CN113141004B - Automatic power-up circuit of small satellite and control method thereof - Google Patents
Automatic power-up circuit of small satellite and control method thereof Download PDFInfo
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- CN113141004B CN113141004B CN202110386102.1A CN202110386102A CN113141004B CN 113141004 B CN113141004 B CN 113141004B CN 202110386102 A CN202110386102 A CN 202110386102A CN 113141004 B CN113141004 B CN 113141004B
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- satellite
- separation switch
- switch
- solar cell
- cell array
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- 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
- H02J1/00—Circuit arrangements for dc mains or dc distribution networks
- H02J1/10—Parallel operation of dc sources
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
- Y02E10/56—Power conversion systems, e.g. maximum power point trackers
Abstract
The invention provides a small satellite autonomous power-up circuit and a control method thereof, wherein the circuit comprises: the solar cell array comprises a satellite bus VBUS, a solar cell array SAS, an isolation diode D1, a separation switch SW1 and a separation switch SW2, a storage battery pack, a relay K1, a resistor R2, a resistor R1, a capacitor C1 and a discharge switch PMOS tube Q1; according to the invention, after the satellite is separated from the carrier rocket, the satellite is automatically powered up, no requirement is required on the sequence of the solar cell array and the storage battery access bus in the whole automatic power-up process, the solar cell array and the storage battery access bus are automatically completed by completely depending on a hardware circuit, and the whole process is free from software participation, so that the reliability is high.
Description
Technical Field
The invention belongs to the technical field of microsatellites, and particularly relates to a microsatellite autonomous power-up circuit and a control method thereof, wherein the microsatellite is stored for a long time and is subjected to rapid emergency emission, and particularly the microsatellite is autonomously powered up to work after being in orbit.
Background
With the rapid development of satellite microminiature technology in recent years, the launching mode of one arrow with multiple satellites becomes a main means for enabling the microsatellites to enter space, and meanwhile, the satellite arrow mode is changed from the traditional power-on state to the power-on-arrow mode without power-on separation and then power-on is carried out autonomously.
Because the rocket breaks away the fairing for a long time before the satellites and the arrows are separated, the satellite sailboard is likely to be irradiated by sunlight. Due to the attitude change and orbit of the rocket, the output power of the solar array is unstable at the moment, so that the whole satellite bus is frequently powered up and powered down, and the on-board equipment is possibly abnormal and even damaged.
Disclosure of Invention
In order to solve the problems, the satellite is in a power-off state after being in butt joint with the rocket, the satellite is automatically powered on after being separated, the bus cannot be powered on even if the sailboard is irradiated by the sun before separation, and the current frequent power-on and power-off phenomenon is avoided, and the invention provides a small satellite automatic power-on circuit and a control method thereof.
The invention is realized by the following steps:
the automatic power-up circuit of the small satellite comprises a satellite bus VBUS, a solar cell array SAS, an isolation diode D1, a separation switch SW2, a storage battery pack, a relay K1, a resistor R2, a resistor R1, a capacitor C1 and a discharge switch PMOS tube Q1;
the output end of the solar cell array SAS is connected with the anode of the isolation diode D1, the cathode of the isolation diode D1 is connected with the satellite bus VBUS, the output end of the solar cell array SAS is also connected with the 3 pin of the separation switch SW1, the 4 pin of the separation switch SW1 is connected with the 3 pin of the separation switch SW2, and the 4 pin of the separation switch SW2 is a ground pin;
the foot 2 of relay K1 is the lower margin, relay K1's 1 foot with resistance R2's one end links to each other, resistance R2's the other end link to each other respectively with electric capacity C1's one end resistance R1's one end separation switch SW 1's 1 foot with discharge switch PMOS tube V1's grid links to each other, separation switch SW 1's 2 foot with separation switch SW 2's 1 foot links to each other, separation switch SW 2's 2 foot respectively with storage battery's positive pole the other end of electric capacity C1 the other end of resistance R1 with discharge switch PMOS tube Q1's source links to each other, discharge switch PMOS tube V1's drain electrode with link to each other satellite busbar VBUS links to each other.
Further, the two groups of switches of the separation switch SW1 are mutually independent, and the two groups of switches are always in a compressed state after the satellite is in butt joint with the carrier rocket until the satellite is separated from the carrier rocket.
Further, the two groups of switches of the separation switch SW2 are mutually independent, and the two groups of switches are always in a compressed state after the satellite is in butt joint with the carrier rocket until the satellite is separated from the carrier rocket.
Further, the connection between the 4 pin of the disconnecting switch SW1 and the 3 pin of the disconnecting switch SW2 needs to be welded after the satellite is docked with the carrier rocket.
The control method applied to the autonomous power-on circuit of the small satellite comprises the following steps that before satellite transmission, when a separation switch SW1 and a separation switch SW2 are in a closed state, two working states are provided:
(1) When the solar cell array SAS has output power, current passes through a path of the separation switch SW1 and a path of the separation switch SW2 and returns to the cathode of the solar cell array SAS, and no current passes through the satellite bus VBUS;
when the satellite is separated from the carrier rocket, the separation switch SW1 and the separation switch SW2 are in an off state, namely the power positive line and the ground line of the solar cell array SAS are disconnected, and the solar cell array SAS supplies power to the satellite bus VBUS;
(2) Setting pin 1 and pin 2 of relay K1 to an on state;
after the satellite is separated from the carrier rocket, the separation switch SW1 and the separation switch SW2 are in an off state, so that the discharging switch PMOS tube Q1 is conducted, and the storage battery pack supplies power to the satellite bus VBUS.
Furthermore, the circuit has no requirement on the disconnection time sequence of 4 switches in total of the separation switch SW1 and the separation switch SW2, namely, the sequence of the solar cell array SAS and the storage battery set bus is not required.
The invention has the beneficial effects that
(1) According to the circuit diagram provided by the invention, before the satellite is separated from the carrier, the storage battery pack and the solar cell array do not supply power to the bus, the whole satellite is always in a power-off state, and the problems that the satellite sailboard is possibly irradiated by sunlight after the rocket breaks a fairing before the satellite and the rocket are separated, the output power of the solar array is unstable, the whole satellite bus is frequently powered on and off, and the on-board equipment is possibly abnormal are solved;
(2) The circuit diagram provided by the invention can be used for automatically powering up the satellite after the satellite is separated from the carrier rocket, has no requirement on the sequence of the solar cell array and the storage battery to be connected with the bus in the whole automatic powering up process, is completely finished by means of a hardware circuit, and has high reliability without software participation in the whole process.
Drawings
Fig. 1 is a circuit diagram of a small satellite autonomous power-up circuit of the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention; all other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The automatic power-up circuit of the small satellite comprises a satellite bus VBUS, a solar cell array SAS, an isolation diode D1, a separation switch SW2, a storage battery pack, a relay K1, a resistor R2, a resistor R1, a capacitor C1 and a discharge switch PMOS tube Q1;
the output end of the solar cell array SAS is connected with the anode of the isolation diode D1, the cathode of the isolation diode D1 is connected with the satellite bus VBUS, the output end of the solar cell array SAS is also connected with the 3 pin of the separation switch SW1, the 4 pin of the separation switch SW1 is connected with the 3 pin of the separation switch SW2, and the 4 pin of the separation switch SW2 is a ground pin;
the foot 2 of relay K1 is the lower margin, relay K1's 1 foot with resistance R2's one end links to each other, resistance R2's the other end link to each other respectively with electric capacity C1's one end resistance R1's one end separation switch SW 1's 1 foot with discharge switch PMOS tube V1's grid links to each other, separation switch SW 1's 2 foot with separation switch SW 2's 1 foot links to each other, separation switch SW 2's 2 foot respectively with storage battery's positive pole the other end of electric capacity C1 the other end of resistance R1 with discharge switch PMOS tube Q1's source links to each other, discharge switch PMOS tube Q1's drain electrode with link to each other satellite busbar VBUS links to each other.
The two groups of switches of the separation switch SW1 are mutually independent, and the two groups of switches are always in a compressed state after the satellite is in butt joint with the carrier rocket until the satellite is separated.
The two groups of switches of the separation switch SW2 are mutually independent, and the two groups of switches are always in a compressed state after the satellite is in butt joint with the carrier rocket until the satellite is separated.
The connection between the 4 pin of the separation switch SW1 and the 3 pin of the separation switch SW2 is needed to be welded after the satellite is in butt joint with the carrier rocket, and the whole satellite can still be powered through the solar array interface before the welding to check the state of the whole satellite.
The control method applied to the autonomous power-on circuit of the small satellite comprises the following steps that before satellite transmission, when a separation switch SW1 and a separation switch SW2 are in a closed state, two working states are provided:
(1) When the solar cell array SAS has output power, current passes through a path of the separation switch SW1 and a path of the separation switch SW2 and returns to the cathode of the solar cell array SAS, and no current passes through the satellite bus VBUS;
when the satellite is separated from the carrier rocket, the separation switch SW1 and the separation switch SW2 are in an off state, namely the power positive line and the ground line of the solar cell array SAS are disconnected, and the solar cell array SAS supplies power to the satellite bus VBUS;
(2) Setting pin 1 and pin 2 of relay K1 to an on state;
after the satellite is separated from the carrier rocket, the separation switch SW1 and the separation switch SW2 are in an off state, so that the discharging switch PMOS tube Q1 is conducted, and the storage battery pack supplies power to the satellite bus VBUS.
The circuit has no requirement on the disconnection time sequence of 4 switches in total of the separation switch SW1 and the separation switch SW2, namely the sequence of the solar cell array SAS and the storage battery set bus is not required.
The whole satellite autonomous power-up process after the satellite is separated from the carrier rocket is completed independently by a hardware circuit, and software participation is not needed in the whole process.
The above describes the principle and the implementation of the present invention in detail, and the above description of the embodiment is only used to help understand the method and the core idea of the present invention; meanwhile, as those skilled in the art will have variations in the specific embodiments and application scope in accordance with the ideas of the present invention, the present description should not be construed as limiting the present invention in view of the above.
Claims (5)
1. A control method of a small satellite autonomous power-up circuit comprises a satellite bus VBUS, a solar cell array SAS, an isolation diode D1, a separation switch SW2, a storage battery pack, a relay K1, a resistor R2, a resistor R1, a capacitor C1 and a discharge switch PMOS tube Q1;
the output end of the solar cell array SAS is connected with the anode of the isolation diode D1, the cathode of the isolation diode D1 is connected with the satellite bus VBUS, the output end of the solar cell array SAS is also connected with the 3 pin of the separation switch SW1, the 4 pin of the separation switch SW1 is connected with the 3 pin of the separation switch SW2, and the 4 pin of the separation switch SW2 is a ground pin;
the foot 2 of relay K1 is the lower margin, relay K1's 1 foot with resistance R2's one end links to each other, resistance R2's the other end link to each other respectively with electric capacity C1's one end resistance R1's one end separation switch SW 1's 1 foot with discharge switch PMOS tube V1's grid links to each other, separation switch SW 1's 2 foot with separation switch SW 2's 1 foot links to each other, separation switch SW 2's 2 foot respectively with storage battery's positive pole the other end of electric capacity C1 the other end of resistance R1 with discharge switch PMOS tube Q1's source links to each other, discharge switch PMOS tube Q1's drain electrode with link to each other satellite busbar VBUS links to each other, its characterized in that:
before satellite transmission, when the separation switch SW1 and the separation switch SW2 are in the closed state, there are two working states:
(1) When the solar cell array SAS has output power, current passes through a path of the separation switch SW1 and a path of the separation switch SW2 and returns to the cathode of the solar cell array SAS, and no current passes through the satellite bus VBUS;
when the satellite is separated from the carrier rocket, the separation switch SW1 and the separation switch SW2 are in an off state, namely the power positive line and the ground line of the solar cell array SAS are disconnected, and the solar cell array SAS supplies power to the satellite bus VBUS;
(2) Setting pin 1 and pin 2 of relay K1 to an on state;
after the satellite is separated from the carrier rocket, the separation switch SW1 and the separation switch SW2 are in an off state, so that the discharging switch PMOS tube Q1 is conducted, and the storage battery pack supplies power to the satellite bus VBUS.
2. A control method of a circuit according to claim 1, characterized in that: the two groups of switches of the separation switch SW1 are mutually independent, and the two groups of switches are always in a compressed state after the satellite is in butt joint with the carrier rocket until the satellite is separated.
3. A control method of a circuit according to claim 1, characterized in that: the two groups of switches of the separation switch SW2 are mutually independent, and the two groups of switches are always in a compressed state after the satellite is in butt joint with the carrier rocket until the satellite is separated.
4. A control method of a circuit according to claim 1, characterized in that: the connection between the 4 pin of the separation switch SW1 and the 3 pin of the separation switch SW2 needs to be welded after the satellite is docked with the carrier rocket.
5. The control method of the circuit according to claim 4, wherein: the circuit has no requirement on the disconnection time sequence of 4 switches in total of the separation switch SW1 and the separation switch SW2, namely the sequence of the solar cell array SAS and the storage battery set bus is not required.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110386102.1A CN113141004B (en) | 2021-04-09 | 2021-04-09 | Automatic power-up circuit of small satellite and control method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110386102.1A CN113141004B (en) | 2021-04-09 | 2021-04-09 | Automatic power-up circuit of small satellite and control method thereof |
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| CN113141004A CN113141004A (en) | 2021-07-20 |
| CN113141004B true CN113141004B (en) | 2023-05-23 |
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| CN106410953A (en) * | 2016-10-26 | 2017-02-15 | 深圳航天东方红海特卫星有限公司 | Separation self power on and battery protection method applied to micro/nano satellite |
| CN110224456A (en) * | 2019-05-21 | 2019-09-10 | 山东航天电子技术研究所 | A kind of satellite low-power consumption starting power supply system |
| CN111934277A (en) * | 2020-06-28 | 2020-11-13 | 上海空间电源研究所 | Shunt regulation isolation diode short-circuit protection control system and method |
| 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 |
| CN112373729A (en) * | 2020-11-04 | 2021-02-19 | 北京微纳星空科技有限公司 | Satellite power supply system |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107483099B (en) * | 2017-08-30 | 2020-09-01 | 长光卫星技术有限公司 | Isolation and guarantee system for satellite-borne equipment |
| CN110562498B (en) * | 2019-10-08 | 2022-04-12 | 深圳航天东方红海特卫星有限公司 | Star and arrow separation is from last electric circuit |
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2021
- 2021-04-09 CN CN202110386102.1A patent/CN113141004B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106410953A (en) * | 2016-10-26 | 2017-02-15 | 深圳航天东方红海特卫星有限公司 | Separation self power on and battery protection method applied to micro/nano satellite |
| CN110224456A (en) * | 2019-05-21 | 2019-09-10 | 山东航天电子技术研究所 | A kind of satellite low-power consumption starting power supply system |
| CN111934277A (en) * | 2020-06-28 | 2020-11-13 | 上海空间电源研究所 | Shunt regulation isolation diode short-circuit protection control system and method |
| 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 |
| CN112373729A (en) * | 2020-11-04 | 2021-02-19 | 北京微纳星空科技有限公司 | Satellite power supply system |
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| CN113141004A (en) | 2021-07-20 |
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Address after: No. 1299, Mingxi Road, Beihu science and Technology Development Zone, Changchun City, Jilin Province Applicant after: Changguang Satellite Technology Co.,Ltd. Address before: No. 1299, Mingxi Road, Beihu science and Technology Development Zone, Changchun City, Jilin Province Applicant before: CHANG GUANG SATELLITE TECHNOLOGY Co.,Ltd. |
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