switch module include P-channel metal-oxide-semiconductor Q1, resistance R1~
R3, the battery control of discharge module include triode Q2, resistance R4~R6.
The anode of the source electrode connection battery of the P-channel metal-oxide-semiconductor Q1, drain electrode connection bus of external satellite, and store
The cathode of battery is grounded；The one end resistance R3 connects the stationary contact of relay K1 and the collector of triode Q2, the other end point simultaneously
Not by the source electrode of resistance R1 connection P-channel metal-oxide-semiconductor Q1, pass through the grid of resistance R2 connection P-channel metal-oxide-semiconductor Q1；Relay K1
Movable contact by satellite and the rocket separating switch S1 be grounded, and the stationary contact of relay K1 and movable contact default be in attached state.
It should be noted that then the voltage at the both ends resistance R1 determines the electricity at Q1 grid source both ends since Q1 is P-channel metal-oxide-semiconductor
Press VGSSize, and work as Q1 grid source both ends voltage VGSReach its cut-in voltage Vth, such as -4V, Q1 can be connected.Therefore, may be used
Guarantee that the partial pressure at the both ends R1 is greater than the cut-in voltage Vth of Q1 with the partial pressure by resistance R1 and R3, to realize the conducting of Q1.
The emitter of the triode Q2 is grounded, and the both ends of resistance R4 are separately connected the base stage and emitter of triode Q2,
The base stage of the one end resistance R5 connecting triode Q2, upper movable contact of the other end in addition to being directly connected to relay K2, also passes through series connection
The upper movable contact of relay K3 is connected after resistance R6, meanwhile, the lower movable contact of relay K2 and K3 are all connected with the anode of battery.
It should be noted that resistance R5 and R6 are current-limiting resistance, resistance R4 voltage between triode Q2 Base-Emitter
The protective resistance of Vbe.
When satellite and the rocket separation and after satellier injection, external spaceborne computer sends provisioning instruction to relay K2 and K3, then after
The lower movable contact of electric appliance K2 and K3 are respectively with corresponding for connecting the stationary contact of the feeder ear of shunt regulating control circuit
Connection, upper movable contact connect with corresponding stationary contact for receiving the control instruction that external spaceborne computer issues respectively
It connects, then battery is powered to shunt regulating control circuit, and the control instruction controls triode Q2 turn-on and turn-off, wherein if
The level of control instruction is higher than setting value, then triode Q2 is connected, and otherwise triode Q2 is turned off.
It should be noted that K2 and K3 is magnetic latching relay, for keeping the state of a control of control instruction, and two are used
The mode of a relay parallel connection is conducive to improve the reliability and stability that command status is kept.
It can be seen that the output phase of the output of Q1 and photovoltaic array in shunt regulating main circuit in battery switch module
Even, bus of satellite is constituted, that is to say, that battery is combined with photovoltaic array for bussed supply of satellite.Wherein, on ground
Shadow zone in area of illumination, is then powered by battery with photovoltaic array jointly mainly by storage battery power supply.
Certainly, the invention may also have other embodiments, without deviating from the spirit and substance of the present invention, ripe
Various corresponding changes and modifications can be made according to the present invention certainly by knowing those skilled in the art, but these it is corresponding change and
Deformation all should fall within the scope of protection of the appended claims of the present invention.
Claims (2)
1. a kind of satellite starts power supply system, which is characterized in that including battery, battery switch module, satellite and the rocket separating switch
S1, battery control of discharge module, relay K1~K3, shunt regulating control circuit, shunt regulating main circuit and photovoltaic battle array
Column；
The battery is used in the conducting of battery switch module, to bussed supply of external satellite；
The satellite and the rocket separating switch S1 is the interface switch of satellite and carrier rocket, and before satellite and the rocket separation, satellite and the rocket separating switch S1
It being in an off state, after satellite and the rocket separation, satellite and the rocket separating switch S1 is in closed state, then when satellite and the rocket separating switch S1 closure, and
When relay K1 is connected with battery control of discharge module one of both, the conducting of battery switch module；
The battery is also used to power when relay K2 or K3 are connected to shunt regulating control circuit；Wherein, relay K2
With the turn-on condition of K3 are as follows: receive the provisioning instruction that external spaceborne computer issues after satellite and the rocket separation；
The photovoltaic array is used for when satellite is in area of illumination to bussed supply of external satellite；
The shunt regulating control circuit is used to detect the voltage of bus of external satellite, when the electricity of bus of external satellite
When pressure is higher than given threshold, shunt regulating main circuit makes external satellite one for shunting the voltage that photovoltaic array exports
The voltage stabilization of secondary bus is in setting range.
2. a kind of satellite as described in claim 1 starts power supply system, which is characterized in that the battery switch module includes
P-channel metal-oxide-semiconductor Q1, resistance R1~R3, the battery control of discharge module include triode Q2, resistance R4~R6；
The anode of the source electrode connection battery of the P-channel metal-oxide-semiconductor Q1, drain electrode connection bus of external satellite；Resistance R3 mono-
It holds while connecting the stationary contact of relay K1 and the collector of triode Q2, the other end passes through resistance R1 connection P-channel MOS respectively
The source electrode of pipe Q1 passes through the grid of resistance R2 connection P-channel metal-oxide-semiconductor Q1；The movable contact of relay K1 passes through satellite and the rocket separating switch
S1 ground connection, and the stationary contact of relay K1 and movable contact default are in attached state；
The emitter of the triode Q2 is grounded, and the both ends of resistance R4 are separately connected the base stage and emitter of triode Q2, resistance
The base stage of the one end R5 connecting triode Q2, upper movable contact of the other end in addition to being directly connected to relay K2, also passes through series resistance
The upper movable contact of relay K3 is connected after R6, meanwhile, the lower movable contact of relay K2 and K3 are all connected with the anode of battery；
After satellite and the rocket separation and satellier injection, external spaceborne computer sends provisioning instruction to relay K2 and K3, then relay
The lower movable contact of K2 and K3 is connected with corresponding stationary contact for connecting the feeder ear of shunt regulating control circuit respectively,
Upper movable contact is connect with corresponding stationary contact for receiving the control instruction that external spaceborne computer issues respectively, then is stored
Battery is powered to shunt regulating control circuit, and the control instruction controls triode Q2 turn-on and turn-off.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910424926.6A CN110224456B (en) | 2019-05-21 | 2019-05-21 | Satellite low-power-consumption starting power supply system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910424926.6A CN110224456B (en) | 2019-05-21 | 2019-05-21 | Satellite low-power-consumption starting power supply system |
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| CN110224456A true CN110224456A (en) | 2019-09-10 |
| CN110224456B CN110224456B (en) | 2022-12-23 |
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| CN201910424926.6A Active CN110224456B (en) | 2019-05-21 | 2019-05-21 | Satellite low-power-consumption starting power supply system |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111422381A (en) * | 2020-05-15 | 2020-07-17 | 中国科学院微小卫星创新研究院 | Satellite seat charging system |
| CN112018869A (en) * | 2020-08-07 | 2020-12-01 | 航天行云科技有限公司 | Star and arrow separation is from power-on circuit independently |
| CN112130474A (en) * | 2020-09-20 | 2020-12-25 | 西北工业大学 | Separated self-powered circuit and method |
| CN112366792A (en) * | 2020-11-25 | 2021-02-12 | 上海空间电源研究所 | Space S4R system charging auxiliary switching circuit and S4R system with same |
| CN112373729A (en) * | 2020-11-04 | 2021-02-19 | 北京微纳星空科技有限公司 | Satellite power supply system |
| CN112520067A (en) * | 2020-12-07 | 2021-03-19 | 山东航天电子技术研究所 | Satellite autonomous power-up circuit after separation of satellite and rocket and control method thereof |
| CN113086252A (en) * | 2021-04-02 | 2021-07-09 | 深圳航天东方红卫星有限公司 | High-reliability solar cell array shunt regulation system and method |
| CN113141004A (en) * | 2021-04-09 | 2021-07-20 | 长光卫星技术有限公司 | Moonlet autonomous power-on circuit and control method thereof |
| CN113682497A (en) * | 2021-08-25 | 2021-11-23 | 北京微纳星空科技有限公司 | Test method for preventing satellite sailboard from being unfolded mistakenly and power supply circuit |
| CN114024351A (en) * | 2021-11-09 | 2022-02-08 | 北京微纳星空科技有限公司 | Power supply system and power supply method used in satellite |
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| CN109710019A (en) * | 2019-01-10 | 2019-05-03 | 深圳航天东方红海特卫星有限公司 | A kind of spaceborne solar battery array output power shunting circuit |
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| JP2001328599A (en) * | 2000-05-18 | 2001-11-27 | Nec Eng Ltd | Ordnance control circuit |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111422381A (en) * | 2020-05-15 | 2020-07-17 | 中国科学院微小卫星创新研究院 | Satellite seat charging system |
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| CN112366792A (en) * | 2020-11-25 | 2021-02-12 | 上海空间电源研究所 | Space S4R system charging auxiliary switching circuit and S4R system with same |
| CN112366792B (en) * | 2020-11-25 | 2022-10-21 | 上海空间电源研究所 | Space S4R system charging auxiliary switching circuit and S4R system with same |
| CN112520067A (en) * | 2020-12-07 | 2021-03-19 | 山东航天电子技术研究所 | Satellite autonomous power-up circuit after separation of satellite and rocket and control method thereof |
| CN113086252A (en) * | 2021-04-02 | 2021-07-09 | 深圳航天东方红卫星有限公司 | High-reliability solar cell array shunt regulation system and method |
| CN113141004A (en) * | 2021-04-09 | 2021-07-20 | 长光卫星技术有限公司 | Moonlet autonomous power-on circuit and control method thereof |
| CN113141004B (en) * | 2021-04-09 | 2023-05-23 | 长光卫星技术股份有限公司 | Automatic power-up circuit of small satellite and control method thereof |
| CN113682497A (en) * | 2021-08-25 | 2021-11-23 | 北京微纳星空科技有限公司 | Test method for preventing satellite sailboard from being unfolded mistakenly and power supply circuit |
| CN114024351A (en) * | 2021-11-09 | 2022-02-08 | 北京微纳星空科技有限公司 | Power supply system and power supply method used in satellite |
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|---|---|
| CN110224456B (en) | 2022-12-23 |
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