CN115549035A - Power protection system and aircraft - Google Patents
Power protection system and aircraft Download PDFInfo
- Publication number
- CN115549035A CN115549035A CN202211109120.6A CN202211109120A CN115549035A CN 115549035 A CN115549035 A CN 115549035A CN 202211109120 A CN202211109120 A CN 202211109120A CN 115549035 A CN115549035 A CN 115549035A
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- Prior art keywords
- aircraft
- power supply
- power
- diode
- protection system
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Classifications
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H7/00—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions
- H02H7/22—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for distribution gear, e.g. bus-bar systems; for switching devices
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
- H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
- H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
- H02J9/068—Electronic means for switching from one power supply to another power supply, e.g. to avoid parallel connection
Abstract
The embodiment of the invention discloses a power supply protection system and an aircraft. The power protection system includes: an aircraft load; the power supply interface module is used for being externally connected with a first power supply, wherein the first power supply is used for supplying power to an aircraft load when the aircraft is in a ground stage; a second power supply for powering an aircraft load when the aircraft is in a launch phase or a flight phase; the action signal receiving module is used for receiving an action signal generated when the aircraft breaks away from the ground and generating a driving signal; the backflow prevention diode is used for preventing the second power supply from influencing the work of the first power supply when the second power supply is in a short-circuit state; and the controllable switch is used for controlling the working state of the normally open contact of the controllable switch based on the driving signal. The invention solves the technical problem that the heating power caused by diode voltage drop influences the power supply reliability of the aircraft in the related technology, and achieves the technical effects of reducing the size and weight of aircraft equipment, reducing the flight cost and improving the power supply reliability of the aircraft.
Description
Technical Field
The invention relates to the technical field of power supplies, in particular to a power supply protection system and an aircraft.
Background
The aircraft power supply can be in a short-circuit state in a short time in the activation process, and if the ground power supply output for supplying power at the same time is influenced without measures for protection, voltage drop is caused, and the power supply of the whole aircraft system is influenced. Therefore, in the fields of aviation, aerospace and the like, in order to avoid the above situation, a backflow prevention diode is usually arranged at the output end of the aircraft power supply, and the influence of the short-circuit state of the aircraft power supply on the system power supply is prevented by utilizing the unidirectional conductivity of the diode. Because the diode is connected in series on the power supply loop, the maximum current value of the power supply in the whole working process of the aircraft is considered when the model selection is designed. In the flying process of the aircraft, the current can reach tens of amperes to the maximum, and the power supply current of the aircraft power supply flows through the backflow prevention diode, so the reliability of power supply is improved by adopting a mode of connecting a plurality of high-power diodes in parallel, the volume and the weight of aircraft equipment are overlarge, and the flying cost is increased. Meanwhile, the heating power caused by the voltage drop of the diode cannot be ignored, and if the heat dissipation design of the equipment is unreliable, the open circuit fault of the backflow-preventing diode can be caused when the junction temperature of the diode exceeds a rated value due to the heat accumulation caused by the voltage drop of the diode, so that the reliability of the power supply of the aircraft is seriously influenced.
An effective solution to the above problems has not been proposed.
Disclosure of Invention
The embodiment of the invention provides a power supply protection system and an aircraft, which at least solve the technical problem that the power supply reliability of the aircraft is influenced by the heating power caused by diode voltage drop in the related technology.
According to an aspect of an embodiment of the present invention, there is provided a power protection system including: an aircraft load; the power supply interface module is connected with the aircraft load and used for being externally connected with a first power supply, wherein the first power supply is used for supplying power to the aircraft load when the aircraft is in a ground stage; a second power supply for powering the aircraft load when the aircraft is in a launch phase or a flight phase; the action signal receiving module is used for receiving an action signal generated when the aircraft breaks away from the ground and generating a driving signal; the backflow prevention diode is respectively connected with the second power supply and the aircraft load and used for preventing the second power supply from influencing the normal work of the first power supply when the second power supply is in a short-circuit state; and the controllable switch is respectively connected with the action signal receiving module, the second power supply and the aircraft load and is used for controlling the working state of a normally open contact of the controllable switch based on the driving signal.
Optionally, a first end of the power interface module is connected to the first power supply, a second end of the power interface module is connected to the first end of the aircraft load, a second end of the aircraft load is grounded, a first end of the second power supply is grounded, a first end of the backflow prevention diode and a first end of the controllable switch are connected in parallel and then connected to a second end of the second power supply, a second end of the backflow prevention diode and a second end of the controllable switch are connected in parallel and then connected to the first end of the aircraft load, and a second end of the controllable switch is connected to the action signal receiving module.
Optionally, the back-flow prevention diode comprises a diode, wherein an anode of the diode is connected to the second terminal of the second power source, and a cathode of the diode is connected to the first terminal of the aircraft load.
Optionally, the backflow prevention diode includes a plurality of diodes, where the plurality of diodes are connected in parallel, anodes of the plurality of diodes after being connected in parallel are connected to the second end of the second power supply, and cathodes of the plurality of diodes after being connected in parallel are connected to the first end of the aircraft load.
Optionally, the diode is a silicon schottky diode, wherein a load current index of the silicon schottky diode is at least twice a current value required when the aircraft is in a ground stage.
Optionally, when the working state of the normally open contact is a closed state, the on-resistance at two ends of the normally open contact is less than 10m Ω.
Optionally, the action signal receiving module includes an optical coupling isolation circuit and a driver, where a first end of the driver is connected to the optical coupling isolation circuit, and a second end of the driver is connected to the controllable switch.
Optionally, when the aircraft is in a ground stage, the positive electrode and the negative electrode of the optical coupling input end of the optical coupling isolation circuit are in a conducting state, and the output end of the optical coupling isolation circuit outputs an invalid level; when the aircraft is in a launching phase or a flight phase, the anode and the cathode of the optical coupler input end of the optical coupler isolation circuit are in a disconnected state, and the optical coupler output end outputs an effective level.
Optionally, when an optocoupler output end of the optocoupler-isolation circuit outputs an invalid level, the driving signal output by the driver is invalid; when the optical coupling output end of the optical coupling isolation circuit outputs an effective level, the driving signal output by the driver is effective to drive the controllable switch to act.
According to another aspect of an embodiment of the present invention, there is also provided an aircraft including the power protection system of any one of the above.
In an embodiment of the present invention, the power protection system includes: an aircraft load; the power supply interface module is connected with the aircraft load and used for being externally connected with a first power supply, wherein the first power supply is used for supplying power to the aircraft load when the aircraft is in a ground stage; a second power supply for powering an aircraft load when the aircraft is in a launch phase or a flight phase; the action signal receiving module is used for receiving an action signal generated when the aircraft breaks away from the ground and generating a driving signal; the backflow prevention diode is respectively connected with the second power supply and the aircraft load and used for preventing the second power supply from influencing the normal work of the first power supply when the second power supply is in a short-circuit state; and the controllable switch is respectively connected with the action signal receiving module, the second power supply and the aircraft load and is used for controlling the working state of a normally open contact of the controllable switch based on the driving signal. That is to say, the power protection system of the embodiment of the invention performs time-sharing control according to the power supply characteristics of the aircraft in different working stages, and can select a diode with smaller power to form a backflow prevention diode, so that the heating power of the diode is almost zero in the flight process of the aircraft, the adverse effect of the heating power caused by diode voltage drop in the flight stage on the power supply reliability is avoided, the technical problem that the heating power caused by diode voltage drop in the related technology affects the power supply reliability of the aircraft is further solved, and the technical effects of reducing the size and weight of aircraft equipment, reducing the flight cost and improving the power supply reliability of the aircraft are achieved.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:
fig. 1 is a schematic diagram of a power protection system according to an embodiment of the present invention;
fig. 2 is a flowchart of time-sharing control based on a power protection system according to an embodiment of the present invention;
fig. 3 is a schematic diagram of another power protection system according to an embodiment of the present invention;
fig. 4 is a schematic diagram of an action signal receiving module according to an embodiment of the present invention.
Wherein the figures include the following reference numerals:
11. an aircraft load; 12. a power interface module; 13. a second power supply; 14. an action signal receiving module; 15. a back-flow prevention diode; 16. a controllable switch; 31. a first power supply; 41. an opto-coupler isolation circuit; 42. a driver.
Detailed Description
In order to make the technical solutions of the present invention better understood, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that the terms "first", "second", and the like in the description and claims of the present invention and the accompanying drawings are used for distinguishing different objects, and are not used for limiting a specific order.
According to an aspect of an embodiment of the present invention, there is provided a power protection system, and fig. 1 is a schematic diagram of a power protection system provided in an embodiment of the present invention, as shown in fig. 1, the power protection system includes:
an aircraft load 11;
the power interface module 12 is connected with the aircraft load 11 and is used for externally connecting a first power supply, wherein the first power supply is used for supplying power to the aircraft load 11 when the aircraft is in a ground stage;
a second power supply 13 for powering the aircraft load 11 when the aircraft is in a launch phase or a flight phase;
the action signal receiving module 14 is used for receiving an action signal generated when the aircraft breaks away from the ground and generating a driving signal;
the backflow prevention diode 15 is connected with the second power supply 13 and the aircraft load 11 respectively and used for preventing the second power supply 13 from being in a short-circuit state and influencing the normal work of the first power supply;
and the controllable switch 16 is connected with the action signal receiving module 14, the second power supply 13 and the aircraft load 11 respectively and is used for controlling the working state of a normally open contact of the controllable switch 16 based on the driving signal.
The first power supply is also called a ground power supply; the second power supply 13 is also called an aircraft power supply, and when the second power supply is in a short-circuit state, the first power supply is easily influenced to supply power to the aircraft load 11, namely the normal operation of the first power supply is influenced; the anti-backflow diode 15 is also called an anti-backflow module, and may be formed by one or more diodes; the various phases of operation of the aircraft include, but are not limited to, the aircraft being in a ground phase, the aircraft being in a launch phase, or a flight phase.
Alternatively, the action signal receiving module 14 may convert an action signal generated when the aircraft is off the ground into a driving signal, and further the driving signal may drive the controllable switch 16, so as to control the normally open contact to be in an open or a conductive state. It should be noted that the controllable switch 16 may adopt a high-power solid relay, which includes a normally open contact, and has the advantages of small volume, large load current, and high reliability; the normally open contact of the controllable switch 16 is connected in parallel with the anti-backflow diode; the anti-backflow diode 15 can select a diode with smaller power according to the power supply current of the aircraft on the ground, so that the size and the weight of equipment on the aircraft can be effectively reduced; when the aircraft is in a flying state, the aircraft power supply backflow prevention protection device can effectively avoid the adverse effect of the heating of the diode on the power supply reliability of the aircraft in the flying process by closing the normally open contact short-circuit backflow prevention diode connected in parallel with the two ends of the diode.
It should be noted that the diode in the back-flow prevention diode 15 can effectively avoid the influence caused by the short-circuit state in the short time when the aircraft power supply is activated when the aircraft is not launched on the ground, the controllable switch 16 is controlled after the successful launching, the normally open contacts connected in parallel with the two ends of the diode are closed, the power supply current flows through the normally open contacts to enable the heating power of the diode to be almost zero, the adverse effect of the heating power of the diode on the power supply of the aircraft is avoided, and the reliability of the power supply of the aircraft is improved. Meanwhile, the backflow prevention diode only works in the transmitting stage, so that the current output of the aircraft is very small, the power requirement on the diode is greatly reduced, the size and weight of equipment on the aircraft are reduced, and the flight cost of the aircraft is reduced.
In an embodiment of the present invention, the power protection system includes: an aircraft load; the power supply interface module is connected with the aircraft load and used for being externally connected with a first power supply, wherein the first power supply is used for supplying power to the aircraft load when the aircraft is in a ground stage; a second power supply for powering an aircraft load when the aircraft is in a launch phase or a flight phase; the action signal receiving module is used for receiving an action signal generated when the aircraft breaks away from the ground and generating a driving signal; the backflow prevention diode is respectively connected with the second power supply and the aircraft load and used for preventing the second power supply from influencing the normal work of the first power supply when the second power supply is in a short-circuit state; and the controllable switch is respectively connected with the action signal receiving module, the second power supply and the aircraft load and is used for controlling the working state of a normally open contact of the controllable switch based on the driving signal. That is to say, the power protection system of the embodiment of the invention performs time-sharing control according to the power supply characteristics of the aircraft in different working stages, and can select a diode with smaller power to form a backflow prevention diode, so that the heating power of the diode is almost zero in the flight process of the aircraft, the adverse effect of the heating power caused by diode voltage drop in the flight stage on the power supply reliability is avoided, the technical problem that the heating power caused by diode voltage drop in the related technology affects the power supply reliability of the aircraft is further solved, and the technical effects of reducing the size and weight of aircraft equipment, reducing the flight cost and improving the power supply reliability of the aircraft are achieved.
Fig. 2 is a flowchart of time-sharing control based on a power protection system according to an embodiment of the present invention, as shown in fig. 2,
step 1: when the aircraft is in the ground stage, the normally open contact of the controllable switch 16 is in an open circuit state;
when the aircraft is in the ground stage, the action signal receiving module 14 has no effective action signal input, the controllable switch 16 does not act, namely the normally open contact is in an open circuit state, the backflow preventing diode 15 plays a role in the process, and the influence of the short circuit state of the aircraft power supply on the aircraft power supply in the activation process can be effectively avoided;
step 2: when the aircraft is in a transmitting stage, the action signal receiving module 14 receives the action signal and then drives the normally open contact of the controllable switch 16 to be closed;
when the aircraft is in a transmitting stage, the action signal receiving module 14 receives an action signal generated when the aircraft breaks away from the ground, and generates a driving signal, and the driving signal drives the controllable switch 16 to act, so as to control the normally open contact of the controllable switch 16 to be closed;
and 3, step 3: when the aircraft is in the flight phase, the normally open contact of the controllable switch 16 is always in a conducting state;
when the aircraft is in a flight phase, the normally open contact of the controllable switch 16 is always in a closed state, that is, in the flight phase, the power supply current of the aircraft flows through the normally open contact, and the heating power of the backflow prevention diode is almost zero.
In the above-mentioned in-process of this application, utilize and prevent flowing backward the diode and avoid the aircraft power supply effectively to the influence of aircraft power supply at the in-process short-circuit state of activation, control controllable switch closure again after the transmission is successful and connect in parallel the normally open contact at diode both ends, supply current flows through the normally open contact, makes the aircraft at the in-process diode's of flight heating power near zero, has avoided the in-process diode of flight to generate heat the harmful effects to aircraft power supply reliability. Meanwhile, the anti-backflow diode only works in the transmitting stage, so that the current output of the aircraft is very small, the power requirement on the diode is reduced, and the low-power diode with smaller volume and weight can be selected, so that the volume and weight of equipment on the aircraft are reduced.
Fig. 3 is a schematic diagram of another power protection system according to an embodiment of the present invention, and as shown in fig. 3, circuit connection modes of modules of the power protection system are as follows: the first end of the power interface module 12 is connected with the second end of the first power supply 31, the first end of the first power supply 31 is grounded, the second end of the power interface module 12 is connected with the first end of the aircraft load 11, the second end of the aircraft load 11 is grounded, the first end of the second power supply 13 is grounded, the first end of the backflow prevention diode 15 and the first end of the controllable switch 16 are connected in parallel and then connected with the second end of the second power supply 13, the second end of the backflow prevention diode 15 and the second end of the controllable switch 16 are connected in parallel and then connected with the first end of the aircraft load 11, and the second end of the controllable switch 16 is connected with the action signal receiving module 14; the anti-backflow diode 15 includes two diodes connected in parallel.
In an alternative embodiment, the back-flow prevention diode 15 comprises a diode, wherein the anode of the diode is connected to the second terminal of the second power source 13 and the cathode of the diode is connected to the first terminal of the aircraft load 11.
In an alternative embodiment, the back-flow prevention diode 15 comprises a plurality of diodes, wherein the plurality of diodes are connected in parallel, wherein the anodes of the plurality of diodes connected in parallel are connected to the second terminal of the second power source 13, and the cathodes of the plurality of diodes connected in parallel are connected to the first terminal of the aircraft load 11.
It should be noted that, the second end of the second power supply 13 is a positive output end of the aircraft power supply, and the first end of the aircraft load 11 is a positive power supply input end of the aircraft load; alternatively, when the back-flow prevention diode 15 comprises a plurality of diodes, the anodes of the respective diodes are all connected to the positive output terminal of the aircraft power supply, and the cathodes of the respective diodes are all connected to the positive power input terminal of the aircraft load.
In an alternative embodiment, the diode is a silicon schottky diode, wherein the load current rating of the silicon schottky diode is at least twice the current rating required when the aircraft is in the ground phase.
Optionally, the anti-backflow diode is composed of two silicon schottky diodes, and a loadable current value of each silicon schottky diode is twice of a maximum current value required when the aircraft is in a ground stage.
In an alternative embodiment, when the working state of the normally open contact is the closed state, the on-resistance of the two ends of the normally open contact is less than 10m Ω.
It should be noted that the on-resistances at the two ends of the normally-open contact are related to the number of diodes in the anti-back-flow diode.
Fig. 4 is a schematic diagram of an action signal receiving module according to an embodiment of the present invention, and as shown in fig. 4, the action signal receiving module 14 may include an optical coupler isolation circuit 41 and a driver 42, where a first end of the driver 42 is connected to the optical coupler isolation circuit 41, and a second end of the driver 42 is connected to the controllable switch 16.
The transmission action of the aircraft can influence the conduction characteristic between the positive pole and the negative pole of the optical coupler input end of the optical coupler isolation circuit, namely, the aircraft is in a conduction state between the positive pole and the negative pole of the optical coupler input end when the aircraft is on the ground, and the aircraft is in a disconnection state between the positive pole and the negative pole of the optical coupler input end when the aircraft is in a flight state.
In an optional implementation manner, when the aircraft is in a ground stage, the positive electrode and the negative electrode of the optocoupler input end of the optocoupler isolation circuit 41 are in a conducting state, and the optocoupler output end outputs an invalid level; when the aircraft is in a launching phase or a flight phase, the anode and the cathode of the optical coupling input end of the optical coupling isolation circuit 41 are in a disconnected state, and the output end of the optical coupling outputs an effective level.
In an alternative embodiment, when the optical coupling output terminal of the optical coupling isolation circuit 41 outputs an inactive level, the driving signal output by the driver 42 is inactive; when the optical coupling output end of the optical coupling isolation circuit 41 outputs an effective level, the driving signal output by the driver 42 is effective, and the controllable switch 16 is driven to act.
The actuation of the controllable switch 16 includes controlling the closing of the normally open contacts of the controllable switch.
According to another aspect of an embodiment of the present invention, there is also provided an aircraft including the power protection system of any one of the above.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention.
Claims (10)
1. A power protection system, comprising:
an aircraft load;
the power supply interface module is connected with the aircraft load and used for being externally connected with a first power supply, wherein the first power supply is used for supplying power to the aircraft load when the aircraft is in a ground stage;
a second power supply for powering the aircraft load when the aircraft is in a launch phase or a flight phase;
the action signal receiving module is used for receiving an action signal generated when the aircraft breaks away from the ground and generating a driving signal;
the backflow prevention diode is respectively connected with the second power supply and the aircraft load and used for preventing the second power supply from influencing the normal work of the first power supply when the second power supply is in a short-circuit state;
and the controllable switch is respectively connected with the action signal receiving module, the second power supply and the aircraft load and is used for controlling the working state of a normally open contact of the controllable switch based on the driving signal.
2. The power protection system of claim 1, wherein a first end of the power interface module is connected to the first power source, a second end of the power interface module is connected to the first end of the aircraft load, a second end of the aircraft load is grounded, a first end of the second power source is grounded, a first end of the back flow prevention diode and a first end of the controllable switch are connected in parallel and then connected to a second end of the second power source, a second end of the back flow prevention diode and a second end of the controllable switch are connected in parallel and then connected to the first end of the aircraft load, and a second end of the controllable switch is connected to the action signal receiving module.
3. The power protection system of claim 1, wherein the back-flow prevention diode comprises a diode, wherein an anode of the diode is coupled to the second terminal of the second power source and a cathode of the diode is coupled to the first terminal of the aircraft load.
4. The power protection system of claim 1, wherein the back-flow prevention diode comprises a plurality of diodes, wherein the plurality of diodes are connected in parallel, wherein anodes of the plurality of diodes after parallel connection are connected to the second terminal of the second power source, and wherein cathodes of the plurality of diodes after parallel connection are connected to the first terminal of the aircraft load.
5. The power protection system of claim 3 or 4, wherein the diode is a silicon Schottky diode, wherein a load current rating of the silicon Schottky diode is at least twice a current value required when the aircraft is in a ground phase.
6. The power protection system according to claim 1, wherein when the operating state of the normally open contact is a closed state, the on-resistance across the normally open contact is less than 10m Ω.
7. The power protection system according to claim 1, wherein the action signal receiving module comprises an optical coupling isolation circuit and a driver, wherein a first end of the driver is connected with the optical coupling isolation circuit, and a second end of the driver is connected with the controllable switch.
8. The power protection system according to claim 7, wherein when the aircraft is in a ground stage, a positive electrode and a negative electrode of an optical coupler input end of the optical coupler isolation circuit are in a conducting state, and an optical coupler output end outputs an invalid level; when the aircraft is in a launching phase or a flight phase, the anode and the cathode of the optical coupler input end of the optical coupler isolation circuit are in a disconnected state, and the optical coupler output end outputs an effective level.
9. The power protection system of claim 7, wherein when an optical coupling output end of the optical coupling isolation circuit outputs an invalid level, the driving signal output by the driver is invalid; when the optical coupling output end of the optical coupling isolation circuit outputs an effective level, the driving signal output by the driver is effective to drive the controllable switch to act.
10. An aircraft comprising a power protection system according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211109120.6A CN115549035A (en) | 2022-09-13 | 2022-09-13 | Power protection system and aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211109120.6A CN115549035A (en) | 2022-09-13 | 2022-09-13 | Power protection system and aircraft |
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| CN115549035A true CN115549035A (en) | 2022-12-30 |
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| CN202211109120.6A Pending CN115549035A (en) | 2022-09-13 | 2022-09-13 | Power protection system and aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116466637A (en) * | 2023-04-19 | 2023-07-21 | 东方空间技术(山东)有限公司 | Power distribution control system and method of aircraft and flight control computer |
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2022
- 2022-09-13 CN CN202211109120.6A patent/CN115549035A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116466637A (en) * | 2023-04-19 | 2023-07-21 | 东方空间技术(山东)有限公司 | Power distribution control system and method of aircraft and flight control computer |
| CN116466637B (en) * | 2023-04-19 | 2024-01-12 | 东方空间技术(山东)有限公司 | Power distribution control system and method of aircraft and flight control computer |
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