Satellite solar panel power supply circuit

Abstract

This satellite solar panel power supply circuit belongs to the technical field of satellite solar panel power supply circuits, and specifically relates to the stability of the entire satellite's power supply circuit during the active phase of satellite launch. It solves the problem in current technology where the solar panel supplies power to the entire satellite during the active phase, leading to the risk of weak voltage power-on or frequent power-offs for individual devices directly powered by the satellite, thus causing instability in their internal circuitry. The circuit includes: a solar panel power supply unit, a bypass current diversion unit, a shunt unit, an isolation unit, an autonomous power-on unit, and a sensor unit. This satellite solar panel power supply circuit is suitable for providing stable power to the satellite during the active phase of launch, the satellite-rocket separation transition period, and the entire on-orbit operation cycle, especially avoiding the instability of traditional power supply circuits during the active phase.

Description

Technical Field

[0001] This utility model relates to the field of satellite solar panel power supply circuit technology, and in particular to the stability of the whole satellite power supply circuit in the active phase of satellite launch. Background Technology

[0002] During the active phase of satellite launch, from fairing jettison to separation from the launch vehicle, the solar panels may be exposed to sunlight. The energy generated by this sunlight enters the power controller to power the entire satellite. However, because the angle at which the solar panels are exposed to sunlight is not constant, the generated energy is unstable. Simultaneously, the batteries are not yet connected to the satellite system, causing the bus voltage VBUS to fluctuate frequently between 0V and the battery pack voltage (Vbat). This unstable power supply exposes directly powered individual devices (such as PCDUs and integrated electronics) to the risk of weak voltage power-on or frequent power-off cycles, leading to unstable operation of their internal circuits. Utility Model Content

[0003] This invention proposes a satellite solar panel power supply circuit, which solves the problem in the current technology where the solar panel supplies power to the entire satellite during the active phase of the satellite, resulting in the risk of weak voltage power-on or frequent power-off for single-unit equipment directly powered by the entire satellite, thus leading to unstable operation of its internal circuits.

[0004] The satellite solar panel power supply circuit of this utility model includes: a solar panel power supply unit, a bypass current diversion unit, a current shunt unit, an isolation unit, an autonomous power supply unit, and a sensor unit;

[0005] The solar panel power supply unit is used to receive sunlight and generate DC voltage;

[0006] The positive terminal of the DC voltage is connected to one end of the bypass current-guiding unit, one end of the shunt unit, and one end of the isolation unit;

[0007] The other end of the isolation unit is connected to the bus voltage VBUS; the isolation unit is unidirectionally conductive, and the conduction direction is from the positive terminal of the DC voltage to the bus voltage VBUS;

[0008] The negative terminal of the DC voltage is connected to the other end of the bypass current diversion unit, the other end of the shunt unit, one end of the autonomous power-on unit, and the GND ground terminal;

[0009] The other end of the autonomous power-on unit is connected to the bus voltage VBUS;

[0010] The shunt unit is used to regulate the DC voltage generated by the solar panel power supply unit and to shunt excess electrical energy to the ground;

[0011] The bypass diversion unit is used to adjust its own conduction status according to the satellite-rocket docking status:

[0012] When the satellite and rocket are docked, the bypass diversion unit is in a short-circuit state;

[0013] When the satellite and rocket separate, the bypass diversion unit is in an open circuit state;

[0014] The autonomous power supply unit includes a battery pack, which is used to make the bus voltage VBUS equal to the battery pack voltage Vbat when the satellite separates from the rocket.

[0015] Furthermore, a preferred embodiment is provided, wherein the solar panel power supply unit includes: a photoelectric conversion module and a diode D2;

[0016] The photoelectric conversion module is used to receive light and generate DC voltage; the positive terminal of the DC voltage is connected to the anode of D2; the cathode of D2 is connected to one end of the bypass current unit, one end of the shunt unit, and one end of the isolation unit.

[0017] Furthermore, a preferred embodiment is provided, wherein the shunt unit includes: resistors R9 and R17, an N-channel MOSFET M1, and a driving unit;

[0018] The drain D of M1 is connected to the cathode of D2;

[0019] The source S of M1 is connected to the GND ground terminal;

[0020] The gate G of M1 is connected to one end of R17;

[0021] The other end of R17 is connected to the output of the drive unit and one end of R9;

[0022] The other end of R9 is connected to the GND ground terminal;

[0023] The output terminal of the drive unit outputs a current drive signal to drive the drain D of M1 to conduct with the source S.

[0024] Furthermore, a preferred embodiment is provided, wherein the driving unit includes resistors R1, R2, R3, R4, R6, and R7, a comparator, a capacitor C6, a PNP transistor Q3, and an NPN transistor Q4.

[0025] The triangular wave signal source is input to one end of R1, and the other end of R1 is connected to the non-inverting input of the comparator.

[0026] One end of R2 is used to connect to an external reference voltage, and the other end of R2 is connected to the negative input terminal of the comparator.

[0027] One end of R7 is connected to VCC, and the other end of R7 is connected to the positive power supply of the comparator.

[0028] The negative power supply terminal of the comparator is connected to the GAND1 signal reference ground;

[0029] The output of the comparator is connected to one end of C6, one end of R3, one end of R4, the base of Q3, and the base of Q4.

[0030] The other end of C6 is connected to the GAND1 signal reference ground;

[0031] The other end of R4 is connected to the GAND1 signal reference ground;

[0032] The other end of R3 is connected to VCC;

[0033] The collector of Q3 is connected to the GAND1 signal reference ground;

[0034] The collector of Q4 is connected to one end of R6, and the other end of R6 is connected to VCC;

[0035] The emitters of Q3 and Q4 are connected to form a push-pull circuit, and the output current drives the signal to the connection of R17 and R9.

[0036] Furthermore, a preferred embodiment is provided, wherein the bypass current-draining unit includes: resistors R5 and R22, a bypass normally open contact K3, a bypass current-draining enable relay contact K2, and an N-channel MOSFET M9.

[0037] One end of R5 is connected to the battery pack voltage Vbat.

[0038] The other end of R5 is connected to one end of K3;

[0039] The other end of K3 is connected to one end of K2;

[0040] The other end of K2 is connected to one end of R22 and the gate G of M9;

[0041] The other end of R22 is connected to the GND ground terminal;

[0042] The drain D of M9 is connected to the cathode of D2 of the solar panel power supply unit;

[0043] The source S of M9 is connected to the GND ground terminal;

[0044] K3 is the normally open contact of the star-rocket docking limit switch, which is controlled to open and close under the star-rocket docking status.

[0045] When the satellite and rocket dock, K3 closes.

[0046] K3 disconnects when the star and rocket separate.

[0047] Furthermore, a preferred embodiment is provided, wherein the bypass diversion unit includes: relay switches K12 and K13;

[0048] Contact 1 of K12 is connected to the cathode of D2 of the solar panel power supply unit;

[0049] Contact 2 of K12 is connected to contact 1 of K13;

[0050] Contact 2 of K13 is connected to the GND ground terminal;

[0051] K12 and K13 are used to receive the current-drain switch on and current-drain switch off commands sent by the satellite master control:

[0052] When the satellite and rocket dock, the satellite master controller sends a command to turn on the diversion switch, and K12 and K13 close.

[0053] When the satellite separates from the launch vehicle, the satellite master controller sends a command to disconnect the diversion switch, and K12 and K13 are disconnected.

[0054] Furthermore, in a preferred embodiment, the isolation unit is a diode D5;

[0055] The anode of D5 is connected to the cathode of D2, one end of the bypass diversion unit, and one end of the shunt unit;

[0056] The cathode of D5 is connected to the bus voltage VBUS.

[0057] Furthermore, a preferred embodiment is provided, wherein the autonomous power-on unit includes: resistors R8, R10, R11, a P-channel MOSFET M2, a battery pack, a normally closed power-on contact K4, an autonomous power-on enable relay contact K1, and a discharge switch relay contact K6.

[0058] The drain D of M2 is connected to the bus voltage VBUS and one end of K6;

[0059] The gate G of M2 is connected to one end of R8;

[0060] The other end of R8 is connected to one end of R10 and one end of R11;

[0061] The other end of R10 is connected to one end of K1; the other end of K1 is connected to one end of K4; the other end of K4 is connected to the negative terminal and GND grounding terminal of the battery pack.

[0062] The other end of R11 is connected to the source terminal S of M2, the other end of K6, and the positive terminal of the battery pack;

[0063] K4 is the normally closed contact of the star-rocket docking limit switch, which is controlled to open and close under the star-rocket docking status:

[0064] K4 disconnects when the satellite and rocket dock;

[0065] When the star and rocket separate, K4 closes;

[0066] K6 is connected to the satellite's master control signal, but remains disconnected after satellite-rocket docking, before satellite launch, and during the active phase.

[0067] Furthermore, in a preferred embodiment, the battery pack is composed of multiple individual batteries B1 to Bn connected sequentially with their positive and negative terminals connected; the positive terminal of B1 is the positive terminal of the battery pack; and the negative terminal of Bn is the negative terminal of the battery pack.

[0068] Furthermore, in a preferred embodiment, the shunt unit further includes an RC snubber circuit connected in parallel between the drain D and source S of the N-channel MOSFET M1.

[0069] The RC absorption circuit consists of a resistor Rx and a capacitor Cx connected in series.

[0070] in:

[0071] One end of resistor Rx is connected to the drain D of M1, and the other end is connected to one end of capacitor Cx;

[0072] The other end of capacitor Cx is connected to the source S of M1 and the GND ground terminal;

[0073] When the solar panel power supply unit generates a voltage surge due to a sudden change in light intensity, the RC absorption circuit absorbs high-frequency energy through RC charging and discharging, suppressing the voltage spike between the drain and source of M1.

[0074] The present invention has the following beneficial effects:

[0075] 1. The satellite solar panel power supply circuit described in this utility model, through the coordinated control of the bypass diversion unit and the shunt unit (forced short circuit to discharge energy during satellite-rocket docking, and precise adjustment of shunt during separation), stabilizes the bus voltage at 0V during the active phase of the satellite (after fairing jettison and before satellite-rocket separation), avoiding interference from unstable solar panel power to the entire satellite equipment and eliminating the risk of power surges caused by sudden changes in illumination during the launch phase.

[0076] 2. The satellite solar panel power supply circuit of this utility model generates a PWM signal through a complementary push-pull drive circuit (Q3 / Q4) to control the shunt unit MOSFET, dynamically adjusts the output voltage of the solar panel, and realizes the discharge of excess electrical energy to the ground.

[0077] 3. The satellite solar panel power supply circuit described in this utility model blocks reverse current through the isolation unit (D5) and cooperates with the contactless switch control of the battery pack of the autonomous power supply unit (M2+K1+K4+K6) to seamlessly switch to battery power supply after separation of the satellite and rocket, so that the bus voltage VBUS is established to the nominal value Vbat, ensuring the stability and continuity of energy during the satellite's on-orbit initialization process.

[0078] 4. The satellite solar panel power supply circuit of this utility model, by adding a normally open contact (K3) of the satellite-rocket docking limit switch and a bypass current-enabling relay contact (K2) of the command control mode to the bypass current-guiding unit, and forming a forced grounding path structure with the voltage divider resistors (R5, R22) and the N-channel MOSFET (M9), ensures that in the satellite-rocket docking (active phase) state, the gate of the MOSFET (M9) receives a driving voltage and becomes saturated and conducts, reliably short-circuiting its drain (connected to the output terminal of the solar panel power supply unit) and source (grounded), clamping the input voltage of the power supply bus (VBUS) to 0V. This physical structure directly avoids the risk of unstable electrical energy generated by the solar panel being exposed to sunlight during the satellite's active phase (such as after the fairing is jettisoned) entering the power supply bus.

[0079] 5. The satellite solar panel power supply circuit of this utility model establishes a physically isolated bypass discharge path structure by directly electrically connecting the drain of the MOSFET (M9) in the bypass current-guiding unit to the cathode of the diode (D2) in the solar panel power supply unit, and directly connecting its source to the entire satellite system ground (GND). This structure replaces and bypasses the function of the shunt unit in the traditional S3R circuit before satellite-rocket separation, ensuring that unstable energy is directly introduced to the ground wire, and completely eliminating the phenomenon of unstable power supply or frequent power interruption of the active segment single-unit equipment.

[0080] The satellite solar panel power supply circuit described in this utility model is suitable for providing stable power to satellites during the active launch phase, the satellite-rocket separation transition period, and the entire on-orbit operation cycle. In particular, it avoids the disadvantage of unstable power supply during the active phase of traditional power supply circuits. Attached Figure Description

[0081] To more clearly illustrate the technical solutions in the embodiments of this utility model, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0082] Figure 1 This is a connection structure diagram of each unit of the satellite solar panel power supply circuit in one embodiment of the present invention;

[0083] Figure 2 This is a circuit diagram of the satellite solar panel power supply circuit (using the bypass diversion unit of embodiment 5) in one embodiment of the present invention.

[0084] Figure 3 This is a circuit diagram of the satellite solar panel power supply circuit (using the bypass diversion unit of embodiment 6) in one embodiment of the present invention.

[0085] Figure 4 This is a schematic diagram of the circuit structure of an RC snubber circuit connected in parallel between the drain D and source S of an N-channel MOSFET M1, as described in one embodiment of the present invention. Detailed Implementation

[0086] To make the technical solution and advantages of this utility model clearer, the specific embodiments of this utility model will be described in further detail and completely below with reference to the accompanying drawings. The various embodiments described below are only some preferred embodiments of this utility model, not all of them; the various embodiments described below are intended to explain this utility model and should not be construed as limiting this utility model; reasonable combinations of the technical features defined by the various embodiments of this utility model, as well as all other embodiments obtained by those skilled in the art based on the embodiments of this utility model without creative effort, are within the scope of protection of this utility model.

[0087] Implementation method 1: Satellite solar panel power supply circuit, the circuit includes: solar panel power supply unit, bypass diversion unit, shunt unit, isolation unit, autonomous power supply unit and sensor unit;

[0088] The solar panel power supply unit is used to receive sunlight and generate DC voltage;

[0089] The positive terminal of the DC voltage is connected to one end of the bypass current-guiding unit, one end of the shunt unit, and one end of the isolation unit;

[0090] The other end of the isolation unit is connected to the bus voltage VBUS; the isolation unit is unidirectionally conductive, and the conduction direction is from the positive terminal of the DC voltage to the bus voltage VBUS;

[0091] The negative terminal of the DC voltage is connected to the other end of the bypass current diversion unit, the other end of the shunt unit, one end of the autonomous power-on unit, and the GND ground terminal;

[0092] The other end of the autonomous power-on unit is connected to the bus voltage VBUS;

[0093] The shunt unit is used to regulate the DC voltage generated by the solar panel power supply unit and to shunt excess electrical energy to the ground;

[0094] The bypass diversion unit is used to adjust its own conduction status according to the satellite-rocket docking status:

[0095] When the satellite and rocket are docked, the bypass diversion unit is in a short-circuit state;

[0096] When the satellite and rocket separate, the bypass diversion unit is in an open circuit state;

[0097] The autonomous power supply unit includes a battery pack, which is used to make the bus voltage VBUS equal to the battery pack voltage Vbat when the satellite separates from the rocket.

[0098] In this embodiment, the DC voltage generated by the solar array power supply unit is used to power the entire satellite.

[0099] In this embodiment, the DC voltage generated by the solar array power supply unit is used to power the entire satellite after passing through the isolation unit and the filtering unit.

[0100] The isolation unit isolates the shunt unit from the filter unit.

[0101] In this embodiment, the bypass diversion unit: during the active phase of the satellite (after the fairing is jettisoned and before the satellite and rocket separate), the electrical energy generated by the solar array power supply unit can be bypassed to avoid entering the entire satellite, so that the bus voltage is 0V, thereby avoiding the use of unstable solar array power to supply the entire satellite.

[0102] In this embodiment, when the satellite and rocket are docked, the bypass current-draining unit is in a short-circuit state, making the bus voltage VBUS 0V.

[0103] In this embodiment, when the satellite separates from the launch vehicle, the bypass diversion unit is in an open circuit state, and the power generated by the solar array power supply unit supplies power to the entire satellite.

[0104] In this embodiment, the autonomous power supply unit: after the satellite separates from the launch vehicle, the battery pack can provide stable power to the entire satellite, enabling the satellite to operate normally in orbit.

[0105] Implementation Method 2: The solar panel power supply unit includes: a photoelectric conversion module and a diode D2;

[0106] The photoelectric conversion module is used to receive light and generate DC voltage; the positive terminal of the DC voltage is connected to the anode of D2; the cathode of D2 is connected to one end of the bypass current unit, one end of the shunt unit, and one end of the isolation unit.

[0107] Implementation method 3: The shunt unit includes: resistors R9 and R17, an N-channel MOSFET M1, and a driving unit;

[0108] The drain D of M1 is connected to the cathode of D2;

[0109] The source S of M1 is connected to the GND ground terminal;

[0110] The gate G of M1 is connected to one end of R17;

[0111] The other end of R17 is connected to the output of the drive unit and one end of R9;

[0112] The other end of R9 is connected to the GND ground terminal;

[0113] The output terminal of the drive unit outputs a current drive signal to drive the drain D of M1 to conduct with the source S.

[0114] In this embodiment, the resistor R9 is called the bleeder resistor.

[0115] In this embodiment, the drive unit: when the satellite is working normally in orbit, it generates adjustment and control according to the energy required by the satellite.

[0116] Implementation method 4: The driving unit includes resistors R1, R2, R3, R4, R6, R7, a comparator, capacitor C6, PNP transistor Q3 and NPN transistor Q4;

[0117] The triangular wave signal source is input to one end of R1, and the other end of R1 is connected to the non-inverting input of the comparator.

[0118] One end of R2 is used to connect to an external reference voltage, and the other end of R2 is connected to the negative input terminal of the comparator.

[0119] One end of R7 is connected to VCC, and the other end of R7 is connected to the positive power supply of the comparator.

[0120] The negative power supply terminal of the comparator is connected to the GAND1 signal reference ground;

[0121] The output of the comparator is connected to one end of C6, one end of R3, one end of R4, the base of Q3, and the base of Q4.

[0122] The other end of C6 is connected to the GAND1 signal reference ground;

[0123] The other end of R4 is connected to the GAND1 signal reference ground;

[0124] The other end of R3 is connected to VCC;

[0125] The collector of Q3 is connected to the GAND1 signal reference ground;

[0126] The collector of Q4 is connected to one end of R6, and the other end of R6 is connected to VCC;

[0127] The emitters of Q3 and Q4 are connected to form a push-pull circuit, and the output current drives the signal to the connection of R17 and R9.

[0128] In this embodiment, R1 is used to limit the input current, match the input impedance of the signal source and the comparator, and prevent high-frequency oscillation.

[0129] In this embodiment, R2 is used to set the input path of the inverting input reference voltage (external reference source) and determine the comparator toggling threshold.

[0130] In this embodiment, R7 serves as a current-limiting resistor at the positive power supply terminal of the comparator to suppress power surge current.

[0131] In this embodiment, C6 serves as a phase compensation capacitor to eliminate high-frequency self-oscillation of the comparator output and improve stability.

[0132] In this embodiment, R4 serves as an output pull-down resistor to stabilize the static level of the output terminal (strengthening the pull-down capability when the output is low).

[0133] In this embodiment, R3 serves as an output pull-up resistor to enhance the output high-level driving capability (especially under light load).

[0134] In this embodiment, Q3 is a PNP transistor that amplifies the current during the negative half-cycle.

[0135] In this embodiment, Q4 is an NPN transistor that amplifies the current during the positive half-cycle.

[0136] In this embodiment, Q3 / Q4 constitute a complementary push-pull output stage:

[0137] When Q3 (PNP) is turned on, it sinks current (low-level drive).

[0138] When Q4 (NPN) is turned on, it pulls current (high-level drive).

[0139] In this embodiment, R6 serves as the collector current limiting resistor, protecting Q4 from overcurrent damage and also acting as the output high-level load.

[0140] In this embodiment, a periodically changing voltage signal is input from a triangular wave signal source to drive a comparator, and the frequency / amplitude determines the square wave output characteristics.

[0141] In this embodiment, the comparator is a voltage comparator:

[0142] If the voltage at the non-inverting input is greater than the voltage at the inverting input, the output will be high.

[0143] When the voltage at the positive input is less than the voltage at the negative input, the output level is low.

[0144] In this embodiment, VCC is the operating voltage of the entire circuit, which supplies power to the comparator, transistor, resistor network, etc.

[0145] In this embodiment, the GAND1 signal reference ground serves as the comparator's negative power supply reference point, and also as the current return path for the bypass capacitor / pull-down resistor and the current loop for the output stage PNP transistor.

[0146] In this embodiment, the driving unit consists of Q3 and Q4 forming a push-pull circuit to drive the MOS transistor M1 of the shunt unit.

[0147] In this embodiment, the shunt unit dynamically adjusts the load by controlling the MOSFET switch through pulse width modulation (PWM) to achieve stable control of the solar panel output voltage and accurately discharge excess energy to ground.

[0148] (1) Key components of the shunt unit:

[0149] M1 (N-channel MOSFET): Main power switch, drain (D) connected to solar panel power output (VIN), source (S) grounded (GND).

[0150] R9 (bleeder resistor): Connected in parallel with the gate and source of M1 to ensure that residual charge is released quickly when M1 is turned off.

[0151] R17 (Gate Current Limiting Resistor): Protects the gate of M1 from damage caused by drive signal overshoot.

[0152] Drive unit: Outputs PWM signal to control the on / off state of M1.

[0153] (2) Implementation logic of voltage regulation and energy diversion:

[0154] ①Dynamic adjustment mechanism:

[0155] The driver unit generates PWM signals:

[0156] The comparator outputs a square wave with an adjustable duty cycle by comparing a triangular wave input (periodic signal) with an external reference voltage (set threshold).

[0157] Push-pull circuit (Q3 / Q4) amplifies current:

[0158] When Q4 (NPN) is turned on, the output is high-level → current is drawn in → M1 is turned on;

[0159] When Q3 (PNP) is turned on, the output is low-level → current sinking → M1 is turned off.

[0160] The drive signal controls the periodic switching of M1.

[0161] ② Pathways for discharging excess electrical energy:

[0162] When M1 is on:

[0163] The solar panel output current (VIN) flows directly into GND from the drain of M1 to the source, and the electrical energy is dissipated as heat.

[0164] When M1 is off:

[0165] Residual charge at VIN → R9 (parallel bleeder resistor) → flows into GND to prevent voltage drift.

[0166] ③ Principle of precise voltage regulation:

[0167] Adjustment objective: Match the solar panel output voltage (VIN) to the satellite's requirements.

[0168] Dynamic feedback control:

[0169] If VIN is higher than the target value, the drive unit increases the PWM duty cycle, the M1 conduction time is extended, more energy is discharged to GND, and VIN decreases.

[0170] If VIN is lower than the target value, the drive unit reduces the PWM duty cycle, shortens the M1 conduction time, reduces energy discharge, and increases VIN.

[0171] VIN is kept stable by adjusting the PWM duty cycle in real time.

[0172] It should be noted that pulse width modulation (PWM) is an existing conventional modulation method and is not an improvement on the method.

[0173] In another embodiment, the negative input terminal of the comparator in the driving unit is connected to a low-pass filter network consisting of resistor R18 and capacitor C9, wherein:

[0174] One end of R18 is connected to the external reference voltage input node, and the other end is connected to the negative phase input of the comparator;

[0175] C9 is connected to the negative input of the comparator at one end and to the GAND1 signal reference ground at the other end.

[0176] The low-pass filter network is used to filter out high-frequency noise in the external reference voltage and prevent abnormal oscillation of the PWM signal.

[0177] Implementation method 5: The bypass current diversion unit includes: resistors R5 and R22, bypass normally open contact K3, bypass current diversion enable relay contact K2, and N-channel MOSFET M9;

[0178] One end of R5 is connected to the battery pack voltage Vbat.

[0179] The other end of R5 is connected to one end of K3;

[0180] The other end of K3 is connected to one end of K2;

[0181] The other end of K2 is connected to one end of R22 and the gate G of M9;

[0182] The other end of R22 is connected to the GND ground terminal;

[0183] The drain D of M9 is connected to the cathode of D2 of the solar panel power supply unit;

[0184] The source S of M9 is connected to the GND ground terminal;

[0185] K3 is the normally open contact of the star-rocket docking limit switch, which is controlled to open and close under the star-rocket docking status.

[0186] When the satellite and rocket dock, K3 closes.

[0187] K3 disconnects when the star and rocket separate.

[0188] In this embodiment, resistor R22 is a voltage divider resistor.

[0189] In this embodiment, the star-rocket docking limit switch (2KX-1) is installed on the side wall of the locking slider guide groove of the star-rocket docking ring:

[0190] During docking, the locking slider of the docking ring slides along the guide groove to the locking position → the star-rocket docking limit switch lever is squeezed and closed by the slider;

[0191] When the slider retracts during separation, the lever spring resets, causing the star-arrow docking limit switch to disconnect.

[0192] In this embodiment, to prevent the MOSFET M1 of the shunt unit from controlling the bus, and to ensure that the energy generated by the solar panel power supply unit can flow into the bus VBUS through the diode D5 in the isolation unit, a MOSFET M9 is added as a bypass current-guiding unit at the front end of MOSFET M1 and the rear end of diode D2:

[0193] The drain D of MOSFET M9 is connected to the cathode of diode D2 in the solar panel power supply unit; the source S of MOSFET M9 is grounded (GND ground terminal); the gate G of MOSFET M9 is connected to one end of voltage divider resistor R22, and the bypass current enable relay contact K2, normally open contact K3 and resistor R5 are connected in series between the battery pack voltage Vbat and the gate G.

[0194] After the satellite docks with the rocket and before the satellite launch, the bypass current enabling relay contact K2 is closed. The normally open contact K3 is also closed due to the satellite docking. Resistors R22 and R5 divide the battery pack voltage Vbat. The voltage divided by resistor R22 is used as the driving voltage of MOSFET M9, making MOSFET M9 conduct to ground, and the bus voltage is 0V.

[0195] During the active phase after satellite launch (before satellite-rocket separation after fairing jettison), if the solar array is exposed to sunlight, the energy it generates will be bypassed through MOSFET M9, and the bus voltage VBUS will remain at 0V.

[0196] After the satellite separates from the rocket, K3 is in the off state. At this time, the voltage of the voltage divider resistor R22 is 0V, and the MOSFET M9 is in the off mode. At this time, the energy generated by the solar array can normally power the entire satellite.

[0197] Implementation method 6: The bypass diversion unit includes: relay switches K12 and K13;

[0198] Contact 1 of K12 is connected to the cathode of D2 of the solar panel power supply unit;

[0199] Contact 2 of K12 is connected to contact 1 of K13;

[0200] Contact 2 of K13 is connected to the GND ground terminal;

[0201] K12 and K13 are used to receive the current-drain switch on and current-drain switch off commands sent by the satellite master control:

[0202] When the satellite and rocket dock, the satellite master controller sends a command to turn on the diversion switch, and K12 and K13 close.

[0203] When the satellite separates from the launch vehicle, the satellite master controller sends a command to disconnect the diversion switch, and K12 and K13 are disconnected.

[0204] In this embodiment, K12 and K13 are used to receive the current-draining switch on command and current-draining switch off command sent by the satellite master controller:

[0205] The first control terminal of K12 is connected to the satellite master controller via the first line signal of the current-draining switch on command, so as to receive the current-draining switch on command sent by the satellite master controller;

[0206] The second control terminal of K12 is connected to the satellite master control via the first line signal of the current-draining switch disconnect command, so as to receive the current-draining switch disconnect command sent by the satellite master control;

[0207] The first control terminal of K13 is connected to the satellite master controller via the second line signal of the current-draining switch on command, so as to receive the current-draining switch on command sent by the satellite master controller;

[0208] The second control terminal of K13 is connected to the satellite master controller via a second line signal for the current cut-off command, in order to receive the current cut-off command sent by the satellite master controller.

[0209] In this embodiment, the bypass diversion unit further includes diodes D12, D13, D14 and D15;

[0210] The anode of D12 is connected to the first control terminal of K12; the cathode of D12 is connected to the first line of the current-driving switch on command.

[0211] The anode of D13 is connected to the second control terminal of K12; the cathode of D13 is connected to the first line of the current-disconnecting switch command.

[0212] The anode of D14 is connected to the first control terminal of K13; the cathode of D14 is connected to the second line of the current switch on command.

[0213] The anode of D15 is connected to the second control terminal of K13; the cathode of D15 is connected to the second line of the current-disconnecting switch.

[0214] Diodes D12, D13, D14, and D15 are used for isolation protection between control commands and the main circuit.

[0215] In this embodiment, the bypass diversion unit further includes a switch status indication circuit; the switch status indication circuit includes: a relay switch K5, resistors R26 and R27, and diodes D16 and D17;

[0216] One end of R26 is connected to a 5V voltage;

[0217] The other end of R26 is connected to contact 1 of K5 and one end of R27;

[0218] Contact 2 of K5 is connected to the other end of R27 and the GAND1 signal reference ground;

[0219] K5 is used to receive the current-drain switch on and current-drain switch off commands sent by the satellite master control:

[0220] The first control terminal of K5 is connected to the satellite master controller via the third line signal of the current-draining switch on command, so as to receive the current-draining switch on command sent by the satellite master controller;

[0221] The second control terminal of K5 is connected to the satellite master control via a third line signal for the current-draining switch disconnect command, so as to receive the current-draining switch disconnect command sent by the satellite master control;

[0222] The anode of D16 is connected to the first control terminal of K5; the cathode of D16 is connected to the third line of the current-driving switch on command.

[0223] The anode of D17 is connected to the second control terminal of K5; the cathode of D17 is connected to the third line of the current-disconnecting switch command.

[0224] In this embodiment, when the satellite and rocket dock, the satellite master controller sends a current-draining switch on command, and K5 closes; when the satellite and rocket separate, the satellite master controller sends a current-draining switch off command, and K5 opens.

[0225] In this embodiment, K5 is used as a switch status indicator for K12 and K13. Specifically, the voltage value between contact 1 and contact 2 of K5 is used as the switch status indicator for K12 and K13.

[0226] When the current-carrying switch is turned on, K12, K13, and K5 close (conduct). Because K5 is closed, the voltage between contact 1 and contact 2 of K5 is 0V.

[0227] When the current-draining switch disconnect command is sent, K12, K13, and K5 disconnect. Because K5 disconnects, the voltage between contacts 1 and 2 of K5 is the voltage division value of 5V by R26 and R27.

[0228] In this embodiment, to prevent the MOSFET M1 of the shunt unit from controlling the bus, and to ensure that the energy generated by the solar panel power supply unit can flow into the bus VBUS through the diode D5 in the isolation unit, two sets of relay switches (K12, K13) are added at the front end of MOSFET M1 and the rear end of diode D2 as bypass current diversion units:

[0229] Contact 1 of relay switch K12 is connected to the rear end of diode D2 and the front end of isolation unit diode D5; contact 2 of relay switch K12 is connected to contact 1 of relay K13; contact 2 of relay switch K13 is grounded.

[0230] After docking with the rocket and before satellite launch, the satellite master controller sends a command to turn on the current diversion switch. K12 and K13 close to connect to the ground, and the bus voltage is 0V.

[0231] During the active phase after satellite launch (before satellite-rocket separation after fairing jettison), if the solar array is exposed to sunlight, the energy it generates will be bypassed through K12 and K13, and the bus voltage VBUS will remain at 0V.

[0232] After the satellite separates from the launch vehicle, the satellite master controller sends a command to disconnect the diversion switch, K12 and K13 are disconnected, and at this time the energy generated by the solar array can normally power the entire satellite.

[0233] Implementation method 7: The isolation unit is diode D5;

[0234] The anode of D5 is connected to the cathode of D2, one end of the bypass diversion unit, and one end of the shunt unit;

[0235] The cathode of D5 is connected to the bus voltage VBUS.

[0236] Implementation method 8: The autonomous power-on unit includes: resistors R8, R10, R11, P-channel MOSFET M2, battery pack, normally closed power-on contact K4, autonomous power-on enable relay contact K1, and discharge switch relay contact K6.

[0237] The drain D of M2 is connected to the bus voltage VBUS and one end of K6;

[0238] The gate G of M2 is connected to one end of R8;

[0239] The other end of R8 is connected to one end of R10 and one end of R11;

[0240] The other end of R10 is connected to one end of K1; the other end of K1 is connected to one end of K4; the other end of K4 is connected to the negative terminal and GND grounding terminal of the battery pack.

[0241] The other end of R11 is connected to the source terminal S of M2, the other end of K6, and the positive terminal of the battery pack.

[0242] K4 is the normally closed contact of the star-rocket docking limit switch, which is controlled to open and close under the star-rocket docking status:

[0243] K4 disconnects when the satellite and rocket dock;

[0244] When the star and rocket separate, K4 closes;

[0245] K6 is connected to the satellite's master control signal, but remains disconnected after satellite-rocket docking, before satellite launch, and during the active phase.

[0246] In this embodiment, the voltage output by the battery pack is Vbat.

[0247] In this embodiment, M2 (P-MOS transistor): main power switch, controlling the power supply path from the battery pack to VBUS; P-MOS characteristics: conduction when gate voltage < source voltage (VGS < 0).

[0248] In this embodiment, K1 (relay contact): enables the control switch, triggered by the satellite master control command; when closed, it activates the voltage divider circuit, and when open, it completely isolates the battery pack.

[0249] In this embodiment, R8 is a gate current-limiting resistor that limits the gate charging current of M2 to prevent the MOS transistor from being damaged.

[0250] In this embodiment, R10 / R11 is a voltage divider resistor network that sets the gate voltage of M2 (VG = Vbat × R11 / (R10+R11)) to ensure conduction margin.

[0251] In this embodiment, the circuit logic for implementing VBUS = Vbat is as follows:

[0252] (1) The star-rocket separation trigger circuit is closed:

[0253] Conditions: Star-rocket separation → K4 closed (normally closed contact physically connected);

[0254] action:

[0255] Battery pack positive terminal → K4 → M2 source terminal (S), establish source terminal reference potential VGS = 0V;

[0256] (2) Enable signal activates voltage divider:

[0257] Condition: The master controller sends a power-on command → K1 closes;

[0258] action:

[0259] Battery positive terminal → K1 → R10 → R8 → M2 gate (G);

[0260] Simultaneously, the positive terminal of the battery → K1 → R10 → R11 → positive terminal of the battery (voltage divider branch).

[0261] (3) Voltage transferred during MOSFET conduction:

[0262] Gate voltage calculation:

[0263] V_G = Vbat × [R11 / (R10 + R11)]

[0264] V_GS = V_G - V_S = negative value (satisfies the P-MOS turn-on condition)

[0265] result:

[0266] M2 is on (internal resistance RDS(on) ≈ 10mΩ) → VBUS ≈ Vbat (voltage drop is negligible).

[0267] In this embodiment, after the satellite separates from the rocket, the normally closed contact K4 is closed, and the autonomous power-on enable relay contact K1 is closed, turning on the MOSFET M2. The battery pack is connected to VBUS through the MOSFET M2, and the VBUS voltage is the battery pack voltage Vbat, ensuring a stable voltage. The shunt unit MOSFET M1 operates normally, and the discharge switch K6 closes via command. After the satellite's status stabilizes, the bypass current enable switch k2 is opened, ensuring that the entire bypass current circuit is completely disconnected.

[0268] Implementation Method 9: The battery pack is composed of multiple individual batteries B1 to Bn connected in sequence with their positive and negative terminals connected; the positive terminal of B1 is the positive terminal of the battery pack; and the negative terminal of Bn is the negative terminal of the battery pack.

[0269] It should be noted that in the diagram, the "short horizontal line" represents the positive terminal and the "long horizontal line" represents the negative terminal.

[0270] Implementation method 10: The current shunt unit further includes an RC snubber circuit connected in parallel between the drain D and source S of the N-channel MOSFET M1.

[0271] The RC absorption circuit consists of a resistor Rx and a capacitor Cx connected in series.

[0272] in:

[0273] One end of resistor Rx is connected to the drain D of M1, and the other end is connected to one end of capacitor Cx;

[0274] The other end of capacitor Cx is connected to the source S of M1 and the GND ground terminal;

[0275] When the solar panel power supply unit generates a voltage surge due to a sudden change in light intensity, the RC absorption circuit absorbs high-frequency energy through RC charging and discharging, suppressing the voltage spike between the drain and source of M1.

[0276] The above description of the technical solution provided by this utility model through several specific embodiments is intended to highlight the advantages and benefits of the technical solution provided by this utility model. However, the above-described specific embodiments are not intended to limit this utility model. Any reasonable modifications and improvements to this utility model, reasonable combinations of embodiments, and equivalent substitutions based on the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A satellite solar wing power supply circuit, characterized by, The circuit includes: a solar panel power supply unit, a bypass current diversion unit, a current shunt unit, an isolation unit, an autonomous power supply unit, and a sensor unit; The solar panel power supply unit is used to receive sunlight and generate DC voltage; The positive terminal of the DC voltage is connected to one end of the bypass current-guiding unit, one end of the shunt unit, and one end of the isolation unit; The other end of the isolation unit is connected to the bus voltage VBUS; the isolation unit is unidirectionally conductive, and the conduction direction is from the positive terminal of the DC voltage to the bus voltage VBUS; The negative terminal of the DC voltage is connected to the other end of the bypass current diversion unit, the other end of the shunt unit, one end of the autonomous power-on unit, and the GND ground terminal; The other end of the autonomous power-on unit is connected to the bus voltage VBUS; The shunt unit is used to regulate the DC voltage generated by the solar panel power supply unit and to shunt excess electrical energy to the ground; The bypass diversion unit is used to adjust its own conduction status according to the satellite-rocket docking status: When the satellite and rocket are docked, the bypass diversion unit is in a short-circuit state; When the satellite and rocket separate, the bypass diversion unit is in an open circuit state; The autonomous power supply unit includes a battery pack, which is used to make the bus voltage VBUS equal to the battery pack voltage Vbat when the satellite separates from the rocket.

2. The satellite solar wing power supply circuit of claim 1, wherein, The solar panel power supply unit includes: a photoelectric conversion module and a diode D2; The photoelectric conversion module is used to receive light and generate DC voltage; the positive terminal of the DC voltage is connected to the anode of D2; the cathode of D2 is connected to one end of the bypass current unit, one end of the shunt unit, and one end of the isolation unit.

3. The satellite solar wing power supply circuit of claim 2, wherein, The current shunt unit includes: resistors R9 and R17, an N-channel MOSFET M1, and a driving unit; The drain D of M1 is connected to the cathode of D2; The source S of M1 is connected to the GND ground terminal; The gate G of M1 is connected to one end of R17; The other end of R17 is connected to the output of the drive unit and one end of R9; The other end of R9 is connected to the GND ground terminal; The output terminal of the drive unit outputs a current drive signal to drive the drain D of M1 to conduct with the source S.

4. The satellite solar wing power supply circuit of claim 3, wherein, The driving unit includes resistors R1, R2, R3, R4, R6, and R7, a comparator, capacitor C6, a PNP transistor Q3, and an NPN transistor Q4. The triangular wave signal source is input to one end of R1, and the other end of R1 is connected to the non-inverting input of the comparator. One end of R2 is used to connect to an external reference voltage, and the other end of R2 is connected to the negative input terminal of the comparator. One end of R7 is connected to VCC, and the other end of R7 is connected to the positive power supply of the comparator. The negative power supply terminal of the comparator is connected to the GAND1 signal reference ground; The output of the comparator is connected to one end of C6, one end of R3, one end of R4, the base of Q3, and the base of Q4. The other end of C6 is connected to the GAND1 signal reference ground; The other end of R4 is connected to the GAND1 signal reference ground; The other end of R3 is connected to VCC; The collector of Q3 is connected to the GAND1 signal reference ground; The collector of Q4 is connected to one end of R6, and the other end of R6 is connected to VCC; The emitters of Q3 and Q4 are connected to form a push-pull circuit, and the output current drives the signal to the connection of R17 and R9.

5. The satellite solar wing power supply circuit of claim 2, wherein, The bypass current-draining unit includes: resistors R5 and R22, a normally open bypass contact K3, a bypass current-draining enable relay contact K2, and an N-channel MOSFET M9. One end of R5 is connected to the battery pack voltage Vbat. The other end of R5 is connected to one end of K3; The other end of K3 is connected to one end of K2; The other end of K2 is connected to one end of R22 and the gate G of M9; The other end of R22 is connected to the GND ground terminal; The drain D of M9 is connected to the cathode of D2 of the solar panel power supply unit; The source S of M9 is connected to the GND ground terminal; K3 is the normally open contact of the star-rocket docking limit switch, which is controlled to open and close under the star-rocket docking status. When the satellite and rocket dock, K3 closes. K3 disconnects when the star and rocket separate.

6. The satellite solar wing power supply circuit of claim 2, wherein, The bypass diversion unit includes: relay switches K12 and K13; Contact 1 of K12 is connected to the cathode of D2 of the solar panel power supply unit; Contact 2 of K12 is connected to contact 1 of K13; Contact 2 of K13 is connected to the GND ground terminal; K12 and K13 are used to receive the current-drain switch on and current-drain switch off commands sent by the satellite master control: When the satellite and rocket dock, the satellite master controller sends a command to turn on the diversion switch, and K12 and K13 close. When the satellite separates from the launch vehicle, the satellite master controller sends a command to disconnect the diversion switch, and K12 and K13 are disconnected.

7. The satellite solar wing power supply circuit of claim 2, wherein, The isolation unit is diode D5; The anode of D5 is connected to the cathode of D2, one end of the bypass diversion unit, and one end of the shunt unit; The cathode of D5 is connected to the bus voltage VBUS.

8. The satellite solar wing power supply circuit of claim 7, wherein, The autonomous power-on unit includes: resistors R8, R10, and R11; a P-channel MOSFET M2; a battery pack; a normally closed power-on contact K4; an autonomous power-on enable relay contact K1; and a discharge switch relay contact K6. The drain D of M2 is connected to the bus voltage VBUS and one end of K6; The gate G of M2 is connected to one end of R8; The other end of R8 is connected to one end of R10 and one end of R11; The other end of R10 is connected to one end of K1; the other end of K1 is connected to one end of K4; the other end of K4 is connected to the negative terminal and GND grounding terminal of the battery pack. The other end of R11 is connected to the source terminal S of M2, the other end of K6, and the positive terminal of the battery pack; K4 is the normally closed contact of the star-rocket docking limit switch, which is controlled to open and close under the star-rocket docking status: K4 disconnects when the satellite and rocket dock; When the star and rocket separate, K4 closes; K6 is connected to the satellite's master control signal, but remains disconnected after satellite-rocket docking, before satellite launch, and during the active phase.

9. The satellite solar wing power supply circuit of claim 8, wherein, The battery pack is composed of multiple individual batteries B1 to Bn connected in sequence with their positive and negative terminals connected; the positive terminal of B1 is the positive terminal of the battery pack; and the negative terminal of Bn is the negative terminal of the battery pack.

10. The satellite solar wing power supply circuit of claim 3, wherein, The shunt unit also includes an RC snubber circuit connected in parallel between the drain D and source S of the N-channel MOSFET M1. The RC absorption circuit consists of a resistor Rx and a capacitor Cx connected in series. in: One end of resistor Rx is connected to the drain D of M1, and the other end is connected to one end of capacitor Cx; The other end of capacitor Cx is connected to the source S of M1 and the GND ground terminal; When the solar wing power supply unit generates voltage surge due to sudden change of illumination, the RC absorption circuit absorbs high frequency energy through resistance-capacitance charging and discharging, and suppresses voltage peak between the drain and source of M1.

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