CN110562498B - Star and arrow separation is from last electric circuit - Google Patents
Star and arrow separation is from last electric circuit Download PDFInfo
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- CN110562498B CN110562498B CN201910949954.XA CN201910949954A CN110562498B CN 110562498 B CN110562498 B CN 110562498B CN 201910949954 A CN201910949954 A CN 201910949954A CN 110562498 B CN110562498 B CN 110562498B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/421—Non-solar power generation
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/428—Power distribution and management
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
- B64G1/443—Photovoltaic cell arrays
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- Aviation & Aerospace Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
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- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention provides a satellite and rocket separated self-powered circuit which comprises a primary power BUS V _ BUS of a satellite, a storage battery pack, a solar cell array SAS, an isolation diode D3, a relay S1, a disconnecting switch S2, a relay K2 and a resistor R34, wherein the output end of the solar cell array SAS is connected with the anode of the isolation diode D3, the cathode of the isolation diode D3 is respectively connected with the primary power BUS V _ BUS and a pin 9 of the relay K2, the anode of the storage battery pack is connected with a pin 3 of the relay S1, and a pin 1 of the relay S1 is a ground pin. The invention has the beneficial effects that: the satellite and the carrier can be automatically electrified and work after being separated, and in the launching process, before the separation of the satellite and the rocket and after the carrier rocket throws the fairing, the situation that the power of the equipment is frequently switched on and off due to insufficient output power of the solar cell array can not occur, so that the design life of the electronic equipment is ensured, and unexpected faults caused by frequent power on and off are avoided.
Description
Technical Field
The invention relates to satellite and rocket separation, in particular to a satellite and rocket separation self-electrifying circuit.
Background
The traditional satellite platform is generally in a power-on state in the launching process, after a satellite and an arrow are separated, a satellite affair computer is used as a timing starting point on the satellite according to the state of a satellite and arrow separation switch, and starts to execute a program control instruction, start an attitude control component and the like. However, the design mode is inflexible, and the requirement of rapid transmission cannot be realized due to the fact that storage battery charging is required to be carried out on a satellite in a transmitting field and the equipment state is set.
Because the fairing can be thrown off by the rocket before the satellite and the carrier rocket are separated for a period of time, at the moment, the solar cell array can be irradiated by sunlight, power output can be realized, and the condition that the satellite is frequently powered on and powered off can occur because the output power is not fixed until the storage battery pack is connected to a power supply bus after the satellite and the rocket are separated. And frequent powering up and down of the satellite may cause individual device anomalies.
Therefore, a circuit needs to be designed, so that the satellite is in a complete power-off state after being in butt joint with the carrier rocket, power cannot be supplied to the primary power bus even if the solar cell array has power output, and the satellite can be automatically powered on only after being separated from the carrier rocket.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a satellite and arrow separation self-powered circuit.
The invention provides a satellite and rocket separated self-powered circuit, which comprises a primary power BUS V _ BUS of a satellite, a storage battery, a solar cell array SAS, an isolation diode D3, a relay S1, a disconnecting switch S2, a relay K2 and a resistor R34, wherein the output end of the solar cell array SAS is connected with the anode of the isolation diode D3, the cathode of the isolation diode D3 is respectively connected with the primary power supply BUS V _ BUS and the pin 9 of the relay K2, the positive pole of the storage battery pack is connected with a pin 3 of the relay S1, a pin 1 of the relay S1 is a ground pin, pin 2 of the relay S1 is connected to pin 12 of the relay K2 through the resistor R34, one end of the disconnecting switch S2 is grounded, the other end of the disconnecting switch S2 is connected with a pin 7 of the relay K2, a pin 4 of the relay K2 is grounded, and a pin 3 of the relay K2 is connected with a primary power supply BUS V _ BUS; before the satellite is launched, a disconnecting switch S2 is in an off state, a pin 2 and a pin 3 of a relay S1 are set to be in an on state, namely a resistor R34 is connected with the anode of a storage battery pack through a pin 2 and a pin 3 of a relay S1, a pin 9 and a pin 8 of a relay K2 are in a connected state, a pin 5 and a pin 4 of a relay K2 are in a connected state, and a pin 4 of a relay K2 is connected to the ground; when the satellite and the arrow are separated, the disconnecting switch S2 is in a closed state, the pin 7 of the relay K2 is in a low level, the pin 9 of the relay K2 is controlled to be connected with the pin 10, the pin 4 is connected with the pin 3, namely, the positive power line of the solar cell array is disconnected with the ground, and power can be supplied to the primary power BUS V _ BUS.
As a further improvement of the present invention, the satellite and arrow separated self-powered circuit further includes a relay S3, a resistor R30, and a discharge switch PMOS transistor V2, pin 2 of the relay S3 is connected to pin 3 of the relay K2, pin 3 of the relay S3 is connected to one end of the resistor R30, the other end of the resistor R30 is connected to a gate of the discharge switch PMOS transistor V2, a source of the discharge switch PMOS transistor V2 is connected to an anode of the battery pack, a drain of the discharge switch PMOS transistor V2 is connected to the primary power BUS V _ BUS, pin 2 and pin 3 of the relay S3 are connected, that is, pin 3 of the relay K2 is connected to the resistor R30 through the relay S3; when the satellite and the arrow are separated, the disconnecting switch S2 is in a closed state, a ground signal is connected to the resistor R30 through the relay K2 and the relay S3, the discharge switch PMOS tube V2 is conducted, the storage battery pack is connected to the primary power BUS V _ BUS, and the whole satellite starts to work according to a set program.
As a further improvement of the invention, after the star and arrow are separated, the relay S1 is controlled to be disconnected through a command, namely the pin 2 of the relay S1 is connected to the pin 1, and the storage battery pack does not provide power for the coil of the relay K2 any more, so that the coil is prevented from being heated or even burnt out due to continuous power supply.
As a further improvement of the invention, the satellite command FDKG-ON and the output signal of the relay S3 form an OR relationship, after the satellite and the arrow are separated, the satellite transmits the FDKG-ON command, and then the output signal of the relay S3 is cut off, namely the pin 2 of the relay S3 is connected with the pin 1, and at the moment, the discharge switch PMOS tube V2 is still in a conducting state under the action of the FDKG-ON command.
As a further improvement of the invention, a resistor R31 is connected in series between the resistor R30 and the gate of the discharge switch PMOS transistor V2.
As a further improvement of the present invention, the satellite and arrow separated self-powered circuit includes a resistor C9 and a resistor R32, one end of the resistor C9 is connected between the resistor R30 and the resistor R31, the other end is connected between the pin 3 of the relay S1 and the positive electrode of the battery pack, one end of the resistor R32 is connected between the resistor R30 and the resistor R31, and the other end is connected between the pin 3 of the relay S1 and the positive electrode of the battery pack.
As a further improvement of the invention, the satellite-rocket self-powered circuit comprises a diode D4 and a resistor R33, the anode of the diode D4 is connected between the pins 7 of the disconnecting switch S2 and the relay K2, and the cathode of the diode D4 is connected between the pins 12 of the resistor R34 and the relay K2.
The invention has the beneficial effects that: by the aid of the scheme, the satellite and the carrier can be automatically electrified and work after being separated, and in the launching process, before separation of the satellite and the rocket and after the carrier rocket throws the fairing, frequent power-on and power-off of equipment due to insufficient output power of the solar cell array cannot occur, so that the design life of electronic equipment is guaranteed, and unexpected faults caused by frequent power-on and power-off are avoided.
Drawings
FIG. 1 is a circuit diagram of a satellite and rocket separated self-powered circuit of the present invention.
Detailed Description
The invention is further described with reference to the following description and embodiments in conjunction with the accompanying drawings.
As shown in FIG. 1, a satellite and rocket separation self-powered circuit comprises a primary power BUS V _ BUS of a satellite, a storage battery, a solar cell array SAS, an isolation diode D3, a relay S1, a separation switch S2, a relay K2 and a resistor R34, wherein the output end of the solar cell array SAS is connected with the anode of the isolation diode D3, the cathode of the isolation diode D3 is respectively connected with the primary power supply BUS V _ BUS and the pin 9 of the relay K2, the positive pole of the storage battery pack is connected with a pin 3 of the relay S1, a pin 1 of the relay S1 is a ground pin, pin 2 of the relay S1 is connected to pin 12 of the relay K2 through the resistor R34, one end of the disconnecting switch S2 is grounded, the other end of the disconnecting switch S2 is connected with a pin 7 of the relay K2, a pin 4 of the relay K2 is grounded, and a pin 3 of the relay K2 is connected with a primary power supply BUS V _ BUS; before the satellite is launched, a disconnecting switch S2 is in an off state, a pin 2 and a pin 3 of a relay S1 are set to be in an on state, namely a resistor R34 is connected with the anode of a storage battery pack through a pin 2 and a pin 3 of a relay S1, a pin 9 and a pin 8 of a relay K2 are in a connected state, a pin 5 and a pin 4 of a relay K2 are in a connected state, and a pin 4 of a relay K2 is connected to the ground; when the satellite and the arrow are separated, the disconnecting switch S2 is in a closed state, the pin 7 of the relay K2 is in a low level, the pin 9 of the relay K2 is controlled to be connected with the pin 10, the pin 4 is connected with the pin 3, namely, the positive power line of the solar cell array is disconnected with the ground, and power can be supplied to the primary power BUS V _ BUS.
As shown in fig. 1, the satellite-rocket separated self-powered circuit further includes a relay S3, a resistor R30, and a discharge switch PMOS transistor V2, pin 2 of the relay S3 is connected to pin 3 of the relay K2, pin 3 of the relay S3 is connected to one end of the resistor R30, the other end of the resistor R30 is connected to a gate of the discharge switch PMOS transistor V2, a source of the discharge switch PMOS transistor V2 is connected to an anode of the battery pack, a drain of the discharge switch PMOS transistor V2 is connected to the primary power BUS V _ BUS, and pin 2 and pin 3 of the relay S3 are connected, that is, pin 3 of the relay K2 is connected to the resistor R30 through the relay S3; when the satellite and the arrow are separated, the disconnecting switch S2 is in a closed state, a ground signal is connected to the resistor R30 through the relay K2 and the relay S3, the discharge switch PMOS tube V2 is conducted, the storage battery pack is connected to the primary power BUS V _ BUS, and the whole satellite starts to work according to a set program.
As shown in fig. 1, after the star and arrow are separated, the relay S1 is controlled to be disconnected through a command, that is, the pin 2 of the relay S1 is connected to the pin 1, and the battery pack does not provide power for the coil of the relay K2 any more, so that the coil is prevented from being heated or even burnt out due to continuous power supply.
As shown in fig. 1, the satellite command FDKG-ON and the output signal of the relay S3 form an or relationship, after the satellite and the arrow are separated, the satellite transmits the FDKG-ON command, and then the output signal of the relay S3 is cut off, that is, the pin 2 of the relay S3 is connected to the pin 1, and at this time, the discharge switch PMOS transistor V2 is still in a conducting state under the action of the FDKG-ON command.
As shown in fig. 1, a resistor R31 is connected in series between the resistor R30 and the gate of the discharge switch PMOS transistor V2.
As shown in fig. 1, the satellite-rocket separation self-powered circuit includes a resistor C9 and a resistor R32, one end of the resistor C9 is connected between the resistor R30 and the resistor R31, the other end is connected between the pin 3 of the relay S1 and the positive electrode of the battery pack, one end of the resistor R32 is connected between the resistor R30 and the resistor R31, and the other end is connected between the pin 3 of the relay S1 and the positive electrode of the battery pack.
As shown in FIG. 1, the satellite-rocket self-powered circuit comprises a diode D4 and a resistor R33, wherein the anode of the diode D4 is connected between the disconnecting switch S2 and the pin 7 of the relay K2, and the cathode of the diode D4 is connected between the resistor R34 and the pin 12 of the relay K2.
According to the satellite-rocket separation self-power-on circuit provided by the invention, before the satellite is separated from a carrier rocket, the satellite is not powered, the discharge switch of the storage battery pack is in a disconnected state, the output power of the solar battery array is short-circuited to the ground, and after the satellite and the rocket are separated, the output power of the solar battery array is connected into the power supply bus and the discharge switch of the storage battery pack is switched on at the same time.
The satellite-rocket separation self-power-on circuit provided by the invention is simple and reliable, can realize autonomous power-on work after separation of the satellite and the carrier, and can avoid frequent power-on and power-off of equipment due to insufficient output power of a solar cell array in the launching process before separation of the satellite and the rocket and after the carrier rocket throws the fairing, thereby ensuring the design life of electronic equipment and avoiding unexpected faults caused by frequent power-on and power-off.
The invention provides a satellite and arrow separation self-electrifying circuit which has the following characteristics:
(1) in the satellite launching process, a full power-off state can be realized, and the solar cell array and the storage battery pack can not supply power to the primary bus;
(2) the storage battery pack starts to supply power to the bus only after the solar cell array starts to supply power to the primary bus, so that the condition that the storage battery pack discharges through a short circuit path to the ground through the solar cell array is avoided;
(3) the time sequence control of the storage battery pack and the solar battery array access bus is realized by adopting the relay, and the safety and the reliability are realized.
The simplification of the satellite and arrow separation self-powered circuit or the design improvement for improving the reliability of the circuit provided by the invention belong to the protection scope of the invention.
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.
Claims (7)
1. A satellite and arrow separation self-powered circuit is characterized in that: the satellite power supply system comprises a primary power supply BUS V _ BUS of a satellite, a storage battery pack, a solar battery array SAS, an isolation diode D3, a relay S1, a disconnecting switch S2, a relay K2 and a resistor R34, wherein the output end of the solar battery array SAS is connected with the anode of the isolation diode D3, the cathode of the isolation diode D3 is respectively connected with the primary power supply BUS V _ BUS and a pin 9 of the relay K2, the anode of the storage battery pack is connected with a pin 3 of the relay S1, a pin 1 of a relay S1 is a ground pin, a pin 2 of the relay S1 is connected with a pin 12 of the relay K2 through the resistor R34, one end of the disconnecting switch S2 is grounded, the other end of the disconnecting switch S2 is connected with a pin 7 of the relay K2, a pin 4 of the relay K2 is grounded, and a pin 3 of the relay K2 is connected with the primary power supply BUS V _ BUS; before the satellite is launched, a disconnecting switch S2 is in an off state, a pin 2 and a pin 3 of a relay S1 are set to be in an on state, namely a resistor R34 is connected with the anode of a storage battery pack through a pin 2 and a pin 3 of a relay S1, a pin 9 and a pin 8 of a relay K2 are in a connected state, a pin 5 and a pin 4 of a relay K2 are in a connected state, and a pin 4 of a relay K2 is connected to the ground; when the satellite and the arrow are separated, the disconnecting switch S2 is in a closed state, the pin 7 of the relay K2 is in a low level, the pin 9 of the relay K2 is controlled to be connected with the pin 10, the pin 4 is connected with the pin 3, namely, the positive power line of the solar cell array is disconnected with the ground, and power can be supplied to the primary power BUS V _ BUS.
2. The satellite-rocket separation self-powered circuit according to claim 1, characterized in that: the satellite and rocket separated self-powered circuit further comprises a relay S3, a resistor R30 and a discharge switch PMOS tube V2, wherein a pin 2 of the relay S3 is connected with a pin 3 of the relay K2, a pin 3 of the relay S3 is connected with one end of a resistor R30, the other end of the resistor R30 is connected with a grid electrode of the discharge switch PMOS tube V2, a source electrode of the discharge switch PMOS tube V2 is connected with the anode of the storage battery pack, a drain electrode of the discharge switch PMOS tube V2 is connected with the primary power supply BUS V _ BUS, a pin 2 and a pin 3 of the relay S3 are connected, namely the pin 3 of the relay K2 is connected with the resistor R30 through a relay S3; when the satellite and the arrow are separated, the disconnecting switch S2 is in a closed state, a ground signal is connected to the resistor R30 through the relay K2 and the relay S3, the discharge switch PMOS tube V2 is conducted, the storage battery pack is connected to the primary power BUS V _ BUS, and the whole satellite starts to work according to a set program.
3. The satellite and rocket separation self-powered circuit according to claim 2, wherein: after the star and arrow are separated, the relay S1 is controlled to be disconnected through a command, namely the pin 2 of the relay S1 is connected to the pin 1, and the storage battery pack does not provide power for the coil of the relay K2 any more, so that the coil is prevented from being heated or even burnt due to continuous power supply.
4. The satellite and rocket separation self-powered circuit according to claim 3, wherein: the satellite-borne command FDKG-ON and the output signal of the relay S3 form an OR relationship, after the satellite and the arrow are separated, the satellite affair sends the FDKG-ON command, then the output signal of the relay S3 is cut off, namely the pin 2 of the relay S3 is connected with the pin 1, and at the moment, the discharge switch PMOS tube V2 is still in a conducting state under the action of the FDKG-ON command.
5. The satellite and rocket separation self-powered circuit according to claim 2, wherein: a resistor R31 is connected in series between the resistor R30 and the gate of the discharge switch PMOS tube V2.
6. The satellite and rocket separation self-powered circuit according to claim 5, wherein: the satellite and arrow separation self-powered circuit comprises a resistor C9 and a resistor R32, one end of the resistor C9 is connected between the resistor R30 and the resistor R31, the other end of the resistor C9 is connected between a pin 3 of the relay S1 and the anode of the storage battery pack, one end of the resistor R32 is connected between the resistor R30 and the resistor R31, and the other end of the resistor R32 is connected between the pin 3 of the relay S1 and the anode of the storage battery pack.
7. The satellite-rocket separation self-powered circuit according to claim 1, characterized in that: the satellite-rocket self-powered circuit comprises a diode D4 and a resistor R33, wherein the anode of the diode D4 is connected between pins 7 of the disconnecting switch S2 and the relay K2, and the cathode of the diode D4 is connected between pins 12 of the resistor R34 and the relay K2.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910949954.XA CN110562498B (en) | 2019-10-08 | 2019-10-08 | Star and arrow separation is from last electric circuit |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910949954.XA CN110562498B (en) | 2019-10-08 | 2019-10-08 | Star and arrow separation is from last electric circuit |
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| CN110562498A CN110562498A (en) | 2019-12-13 |
| CN110562498B true CN110562498B (en) | 2022-04-12 |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110890774B (en) * | 2019-12-06 | 2022-03-15 | 中国科学院微小卫星创新研究院 | Device for protecting discharge switch of satellite storage battery and operation method thereof |
| CN116231793A (en) * | 2020-08-26 | 2023-06-06 | 中国科学院微小卫星创新研究院 | Double-redundancy control method for autonomous power-up after separation of satellite active section from satellite rocket |
| 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 |
| 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 |
| 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 |
| CN116119031B (en) * | 2023-04-18 | 2023-06-13 | 银河航天(北京)网络技术有限公司 | Satellite and rocket separation control system, method and storage medium |
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Address after: 518000 whole building of satellite building, 61 Gaoxin South Jiudao, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province Patentee after: Shenzhen Aerospace Dongfanghong Satellite Co.,Ltd. Address before: 518000 whole building of satellite building, 61 Gaoxin South Jiudao, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province Patentee before: AEROSPACE DONGFANGHONG DEVELOPMENT Ltd. |
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