Autonomous power-up circuit and satellite power supply system

Abstract

The invention discloses an autonomous power-up circuit and a satellite power supply system. The autonomous power-up circuit comprises a satellite-rocket separation enabling unit, a storage battery discharge switch unit and a bus switch unit; wherein the satellite-rocket separation enabling unit is connected with the storage battery discharge switch unit and the bus switch unit, and is used for controlling the storage battery discharge switch unit and the bus switch unit to be in a conducting state when a satellite and a rocket are separated and injected into an orbit; the storage battery discharging switch unit is connected with a storage battery pack of the satellite and the bus switch unit, the bus switch unit is connected with a load of the satellite, and the storage battery discharging switch unit and the bus switch unit are used for providing electric energy output by the storage battery pack for the load when being in a conducting state. According to the autonomous power-up circuit and the satellite power supply system provided by the invention, when the satellite and the rocket are separated, autonomous power-up can be carried out on the satellite through the storage battery pack, and meanwhile, the problem of uncontrollable power-up of the satellite after a fairing is thrown in an active section can be avoided.

Description

Technical Field

[0001] The present application relates to the field of satellite power supply technology, and in particular to an autonomous power-on circuit and a satellite power supply system. Background Art

[0002] In recent years, with the rapid development of satellite micro-technology, the launch of multiple satellites with one rocket has gradually become the main means for micro-satellites to enter space. Due to the constraints of orbital illumination and the structural layout of satellites, micro-satellites usually adopt a double-wing configuration, and n solar arrays are evenly distributed on each solar wing (i.e., solar sail). Before launch, the solar wings on both sides are folded on the satellite body. When the satellite separates from the carrier rocket and enters orbit, the solar wings are still in a folded state and cannot power the entire satellite. At this time, the battery on the satellite needs to complete the initial power-on of the satellite through autonomous power-up. After the satellite service computer is powered on and runs, the orbit entry process is executed, the solar wings on both sides are unfolded, and the solar orientation is completed. Only then can the solar energy be normally obtained to power the satellite load and charge the battery.

[0003] In the prior art, in order to prevent the failure of the autonomous power-up function of the battery when the rocket separates and enters orbit, and to increase the reliability of orbital power-up, when designing the solar panels of micro-satellites, when the solar panels are folded, the cells of at least one side of the solar panels face outward. In this state, even if the autonomous power-up function fails after the rocket separates, the satellite cannot be initially powered by the battery. When the solar panels facing outward are exposed to light, the satellite has a certain probability of obtaining solar energy to initially power the entire satellite. However, if the design of the panels folded and the cells facing outward is adopted, in the active phase of satellite launch, the carrier rocket usually carries the satellite to continue flying for a period of time after completing the fairing jettisoning action to reach the designated orbital position, and then separates the rocket from the rocket. During this process, because there is no fairing to block, the cells of the solar panels may be in a state of sunlight exposure, but due to the unstable light intensity and light angle, the output power of the solar array is unstable, resulting in an uncontrollable power-up state. The load equipment on the satellite may be undervoltage, repeatedly powered on and off due to unstable power supply conditions, causing damage to the satellite equipment. Summary of the invention

[0004] The purpose of this application is to provide an autonomous power-on circuit and a satellite power supply system, which can autonomously power the satellite through a battery pack when the satellite and rocket are separated, thereby avoiding the problem of uncontrollable powering of the satellite after the fairing is jettisoned in the active stage.

[0005] To achieve the above objectives: In a first aspect, an embodiment of the present application provides an autonomous power-on circuit, including a satellite-rocket separation enabling unit, a battery discharge switch unit, and a bus switch unit; wherein: The satellite-rocket separation enabling unit is connected to the battery discharge switch unit and the bus switch unit, and is used to control the battery discharge switch unit and the bus switch unit to be in a conducting state when the satellite is separated from the rocket and enters orbit; The battery discharge switch unit is connected to the battery group of the satellite and the bus switch unit, and the bus switch unit is connected to the load of the satellite. When the battery discharge switch unit and the bus switch unit are in an on state, they are used to provide the electric energy output by the battery group to the load.

[0006] In one embodiment, the satellite-rocket separation enabling unit includes an autonomous power-on prohibition switch, a satellite meter socket, and a satellite-rocket separation travel switch; wherein, The first end of the autonomous power-on prohibition switch is connected to the battery discharge switch unit, and the second end of the autonomous power-on prohibition switch is connected to the first connection node of the star meter socket; The satellite-rocket separation travel switch includes a normally closed contact and a normally open contact, the first end of the normally closed contact is connected to the second connection node of the satellite socket, and the second end of the normally closed contact is connected to the negative pole of the battery pack; the first end of the normally open contact is connected to the fourth connection node of the satellite socket, and the second end of the normally open contact is connected to the negative pole of the battery pack.

[0007] In one embodiment, there are at least two satellite-rocket separation travel switches, and the satellite-rocket separation travel switches are redundantly arranged in parallel.

[0008] In one embodiment, the satellite-rocket separation enabling unit further includes a satellite-rocket separation signal acquisition unit; wherein, The satellite-rocket separation signal acquisition unit includes a first sampling resistor and a second sampling resistor; The first sampling resistor and the second sampling resistor are connected in series between the satellite's telemetry collection power supply and ground; The common end of the first sampling resistor and the second sampling resistor is connected to the third connection node of the satellite meter socket, and the common end of the first sampling resistor and the second sampling resistor is the output end of the satellite-rocket separation signal acquisition unit.

[0009] In one embodiment, the battery discharge switch unit includes a battery discharge power switch, a first voltage-dividing resistor and a second voltage-dividing resistor; wherein, The control end of the battery discharge power switch is connected to the first end of the autonomous power-on prohibition switch through a first voltage-dividing resistor, the first path end of the battery discharge power switch is connected to the positive electrode of the battery pack, and the second path end of the battery discharge power switch is connected to the bus switch unit; The second voltage-dividing resistor is connected between the control terminal and the first path terminal of the battery discharging power switch.

[0010] In one embodiment, the bus switch unit includes a bus power switch, a third voltage-dividing resistor and a fourth voltage-dividing resistor; wherein, The control end of the busbar power-on power switch is connected to the first connection node of the star meter socket through a third voltage-dividing resistor, the first path end of the busbar power switch is connected to the second path end of the battery discharge power switch, and the second path end of the busbar power switch is connected to the load; The fourth voltage-dividing resistor is connected between the control terminal and the first path terminal of the busbar power-on power switch.

[0011] In one embodiment, the bus switch unit further comprises a bus energizing relay, wherein the bus energizing relay is connected in parallel between the first channel end and the second channel end of the bus energizing power switch.

[0012] In a second aspect, an embodiment of the present application provides a satellite power supply system, comprising the autonomous power-on circuit as described above.

[0013] In one embodiment, the satellite power supply system further includes a battery charging and discharging module, wherein the battery charging and discharging module includes a battery pack, a battery discharging relay and a charging diode; wherein, The first end of the battery discharge relay is connected to the positive electrode of the battery pack, and the second end of the battery discharge relay is connected to the bus switch unit of the autonomous power-on circuit; The charging diode is arranged in parallel with the battery discharging relay.

[0014] In one embodiment, the satellite power supply system further includes a sequential switch shunt regulation module; wherein, The sequential switch shunt regulation module includes a plurality of solar cell arrays and a shunt regulation circuit correspondingly connected to each solar cell array; The solar cell array is used to provide working current for the satellite's load and charging current for the battery pack while the satellite is in orbit; The shunt regulating circuit is used to shunt the excess electric energy output by the solar cell array when the power supply current of the solar cell array is greater than the sum of the working current of the load and the charging current of the storage battery group.

[0015] The autonomous power-on circuit and satellite power supply system provided in the embodiment of the present application, when the satellite separates from the rocket and enters orbit, controls the battery discharge switch unit and the bus switch unit to be in the on state through the satellite-rocket separation enabling unit; after the battery discharge switch unit and the bus switch unit are connected, the electric energy output by the battery pack is provided to the load. In this way, the autonomous power-on process of the satellite can be completed through the battery pack when the satellite and rocket are separated, and the problem of uncontrollable power-on of the satellite after the fairing is jettisoned in the active stage can be avoided. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without paying creative work.

[0017] Figure 1 A schematic diagram of the structure of an autonomous power-on circuit provided in an embodiment of the present application.

[0018] Figure 2 A circuit diagram of the autonomous power-on circuit provided in an embodiment of the present application before the separation of the satellite and the rocket.

[0019] Figure 3 A circuit diagram of the autonomous power-on circuit provided in an embodiment of the present application after the separation of the satellite and the rocket.

[0020] Figure 4 A circuit diagram of a satellite power supply system provided in an embodiment of the present application.

[0021] In the figure: autonomous power-on circuit 100; satellite-rocket separation enabling unit 110, autonomous power-on prohibition switch 111, satellite meter socket 112, satellite-rocket separation travel switch 113, satellite-rocket separation signal acquisition unit 114, first sampling resistor R5, second sampling resistor R6; battery discharge switch unit 120, battery discharge power switch D1, first voltage-dividing resistor R1, second voltage-dividing resistor R2; bus switch unit 130, bus power-on power switch D2, third voltage-dividing resistor R3, fourth voltage-dividing resistor R4, bus power-on relay K1; Battery charge and discharge module 200, battery pack BAT, battery discharge relay K2, charging diode V1; The shunt regulating module 300 , the solar cell array 310 , and the shunt regulating circuit 320 are switched in sequence. DETAILED DESCRIPTION

[0022] Exemplary embodiments will be described in detail herein, examples of which are shown in the accompanying drawings. When the following description refers to the drawings, the same numbers in different drawings represent the same or similar elements unless otherwise indicated. The implementations described in the following exemplary embodiments do not represent all implementations consistent with the present application. Instead, they are merely examples of devices and methods consistent with some aspects of the present application as detailed in the appended claims.

[0023] It should be noted that, in this article, the terms "include", "comprises" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the sentence "includes a ..." does not exclude the existence of other identical elements in the process, method, article or device including the element. In addition, components, features, and elements with the same name in different embodiments of the present application may have the same meaning or different meanings, and their specific meanings need to be determined by their explanation in the specific embodiment or further combined with the context of the specific embodiment.

[0024] It should be understood that, although the terms first, second, third, etc. may be used to describe various information in this article, these information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other. For example, without departing from the scope of this article, the first information may also be referred to as the second information, and similarly, the second information may also be referred to as the first information. Depending on the context, the word "if" as used herein can be interpreted as "at the time of..." or "when..." or "in response to determination". Furthermore, as used in this article, the singular forms "one", "one" and "the" are intended to also include plural forms, unless there is an opposite indication in the context. It should be further understood that the terms "comprising", "including" indicate that there are described features, steps, operations, elements, components, projects, kinds, and / or groups, but do not exclude the existence, occurrence or addition of one or more other features, steps, operations, elements, components, projects, kinds, and / or groups. The terms "or" and "and / or" used herein are interpreted as inclusive, or mean any one or any combination. Thus, “A, B, or C” or “A, B and / or C” means “any of the following: A; B; C; A and B; A and C; B and C; A, B, and C.” An exception to this definition will occur only when a combination of elements, functions, steps, or operations are inherently mutually exclusive in some manner.

[0025] It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0026] In the subsequent description, the suffixes such as "module", "component" or "unit" used to represent elements are only used to facilitate the description of the present application, and have no specific meanings. Therefore, "module", "component" or "unit" can be used in a mixed manner.

[0027] Figure 1 A schematic diagram of the structure of the autonomous power-on circuit provided in the embodiment of the present application; Figure 1 As shown, the autonomous power-on circuit 100 provided in the embodiment of the present application includes a satellite-rocket separation enabling unit 110 , a battery discharge switch unit 120 and a bus switch unit 130 .

[0028] Among them, the satellite-rocket separation enabling unit 110 is connected to the battery discharge switch unit 120 and the bus switch unit 130, and is used to control the battery discharge switch unit 120 and the bus switch unit 130 to be in the on state when the satellite separates from the rocket and enters orbit; the battery discharge switch unit 120 is connected to the satellite's battery pack BAT+ and the bus switch unit 130, and the bus switch unit 130 is connected to the satellite's load. When the battery discharge switch unit 120 and the bus switch unit 130 are in the on state, they are used to provide the electric energy output by the battery pack to the load.

[0029] In this embodiment, before the satellite separates from the carrier rocket, the battery discharge switch unit 120 and the bus switch unit 130 are both in the disconnected state, and the satellite is completely powered off at this time. Even after the carrier rocket completes the fairing jettisoning action, the solar panels are under illumination, but because the bus switch unit 130 is in the disconnected state, the power output by the solar panels cannot be provided to the satellite load through the bus, thereby ensuring that there will be no uncontrollable power-on problem before the satellite-rocket separation. When the satellite separates from the carrier rocket and enters orbit, the battery discharge switch unit 120 and the bus switch unit 130 are controlled to be in the on state through the satellite-rocket separation enabling unit 110, forming a closed autonomous power-on loop, so that the battery pack can provide the stored power to the satellite's load equipment through the autonomous power-on loop, and complete the initial power-on for the satellite.

[0030] Figure 2 This is a circuit diagram of the autonomous power-on circuit provided in an embodiment of the present application before the separation of the satellite and the rocket. Figure 3 The circuit diagram of the autonomous power-on circuit provided in the embodiment of the present application after the satellite-rocket separation; Figure 2 and Figure 3 The specific circuit structure and working principle of the autonomous power-on circuit are introduced.

[0031] In the embodiment of the present application, the satellite-rocket separation enabling unit 110 includes an autonomous power-on prohibition switch 111 , a satellite meter socket 112 , and a satellite-rocket separation travel switch 113 . Among them, the first end of the autonomous power-on prohibition switch 111 is connected to the battery discharge switch unit 120, and the second end of the autonomous power-on prohibition switch 111 is connected to the first connection node P1 of the satellite socket 112; the satellite-rocket separation travel switch 113 includes a normally open contact (S1_1, S2_1) and a normally closed contact (S1_2, S2_2), the first end of the normally closed contact (S1_2, S2_2) is connected to the second connection node P2 of the satellite socket 112, and the second end of the normally closed contact (S1_2, S2_2) is connected to the negative electrode BAT- of the battery pack; the first end of the normally open contact (S1_1, S2_1) is connected to the fourth connection node P4 of the satellite socket 112, and the second end of the normally open contact (S1_1, S2_1) is connected to the negative electrode BAT- of the battery pack.

[0032] The battery discharge switch unit 120 includes a battery discharge power switch D1, a first voltage-dividing resistor R1, and a second voltage-dividing resistor R2. The control end of the battery discharge power switch D1 is connected to the first end of the autonomous power-on prohibition switch 111 through the first voltage-dividing resistor R1, the first path end of the battery discharge power switch D1 is connected to the positive electrode BAT+ of the battery pack, and the second path end of the battery discharge power switch D1 is connected to the bus switch unit 130; the second voltage-dividing resistor R2 is connected between the control end and the first path end of the battery discharge power switch D1.

[0033] The bus switch unit 130 includes a bus power switch D2, a third voltage-dividing resistor R3 and a fourth voltage-dividing resistor R4. The control end of the bus power switch D2 is connected to the first connection node P1 of the star meter socket 112 through the third voltage-dividing resistor R3, the first path end of the bus power switch D2 is connected to the second path end of the battery discharge power switch D1, and the second path end of the bus power switch D2 is connected to the load; the fourth voltage-dividing resistor R4 is connected between the control end and the first path end of the bus power switch D2.

[0034] Preferably, there are at least two satellite-rocket separation travel switches, and the satellite-rocket separation travel switches are redundantly arranged in parallel. Figure 2 and Figure 3 In the illustrated embodiment, two satellite-rocket separation travel switches are provided, namely, a first satellite-rocket separation travel switch S1 and a second satellite-rocket separation travel switch S2.

[0035] Preferably, the battery discharge power switch D1 in the battery discharge switch unit 120 and the busbar power-on power switch D2 in the busbar switch unit 130 are metal oxide semiconductor transistors (MOSFETs), such as Figure 2 and Figure 3In the embodiment shown, the battery discharge power switch D1 and the bus power switch D2 are both P-type metal oxide semiconductor transistors (P-MOSFET). In other embodiments, the battery discharge power switch D1 and the bus power switch D2 can also be other semiconductor devices that can be used to control the on and off of current, such as bipolar transistors.

[0036] In the embodiment of the present application, the satellite table socket 112 and the satellite-rocket separation travel switch 113 are arranged on the satellite-rocket separation surface. The satellite table socket 112 is an exposed connector arranged on the surface of the satellite, which is used to lead the power-on control node to the satellite table. After the satellite and the rocket are docked, that is, when the satellite and the rocket are not separated, the satellite table plug will be connected to the satellite table socket on the satellite, and the satellite-rocket separation travel switch 113 is in a compressed state. Figure 2 As shown, at this time, the normally closed contacts (S1_2, S2_2) of the first satellite-rocket separation stroke switch S1 and the second satellite-rocket separation stroke switch S2 are disconnected, and the normally open contacts (S1_1, S2_1) are closed. The autonomous power-on prohibition switch 111 is set to the enabled state, that is, the closed state, before the satellite is launched. At this time, the satellite-rocket separation enabling path composed of the autonomous power-on prohibition switch 111-satellite meter socket 112-satellite-rocket separation stroke switch 113 is disconnected at the satellite-rocket separation stroke switch 113, so that the control end of the battery discharge power switch D1 and the bus power-on power switch D2, that is, the gate of the P-MOSFET is suspended, the gate-source voltage Vgs=0, and the P-MOSFET is in the cut-off state, that is, the battery discharge power switch D1 and the bus power-on power switch D2 are in the disconnected state, and the battery pack BAT cannot supply power to the satellite load through the battery discharge power switch D1 and the bus power-on power switch D2, and the entire satellite is in the power-off state. At this time, regardless of whether the satellite's solar panels are under lighting conditions, the satellite bus can ensure that there is no output before the separation of the satellite and the rocket, thereby ensuring that there will be no uncontrollable power-on problems before the separation of the satellite and the rocket.

[0037] After the satellite-rocket separation, the satellite table plug is disconnected from the satellite table socket 112 on the satellite, and the satellite-rocket separation travel switch 113 is in a released state. Figure 3As shown, at this time, the normally closed contacts (S1_2, S2_2) of the satellite-rocket separation travel switch 113 are closed, and the normally open contacts (S1_1, S2_1) are disconnected. The autonomous power-on quasi-inhibit switch 111 remains in a closed state, and the satellite-rocket separation enabling path composed of the autonomous power-on quasi-inhibit switch 111-satellite meter socket 112-satellite-rocket separation travel switch 113 is turned on, and is connected to the control ends of the battery discharge power switch D1 and the busbar power-on power switch D2 through the first voltage-dividing resistor R1 and the third voltage-dividing resistor R3, respectively, so that the voltage difference between the gate and the source of the P-MOSFET reaches the turn-on voltage of the P-MOSFET, and the P-MOSFET is in a conducting state, that is, the battery discharge power switch D1 and the busbar power-on power switch D2 are in a conducting state, and the battery pack BAT provides initial power to the satellite load through the battery discharge power switch D1 and the busbar power-on power switch D2, and the entire satellite is in a powered-on state. After the entire satellite is powered on, the satellite service computer starts to work, and the satellite service computer is responsible for the operation of the satellite.

[0038] After the star service computer works normally, it first controls the battery discharge relay K2 in the battery charge and discharge module 200 to be turned on according to the energy situation, so that the battery pack BAT can supply power to the load through the battery discharge relay K2 and the bus power switch D2.

[0039] Preferably, in an embodiment of the present application, the bus switch unit 130 further includes a bus power-on relay K1, which is connected in parallel between the first channel end and the second channel end of the bus power-on power switch D2. After the star service computer works normally, in addition to controlling the battery discharge relay K2 in the battery charge and discharge module 200 to be turned on, the bus power-on relay D2 is also controlled to be in the on state, so that the battery pack BAT supplies power to the load through the turned-on battery discharge relay D2 and the bus power-on relay K1. Since the impedance of the relay is extremely low, the heat and voltage drop problems caused by long-term use of power switches such as MOSFET to supply power to the load can be avoided, which can reduce energy loss and is conducive to the long-term stable operation of the bus.

[0040] After the battery discharge relay K2 in the battery charge and discharge module 200 is turned on, the autonomous power-on prohibition switch 111 is disconnected through the satellite computer or ground command control, so that the battery discharge power switch D1 connected to the autonomous power-on prohibition switch 111 is disconnected, and the battery discharge switch unit 120 is in a disconnected state to avoid the situation where the battery pack cannot be disconnected from the busbar when an energy crisis occurs, thereby further realizing the over-discharge protection function of the battery pack.

[0041] In the embodiment of the present application, since the control end of the bus power-on power switch D2 is directly connected to the first connection node P1 of the satellite socket 112 through the third voltage-dividing resistor R3, and is not controlled by the autonomous power-on prohibition switch 111, even if the autonomous power-on prohibition switch 111 is turned off, the bus power-on power switch D2 is still in the on state, and can supply power to the load together with the bus power-on relay K1, thereby playing a role of redundant backup, avoiding the situation where the bus power-on relay K1 is accidentally disconnected while the satellite is in orbit, causing the bus power to fail and cannot be restored.

[0042] In the above embodiment, the normally closed contacts (S1_2, S2_2) and the normally open contacts (S1_1, S2_1) of the satellite-rocket separation travel switch 113 are connected or disconnected by the mechanical movement generated when the satellite-rocket separation socket 112 and the satellite-rocket plug are plugged in or out, thereby determining whether the satellite-rocket separation occurs. Therefore, the satellite-rocket separation signal can also be collected by connecting or disconnecting the normally closed contacts (S1_2, S2_2) and the normally open contacts (S1_1, S2_1) of the satellite-rocket separation travel switch 113. Furthermore, when the autonomous power-on circuit 100 supplies power to the satellite, it only uses the normally closed contacts (S1_2, S2_2) of the satellite-rocket separation travel switch 113 and the first connection node P1, the second connection node P2, and the fourth connection node P4 of the satellite meter socket 112. The normally open contacts (S1_1, S2_1) of the satellite-rocket separation travel switch and the third connection node P3 of the satellite meter socket 112 are in an idle state during the autonomous power-on process and can be used to collect the satellite-rocket separation signal. Figure 2 and Figure 3 As shown, in one embodiment of the present application, the satellite-rocket separation enabling unit 110 further includes a satellite-rocket separation signal acquisition unit 114. The satellite-rocket separation signal acquisition unit 114 includes a first sampling resistor R5 and a second sampling resistor R6; the first sampling resistor R5 and the second sampling resistor R6 are connected in series between the satellite telemetry acquisition power supply and the ground; the common end of the first sampling resistor R5 and the second sampling resistor R6 is connected to the third connection node P3 of the satellite meter socket 112, and the common end of the first sampling resistor R5 and the second sampling resistor R6 is the output end of the satellite-rocket separation signal acquisition unit 114.

[0043] Specifically, in the above-mentioned satellite-rocket separation signal acquisition unit 114, the first sampling resistor R5 and the second sampling resistor R6 form a voltage divider circuit to divide the voltage provided by the telemetry acquisition power supply, and the normally open contacts (S1_1, S2_1) of the satellite-rocket separation travel switch 113 are equivalent to being connected in parallel to the two ends of the second sampling resistor R6, and the output end of the satellite-rocket separation signal acquisition unit 114 is the common end of the first sampling resistor R5 and the second sampling resistor R6, so the output satellite-rocket separation signal is equivalent to the voltage divided by the second sampling resistor R6, and the conduction or not of the normally open contacts (S1_1, S2_1) of the satellite-rocket separation travel switch 113 controls whether the second sampling resistor R6 is short-circuited. Before the satellite-rocket separation, the satellite-rocket separation travel switch 113 is in a compressed state, at which time the normally open contacts (S1_1, S2_1) are closed, the second sampling resistor R6 is short-circuited, and the voltage at the output end of the satellite-rocket separation signal acquisition unit 114 is 0V; after the satellite-rocket separation, the satellite-rocket separation travel switch 113 is in a released state, at which time the normally open contacts (S1_1, S2_1) are disconnected, the second sampling resistor R6 is not short-circuited, and the voltage at the output end of the satellite-rocket separation signal acquisition unit 114 is the voltage divided by the second sampling resistor R6.

[0044] It should be noted that the setting of the first sampling resistor R5 and the second sampling resistor R6 is only a simple way to implement a voltage divider circuit. In fact, the above preferred scheme is to use the satellite-rocket separation travel switch to control whether a part of the resistors in the voltage divider circuit is short-circuited to affect the voltage value at the output end of the satellite-rocket separation signal, thereby realizing the sampling of the satellite-rocket separation signal. Therefore, in some specific application scenarios, the implementation of the satellite-rocket separation signal sampling unit 114 can also be based on a more complex voltage divider circuit.

[0045] In addition, the autonomous power-on circuit provided in the embodiment of the present application is in a disconnected state when the satellite plug is not inserted, and the entire satellite cannot be powered on. Therefore, accidental power-on of the satellite can be avoided during the satellite ground testing phase, ensuring the safety of the satellite testing process.

[0046] Figure 4 This is a circuit diagram of a satellite power supply system provided in an embodiment of the present application. Figure 4 As shown, the satellite power supply system provided in this embodiment includes not only the autonomous power-on circuit 100 as described in the above embodiment, but also a battery charging and discharging module 200 and a sequential switch shunt regulation (S3R) module 300.

[0047] The battery charging and discharging module 200 includes a battery pack BAT, a battery discharge relay K2 and a charging diode V1. The first end of the battery discharge relay K2 is connected to the positive electrode BAT+ of the battery pack, and the second end of the battery discharge relay K2 is connected to the bus switch unit 130 of the autonomous power-on circuit 100; the charging diode V1 is arranged in parallel with the battery discharge relay K2. When the satellite is in orbit, when the battery discharge relay K2 is disconnected, the battery pack BAT can be charged through the charging diode V1; when the battery discharge relay K2 is connected, the battery pack BAT can be charged through the battery discharge relay K2, and the battery pack BAT can also be discharged to the load through the battery discharge relay K2.

[0048] The sequential switch shunt regulation module 300 includes a plurality of solar cell arrays 310 and a shunt regulation circuit 320 correspondingly connected to each solar cell array 310; the solar cell array 310 is used to provide working current for the satellite's load and charging current for the battery pack BAT while the satellite is in orbit; the shunt regulation circuit 320 is used to shunt excess electric energy output by the solar cell array 310 when the power supply current of the solar cell array 310 is greater than the sum of the working current of the load and the charging current of the battery pack BAT.

[0049] In the embodiment of the present application, the shunt regulation circuit 320 includes a power switch element Mn and an S3R control unit, the control end of the power switch element Mn is connected to the corresponding S3R control unit, the first channel end of the power switch element Mn is connected to the output end of the corresponding solar cell array, and the second channel end of the power switch element Mn is grounded; the S3R control unit is used to generate a shunt control voltage when the power supply current of the solar cell array is greater than the sum of the working current of the load and the charging current of the battery group BAT; when the power switch element Mn is in a conducting state under the control of the shunt control voltage, it is used to shunt the excess electric energy output by the solar cell array to the ground. The shunt regulation circuit may also include a circuit protection unit, the circuit protection unit includes a fuse Fn connected to the first channel end of the power switch element Mn to prevent the current on the shunt branch from being too large, causing damage to the power switch element Mn, and the circuit protection unit also includes isolation diodes VA and VB connected to the busbar to prevent the current in the busbar from flowing in reverse and protect the circuit from being affected by the reverse voltage.

[0050] In this embodiment, the satellite power supply system further includes a bus capacitor array 330, which is used to smooth voltage fluctuations on the bus, provide a stable operating voltage for the load, and maintain stable operation of the satellite.

[0051] In summary, the autonomous power-on circuit and satellite power supply system provided in the embodiment of the present application, when the satellite is separated from the rocket and enters orbit, controls the battery discharge switch unit and the bus switch unit to be in the on state through the satellite-rocket separation enabling unit; after the battery discharge switch unit and the bus switch unit are connected, the electric energy output by the battery pack is provided to the load, which can not only complete the autonomous power-on process of the satellite through the battery pack when the satellite-rocket is separated, but also avoid the problem of uncontrollable power-on of the satellite after the fairing is thrown away in the active stage. In addition, in the bus switch unit, by connecting the bus power-on relay in parallel between the first channel end and the second channel end of the bus power-on power switch, after the satellite completes the initial power-on, the closed bus power-on relay is used to power the load, and the voltage drop and heat generation are low, which not only reduces energy loss, but also is conducive to the long-term stable operation of the bus. The satellite meter control is realized through the satellite meter socket and the satellite-rocket separation travel switch, which can not only further realize the collection of the satellite-rocket separation signal and determine whether the satellite-rocket is in a separated state, but also avoid the accidental power-on of the satellite during the satellite ground test phase, and ensure the safety of the satellite test process.

[0052] The technical features of the above-described embodiments may be arbitrarily combined. To make the description concise, not all possible combinations of the technical features in the above-described embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0053] In this document, the terms "comprises," "comprising," or any other variations thereof, are intended to cover a non-exclusive inclusion of elements other than those listed and may also include additional elements not expressly listed.

[0054] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. An autonomous power-on circuit, characterized in that: It includes a satellite-rocket separation enabling unit, a battery discharge switch unit and a bus switch unit; wherein, The satellite-rocket separation enabling unit is connected to the battery discharge switch unit and the bus switch unit, and is used to control the battery discharge switch unit and the bus switch unit to be in a conducting state when the satellite is separated from the rocket and enters orbit; The battery discharge switch unit is connected to the battery group of the satellite and the bus switch unit, and the bus switch unit is connected to the load of the satellite. When the battery discharge switch unit and the bus switch unit are in an on state, they are used to provide the electric energy output by the battery group to the load.

2. The autonomous power-on circuit according to claim 1, characterized in that: The satellite-rocket separation enabling unit includes an autonomous power-on prohibition switch, a satellite meter socket, and a satellite-rocket separation travel switch; wherein, The first end of the autonomous power-on prohibition switch is connected to the battery discharge switch unit, and the second end of the autonomous power-on prohibition switch is connected to the first connection node of the star meter socket; The satellite-rocket separation travel switch includes a normally closed contact and a normally open contact, the first end of the normally closed contact is connected to the second connection node of the satellite socket, and the second end of the normally closed contact is connected to the negative pole of the battery pack; the first end of the normally open contact is connected to the fourth connection node of the satellite socket, and the second end of the normally open contact is connected to the negative pole of the battery pack.

3. The autonomous power-on circuit according to claim 2, characterized in that: There are at least two satellite-rocket separation travel switches, and the satellite-rocket separation travel switches are redundantly arranged in parallel.

4. The autonomous power-on circuit according to claim 2, characterized in that: The satellite-rocket separation enabling unit also includes a satellite-rocket separation signal acquisition unit; wherein, The satellite-rocket separation signal acquisition unit includes a first sampling resistor and a second sampling resistor; The first sampling resistor and the second sampling resistor are connected in series between the satellite's telemetry collection power supply and ground; The common end of the first sampling resistor and the second sampling resistor is connected to the third connection node of the satellite meter socket, and the common end of the first sampling resistor and the second sampling resistor is the output end of the satellite-rocket separation signal acquisition unit.

5. The autonomous power-on circuit according to claim 2, characterized in that: The battery discharge switch unit includes a battery discharge power switch, a first voltage-dividing resistor and a second voltage-dividing resistor; wherein, The control end of the battery discharge power switch is connected to the first end of the autonomous power-on prohibition switch through a first voltage-dividing resistor, the first path end of the battery discharge power switch is connected to the positive electrode of the battery pack, and the second path end of the battery discharge power switch is connected to the bus switch unit; The second voltage-dividing resistor is connected between the control terminal and the first path terminal of the battery discharging power switch.

6. The autonomous power-on circuit according to claim 5, characterized in that: The bus switch unit includes a bus power switch, a third voltage-dividing resistor and a fourth voltage-dividing resistor; wherein, The control end of the busbar power-on power switch is connected to the first connection node of the star meter socket through a third voltage-dividing resistor, the first path end of the busbar power switch is connected to the second path end of the battery discharge power switch, and the second path end of the busbar power switch is connected to the load; The fourth voltage-dividing resistor is connected between the control terminal and the first path terminal of the busbar power-on power switch.

7. The autonomous power-on circuit according to claim 6, characterized in that: The bus switch unit further includes a bus energizing relay connected in parallel between a first channel end and a second channel end of the bus energizing power switch.

8. A satellite power supply system, characterized in that: Comprising an autonomous power-up circuit as claimed in any one of claims 1 to 7.

9. The satellite power supply system according to claim 8, characterized in that: It also includes a battery charging and discharging module, which includes a battery pack, a battery discharge relay and a charging diode; wherein, The first end of the battery discharge relay is connected to the positive electrode of the battery pack, and the second end of the battery discharge relay is connected to the bus switch unit of the autonomous power-on circuit; The charging diode is arranged in parallel with the battery discharging relay.

10. The satellite power supply system according to claim 9, characterized in that: It also includes a sequential switch shunt regulation module; wherein, The sequential switch shunt regulation module includes a plurality of solar cell arrays and a shunt regulation circuit correspondingly connected to each solar cell array; The solar cell array is used to provide working current for the satellite's load and charging current for the battery pack while the satellite is in orbit; The shunt regulating circuit is used to shunt the excess electric energy output by the solar cell array when the power supply current of the solar cell array is greater than the sum of the working current of the load and the charging current of the storage battery group.

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