CN110224456B - Satellite low-power-consumption starting power supply system - Google Patents
Satellite low-power-consumption starting power supply system Download PDFInfo
- Publication number
- CN110224456B CN110224456B CN201910424926.6A CN201910424926A CN110224456B CN 110224456 B CN110224456 B CN 110224456B CN 201910424926 A CN201910424926 A CN 201910424926A CN 110224456 B CN110224456 B CN 110224456B
- Authority
- CN
- China
- Prior art keywords
- satellite
- storage battery
- rocket
- resistor
- shunt regulation
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000003068 static effect Effects 0.000 claims abstract description 15
- 238000000926 separation method Methods 0.000 claims description 16
- 238000005286 illumination Methods 0.000 claims description 4
- 238000004146 energy storage Methods 0.000 abstract description 8
- 238000010586 diagram Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000004870 electrical engineering Methods 0.000 description 1
- 229910044991 metal oxide Inorganic materials 0.000 description 1
- 150000004706 metal oxides Chemical class 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000004065 semiconductor Substances 0.000 description 1
Images
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)
- Photovoltaic Devices (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention provides a low-power-consumption starting power supply system for a satellite, which utilizes a satellite-rocket disconnecting switch S1, a relay K1 and a battery discharge control module as a change-over switch for judging whether a storage battery switch module is conducted or not, and simultaneously utilizes relays K2 and K3 as change-over switches for judging whether storage batteries supply power for a shunt regulation control circuit or not, so that the shunt regulation control circuit has the function of normally supplying power before the satellite is separated from a carrier rocket, and the shunt regulation control circuit has the function of normally supplying power after the satellite is separated from the carrier rocket, and the attenuation of the static power consumption of the shunt regulation control circuit of the satellite before the satellite is separated from the carrier rocket to an energy storage battery is further reduced; therefore, the invention improves the reliability of satellite power supply on one hand, and reduces the requirement on the capacity of the satellite energy storage battery on the other hand, thereby reducing the weight of the satellite.
Description
Technical Field
The invention belongs to the technical field of energy management in the field of electrical engineering, and particularly relates to a low-power-consumption starting power supply system for a satellite.
Background
In order to ensure the normal operation of the satellite power supply control circuit, the power supply of the shunt regulation control circuit of the satellite is usually provided by a satellite energy storage battery. The satellite may be stored in the launch vehicle for several days before it enters orbit. If no measures are taken, the shunt regulation control circuit is directly and continuously powered by the energy storage battery, and the static power consumption of the shunt regulation control circuit can cause the energy storage in the storage battery to be greatly reduced, even reduced to zero, which seriously influences the normal operation of the satellite.
Disclosure of Invention
In order to solve the problems, the invention provides a low-power-consumption starting power supply system for a satellite, wherein a control circuit does not supply power before the satellite is separated from a carrier rocket, and the satellite is normally supplied with power after the satellite is separated from the carrier rocket, so that the attenuation of the static power consumption of a shunt regulation control circuit of the satellite before the satellite is separated from the carrier rocket to an energy storage battery is reduced.
A satellite starting power supply system comprises a storage battery, a storage battery switch module, a satellite and rocket separation switch S1, a storage battery discharge control module, relays K1-K3, a shunt regulation control circuit, a shunt regulation main circuit and a photovoltaic array;
the storage battery is used for supplying power to the external satellite primary bus when the storage battery switch module is switched on;
the satellite and rocket separating switch S1 is an interface switch of a satellite and a carrier rocket, the satellite and rocket separating switch S1 is in a disconnected state before the satellite and the rocket are separated, and the satellite and rocket separating switch S1 is in a closed state after the satellite and the rocket are separated, so that when the satellite and rocket separating switch S1 is closed and one of the relay K1 and the storage battery discharge control module is conducted, the storage battery switch module is conducted;
the storage battery is also used for supplying power to the shunt regulation control circuit when the relay K2 or the relay K3 is switched on; the conduction conditions of the relays K2 and K3 are as follows: after separating the star and the arrow, receiving a starting instruction sent by an external satellite-borne computer;
the photovoltaic array is used for supplying power to a primary bus of an external satellite when the satellite is in an illumination area;
the shunt regulation control circuit is used for detecting the voltage of the external satellite primary bus, and when the voltage of the external satellite primary bus is higher than a set threshold value, the shunt regulation main circuit is used for shunting the voltage output by the photovoltaic array to enable the voltage of the external satellite primary bus to be stabilized in a set range.
Further, the storage battery switch module comprises a P-channel MOS (metal oxide semiconductor) transistor Q1 and resistors R1-R3, and the storage battery discharge control module comprises a triode Q2 and resistors R4-R6;
the source electrode of the P-channel MOS tube Q1 is connected with the anode of the storage battery, and the drain electrode of the P-channel MOS tube Q1 is connected with an external satellite primary bus; one end of the resistor R3 is simultaneously connected with a static contact of the relay K1 and a collector of the triode Q2, and the other end of the resistor R3 is respectively connected with a source electrode of the P-channel MOS tube Q1 through the resistor R1 and a grid electrode of the P-channel MOS tube Q1 through the resistor R2; the movable contact of the relay K1 is grounded through the satellite-rocket disconnecting switch S1, and the static contact and the movable contact of the relay K1 are in a connection state by default;
the emitting electrode of the triode Q2 is grounded, the two ends of the resistor R4 are respectively connected with the base electrode and the emitting electrode of the triode Q2, one end of the resistor R5 is connected with the base electrode of the triode Q2, the other end of the resistor R6 is directly connected with the upper movable contact of the relay K2 and is also connected with the upper movable contact of the relay K3 after being connected with the resistor R6 in series, and meanwhile, the lower movable contacts of the relays K2 and K3 are both connected with the positive electrode of the storage battery;
when the satellite and the arrow are separated and the satellite enters the orbit, the external satellite-borne computer sends a switching-on instruction to the relays K2 and K3, the lower movable contacts of the relays K2 and K3 are respectively connected with the corresponding static contacts which are used for connecting the power supply ends of the shunt regulation control circuits, the upper movable contacts are respectively connected with the corresponding static contacts which are used for receiving the control instruction sent by the external satellite-borne computer, the storage battery supplies power to the shunt regulation control circuits, and the control instruction controls the on-off of the triode Q2.
Has the advantages that:
the invention provides a low-power-consumption starting power supply system for a satellite, which utilizes a satellite-rocket disconnecting switch S1, a relay K1 and a battery discharge control module as a change-over switch for judging whether a storage battery switch module is conducted or not, and simultaneously utilizes relays K2 and K3 as change-over switches for judging whether storage batteries supply power for a shunt regulation control circuit or not, so that the shunt regulation control circuit has the function of normally supplying power before the satellite is separated from a carrier rocket, and the shunt regulation control circuit has the function of normally supplying power after the satellite is separated from the carrier rocket, and the attenuation of the static power consumption of the shunt regulation control circuit of the satellite before the satellite is separated from the carrier rocket to an energy storage battery is further reduced; therefore, the invention improves the reliability of satellite power supply on one hand, and reduces the requirement on the capacity of the satellite energy storage battery on the other hand, thereby reducing the weight of the satellite.
Drawings
Fig. 1 is a schematic diagram of a low-power-consumption startup power supply system for a satellite according to the present invention.
Detailed Description
In order to make the technical solutions better understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application.
Referring to fig. 1, the figure is a schematic diagram of a low-power-consumption startup power supply system for a satellite according to this embodiment. A satellite low-power-consumption starting power supply system is characterized by comprising a storage battery, a storage battery switch module, a satellite and rocket separation switch S1, a storage battery discharge control module, relays K1-K3, a shunt regulation control circuit, a shunt regulation main circuit and a photovoltaic array.
The storage battery is used for supplying power to the external satellite primary bus when the storage battery switch module is switched on.
The satellite and rocket separation switch S1, the relay K1 and the storage battery discharging control module are used for controlling the conduction of the storage battery switch module; the satellite and rocket separation switch S1 is an interface switch of a satellite and a carrier rocket, the satellite and rocket separation switch S1 is in a disconnected state before separation of the satellite and the rocket, and the satellite and rocket separation switch S1 is in a closed state after separation of the satellite and the rocket, so that when the satellite and rocket separation switch S1 is closed and one of the relay K1 and the storage battery discharge control module is switched on, the storage battery switch module is switched on.
The storage battery is also used for supplying power to the shunt regulation control circuit when the relay K2 or the relay K3 is switched on; the on-state conditions of the relays K2 and K3 are as follows: and after the star and the arrow are separated, a starting instruction sent by an external satellite-borne computer is received.
The photovoltaic array is used for supplying power to an external satellite primary bus when the satellite is in an illumination area.
The shunt regulation control circuit is used for detecting the voltage of the external satellite primary bus, and when the voltage of the external satellite primary bus is higher than a set threshold value, the shunt regulation main circuit is used for shunting the voltage output by the photovoltaic array to the external satellite primary bus so as to stabilize the voltage of the external satellite primary bus within a set range.
It should be noted that the shunt regulation main circuit and the shunt regulation control circuit jointly form a satellite power supply controller, and the satellite power supply controller is a key device in a satellite power supply system, and is used for converting unstable output voltage of a solar cell array, namely a photovoltaic array, into stable primary bus voltage of a satellite platform and performing charge and discharge control on a storage battery pack. When the output voltage of the photovoltaic array is higher than the primary bus voltage, the shunt regulation main circuit is controlled by the shunt regulation control circuit to shunt by a bypass, and when the primary bus voltage is lower than a set value, the shunt regulation main circuit is prohibited from shunting by the bypass. Therefore, the reliable operation and the reliable power supply of the shunt regulation control circuit directly influence the reliable operation of the satellite power supply controller and the whole satellite power supply system, and further influence the success or failure of satellite tasks.
A specific circuit structure of the storage battery switch module and the storage battery discharge control module is given below, and the connection and disconnection of the storage battery switch module, the storage battery discharge control module, and the relays K1 to K3 are further explained by combining the specific circuit structures of the storage battery switch module and the storage battery discharge control module. As shown in fig. 1, the storage battery switch module includes a P-channel MOS transistor Q1 and resistors R1 to R3, and the storage battery discharge control module includes a triode Q2 and resistors R4 to R6.
The source electrode of the P-channel MOS tube Q1 is connected with the positive electrode of the storage battery, the drain electrode of the P-channel MOS tube Q1 is connected with an external satellite primary bus, and the negative electrode of the storage battery is grounded; one end of the resistor R3 is simultaneously connected with a static contact of the relay K1 and a collector of the triode Q2, and the other end of the resistor R3 is respectively connected with a source electrode of the P-channel MOS tube Q1 through the resistor R1 and a grid electrode of the P-channel MOS tube Q1 through the resistor R2; the movable contact of the relay K1 is grounded through the satellite-rocket disconnecting switch S1, and the fixed contact and the movable contact of the relay K1 are in a connected state by default.
It should be noted that, since Q1 is a P-channel MOS transistor, the voltage across the resistor R1 determines the voltage V across the gate-source of Q1 GS When the voltage V is applied across the gate and source of Q1 GS When the starting voltage Vth reaches, the power supply can be conducted as-4V and Q1. Therefore, the divided voltage across the resistor R1 can be ensured to be larger than the starting voltage Vth of the Q1 through the divided voltage of the resistors R1 and R3, so that the conduction of the Q1 is realized.
The emitting electrode of the triode Q2 is grounded, the two ends of the resistor R4 are respectively connected with the base electrode and the emitting electrode of the triode Q2, one end of the resistor R5 is connected with the base electrode of the triode Q2, the other end of the resistor R6 is directly connected with the upper movable contact of the relay K2 and is also connected with the upper movable contact of the relay K3 through the series resistor R6, and meanwhile, the lower movable contacts of the relays K2 and K3 are both connected with the positive electrode of the storage battery.
The resistors R5 and R6 are current limiting resistors, and the resistor R4 is a protection resistor for the voltage Vbe between the base and emitter of the transistor Q2.
When the satellite and the arrow are separated and the satellite enters the orbit, an external satellite-borne computer sends a switching-on instruction to the relays K2 and K3, the lower movable contacts of the relays K2 and K3 are respectively connected with the corresponding static contacts which are used for connecting the power supply ends of the shunt regulation control circuits, the upper movable contacts are respectively connected with the corresponding static contacts which are used for receiving the control instruction sent by the external satellite-borne computer, the storage battery supplies power to the shunt regulation control circuits, the control instruction controls the triode Q2 to be switched on and off, wherein if the level of the control instruction is higher than a set value, the triode Q2 is switched on, and otherwise, the triode Q2 is switched off.
It should be noted that K2 and K3 are magnetic latching relays for maintaining the control state of the control command, and the two relays are connected in parallel, which is beneficial to improving the reliability and stability of maintaining the command state.
Therefore, the output of the Q1 in the storage battery switch module is connected with the output of the photovoltaic array in the shunt regulation main circuit to form a satellite primary bus, namely, the storage battery and the photovoltaic array are combined to supply power to the satellite primary bus. The storage battery is mainly used for supplying power in the ground shadow area, and the storage battery and the photovoltaic array are used for supplying power together in the illumination area.
The present invention is capable of other embodiments, and various changes and modifications can be made by one skilled in the art without departing from the spirit and scope of the invention.
Claims (1)
1. A satellite starting power supply system is characterized by comprising a storage battery, a storage battery switch module, a satellite and rocket separation switch S1, a storage battery discharge control module, relays K1-K3, a shunt regulation control circuit, a shunt regulation main circuit and a photovoltaic array;
the storage battery is used for supplying power to the external satellite primary bus when the storage battery switch module is switched on;
the satellite and rocket separation switch S1 is an interface switch of a satellite and a carrier rocket, the satellite and rocket separation switch S1 is in a disconnected state before separation of the satellite and the rocket, and the satellite and rocket separation switch S1 is in a closed state after separation of the satellite and the rocket, so that when the satellite and rocket separation switch S1 is closed and one of the relay K1 and the storage battery discharge control module is conducted, the storage battery switch module is conducted;
the storage battery is also used for supplying power to the shunt regulation control circuit when the relay K2 or K3 is switched on; the conduction conditions of the relays K2 and K3 are as follows: after separating the satellite and the arrow, receiving a starting instruction sent by an external satellite-borne computer;
the photovoltaic array is used for supplying power to a primary bus of an external satellite when the satellite is in an illumination area;
the shunt regulation control circuit is used for detecting the voltage of the external satellite primary bus, and when the voltage of the external satellite primary bus is higher than a set threshold, the shunt regulation main circuit is used for shunting the voltage output by the photovoltaic array to stabilize the voltage of the external satellite primary bus within a set range;
the storage battery discharge control module comprises a triode Q2 and resistors R4-R6;
the source electrode of the P-channel MOS tube Q1 is connected with the anode of the storage battery, and the drain electrode of the P-channel MOS tube Q1 is connected with an external satellite primary bus; one end of the resistor R3 is simultaneously connected with a static contact of the relay K1 and a collector of the triode Q2, and the other end of the resistor R3 is respectively connected with a source electrode of the P-channel MOS tube Q1 through the resistor R1 and a grid electrode of the P-channel MOS tube Q1 through the resistor R2; the movable contact of the relay K1 is grounded through the satellite-rocket disconnecting switch S1, and the static contact and the movable contact of the relay K1 are connected by default;
the emitting electrode of the triode Q2 is grounded, the two ends of the resistor R4 are respectively connected with the base electrode and the emitting electrode of the triode Q2, one end of the resistor R5 is connected with the base electrode of the triode Q2, the other end of the resistor R6 is directly connected with the upper movable contact of the relay K2 and is also connected with the upper movable contact of the relay K3 after being connected with the resistor R6 in series, and meanwhile, the lower movable contacts of the relays K2 and K3 are both connected with the positive electrode of the storage battery;
when the satellite and the arrow are separated and the satellite enters the orbit, the external satellite-borne computer sends a switching-on instruction to the relays K2 and K3, the lower movable contacts of the relays K2 and K3 are respectively connected with the corresponding static contacts which are used for connecting the power supply ends of the shunt regulation control circuits, the upper movable contacts are respectively connected with the corresponding static contacts which are used for receiving the control instruction sent by the external satellite-borne computer, the storage battery supplies power to the shunt regulation control circuits, and the control instruction controls the triode Q2 to be switched on and 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 |
Applications Claiming Priority (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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110224456A CN110224456A (en) | 2019-09-10 |
| CN110224456B true CN110224456B (en) | 2022-12-23 |
Family
ID=67821608
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910424926.6A Active CN110224456B (en) | 2019-05-21 | 2019-05-21 | Satellite low-power-consumption starting power supply system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110224456B (en) |
Families Citing this family (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 |
| CN112018869B (en) * | 2020-08-07 | 2021-12-28 | 航天行云科技有限公司 | Star and arrow separation is from power-on circuit independently |
| CN112130474B (en) * | 2020-09-20 | 2022-11-01 | 西北工业大学 | Separated self-powered circuit and method |
| CN112373729B (en) * | 2020-11-04 | 2022-04-26 | 北京微纳星空科技有限公司 | Satellite power supply system |
| 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 |
| CN112520067B (en) * | 2020-12-07 | 2023-05-23 | 山东航天电子技术研究所 | Satellite autonomous power-up circuit after satellite and rocket separation and control method thereof |
| CN113086252B (en) * | 2021-04-02 | 2022-05-10 | 深圳航天东方红卫星有限公司 | High-reliability solar cell array shunt regulation system and method |
| 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 |
| CN114024351B (en) * | 2021-11-09 | 2023-04-18 | 北京微纳星空科技有限公司 | Power supply system and power supply method used in satellite |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4428814B2 (en) * | 2000-05-18 | 2010-03-10 | Ｎｅｃエンジニアリング株式会社 | Ordnance control circuit |
| CN106100096B (en) * | 2016-06-23 | 2018-08-21 | 航天东方红卫星有限公司 | A kind of micro-nano satellite low-voltage high-efficiency power-supply system |
| CN106410953B (en) * | 2016-10-26 | 2019-05-07 | 深圳航天东方红海特卫星有限公司 | It is a kind of to be powered on and accumulator protecting method suitable for being isolated from for micro-nano satellite |
| CN108375919B (en) * | 2018-02-08 | 2020-06-16 | 哈尔滨工业大学 | Satellite autonomous power supply control circuit based on satellite and rocket separation |
| CN109710019B (en) * | 2019-01-10 | 2020-09-25 | 深圳航天东方红海特卫星有限公司 | Output power shunt control circuit of satellite-borne solar cell array |
-
2019
- 2019-05-21 CN CN201910424926.6A patent/CN110224456B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN110224456A (en) | 2019-09-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110224456B (en) | Satellite low-power-consumption starting power supply system | |
| CN110588542A (en) | Low-power-consumption self-awakening control circuit and control method for vehicle-mounted power supply | |
| CN111934401B (en) | Battery protection circuit and lithium battery system | |
| CN112217260A (en) | Storage battery pack charge and discharge control module and control method | |
| US20210218070A1 (en) | Method for switch the mode of the battery pack from outside and the battery pack from the outside | |
| CN115085357A (en) | Power supply switching device and unmanned vehicle | |
| CN111313374A (en) | Battery system under-voltage protection circuit and method applied to electric bicycle BMS | |
| CN214176987U (en) | Multi-power supply system and multi-power supply switching circuit | |
| CN210957897U (en) | Battery parallel switch control circuit device | |
| CN212784806U (en) | Rocket self-holding power supply and distribution control circuit and electrical equipment | |
| CN112260370B (en) | Battery protection circuit board | |
| JP2002078216A (en) | Load starter for high-voltage battery | |
| CN114552766A (en) | Power supply device and power supply method for robot | |
| CN108512295B (en) | Short-circuit prevention control method for shunt regulating circuit of spacecraft power system | |
| CN213717638U (en) | Dual-redundancy selection circuit based on constant current charging | |
| CN111555397A (en) | Control circuit for turning off discharge output during lithium battery charging | |
| CN210517885U (en) | Emergency power supply automatic switching circuit and electronic equipment thereof | |
| CN220421481U (en) | Voltage overturning charge-discharge control circuit | |
| CN211556916U (en) | Bidirectional equalization circuit and battery online maintenance system | |
| CN217767226U (en) | Standby control circuit and device | |
| CN220586021U (en) | Battery control device | |
| CN219351310U (en) | Energy storage power supply system | |
| CN219458659U (en) | Zero standby power consumption switching power supply control circuit | |
| CN220234252U (en) | Battery-powered control circuit and cosmetic device | |
| CN214506541U (en) | Battery over-discharge protection circuit and power supply device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |