CN112018869B - Star and arrow separation is from power-on circuit independently - Google Patents
Star and arrow separation is from power-on circuit independently Download PDFInfo
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- CN112018869B CN112018869B CN202010790434.1A CN202010790434A CN112018869B CN 112018869 B CN112018869 B CN 112018869B CN 202010790434 A CN202010790434 A CN 202010790434A CN 112018869 B CN112018869 B CN 112018869B
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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
- H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
- H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
- H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
- H02J9/061—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems for DC powered loads
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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
- H02J7/34—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
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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
- Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
- Y02B10/00—Integration of renewable energy sources in buildings
- Y02B10/70—Hybrid systems, e.g. uninterruptible or back-up power supplies integrating renewable energies
Abstract
The embodiment of the invention discloses a satellite and rocket separation autonomous power-on circuit, which comprises a solar battery array, a bus, a storage battery pack, an autonomous power-on switch, an autonomous separation circuit, a separation switch, a discharge switch, a satellite computer and a DC/DC module, wherein before satellite and rocket separation, the autonomous separation circuit is set to be in an enabling state, the separation switch is set to be in a closing state, the discharge switch is set to be in an opening state, the entire satellite is in a power-off state, after the satellite is separated from a rocket, the separation switch is changed from the closing state to the opening state, the autonomous power-on switch is conducted, the storage battery pack supplies power to the bus, the entire satellite is powered on, in order to avoid the failure of the separation switch or the autonomous power-on switch, so that the entire satellite cannot be powered on, then the satellite computer sends a switching-on instruction to open the discharge switch, and sets the autonomous separation circuit to be in a disabling state from the enabling state, and the autonomous separation autonomous power-on circuit controls the autonomous power-on switch to be switched off, the storage battery supplies power to the bus through the discharge switch, and the satellite is automatically electrified after the satellite and the arrow are separated.
Description
Technical Field
The invention relates to the technical field of satellite and arrow separation, in particular to an autonomous power-on circuit for satellite and arrow separation.
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 computer detects a satellite and arrow separation effective signal, the satellite and the arrow separation effective signal is used as the initial moment of the whole satellite, a program control program is started to be executed, and operations such as attitude control, initiating explosive device detonation control, state monitoring load photographing and the like are started. However, with the rapid development of the microsatellite technology and the rapid development of the commercial space flight, the task demand of carrying one rocket with multiple satellites or satellites is increasing day by day, if the satellites are also in a normally powered-on state when carrying on the rocket, unnecessary signal interference can be caused to the main satellite, the design thought is inflexible, the satellite storage battery needs to be subjected to power supplementing operation before launching, and the demand of the commercial space flight rapid launching cannot be realized.
Therefore, a circuit needs to be designed, so that the satellite is in a normally-off state after being in butt joint with the carrier rocket, and meanwhile, after the satellite and the rocket are separated, the satellite can also be automatically electrified.
Disclosure of Invention
The embodiment of the invention provides an autonomous electrifying circuit for satellite and arrow separation, and after separation of a satellite and an arrow, the satellite can be electrified autonomously.
The invention provides an autonomous star-arrow separation power-on circuit, which comprises a solar cell array, a bus, a storage battery pack, a self-starting power-on switch, a separation self-starting circuit, a separating switch, a discharging switch, a star computer, a DC/DC module and a backflow prevention charging circuit, wherein,
the solar cell array is connected with the bus, the storage battery pack is connected with the bus through the self-starting power-on switch and the discharge switch respectively, the bus is connected with the satellite computer through the DC/DC module, the self-starting power-on switch is controlled by the separation self-starting circuit and the separation switch respectively, the separation switch is controlled by the satellite computer, and the solar cell array is connected with the storage battery pack through the backflow-preventing charging circuit;
after the satellite and the rocket are in butt joint and are mechanically connected, the separation self-starting circuit is set to be in an enabling state until the satellite and the rocket are separated, the separation switch is set to be in a closed state, the discharge switch is set to be in an off state, the satellite is located in the fairing, and the whole satellite is in a power-down state;
after the satellite and the rocket are normally separated in orbit, the disconnecting switch is changed from a closed state to an open state, the self-starting power-on switch is switched on at the moment, the storage battery pack supplies power to the bus through the self-starting power-on switch, and the whole satellite is powered on and started;
the star affair computer sends a switching-on instruction to the discharge switch, the discharge switch is switched on, the star affair computer sends a forbidding instruction to the separation self-starting circuit, the separation self-starting circuit is set to be in a forbidding state from an enabling state, the separation self-starting circuit controls the self-starting power-on switch to be switched off at the moment, and the storage battery pack supplies power to the bus through the discharge switch at the moment.
In some embodiments, the self-starting power-on switch is formed by connecting a P-MOS transistor Q1 and a P-MOS transistor Q2 in parallel.
In some embodiments, the sources of Q1 and Q2 are connected to the battery pack and the drains of Q1 and Q2 are connected to the bus.
In some embodiments, the discharge switch is a magnetic hold relay K1.
In some embodiments, the K1 is 3JB 10-1.
In some embodiments, the separate self-starting circuit is formed by connecting a magnetic latching relay K2 and a magnetic latching relay K3 in parallel.
In some embodiments, the K2 and the K3 are 2JB1-910-28V in model number.
In some embodiments, the K2 and K3 are in an open state when the split self-enabling circuit is in an inhibit state.
In some embodiments, the satellite-rocket separation autonomous power-on circuit further comprises a back-flow prevention charging circuit, and the solar cell array is connected with the storage battery pack through the back-flow prevention charging circuit.
In some embodiments, the anti-backflow charging circuit is formed by connecting a first parallel diode and a second parallel diode in series, wherein the first parallel diode and the second parallel diode are respectively formed by connecting two diodes in parallel.
In some embodiments, the model of the diode includes MBR2060CT or 48CTQ 060.
In the scheme, the satellite-rocket separation autonomous power-on circuit comprises a solar cell array, a bus, a storage battery pack, an autonomous power-on switch, an autonomous separation circuit, a disconnecting switch, a discharging switch, a satellite computer and a DC/DC module, wherein the solar cell array is connected with the bus, the storage battery pack is respectively connected with the bus through the autonomous power-on switch and the discharging switch, the bus is connected with the satellite computer through the DC/DC module to supply power to the satellite computer, the autonomous power-on switch is respectively controlled by the autonomous separation circuit and the disconnecting switch, the disconnecting switch is controlled by the satellite computer, after the satellite is in butt joint with a rocket and is mechanically connected, the whole satellite is in a power-off state until the satellite and the rocket are separated, after the satellite and the rocket are normally separated in an orbit, the disconnecting switch is changed into a disconnecting state, the autonomous power-on switch is switched on at the moment, the storage battery pack supplies power to the bus through the autonomous power-on switch, the whole satellite is powered on and started, in order to avoid the fault of a disconnecting switch or a self-starting power-on switch, the whole satellite cannot be powered on, then the satellite affair computer sends a switching-on instruction to turn on a discharge switch, the enabling state of a self-starting circuit is set to be a forbidden state, the self-starting circuit controls the self-starting power-on switch to be switched off, and at the moment, the storage battery supplies power to a bus through the discharge switch, so that the satellite can be powered on automatically after the satellite and the arrow are separated.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic structural diagram of an autonomous power-on circuit for satellite and rocket separation according to an embodiment of the present invention;
fig. 2 is a schematic circuit structure diagram of a satellite-rocket separation autonomous power-on circuit provided in the embodiment of the present invention.
DETAILED DESCRIPTION OF EMBODIMENT (S) OF INVENTION
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more features. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present disclosure, the word "exemplary" is used to mean "serving as an example, instance, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. The following description is presented to enable any person skilled in the art to make and use the invention. In the following description, details are set forth for the purpose of explanation. It will be apparent to one of ordinary skill in the art that the present invention may be practiced without these specific details. In other instances, well-known structures and processes are not shown in detail to avoid obscuring the description of the invention with unnecessary detail. Thus, the present invention is not intended to be limited to the embodiments shown, but is to be accorded the widest scope consistent with the principles and features disclosed herein.
Referring to fig. 1, fig. 1 is a schematic structural diagram of an autonomous star-arrow power-on circuit according to an embodiment of the present invention, where the autonomous star-arrow power-on circuit includes a solar cell array 101, a bus 102, a storage battery 103, a self-starting power-on switch 104, a self-starting circuit 105, a separating switch 106, a discharging switch 107, a star computer 108, a DC/DC module 109, and a backflow prevention charging circuit 110, where:
the solar cell array 101 is connected with a bus 102, a storage battery pack 103 is respectively connected with the bus 102 through a self-starting power-on switch 104 and a discharge switch 107, the bus 102 is connected with a star computer 108 through a DC/DC module 109, the self-starting power-on switch 104 is respectively controlled by a separation self-starting circuit 105 and a separation switch 106, the separation switch 106 is controlled by the star computer 108, and the solar cell array 101 is connected with the storage battery pack 103 through a backflow prevention charging circuit 110;
after the satellite and the rocket are in butt joint and mechanically connected, the separation self-starting circuit 105 is set to be in an enabling state until the satellite and the rocket are separated, the separation switch 106 is set to be in a closing state, the discharge switch 107 is set to be in a disconnecting state, the satellite is in the fairing, and the whole satellite is in a power-down state, so that the butt joint of the satellite and the rocket after the power of the whole satellite is cut off is realized;
after the satellite and the rocket are normally separated in orbit, the disconnecting switch 106 is changed from a closed state to an open state, the self-starting power-on switch 104 is switched on at the moment, the storage battery pack 103 supplies power to the bus 102 through the self-starting power-on switch 104, and the whole satellite is powered on and started;
in order to avoid the fault of the disconnecting switch 106 or the self-starting power-on switch 104, the star computer 108 sends a switch-on instruction to the discharge switch 107, the discharge switch 107 is switched on, the star computer 108 sends a disable instruction to the disconnecting self-starting circuit 105, the disconnecting self-starting circuit 105 is set to be in a disable state from an enable state, the disconnecting self-starting circuit 105 controls the self-starting power-on switch 104 to be switched off, and the storage battery pack 103 supplies power to the bus 102 through the discharge switch 107.
In the present embodiment, the anti-backflow charging circuit 110 is formed by connecting a first parallel diode DC-1 and a second parallel diode DC-2 in series, wherein the first parallel diode DC-1 and the second parallel diode DC-2 are respectively formed by connecting two diodes in parallel.
The solar cell array 101 in this embodiment is a power generation device of a satellite power system, and can receive sunlight and continuously provide electric energy for a satellite through photoelectric conversion. The solar cell array 101 is directly connected to the bus 102 and is connected to the storage battery pack 103 through the anti-backflow charging circuit 110, the storage battery current is prevented from flowing backwards to the solar cell array 101 by utilizing the unidirectional conductivity of the diode in the anti-backflow charging circuit 110, and the current of the solar cell array 101 can flow to the storage battery pack 103, so that the storage battery pack 103 can still be charged through the diode by the solar cell array 101 under the condition that the discharge switch 107 is switched off. The diode can be selected from MBR2060CT or 48CTQ060 and other types which can meet the use requirement, and the reliability can be improved by adopting a parallel connection and series connection mode, so that the protection function fault caused by the open circuit or short circuit failure of the diode can be prevented.
Referring to fig. 2, fig. 2 is a schematic circuit structure diagram of a satellite-rocket separation autonomous power-on circuit according to an embodiment of the present invention, in which an output positive line of a solar cell array 101 is connected to pins 1 and 3 of a DC-1 in a backflow prevention charging circuit 110, pin 2 is connected to pins 1 and 3 of the DC-2, and pin 2 of the DC-2 is connected to a positive line of a storage battery 103. The storage battery is respectively connected with the bus 102 through two paths, one is connected with the bus through two parallel P-MOS tubes Q1 and Q2 (a self-starting power-on switch 104), and the other is connected with the bus through a magnetic latching relay K1 (a discharging switch 107). The sources (S poles) of Q1 and Q2 are connected to the positive terminal of the battery, the drains (D poles) are connected to the positive line of the bus 102, and the discharge current of the battery flows from the S poles to the D poles, thereby supplying power to the bus 102. Resistors R1, R2, R5, R7, capacitors C1, and C2 together form a control loop portion of Q1, and similarly, resistors R3, R4, R6, R7, capacitors C3, and C4 are control loop portions of Q2. The other ends of R5 and R6 are connected with a contact 1 of a disconnecting switch 106, the other end of R7 is connected with a contact 2 of the disconnecting switch 106, and the disconnecting switch 106 is a normally open contact. One ends of R1 and R3 are connected to the gate (G pole) of the P-MOS tube, and the other ends are connected with 3 pins of the relays K2 and K3.
The magnetic latching relays K2 and K3 are used in parallel to form the separated self-starting circuit 105, and the parallel design has the function of improving the reliability and playing a role in hot backup. The relay model can be selected from 2JB1-910-28V, and the connection of each pin is shown in FIG. 2. X1 is the positive end of the conducting coil, X2 is the negative end of the conducting coil, Y1 is the positive end of the off coil, and Y2 is the negative end of the off coil. One ends of the resistors R10, R11, R12 and R13 are connected with the positive ends X1 and Y1 of the relay coils, and the other ends are connected with the power supply bus 102, so that the current limiting function is realized, and the coils are prevented from being burnt by overlarge current. The negative end of the coil is respectively connected to an enabling/disabling control end, and the coil is in a disabling state by default before being electrified. D5, D6, D7 and D8 are freewheeling diodes of the relay K1, D9, D10, D11 and D12 are freewheeling diodes of the relay K2, and the functions of the freewheeling diodes are to provide a freewheeling circuit for induced electromotive force generated when the coil is powered off, and the generated induced electromotive force is consumed by applying work through the circuit formed by the diodes and the coil.
The magnetic latching relay K1 of the other discharging path of the storage battery pack 103 can be 3JB10-1, the positive line of the storage battery pack 103 is connected to pins 2, 5 and 8, the pins 3, 6 and 9 are connected to the power supply bus 102, and the on-off of the switch is realized by controlling the on-off of the coil, so that the discharging path of the storage battery pack 103 is controlled. The +28V bus 102 is connected in series to the coil positive end through R8 and R9, the coil negative end is connected to the control ends FDKG _ ON and FDKG _ OFF, R8 and R9 play a current limiting protection role, and the switching state is default to be OFF. The positive and negative ends of the turn-on and turn-off coil are connected with two diodes in anti-parallel, namely D1 and D2, D3 and D4 respectively, and the function of the diode is to provide a discharge loop for the induced electromotive force of the magnetic coil.
In addition, the star computer 108 is connected to the bus 102 via a DC/DC module 109 to obtain electrical energy from the bus 102 (not shown in FIG. 2)
For the convenience of understanding, the working principle of the satellite-arrow separation autonomous power-on circuit provided by the present embodiment will be described in detail below with reference to fig. 2, as follows:
after the whole satellite completes the last test before the transmitting field is ready to transmit, before the power is cut off, the satellite computer 108 sends an enabling instruction of the separation self-starting circuit 105, namely MOS _ ON is in low level, K2 and K3 are switched ON, and the separation self-starting circuit 105 is set to be in an enabling state. The discharge switch 107K1 is turned OFF, i.e., FDKG _ OFF is low, and K1 is turned OFF. After the whole satellite is loaded with the arrow, the disconnecting switch 106 is in an unseparated state, at the moment, the disconnecting switch 106 is in a closed state, the FLKG _1 and the FLKG _2 are conducted, the potentials are equal, namely the G pole and the S pole of the P-MOS tube of the storage battery discharging passage are always consistent, the Q1 and the Q2 cannot be conducted, and the disconnecting switch is always in a disconnected state, so that the loop of the storage battery 103 and the bus 102 is disconnected. And the satellite is in the radome, and solar array 101 does not receive the sun illumination and also has no power output, can guarantee that whole satellite is in the power failure state.
When the satellite is launched into the orbit along with the carrying, and the satellite and the arrow are separated, the disconnecting switch 106 is switched from being closed to being opened, and the G pole and the S pole of the P-MOS tube are horizontally unlocked. The S stages of Q1 and Q2 are both directly connected to the positive electrode of the storage battery pack 103, and the potential is the voltage of the storage battery pack 103; the G poles of Q1 and Q2 are connected to the negative pole (the negative pole of the storage battery pack 103) of the bus 102 through R1 and R3 respectively and then K2 and K3, the potential of the G pole of a Q1 switching tube is divided through R1 and R2, the potential of the G pole of a Q2 switching tube is divided through R3 and R4, the voltage difference of G, S ends of the two switching tubes reaches the starting voltage of the MOS tube, so that Q1 and Q2 are conducted, the storage battery pack 103 supplies power to the bus 102 through the MOS tube, and the whole satellite is started electrically.
Then, the star computer 108 sends a turn-ON command "discharge switch 107 of the battery pack 103 is turned ON", so that FDKG _ ON is set to a low level, and the relay K1 is turned ON. Then the star computer 108 sends a prohibition instruction "star and arrow separation self-starting circuit 105 is prohibited", so that MOS _ OFF is changed to low level, the relays K2 and K3 are disconnected, the G pole of the MOS tube is connected to the positive line of the storage battery pack 103 through R2 or R4, a loop is not formed, therefore, the G pole and the S pole are equal in potential, the MOS tube is disconnected, and the storage battery pack 103 supplies power to the bus 102 through K1. This is to prevent disconnection switch 106 from failing or being unstable in state causing Q1 and Q2 to open, causing bus 102 to be de-energized, when the rail is in operation for a long period of time. And the satellite completes the whole process of separating the satellite from the rocket.
It should be noted that when the separation self-starting circuit 105 is in the disabled state, K2 and K3 are in the open state, and no matter the separation switch 106 is closed or opened, the potentials at the G, S terminal of the self-starting power-on switch 104 are equal, and Q1 and Q2 cannot be controlled to be turned on and off through the separation switch 106.
If the disconnecting switch 106 fails and the satellite and the arrow are always in a closed state after being separated, the whole satellite cannot be powered on, and the whole task is not benefited. Therefore, the star-arrow separation autonomous power-on circuit designed by the invention also considers the condition of the faults. After the separation of the orbit, if the storage battery 103 fails to supply power to the bus 102 due to the fault of the separation switch 106, the cell mounting surface of the solar cell array 101 faces outwards, and in the process of free floating in the space after the satellite is in orbit, once the solar cell array 101 is sunned, the power can be output to supply power to the bus 102, the star computer 108 can be powered on, and then a switching-on instruction 'the discharge switch 107 of the storage battery 103 is switched on' is sent to the discharge switch 107, so that the storage battery 103 is connected to the bus 102 through the discharge switch 107, and the whole satellite is powered on. Due to the fault of the disconnecting switch 106, the satellite computer 108 cannot normally detect a satellite and arrow separating signal, and after the ground judges that the disconnecting switch 106 has the fault through remote measurement, the whole satellite is controlled through a ground remote control instruction to execute program control operation after the satellite and the arrow are separated.
Considering another possible situation, if the radome throwing time is relatively early, the solar cell array 101 may be exposed to the sun before separation to power up the whole satellite, but the satellite affair computer 108 still collects satellite-arrow separation signals in an unseparated state, so that program control instructions after separation of the satellite and the arrow, such as initiating of initiating explosive devices, starting and controlling of attitude control single machine and the like, cannot be executed, and normal starting and controlling of the satellite cannot be influenced.
In the scheme, the satellite and rocket separation autonomous power-on circuit comprises a solar cell array, a bus, a storage battery pack, an autonomous power-on switch, an autonomous separation circuit, a disconnecting switch, a discharging switch, a satellite computer and a DC/DC module, wherein the solar cell array is connected with the bus, the storage battery pack is respectively connected with the bus through the autonomous power-on switch and the discharging switch, the bus is connected with the satellite computer through the DC/DC module, the autonomous power-on switch is respectively controlled by the autonomous separation circuit and the disconnecting switch, the disconnecting switch is controlled by the satellite computer, after the satellite is in butt joint with a rocket and mechanically connected, the whole satellite is in a power-off state until the satellite and the rocket are separated, after the satellite and the rocket are normally separated in orbit, the disconnecting switch is changed into a disconnecting state, the autonomous power-on switch is switched on at the moment, the storage battery pack supplies power to the bus through the autonomous power-on switch, the whole satellite is powered on and started, in order to avoid the fault of a disconnecting switch or a self-starting power-on switch, the whole satellite cannot be powered on, then the satellite affair computer sends a switching-on instruction to turn on a discharge switch, the enabling state of a self-starting circuit is set to be a forbidden state, the self-starting circuit controls the self-starting power-on switch to be switched off, and at the moment, the storage battery supplies power to a bus through the discharge switch, so that the satellite can be powered on automatically after the satellite and the arrow are separated.
The satellite-rocket separation autonomous power-on circuit provided by the embodiment of the invention is described in detail, a specific embodiment is applied in the description to explain the principle and the embodiment of the invention, and the description of the embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for those skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.
Claims (10)
1. An autonomous electrifying circuit for satellite and rocket separation is characterized by comprising a solar cell array, a bus, a storage battery pack, an automatic electrifying switch, a self-starting circuit for separation, a separating switch, a discharging switch, a satellite computer, a DC/DC module and a backflow preventing charging circuit, wherein,
the solar cell array is connected with the bus, the storage battery pack is connected with the bus through the self-starting power-on switch and the discharge switch respectively, the bus is connected with the satellite computer through the DC/DC module, the self-starting power-on switch is controlled by the separation self-starting circuit and the separation switch respectively, the separation switch is controlled by the satellite computer, and the solar cell array is connected with the storage battery pack through the backflow-preventing charging circuit;
after the satellite and the rocket are in butt joint and are mechanically connected, the separation self-starting circuit is set to be in an enabling state until the satellite and the rocket are separated, the separation switch is set to be in a closed state, the discharge switch is set to be in an off state, the satellite is located in the fairing, and the whole satellite is in a power-down state;
after the satellite and the rocket are normally separated in orbit, the disconnecting switch is changed from a closed state to an open state, the self-starting power-on switch is switched on at the moment, the storage battery pack supplies power to the bus through the self-starting power-on switch, and the whole satellite is powered on and started;
the star affair computer sends a switching-on instruction to the discharge switch, the discharge switch is switched on, the star affair computer sends a forbidding instruction to the separation self-starting circuit, the separation self-starting circuit is set to be in a forbidding state from an enabling state, the separation self-starting circuit controls the self-starting power-on switch to be switched off at the moment, and the storage battery pack supplies power to the bus through the discharge switch at the moment.
2. The star-arrow separation autonomous power-on circuit according to claim 1, characterized in that the self-starting power-on switch is formed by connecting a P-MOS transistor Q1 and a P-MOS transistor Q2 in parallel.
3. The star-arrow separation autonomous power-on circuit according to claim 2, characterized in that the sources of Q1 and Q2 are connected to the battery pack, and the drains of Q1 and Q2 are connected to the bus bar.
4. The star-arrow separation autonomous power-on circuit according to claim 1, characterized in that the discharge switch is a magnetic latching relay K1.
5. The star-arrow separation autonomous power-on circuit according to claim 4, characterized in that the type of K1 is 3JB 10-1.
6. The star-arrow separation autonomous power-on circuit according to claim 1, characterized in that the separation self-starting circuit is formed by connecting a magnetic latching relay K2 and a magnetic latching relay K3 in parallel.
7. The star-arrow separation autonomous power-on circuit according to claim 6, characterized in that the models of the K2 and the K3 are 2JB 1-910-28V.
8. The satellite-rocket separation autonomous power-on circuit according to claim 7, wherein when the separation self-enabling circuit is in an inhibit state, the K2 and K3 are in an open state.
9. The star-arrow separation autonomous power-on circuit according to any one of claims 1 to 8, characterized in that the anti-backflow charging circuit is formed by connecting a first parallel diode and a second parallel diode in series, wherein the first parallel diode and the second parallel diode are respectively formed by connecting two diodes in parallel.
10. The star-arrow separation autonomous power-on circuit according to claim 9, characterized in that the type of the diode comprises MBR2060CT or 48CTQ 060.
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|---|---|---|---|---|
| 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 |
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