CN112018845A - Satellite autonomous power-on system and control method thereof - Google Patents
Satellite autonomous power-on system and control method thereof Download PDFInfo
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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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- 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
- H02J7/0029—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits
- H02J7/00306—Overdischarge protection
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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
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0029—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits
- H02J7/0031—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits using battery or load disconnect circuits
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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
- 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
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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
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
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Abstract
The invention provides a satellite autonomous power-on system and a control method thereof, wherein the control method comprises the following steps: the first-stage separation circuit is configured to provide a first control signal and a first power supply signal according to a satellite-rocket separation state; a second stage separation circuit configured to provide a second power supply signal according to the first remote control instruction; a star computer configured to provide a discharge instruction according to a first control signal; a first stage discharge circuit configured to turn on a circuit between the bus and the secondary battery according to a first power supply signal and a second power supply signal; and a second stage discharge circuit configured to close a circuit between the bus bar and the secondary battery according to a discharge instruction.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to an autonomous satellite power-on system and a control method thereof.
Background
The micro-nano satellite has the characteristics of low cost, short development period and the like, and is increasingly researched and applied in the world. Because the capacity of the adopted storage battery is generally very small, and the time from the launching to the orbit entering of the satellite is constant, if the design mode of the traditional satellite is adopted, namely the satellite is in a working state in the launching process, the discharge depth of the storage battery can reach more than 70 percent after the satellite is separated from the carrying, and the risk of power failure and even loss of the satellite exists. Therefore, it is necessary to design a circuit to make the satellite in the power-off state during the transmitting stage and automatically power up after being separated from the carrying.
The satellite generally has two launching states of power-up and non-power-up in a carrying fairing, the traditional active section powered-up satellite is converted from external ground power supply into storage battery internal power supply about 1-2 hours before launching, the satellite mainly supplies power to satellite equipment through a discharge switch by virtue of the storage battery, so that the electric quantity of the storage battery used by the satellite needs to bear the power consumption of the satellite equipment until the satellite unfolds a sailboard after separation of a satellite and an arrow, the satellite can be powered by a sailboard solar cell and the storage battery is charged at the moment, the capacity of the storage battery needs to be designed to be relatively large, and the discharge depth reaches more than 50%. The average discharge depth of the storage battery is usually only about 20-30% when the satellite performs on-orbit tasks, and the over-design capability exists.
Disclosure of Invention
The invention aims to provide an autonomous satellite power-on system and a control method thereof, which aim to solve the problem that the conventional storage battery has the risk of overlarge discharge depth.
In order to solve the above technical problem, the present invention provides an autonomous satellite power-on system, including:
the first-stage separation circuit is configured to provide a first control signal and a first power supply signal according to a satellite-rocket separation state;
a second stage separation circuit configured to provide a second power supply signal according to the first remote control instruction;
a star computer configured to provide a discharge instruction according to the first control signal;
a first stage discharge circuit configured to turn on a circuit between a bus and a secondary battery according to the first power supply signal and the second power supply signal; and
and the second-stage discharge circuit is configured to switch on a circuit between the bus and the storage battery according to the discharge instruction.
Optionally, in the autonomous satellite power-on system, when the second-stage discharging circuit disconnects the circuit between the bus and the storage battery, a second remote control instruction provided by the star service computer causes the second-stage separating circuit to stop providing the second power supply signal.
Optionally, in the satellite autonomous power-on system, the first-stage separation circuit includes two parallel travel switches connected between ground and the second-stage separation circuit, the second-stage separation circuit includes two parallel relays connected between the first-stage separation circuit and the control end of the first-stage discharge circuit, the first-stage discharge circuit includes two parallel transistors connected between the positive end of the bus and the positive end of the storage battery, and the second-stage discharge circuit includes two parallel discharge switches connected between the positive end of the bus and the positive end of the storage battery.
Optionally, in the autonomous satellite power-on system, the normally closed contact of the travel switch sends an autonomous power-on instruction to the house service computer when the satellite and the arrow are separated.
Optionally, in the satellite autonomous power-on system, the method further includes:
an autonomous power-up circuit configured to turn on both ends of the battery for discharging, the second stage discharge circuit being directly turned on when a discharge amount exceeds a threshold.
Optionally, in the satellite autonomous power-on system, the autonomous power-on circuit includes:
the resistor is connected between the positive end of the storage battery and the negative end of the storage battery and used for consuming the electric quantity of the storage battery;
the reference circuit is connected between the positive end of the storage battery and the negative end of the storage battery and used for generating voltage relative to a threshold value to obtain reference voltage;
the detection circuit is connected between the positive end of the storage battery and the negative end of the storage battery and is used for detecting the voltage between the positive end of the storage battery and the negative end of the storage battery to obtain a detection voltage;
and the comparison circuit is used for comparing the reference voltage with the detection voltage and generating an autonomous power-on signal according to a comparison result.
Optionally, in the satellite autonomous power-on system, the method further includes: an enable switch disposed between the autonomous power-up circuit and the second stage discharge circuit;
and when the satellite orbit-entering flight state is set, the enabling switch is switched off.
The invention also provides a control method of the satellite autonomous power-on system, which comprises the following steps:
the first-stage separation circuit provides a first control signal and a first power supply signal according to the satellite-rocket separation state;
the second-stage separation circuit provides a second power supply signal according to the first remote control instruction;
the star affair computer provides a discharge instruction according to the first control signal;
the first-stage discharge circuit is connected with a circuit between the bus and the storage battery according to the first power supply signal and the second power supply signal;
and the second-stage discharge circuit is connected with a circuit between the bus and the storage battery according to the discharge instruction.
According to the autonomous satellite power-on system and the control method thereof, the first-stage separation circuit provides a first control signal and a first power supply signal according to the satellite-rocket separation state, the second-stage separation circuit provides a second power supply signal according to the first remote control instruction, the satellite computer provides a discharge instruction according to the first control signal, the first-stage discharge circuit is connected with a circuit between the bus and the storage battery according to the first power supply signal and the second power supply signal, and the second-stage discharge circuit is connected with a circuit between the bus and the storage battery according to the discharge instruction, so that the situation that the power is not supplied to the active section and the power is supplied to the active section after the active section is added to the orbit is realized, and the satellite which is not supplied with power to the active section not only can reduce the complicated test flow and drill before the satellite is launched, but also can avoid hidden danger caused by vibration or impact response of vibration impact on a satellite.
Drawings
FIG. 1 is a schematic diagram of an autonomous satellite power-on system according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of an autonomous power-on circuit of the autonomous power-on system for a satellite according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a second stage discharging circuit of the satellite autonomous power-on system according to an embodiment of the invention.
Detailed Description
The autonomous satellite power-on system and the control method thereof according to the present invention will be described in further detail with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims. It is to be noted that the drawings are in a very simplified form and are not to precise scale, which is merely for the purpose of facilitating and distinctly claiming the embodiments of the present invention.
Furthermore, features from different embodiments of the invention may be combined with each other, unless otherwise indicated. For example, a feature of the second embodiment may be substituted for a corresponding or functionally equivalent or similar feature of the first embodiment, and the resulting embodiments are likewise within the scope of the disclosure or recitation of the present application.
In view of the possibility of unstable attitude or abnormal equipment state during the in-orbit operation of the satellite, it is necessary to design a battery protection circuit to prevent the battery from being damaged by over-discharge or over-discharge and to recover the power supply of the battery after the failure disappears.
The satellite generally has two launching states of power-up and non-power-up in a carrying fairing, the traditional active section powered-up satellite is converted from external ground power supply into storage battery internal power supply about 1-2 hours before launching, the satellite mainly supplies power to satellite equipment through a discharge switch by virtue of the storage battery, so that the electric quantity of the storage battery used by the satellite needs to bear the power consumption of the satellite equipment until the satellite unfolds a sailboard after separation of a satellite and an arrow, the satellite can be powered by a sailboard solar cell and the storage battery is charged at the moment, the capacity of the storage battery needs to be designed to be relatively large, and the discharge depth reaches more than 50%. The average discharge depth of the storage battery is usually only about 20-30% when the satellite performs on-orbit tasks, and the over-design capability exists.
The invention provides an autonomous satellite power-on system and a control method thereof, and aims to solve the problem that the conventional storage battery has a risk of overlarge discharge depth.
In order to realize the thought, the invention provides a satellite autonomous power-on system and a control method thereof, wherein the satellite autonomous power-on system comprises the following steps: the first-stage separation circuit is configured to provide a first control signal and a first power supply signal according to a satellite-rocket separation state; a second stage separation circuit configured to provide a second power supply signal according to the first remote control instruction; a star computer configured to provide a discharge instruction according to a first control signal; a first stage discharge circuit configured to turn on a circuit between the bus and the secondary battery according to a first power supply signal and a second power supply signal; and the second-stage discharge circuit is configured to be connected with a circuit between the bus and the storage battery according to the discharge instruction, so that the dual-redundancy control method for automatically electrifying the satellite after the satellite active section is separated from the satellite and the satellite arrow is realized.
The invention particularly relates to the field of satellite power supplies, in particular to a dual-redundancy control method for realizing autonomous electrification of a satellite after separation from a satellite active section to a satellite arrow by using a 2KX-1 type travel switch. The first stage separation circuit includes the travel switch who connects between ground and the second stage separation circuit, the second stage separation circuit is including connecting the relay between first stage separation circuit and first stage discharge circuit control end, first stage discharge circuit is including connecting the transistor between the positive end of generating line and the positive end of battery, the second stage discharge circuit is including connecting the discharge switch between the positive end of generating line and the positive end of battery.
Furthermore, the travel switch is a device for physical connection between the satellite and the carrier, and the 2KX-1 type travel switch is frequently adopted in small satellites and has the function of clearly determining the state of separation of the satellite and the arrow from the physical state. The switch is arranged on a satellite and rocket butt joint ring in a double backup mode, and the travel switch is provided with two pairs of contacts with opposite functions. When the travel is compressed, the connection state of the outgoing line of one pair of normally open contacts is short-circuit connection (namely the star and the arrow are not separated), the travel switch is physically bounced off after the star and the arrow are separated, the connection state of the outgoing line of the contact is open-circuit disconnection (the star and the arrow are separated), the connection state of the travel switch is transmitted to a satellite-borne computer of the satellite through a satellite-borne cable, the satellite-borne computer judges the current state of the separation of the star and the arrow of the satellite, and corresponding program control operation is executed. The other pair of normally closed contacts with opposite functions can be used on a satellite which cannot be powered on in an active section, when the satellite and the arrow are separated, the travel switch is flicked and released, the normally closed contacts are changed from a disconnection state to a short circuit connection state, the uncharged signal is directly connected to an instruction end of a satellite storage battery discharge switch through a cable, and the satellite starts to be powered on to work after the satellite discharge switch is connected.
And a normally closed contact of the travel switch sends an autonomous power-on instruction to the satellite affair computer when the satellite and the arrow are separated. The invention is mainly inspired by the fact that a 2KX-1 type travel switch has two pairs of contacts with opposite functions and the over-discharge protection function of a satellite storage battery, and a satellite with an unpowered active section can reduce the complicated test flow and pre-shooting practice before satellite launching and can also avoid the hidden danger caused by the vibration or impact response of the satellite storage battery discharge switch due to the vibration impact separated by a satellite and an arrow.
Aiming at the transmitting mode of a satellite which can not be powered on in an active section, a 2KX-1 type travel switch with opposite functions and double contacts are used, and a separation signal is sent autonomously in a physical connection mode, wherein the method belongs to external input passive control; meanwhile, the capacity of triggering a discharge switch to switch on a command signal after micro-discharge of the storage battery can be utilized, and the method belongs to internal output active control; a control method for autonomous power-on dual redundancy from a satellite active section to a satellite-rocket separation is designed.
As shown in fig. 1, when the fixed point of the contact of the travel switch S1 is grounded, and the star and arrow are not separated or the relay K2 is turned off, the gate of the PMOS transistor connected in parallel with the discharge switch K1 is floating, VGS is 0, and the P-MOS transistor is turned off. The satellite is connected with the relay K2 through a remote control command during the last ground test before the satellite and arrow combination body is butted and installed into the carrying fairing, after the satellite and the arrow are separated, the travel switch is flicked, the S1 and the S2 are in a short circuit connection state, at the moment, the grids of the two P-MOS tubes are pulled down, the P-MOS tubes are connected, and the storage battery pack supplies energy to the whole satellite through the P-MOS tubes. After the satellite computer is electrified, the program-controlled sending command of 'discharge switch connection' is sent, the discharge switch K1 is connected, and the P-MOS tube and the discharge switch can supply power to the satellite through the same channel.
When the second-stage discharging circuit disconnects the circuit between the bus and the storage battery, a second remote control instruction provided by the star computer enables the second-stage separating circuit to stop providing the second power supply signal. In order to avoid the failure of the over-discharge protection function of the storage battery caused by the existence of the P-MOS tube, a 'discharge switch off' command is also connected to the disconnection package of the relay K2, the relay K2 is switched off while the discharge switch is switched off, the over-discharge protection function can still be triggered when the over-discharge of the storage battery of the orbit satellite caused by the existence of the P-MOS channel is ensured, and the discharge switch K1 is switched off.
The relay K2 sets a switch-on command to the wire pack, and the positive end of the wire pack is connected with the positive end of the bus. After the satellite is tested for the last time before the field is transmitted to the fairing, the relay K2 needs to be switched on after the discharge switch is switched off. In order to ensure reliability, the P-MOS tube is designed for 2 backups, the relay K2 is designed for 2 backups, and the travel switch is also provided with two mutual backups to form parallel state multipoint control, so that the whole satellite can be automatically electrified after the satellite and the arrow are separated. Namely, the first stage separation circuit comprises two travel switches connected in parallel, the second stage separation circuit comprises two relays connected in parallel, the first stage discharge circuit comprises two transistors connected in parallel, and the second stage discharge circuit comprises two discharge switches connected in parallel.
Specifically, the autonomous power-on circuit is configured to switch on both ends of the storage battery for discharging, and the secondary discharging circuit is directly switched on when the discharging amount exceeds a threshold value. The autonomous power-up circuit includes: the resistor is connected between the positive end of the storage battery and the negative end of the storage battery and used for consuming the electric quantity of the storage battery; the reference circuit is connected between the positive end of the storage battery and the negative end of the storage battery and used for generating voltage relative to a threshold value to obtain reference voltage; the detection circuit is connected between the positive end of the storage battery and the negative end of the storage battery and is used for detecting the voltage between the positive end of the storage battery and the negative end of the storage battery to obtain a detection voltage; and the comparison circuit is used for comparing the reference voltage with the detection voltage and generating an autonomous power-on signal according to a comparison result.
As shown in fig. 2, the battery voltage is composed of 7 sections of 4.1V monomers with nominal full-state voltage, the whole group of voltage is 28.7V after the battery is fully charged, and the connection form of the C-D port can be a contact originally connected to a star computer to judge the separation use of a star arrow by a travel switch, or a star-watch short circuit enabling plug. When the satellite emission window is determined, the satellite and arrow separation time can also be roughly determined, and the autonomous control can be carried out by adding a certain margin according to the time from the last power failure (short circuit insertion) of the satellite to the satellite and arrow separation. For example, after the satellite and rocket combination is butted for 30 hours, the satellite and the rocket can be separated, after the CD end is connected, the storage battery is subjected to micro-discharge through 2 power resistors RXG 2141 omega/6W, the discharge current is 28.7/82 to 0.35A, the power consumption of the circuit is about 0.04A, the total power consumption is 0.4A, the discharge time is about 12Ah for 30 hours, the voltage of the whole group of storage batteries after the storage batteries are discharged for 12Ah from the full charge 60Ah is about 27.3V (the energy can still meet the requirement of initial orbit entering of the satellite), and the reference voltage is formed by a diode; the detection circuit comprises a delay gear 1 controlled by a switch K3 and a delay gear 2 controlled by a switch K4, wherein the delay gear 1 is set to be feedback corresponding to 27.3V, the delay gear 2 is set to be feedback corresponding to 27V, and a closed K3 and an enabling switch K5 are set in a state before the satellite is powered off. After 30 hours, even if the travel switches are all in physical failure and cannot be bounced off, when the storage battery is discharged to 27.3V, the autonomous switch-on circuit in the satellite recognizes and judges that the reference voltage 6.4V of the equidirectional end of the 7F193 comparator is greater than the divided voltage of the feedback voltage of the reverse end, the comparator 7F193 (namely the comparison circuit) outputs a driving signal to a 'discharge switch on' wire packet of the discharge switch relay 3JB20-3, and the discharge switch is switched on.
Additionally, as shown in fig. 3, an enable switch K5 is disposed between the autonomous power-up circuit and the second stage discharge circuit; and when the satellite orbit-entering flight state is set, the enabling switch is switched off. Namely, after the whole satellite orbit entering flight state is set, the enabling switch K5 can be switched off through a remote control command. The accuracy of the time delay can be verified for many times on the ground, and the error is controlled to be minute-level. All parameters in the control circuit can meet the total time from the last ground power-on state setting of the satellite to the separation of the on-orbit satellite and the on-orbit satellite through ground correction and experimental verification.
The invention utilizes the characteristic that a 2KX-1 type travel switch has two pairs of contacts with completely opposite functions, takes the normally closed contacts which are not used by most satellites as signal transmission sources for automatically electrifying after the satellite active section is separated from a satellite and an arrow, and simultaneously adds a redundancy control method for delaying the automatic driving of the satellite storage battery discharge switch when the micro current discharge of the storage battery reaches a set voltage threshold value, thereby ensuring that the satellite can still be automatically electrified under multiple faults. The method not only avoids the influence of vibration and impact response generated at the time of separating the carrier takeoff section and the satellite and the rocket on the discharge switch relay of the satellite storage battery, but also saves a series of testing and practicing links before the satellite is carried and transferred to a launching position and then launched, and simultaneously reduces the capacity design redundancy of the satellite storage battery.
After the satellite and the rocket are in butt joint, a travel switch is pressed, the travel switch comprises two pairs of contacts, after the travel switch is pressed, one pair of contacts is in a disconnected state, the other pair of contacts is in a connected state, the disconnected contacts are used for separating a point A and a point B in a graph 1, the connected contact signals are provided for a satellite computer to use (judging satellite and rocket separation), after the satellite and the rocket are separated, the originally disconnected contacts are connected, namely S1 and S2 in the graph 1 are connected, an MOS (metal oxide semiconductor) pipe control loop of a second-stage separation circuit is connected, the satellite is automatically electrified through the path, at the moment, the satellite computer judges that the satellite and the rocket are separated according to the contact switched from the connection of the travel switch to the disconnection, a discharge switch K1 is connected through a remote control instruction, and the K2 is disconnected at the same; furthermore, the invention introduces a redundancy means of function failure, after the two ends C and D in fig. 2 are connected, the autonomous power-on circuit starts to start, and the discharging switch is automatically switched on by the fact that the storage battery slowly discharges and reaches a threshold value. The connection mode of the C and the D is divided into two modes, one mode is that a short-circuit plug is directly used and is inserted when a satellite and a rocket are assembled, a contact signal of a travel switch acquired by a satellite computer can be used, and the satellite computer can judge the separation of the satellite and the rocket by judging other state quantities.
In summary, the above embodiments have described in detail different configurations of the satellite autonomous power-on system and the control method thereof, and it is understood that the present invention includes, but is not limited to, the configurations listed in the above embodiments, and any configuration that is changed based on the configurations provided in the above embodiments is within the scope of the present invention. One skilled in the art can take the contents of the above embodiments to take a counter-measure.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system disclosed by the embodiment, the description is relatively simple because the system corresponds to the method disclosed by the embodiment, and the relevant points can be referred to the method part for description.
The above description is only for the purpose of describing the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention, and any variations and modifications made by those skilled in the art based on the above disclosure are within the scope of the appended claims.
Claims (8)
1. A satellite autonomous power-on system, comprising:
the first-stage separation circuit is configured to provide a first control signal and a first power supply signal according to a satellite-rocket separation state;
a second stage separation circuit configured to provide a second power supply signal according to the first remote control instruction;
a star computer configured to provide a discharge instruction according to the first control signal;
a first stage discharge circuit configured to turn on a circuit between a bus and a secondary battery according to the first power supply signal and the second power supply signal; and
and the second-stage discharge circuit is configured to switch on a circuit between the bus and the storage battery according to the discharge instruction.
2. The satellite autonomous power up system of claim 1 wherein a second remote command provided by the star computer causes the second stage separation circuit to discontinue providing the second power signal when the second stage discharge circuit breaks the circuit between the bus and the battery.
3. The satellite autonomous power system of claim 1 wherein the first stage separation circuit comprises two parallel travel switches connected between ground and a second stage separation circuit, the second stage separation circuit comprises two parallel relays connected between the first stage separation circuit and a first stage discharge circuit control terminal, the first stage discharge circuit comprises two parallel transistors connected between a positive bus terminal and a positive battery terminal, and the second stage discharge circuit comprises two parallel discharge switches connected between the positive bus terminal and the positive battery terminal.
4. The satellite autonomous power-on system of claim 3 wherein the normally closed contact of the travel switch sends an autonomous power-on instruction to the satellite computer upon separation of a satellite from an arrow.
5. The satellite autonomous power up system of claim 3, further comprising:
an autonomous power-up circuit configured to turn on both ends of the battery for discharging, the second stage discharge circuit being directly turned on when a discharge amount exceeds a threshold.
6. The satellite autonomous power-on system of claim 5, wherein the autonomous power-on circuit comprises:
the resistor is connected between the positive end of the storage battery and the negative end of the storage battery and used for consuming the electric quantity of the storage battery;
the reference circuit is connected between the positive end of the storage battery and the negative end of the storage battery and used for generating voltage relative to a threshold value to obtain reference voltage;
the detection circuit is connected between the positive end of the storage battery and the negative end of the storage battery and is used for detecting the voltage between the positive end of the storage battery and the negative end of the storage battery to obtain a detection voltage;
and the comparison circuit is used for comparing the reference voltage with the detection voltage and generating an autonomous power-on signal according to a comparison result.
7. The satellite autonomous power up system of claim 5, further comprising: an enable switch disposed between the autonomous power-up circuit and the second stage discharge circuit;
and when the satellite orbit-entering flight state is set, the enabling switch is switched off.
8. A control method of a satellite autonomous power-on system is characterized by comprising the following steps:
the first-stage separation circuit provides a first control signal and a first power supply signal according to the satellite-rocket separation state;
the second-stage separation circuit provides a second power supply signal according to the first remote control instruction;
the star affair computer provides a discharge instruction according to the first control signal;
the first-stage discharge circuit is connected with a circuit between the bus and the storage battery according to the first power supply signal and the second power supply signal;
and the second-stage discharge circuit is connected with a circuit between the bus and the storage battery according to the discharge instruction.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010868323.8A CN112018845B (en) | 2020-08-26 | 2020-08-26 | Autonomous satellite power-on system and control method thereof |
| CN202310051914.XA CN116231793A (en) | 2020-08-26 | 2020-08-26 | Double-redundancy control method for autonomous power-up after separation of satellite active section from satellite rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010868323.8A CN112018845B (en) | 2020-08-26 | 2020-08-26 | Autonomous satellite power-on system and control method thereof |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202310051914.XA Division CN116231793A (en) | 2020-08-26 | 2020-08-26 | Double-redundancy control method for autonomous power-up after separation of satellite active section from satellite rocket |
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| Publication Number | Publication Date |
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| CN112018845A true CN112018845A (en) | 2020-12-01 |
| CN112018845B CN112018845B (en) | 2022-12-23 |
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| CN202310051914.XA Pending CN116231793A (en) | 2020-08-26 | 2020-08-26 | Double-redundancy control method for autonomous power-up after separation of satellite active section from satellite rocket |
| CN202010868323.8A Active CN112018845B (en) | 2020-08-26 | 2020-08-26 | Autonomous satellite power-on system and control method thereof |
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| CN112018845B (en) | 2022-12-23 |
| CN116231793A (en) | 2023-06-06 |
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