CN109873560B - High-power high-stability boosting power supply system - Google Patents
High-power high-stability boosting power supply system Download PDFInfo
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Abstract
The invention relates to a high-power high-stability boosting power supply system which is directly boosted to satellite load voltage for the first time and then transmitted. The adoption of the boosting power supply system also solves the problem that the aircraft is insufficient in long-distance high-power supply capacity of the load satellite, so that the long-distance power supply cable is simple in design and low in loss on the cable, the power supply efficiency is improved, the bus voltage can be stabilized during high-power supply or sudden load change, and the design of a load secondary power supply module is easier. Partial components of the boosting power in the boosting circuit are replaced, the voltage requirements of various buses of the satellite can be met after the threshold value of the comparator is changed, the expandability is good, and space is opened up for a boosting power supply system of an aircraft.
Description
Technical Field
The invention relates to a high-power high-stability boosting power supply system, and belongs to the field of aircraft electrical system design.
Background
The electric power supply system of the carrier rocket is the basis of all electric equipment of the system and is also the key point for the reliability of the overall quality of the system. With the continuous development and progress of the design of the electric system of the launch vehicle, the circuit is more and more complicated, and the requirements on the power output and the bus characteristics of the power supply are higher and higher. Electrical power supply systems typically employ a battery in conjunction with a secondary power module. The stored chemical energy is converted into electric energy by the battery and is provided for a subsequent secondary power supply module. Each equipment secondary power supply module converts a high-voltage bus of a battery into a required low-voltage bus through DC/DC, and the power consumption is generally about a few watts to dozens of watts. The carrier rocket provides a power supply path for the loading satellite, and the loading satellite is used for completing power supply of the rocket-mounted equipment and charging of the rocket-mounted battery. Before launching, the power supply of the unplugging and unplugging landing plane is disconnected, and the power supply of the load satellite equipment during the flight of the carrier rocket is provided by the battery of the load satellite.
The flight time of the aircraft is long, the battery of the load satellite needs to be designed by increasing the capacity, the weight of the load satellite is increased, and the effective utilization rate of the load satellite is reduced. Because the distance between the aircraft instrument and the load satellite instrument is far, the voltage drop of the direct power supply voltage of the battery is large, and under the high-power work of the load satellite, the cable loss is large, the heat productivity is large, and the control of the thermal environment of the aircraft is not facilitated.
How to provide a system suitable for supplying power for long-time flight of an aircraft is a technical problem to be solved urgently in the field.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide a high-power high-stability boosting power supply system, which is used for boosting the battery voltage to the satellite load voltage and then transmitting the boosted battery voltage to the satellite load voltage, so that the power supply efficiency of a load satellite power supply system is improved.
The purpose of the invention is realized by the following technical scheme:
the utility model provides a high-power high stability power supply system that steps up, includes: the device comprises a battery, a command switch control circuit, a boosting power circuit, a boosting control PWM loop and a protection circuit;
after the command switch control circuit receives a power-on command, the power-on switch is controlled to be closed, and the boosting power circuit boosts the battery voltage to the required output voltage; after the instruction switch control circuit receives a power conversion instruction, the instruction switch control circuit controls the power conversion switch to be closed, and the boosting power circuit supplies power to the load;
the boost control PWM loop is used for reducing the PWM duty ratio and reducing the output voltage when the power supply voltage for the load exceeds a set first voltage threshold or the load current is smaller than a set first output current threshold; otherwise, the PWM duty ratio is increased, and the output voltage is improved;
the protection circuit stops supplying power when the output voltage is over-voltage and the output current is over-current; and when the output current exceeds the current limiting threshold value, controlling the boost control PWM loop to keep the current PWM duty ratio unchanged.
Preferably, the system also comprises an input filter network and an output filter network; the input filter network is used for filtering interference on a battery power supply bus; the output filter network comprises a high-frequency filter capacitor circuit and a low-frequency filter capacitor circuit, and the output voltage of the boost power circuit is stabilized.
Preferably, the boosting power circuit adopts a Weinberg boosting push-pull circuit.
Preferably, the boosting power circuit boosts the battery voltage through a transformer M2; when the power tubes Q1 and Q2 are turned on, the diodes D2 and D1 are respectively driven to be turned on under the action of the coupling transformer M1, and the boosted voltage is output, and at the moment, the freewheeling diode D3 of the transformer M2 is turned off; when the power transistors Q1 and Q2 are turned off, the freewheeling diode D3 is turned on to maintain the voltage output.
Preferably, the boost control PWM loop includes a first comparator, a second comparator and a PWM controller;
the first comparator compares the output voltage of the boost power circuit with the first voltage threshold, and if the output voltage is higher than the first voltage threshold, a high level is output, otherwise, a low level is output; the negative input end of the second comparator is simultaneously connected with the output level of the comparator 1 and the voltage converted by the load current regulated by the inverse proportion, if the first comparator outputs a high level or the load current is smaller than the first output current threshold value, the second comparator outputs a low level to the PWM controller, the PWM controller reduces the PWM duty ratio and reduces the output voltage; on the contrary, the PWM duty ratio is increased, and the output voltage is improved.
Preferably, the first voltage threshold is a desired output voltage standard value, and the first output current threshold is a current required when the load is in an average power state.
Preferably, the protection circuit comprises a third comparator, a fourth comparator, a fifth comparator and an and gate;
the third comparator compares the output voltage of the boosting power circuit with an overvoltage threshold value, and outputs a high level to the first input end of the AND gate when the overvoltage threshold value is exceeded;
the fourth comparator compares the voltage converted by the output current of the boost power circuit with the voltage value converted by the overcurrent threshold value, and outputs a high level to the second input end of the AND gate when the voltage value is exceeded;
the fifth comparator compares the voltage converted by the output current of the boost power circuit with the voltage value converted by the current limiting threshold, and outputs a high level to the protection circuit when the voltage exceeds the voltage value; the protection circuit sends an overcurrent signal to the PWM controller to keep the current PWM duty ratio unchanged until the output current is lower than the current limiting threshold value;
and the output end of the AND gate is connected with a protection circuit, and when the AND gate outputs high level, the output power tube of the boosting power circuit is turned off to stop supplying power.
Preferably, the current limit threshold is a current required when the load is in a maximum set power state; the overcurrent threshold is 1.2 times of the current required when the load is in the maximum actual power state; the overvoltage threshold is 1.2 times of the standard value of the required output voltage.
Preferably, one group of switch contacts of the power-on switch is used for controlling power-on, and the other group of switch contacts is connected with a ground state indicator lamp and feeds back the power-on state to the ground; one group of switch contacts of the power transfer switch are used for controlling power transfer, and the other group of switch contacts are connected with a ground state indicator lamp and feed back success of power transfer to the ground.
Preferably, the method also comprises the steps that the ground monitors the voltage and the current output to the satellite through an output current remote terminal and an output voltage remote terminal; if the current values are within the set range, judging that the power supply output and conversion state of the equipment is normal, and calculating the power supply power of the current equipment for the rear-end load through the current remote measurement value; if the voltage is not within the set range, stopping outputting the voltage to the satellite; if the current is not in the set range, the power utilization condition of the satellite load is checked, the satellite has the condition of overlarge short-circuit power utilization, or part of equipment is not started to work, so that the current is too small.
Compared with the prior art, the invention has the following advantages:
(1) according to the invention, the voltage is directly boosted to the satellite load voltage for the first time and then transmitted, and after the boosting power supply system is adopted, the requirement of simultaneously supplying power to a plurality of load satellite loads can be met, the battery consumption of the load satellite during the flight of an aircraft can be saved, the design difficulty of a load satellite storage battery is reduced, and the power supply efficiency of a load satellite power supply system is improved.
(2) The invention also solves the problem that the aircraft has insufficient long-distance high-power supply capacity for the load satellite by adopting the boosting power supply system, so that the long-distance power supply cable is simple in design and low in loss on the cable, the power supply efficiency is improved, meanwhile, the bus voltage can be stabilized during high-power supply or sudden load change, and the design of a load secondary power supply module is easier.
(3) Partial components of the boosting power in the boosting circuit are replaced, the voltage requirements of various buses of the satellite can be met after the threshold value of the comparator is changed, the expandability is good, and space is opened up for a boosting power supply system of an aircraft.
(4) Compared with the traditional mode that the power supply output is cut off once overvoltage or overcurrent occurs, the invention supplies electric energy to the satellite to the maximum extent through overvoltage and overcurrent combined control, and reduces the loss of the electric energy carried by the satellite.
Drawings
FIG. 1 is a schematic diagram of a boost power supply system for a loaded satellite according to the present invention;
FIG. 2 is a schematic diagram of a boost power circuit;
FIG. 3 is a schematic diagram of boost PWM control;
fig. 4 is a schematic view of the protection principle.
Detailed Description
The system scheme of the aircraft for supplying power to loads such as loading satellites is shown in figure 1. The aircraft adopts a scheme of a battery and a boost controller to provide power supply energy for the loading satellite. The output voltage of the battery is 28V, and the rocket-borne voltage boosting controller switches on a relay switch to enable the voltage booster to work and output a voltage of 45V, and then the voltage is output to a load satellite load. Because the load of the load satellite has larger working power, the boost controller also needs to keep working stably and reliably when outputting high power.
1. Boosting technique
The battery converts the stored chemical energy into electric energy and outputs voltage, the bus voltage 45V required by the load of the load satellite is higher than the battery bus voltage 28V, the bus needs to be regulated and controlled, the bus voltage is increased, and meanwhile the performance of the bus is kept equivalent to that of the battery, so that the requirement of normally supplying power for loads such as the load satellite is met. Although the input/output isolation boost circuit has a high safety factor, the isolation transformer has disadvantages such as magnetic leakage and loss, so it is particularly important to be able to stably output a high-power non-isolation boost DC/DC module.
The battery voltage is boosted to a slightly higher voltage of the power supply voltage required by the satellite load, the voltage drop of a cable for long-line transmission is considered, and the voltage higher than the voltage is 1-3V.
The boost circuit is designed mainly by considering: reliability of the circuit, conversion efficiency of the circuit, performance, structural and quality requirements of the output bus, device power density and thermal environment requirements. The reliability of the booster circuit is the primary consideration of the aircraft for supplying power to loads such as load satellites, and the design and use of components and parts need to meet the requirement of first-level derating, so that long-time working damage is avoided, and the reliability of the booster circuit is guaranteed. The high conversion efficiency of the booster circuit is a necessary factor of high-power supply design, and the capacity of a battery can be effectively reduced by improving the conversion efficiency, so that the effective power of a system is improved; meanwhile, the conversion efficiency is improved, the structural size and the quality of equipment can be reduced, and the effective load weight of the aircraft is improved.
The current valley-filled phase-shifted full-bridge, Super boost and Weinberg converters of the boost circuit are compared, and are shown in Table 1.
Table 1 performance comparison of three boost topology schemes
Comparing the three topologies, the Weinberg boost circuit mode is selected to reduce the size and weight of the converter, improve the efficiency of the converter, easily realize circuit control and meet the principle of maximum high reliability. The Weinberg booster circuit can achieve high-efficiency output of more than 95%, the power tube is driven by low voltage, switching loss of a gate driving circuit and the power tube is simplified, and output current is continuous. The power tube has small stress and can meet the requirement of the reliability of the system booster circuit.
The Weinberg booster circuit adopts a push-pull improved circuit structure, when two MOSFETs are alternately switched on, the energy storage inductor is charged, and a transformer of the push-pull structure outputs energy to a secondary side. When the two MOSFETs are closed, the energy storage inductor outputs energy to the secondary side. After the improvement mode, compared with the traditional booster circuit structure, in the process of energy storage of the main inductor, current output still exists through the coupling effect of the transformer, so that in one period, output current is continuous, output capacitance can be very small, and the booster circuit has very obvious advantages for being used as a current source and a push-pull circuit of the booster circuit.
2. Protection circuit design
The boost power supply system is provided with a system protection circuit, so that the rear-end load fault is prevented from being enlarged to an aircraft battery, and the launching success of the aircraft is threatened. The boost power supply system is provided with two fault modes, namely, input overcurrent protection is adopted to prevent the load short circuit of the rear end load, the output current is overlarge, and the battery is discharged rapidly under a large current; and secondly, output overvoltage protection is performed, and when the internal boost control loop fails to regulate the bus voltage, the output of equipment is cut off. And meanwhile, during normal work, the output power of the load is limited, the out-of-limit high power of the load without faults is limited, and the thermal environments of the battery equipment of the boosting power supply system and the aircraft equipment are protected.
The input overcurrent protection circuit consists of two parts, namely a current sampling part and a power switch. The input overcurrent protection circuit is positioned at an input port of the boost control circuit, and when the output of the aircraft battery is overcurrent due to an internal circuit or an element of the boost control circuit, the overcurrent protection circuit automatically cuts off the power switch. The aircraft battery discharging current signal is amplified by the operational amplifier and sent to the in-phase end of the hysteresis comparator, when the aircraft battery discharging current exceeds a set value, the output voltage of the hysteresis comparator is reversed, a signal for turning off the power switch is generated, and the failed boost control loop is separated from the aircraft battery.
The output overvoltage protection circuit cuts off the voltage boosting regulator caused by overvoltage when the bus is in overvoltage, and the reason of the overvoltage of the bus is that the output of the voltage boosting control circuit is not controlled by the error amplification circuit. After the bus overvoltage protection occurs, the booster monomer causing the overvoltage fault is judged and turned off.
The present invention will be described in further detail with reference to the accompanying drawings.
Fig. 1 is a schematic diagram of a design principle of a boost power supply system. The boosting power supply system comprises a battery part, a command switch control part, an input filter network, a boosting circuit (comprising a boosting power circuit, a boosting control PWM loop and a protection circuit), an output filter network and a telemetering part. And driving the equipment to be powered on and powered off through control commands. After receiving a power-on instruction, the power-on switch is closed, the other group of switch contacts of the power-on switch is connected with the ground state indicator lamp, the power-on state is fed back to the ground, meanwhile, the booster circuit starts to work and stably outputs 45V voltage, the ground can monitor whether the output voltage of the battery is normal in real time through the input voltage remote detection end, and then whether the power-on state of the equipment is normal can be judged; after receiving a power conversion command, the power conversion switch is closed, the other group of switch contacts of the power conversion switch is connected with a ground state indicator lamp, the success of power conversion is fed back to the ground, and meanwhile 45V voltage is output to the satellite load; the ground monitors voltage and current output to the satellite through an output current remote measuring end and an output voltage remote measuring end, if the voltage and the current are both in a set range, the power supply output of equipment and the power conversion state of the equipment are judged to be normal, the power supply power of the equipment for a rear-end load can be calculated through a current remote measuring value, if the voltage is not in the set range, the voltage is stopped being output to the satellite, if the current is not in the set range, the power utilization condition of the satellite load is checked, the satellite may have the condition of overlarge power utilization such as short circuit, or part of the equipment is not started to work, so that the current is too small.
The input filter network mainly functions to filter out space interference on the cable and avoid large fluctuation in signals entering the booster circuit. And an inductance-capacitance filter circuit is adopted to ensure the continuity of input current and limit the discharge ripple current of the battery.
The output filter network adopts a high-frequency filter capacitor and a low-frequency filter capacitor circuit, and has the main effects of stabilizing output voltage, filtering peak signals of the switching power supply, and simultaneously improving the characteristic indexes of the load bus after long-distance power supply, so that the back-end load bus has smaller ripples and smaller peaks.
The main components of the booster circuit include:
1) boost power circuit
The boosting power circuit adopts a Weinberg boosting push-pull circuit, and mainly comprises core components such as a power tube, a transformer, an inductor and the like, and peripheral auxiliary isolation diodes, capacitors and resistors, as shown in figure 2. The voltage is boosted by 45V by transformer M2. The power tubes Q1 and Q2 are conducted, the diodes D2 and D1 are respectively promoted to be conducted under the action of the coupling transformer M1, and the freewheeling diode D3 is turned off at the moment; the power tube is turned off, and the freewheeling diode D3 is turned on to stabilize the voltage. The boost power circuit works in a non-synchronous 100kHz state and is used for boosting the output voltage of the battery and controlling the output current.
2) Boost control PWM loop
The boost control PWM loop takes the output voltage and the output current of the boost power circuit as the sampling voltage and the sampling current, see fig. 3. The load conversion causes the fluctuation of the sampling voltage, the sampling voltage is compared with the reference voltage 1 through an error amplifier comparator, the output voltage is compared with the control reference voltage 2, and further the PWM duty ratio is controlled. The sampling current is compared with the control reference voltage 2 through a secondary operational amplifier, and a control signal is output. And current control is added, so that the small change of the load current can be adjusted, and the output voltage of the bus is stabilized. When the power supply voltage to the load increases and is higher than the reference voltage 1, the comparator 1 outputs a high level which is higher than the reference voltage 2, so that the comparator 2 outputs a low level, the PWM controller reduces the PWM duty ratio, and the output voltage is reduced; the load current is sampled by adopting the inverse proportion regulating circuit, when the current provided for the load is reduced, the comparison voltage is increased after the current is amplified in the inverse proportion and converted into the voltage, and after the comparison voltage is higher than the reference voltage 2, the comparator 2 outputs a low level, the PWM controller reduces the PWM duty ratio and reduces the output voltage. When the power supply voltage to the load exceeds a set threshold (45V) or the load current is smaller than a set threshold (3A), reducing the PWM duty ratio and reducing the output voltage; conversely, when the power supply voltage to the load is lower than a set threshold (45V) or the load current is larger than a set threshold (3A), the PWM duty ratio is increased to increase the output voltage.
3) Protective circuit
Fig. 4 is a schematic diagram of the design principle of the protection circuit. The input overcurrent and output overvoltage protection circuit consists of three comparators and a protection locking circuit. The input overcurrent signal is derived from current sampling and amplified by an operational amplifier.
The overvoltage signal is derived from the output voltage conversion value of the booster, the output of the comparator 3 is at a low level when the output voltage is normal, and the output of the comparator 3 is at a high level when the output voltage is overvoltage. The current limit signal corresponds to the booster output current 22.5A and the over current signal threshold corresponds to the booster output current 30A.
When the current is larger than 22.5A, the output of the comparator 5 is inverted to high level, and the protection circuit controls the PWM controller to keep the current PWM duty ratio unchanged until the current returns to normal.
When the internal circuit or the components of the booster cause the output overcurrent of the storage battery to exceed 30A, the overcurrent signal is greater than the overcurrent signal threshold, the comparator 4 outputs high level, the overcurrent signal and the overvoltage signal are phase-inverted and then output to the protection circuit, if the overcurrent signal and the overvoltage signal are high, the protection circuit starts cut-off protection, the power tubes Q1 and Q2 are turned off, and the fault booster stops working. At this point, unlocking of the circuit requires the battery input relay to be powered back up after being powered off.
If only overvoltage or overcurrent occurs, the output can be automatically recovered through the PWM control of FIG. 2 without starting protection.
The aircraft supplies power to the load satellite is limited by the fact that the distance between the instrument installation position and the load satellite power utilization equipment is long and the power is supplied to two satellites simultaneously, the power of the whole load satellite can reach over 600 watts during the flight of the aircraft, if the power is directly supplied by a battery, the design of a cable is huge, the loss on the cable is large, and optimization of an electrical system of the aircraft is not facilitated. The aircraft satellite power supply system adopting the invention can improve the power supply voltage, not only can reduce the loss and improve the efficiency, but also can directly supply power to the load of the load satellite, reduce the working time of the load satellite and prolong the in-orbit service life of the load satellite.
The above description is only for the best mode of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
Those skilled in the art will appreciate that the invention may be practiced without these specific details.
Claims (7)
1. A high-power high stability step-up power supply system, its characterized in that includes: the device comprises a battery, a command switch control circuit, a boosting power circuit, a boosting control PWM loop and a protection circuit;
after the command switch control circuit receives a power-on command, the power-on switch is controlled to be closed, and the boosting power circuit boosts the battery voltage to the required output voltage; after the instruction switch control circuit receives a power conversion instruction, the instruction switch control circuit controls the power conversion switch to be closed, and the boosting power circuit supplies power to the load;
the boost control PWM loop is used for reducing the PWM duty ratio and reducing the output voltage when the power supply voltage for the load exceeds a set first voltage threshold or the load current is smaller than a set first output current threshold; otherwise, the PWM duty ratio is increased, and the output voltage is improved;
the protection circuit stops supplying power when the output voltage is over-voltage and the output current is over-current; when the output current exceeds a current limiting threshold value, controlling the boost control PWM loop to keep the current PWM duty ratio unchanged;
the boosting power circuit adopts a Weinberg boosting push-pull circuit;
the boosting power circuit boosts the voltage of the battery through a transformer M2; when the power tubes Q1 and Q2 are turned on, the diodes D2 and D1 are respectively driven to be turned on under the action of the coupling transformer M1, and the boosted voltage is output, and at the moment, the freewheeling diode D3 of the transformer M2 is turned off; when the power tubes Q1 and Q2 are turned off, the freewheeling diode D3 is turned on to maintain voltage output;
the boost control PWM loop comprises a first comparator, a second comparator and a PWM controller;
the first comparator compares the output voltage of the boost power circuit with the first voltage threshold, and if the output voltage is higher than the first voltage threshold, a high level is output, otherwise, a low level is output; the negative input end of the second comparator is simultaneously connected with the output level of the first comparator and the voltage converted by the load current regulated by the inverse proportion, if the first comparator outputs a high level or the load current is smaller than the first output current threshold value, the second comparator outputs a low level to the PWM controller, the PWM controller reduces the PWM duty ratio and reduces the output voltage; on the contrary, the PWM duty ratio is increased, and the output voltage is improved.
2. The high power, high stability boost power supply system according to claim 1, further comprising an input filter network and an output filter network; the input filter network is used for filtering interference on a battery power supply bus; the output filter network comprises a high-frequency filter capacitor circuit and a low-frequency filter capacitor circuit, and the output voltage of the boost power circuit is stabilized.
3. The high power, high stability boost power supply system according to claim 1, wherein the first voltage threshold is a desired output voltage reference value and the first output current threshold is the current required by the load when in an average power state.
4. The high power high stability boost power supply system according to claim 1, wherein the protection circuit comprises a third comparator, a fourth comparator, a fifth comparator and an and gate;
the third comparator compares the output voltage of the boosting power circuit with an overvoltage threshold value, and outputs a high level to the first input end of the AND gate when the overvoltage threshold value is exceeded;
the fourth comparator compares the voltage converted by the output current of the boost power circuit with the voltage value converted by the overcurrent threshold value, and outputs a high level to the second input end of the AND gate when the voltage value is exceeded;
the fifth comparator compares the voltage converted by the output current of the boost power circuit with the voltage value converted by the current limiting threshold, and outputs a high level to the protection circuit when the voltage exceeds the voltage value; the protection circuit sends an overcurrent signal to the PWM controller to keep the current PWM duty ratio unchanged until the output current is lower than the current limiting threshold value;
and the output end of the AND gate is connected with a protection circuit, and when the AND gate outputs high level, the output power tube of the boosting power circuit is turned off to stop supplying power.
5. The high power high stability boost power supply system according to claim 1, wherein the current limit threshold is the current required by the load in the maximum set power state; the overcurrent threshold is 1.2 times of the current required when the load is in the maximum actual power state; the overvoltage threshold is 1.2 times of the standard value of the required output voltage.
6. The high-power high-stability boost power supply system according to claim 1, wherein one set of switch contacts of the power-on switch is used for controlling power-on, and the other set of switch contacts is connected with a ground state indicator lamp for feeding back the power-on state to the ground; one group of switch contacts of the power transfer switch are used for controlling power transfer, and the other group of switch contacts are connected with a ground state indicator lamp and feed back success of power transfer to the ground.
7. The high power high stability boost power supply system according to claim 1, further comprising monitoring the output voltage and current to the satellite on the ground through an output current telemetry terminal and an output voltage telemetry terminal; if the current values are within the set range, judging that the power supply output and conversion state of the equipment is normal, and calculating the power supply power of the current equipment for the rear-end load through the current remote measurement value; if the voltage is not within the set range, stopping outputting the voltage to the satellite; if the current is not in the set range, the power utilization condition of the satellite load is checked, the satellite has the condition of overlarge short-circuit power utilization, or part of equipment is not started to work, so that the current is too small.
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| CN113946199B (en) * | 2020-07-15 | 2024-07-05 | 台达电子企业管理（上海）有限公司 | Power supply system |
| CN110112905A (en) | 2018-02-01 | 2019-08-09 | 台达电子企业管理（上海）有限公司 | Main chip on board power supply system |
| CN113285594A (en) * | 2021-05-28 | 2021-08-20 | 太原航空仪表有限公司 | Airborne aviation 270V power supply |
| CN114488886A (en) * | 2022-01-13 | 2022-05-13 | 上海卫星工程研究所 | High-voltage control power supply and remote measurement acquisition circuit for spacecraft |
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| CN103337892A (en) * | 2013-07-10 | 2013-10-02 | 上海空间电源研究所 | Independent dormancy awakening control system of satellite power source |
| CN107404232A (en) * | 2017-06-23 | 2017-11-28 | 深圳市航天新源科技有限公司 | A kind of two-way DC DC converters |
| CN108512429A (en) * | 2018-03-20 | 2018-09-07 | 南京理工大学 | A kind of number isolated form DC/DC converters and control method |
| CN108666980A (en) * | 2018-04-10 | 2018-10-16 | 上海空间电源研究所 | A kind of discharge fault integration protection circuit |
| CN208112509U (en) * | 2018-04-23 | 2018-11-16 | 顺德职业技术学院 | A kind of twin-stage input step-up DC constant voltage output converter |
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