CN202218058U - Redundancy power source power supply system - Google Patents
Redundancy power source power supply system Download PDFInfo
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- CN202218058U CN202218058U CN 201120337447 CN201120337447U CN202218058U CN 202218058 U CN202218058 U CN 202218058U CN 201120337447 CN201120337447 CN 201120337447 CN 201120337447 U CN201120337447 U CN 201120337447U CN 202218058 U CN202218058 U CN 202218058U
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- power supply
- power source
- control box
- power
- redundancy
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Abstract
The utility model relates to a redundancy power source power supply system. A safety device is respectively connected in series with the input end of each power source converter, the other end of each safety device is respectively connected with a power supply power source positive electrode of an airplane power source system, the output ends of a first power source converter and a second power source converter 4 are respectively connected in series with a diode, the output ends of the two diodes are connected in parallel and are then connected with an output circuit, and a required direct current power source is output into a control box. The number of the power source converters is two or three, and a two-redundancy power source power supply system or a three-redundancy power source power supply system is formed. The redundancy power source power supply system overcomes the potential defects of the existing redundancy power source power supply structure of the control box of an airplane electronic anti-slip brake system, the redundancy power supply is realized in the real sense, the other or rest power source device can still realize the power supply even when one power source device fails regardless of the open circuit failure or the short circuit failure, and a control box power supply system is ensured not to generate power failure, so the normal operation of the control box is ensured.
Description
Technical field
The present invention relates to a kind of remaining electric supply system, particularly, relate to a kind of improved remaining electric supply system, more specifically, relate to a kind of improved remaining electric supply system that is used for aircraft electronic anti-skid braking system control box.
Background technology
Present generation aircraft extensive use electronic anti-skid braking system, control box then are one of key devices of this system.The dc power supply of control box is provided by aircraft power system.Because the more inner unit of control box need different power supplys with device; The aircraft supply power is transformed into suitable power supply by its inner power panel or power supply changeover device (PCM), for example after getting into control box; The 28V direct current that aircraft is provided is transformed into 15V, the 4V dc power supply.In order to ensure the electronic anti-skid braking system safe and reliable operation, must guarantee at first that power supply safety is reliable, adopt the power supply of redundance technology usually, to realize using the electric loading uninterrupted power supply.Usually, aircraft is that control box provides two tunnel dc power supplies (two remaining power supplys) independently simultaneously, as the primary power source of control box.Power panel that control box is inner or power supply changeover device (PCM) also adopt the redundancy technology power supply, receive factor affecting such as volume, expense, and two remaining power supplys power supply configuration is in the majority.Fig. 1 is a kind of existing remaining electric supply system schematic diagram, and it comprises two power supply changeover devices (PCM) device.Concerning control box, even there is a supply unit to break down, another supply unit still can be supplied power, and guarantees that control box normally moves.But theory analysis finds that with using to put into practice there is defective in the remaining power supply power supply configuration of current control box.It considers power supply changeover device (PCM) open fault, has ignored short trouble.If open fault has taken place a power supply changeover device (PCM), for example, open fault has taken place in first power supply changeover device (PCM) 2, and second power supply transducer (PCM) 4 can provide out-put supply, guarantees the normal electricity consumption of control box.But; If short trouble has taken place a power supply changeover device (PCM), for example, short trouble has taken place in first power supply changeover device (PCM) 2; Another or remaining power supply changeover device (PCM) 4; Even function own is intact, the final output voltage of power supply is almost nil, control box can't normally be moved and loses its function.The reason of this incident is to be current-limiting resistance or safeties in the control box supply line (direct current is anodal), blows or scorification because of violent increase of the electric current that flows through after the short circuit, has cut off the power supply of aircraft power system to control box.Therefore, need improve control box remaining power supply power supply configuration.
Summary of the invention
Almost nil for overcoming the final output voltage of power supply when the failed because that exists in the prior art, control box can't normally be moved and lose the deficiency of its function, the present invention proposes a kind of remaining electric supply system.
The present invention is in series with safeties respectively at the input of each power supply changeover device.All be connected at each safeties other end with the anodal line of aircraft power system power supply.The output of first power supply changeover device and second source transducer 4 is in series with a diode respectively.Be connected with outlet line after the output parallel connection of two diodes, to the DC power supply of the inner output needs of control box.
Described power supply changeover device is two or three, has formed two remaining electric supply systems or three remaining electric supply systems.
Control box of the present invention adopts two or more power supply changeover devices (PCM), and these power supply changeover devices (PCM) are connected in parallel to each other together, constitutes the remaining electric supply system, for control box inside provides required power supply.The input of each power supply changeover device (PCM) is in series with safeties, is connected with the aircraft power system power supply through it; The output of each power supply changeover device (PCM) is in series with diode, through its DC power supply to the inner output needs of control box.
According to remaining electric supply system of the present invention; Do not increasing under the situation such as control box power panel quantity, volume, expense; Between second power supply transducer (PCM) and positive source, increase line; And safeties of serial connection on this line have been eliminated the defective that current aircraft electronic anti-skid braking system control box remaining power supply power supply configuration exists, and guarantee that the aircraft power system power supply reliably is connected with control box remaining electric supply system; The real redundant electrical pow er supply of realizing is guaranteed the control box reliability service.The present invention is simple and easy to do, both has been applicable to newly to develop product, is applicable to that also old product upgrades.
The effect of diode is to guarantee correct voltage output, if there is one road power supply changeover device (PCM) output to be lower than another road power supply changeover device (PCM) output, what the existence of diode made the output of remaining electric supply system is high voltage.Simultaneously, the reverse obstruct with electric loading by effect of diode possibly conducted unfavorable electric current or electromagnetic interference to control box power supply or aircraft power supply.
The invention solves the latent defect that the existing remaining power supply power supply of aircraft electronic anti-skid braking system control box configuration exists; Realize redundant electrical pow er supply truly; Even there is a supply unit to break down, no matter be open circuit or short circuit, another or remaining power supply device still can be supplied power; Assurance control box electric power system can not cut off the power supply, thereby guarantees that control box normally moves.
Description of drawings
Description of drawings of the present invention:
Accompanying drawing 1 is existing remaining electric supply system sketch map.
Accompanying drawing 2 is two remaining electric supply system sketch mapes.
Accompanying drawing 3 is three remaining electric supply system sketch mapes.Among the figure:
1. 3. diode 4. second source transducers of safeties 2. first power supply changeover devices (PCM)
5. the 3rd power supply changeover device
Embodiment
Embodiment one
Present embodiment is a kind of single output two remaining electric supply systems that are used for aircraft electronic anti-skid braking system control box.The aviation power supply power supply is the 28V direct current, power supply changeover device 2 output 15V direct currents, and the remaining electric supply system is output as 15V.
Shown in accompanying drawing 2.Present embodiment comprises first power supply changeover device 2, second source transducer 4 and safeties 1, and described two power supply changeover devices 2 are parallel with one another.Power supply changeover device 2 adopts uses DC-to-dc (DC-DC) power module; Safeties 1 adopt current-limiting resistance.Parallel power channel is two.
Input at two power supply changeover devices 2 is in series with safeties 1 respectively.The other end of two safeties 1 all is connected with the anodal line of aircraft power system power supply.The output of first power supply changeover device 2 and second source transducer 4 is in series with a diode 3 respectively.Be connected with outlet line after the output parallel connection of two diodes, to the DC power supply of the inner output needs of control box.
Embodiment two
Present embodiment is a kind of single output three remaining electric supply systems that are used for aircraft electronic anti-skid braking system control box.The aviation power supply power supply is the 28V direct current, power supply changeover device 2 output 5V direct currents, and the remaining electric supply system is output as 5V.
Shown in accompanying drawing 3.Present embodiment comprises first power supply changeover device (PCM) 2, second source transducer 4, the 3rd power supply changeover device 5 and safeties 1, and described first power supply changeover device (PCM) 2, second source transducer 4, the 3rd power supply changeover device 5 are parallel with one another.Power supply changeover device 2 adopts uses DC-to-dc (DC-DC) power module; Safeties 1 adopt fusible link.Parallel power channel is three.
Input at first power supply changeover device (PCM) 2, second source transducer 4, the 3rd power supply changeover device 5 is in series with safeties 1 respectively.The other end of three safeties 1 all is connected with the anodal line of aircraft power system power supply.The output of first power supply changeover device (PCM) 2, second source transducer 4, the 3rd power supply changeover device 5 is in series with a diode 3 respectively.Be connected with outlet line after the output parallel connection of three diodes, to the DC power supply of the inner output needs of control box.
Embodiment three
Present embodiment is a kind of dual output two remaining electric supply systems that are used for aircraft electronic anti-skid braking system control box.The aviation power supply power supply is the 28V direct current, and the power output of power supply changeover device 2 is the 4V direct current, and the output of remaining electric supply system also is the 4V direct current.
Shown in accompanying drawing 2.Present embodiment comprises first power supply changeover device 2, second source transducer 4 and safeties 1, and described two power supply changeover devices 2 are parallel with one another.Power supply changeover device 2 adopts discrete component; Safeties 1 adopt current-limiting resistance.Parallel power channel is two.
Input at two power supply changeover devices 2 is in series with safeties 1 respectively.The other end of two safeties 1 all is connected with the anodal line of aircraft power system power supply.The output of first power supply changeover device 2 and second source transducer 4 is in series with a diode 3 respectively.Be connected with outlet line after the output parallel connection of two diodes, to the DC power supply of the inner output needs of control box.
Among the present invention, the remaining quantity of remaining power supply depends on actual requirement.Remaining quantity improves; The reliability of power supply power supply improves; But after corresponding increases such as electronic devices and components quantity, duty volume, weight, cost, particularly component number increase, on the limited printed circuit board of size or in the limited control box in space, arrange very difficulty of assembling components and parts.Power supply changeover device (PCM) adopts discrete component or DC-to-dc (DC-DC) power module, because stock in hand supply in market is used more convenient.In embodiment two and embodiment three, only export No. one DC power supply voltage (single output).Safeties adopt traditional device, and like fusible link, fuse link, perhaps current-limiting resistance depends on concrete application requirements.The effect of diode is to guarantee correct voltage output, is lower than another road power supply changeover device (PCM) output as one road power supply changeover device (PCM) output, and what the existence of diode made the output of remaining electric supply system is high voltage.Simultaneously, the reverse obstruct with electric loading by effect of diode possibly conducted unfavorable electric current or electromagnetic interference to control box power supply or aircraft power supply.
Claims (1)
1. a remaining electric supply system comprises power supply changeover device and safeties, it is characterized in that, is in series with safeties respectively at the input of each power supply changeover device; All be connected at each safeties other end with the anodal line of aircraft power system power supply; The output of first power supply changeover device and second source transducer 4 is in series with a diode respectively; Be connected with outlet line after the output parallel connection of two diodes, to the DC power supply of the inner output needs of control box; Described power supply changeover device is two or three, has formed two remaining electric supply systems or three remaining electric supply systems.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120337447 CN202218058U (en) | 2011-09-08 | 2011-09-08 | Redundancy power source power supply system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120337447 CN202218058U (en) | 2011-09-08 | 2011-09-08 | Redundancy power source power supply system |
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| Publication Number | Publication Date |
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| CN202218058U true CN202218058U (en) | 2012-05-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201120337447 Expired - Lifetime CN202218058U (en) | 2011-09-08 | 2011-09-08 | Redundancy power source power supply system |
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| CN (1) | CN202218058U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102700542A (en) * | 2012-05-31 | 2012-10-03 | 西北工业大学 | Dual-redundancy electric brake device of airplane and control method for dual-redundancy electric brake device |
| CN102700706A (en) * | 2012-05-31 | 2012-10-03 | 西北工业大学 | Dual-redundancy actuator system and control method |
| CN102700530A (en) * | 2012-05-31 | 2012-10-03 | 西北工业大学 | Redundant driving electric brake of airplane and control method for redundant driving electric brake |
| CN103332296A (en) * | 2013-07-17 | 2013-10-02 | 国家电网公司 | Power supply for unmanned aerial vehicle |
-
2011
- 2011-09-08 CN CN 201120337447 patent/CN202218058U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102700542A (en) * | 2012-05-31 | 2012-10-03 | 西北工业大学 | Dual-redundancy electric brake device of airplane and control method for dual-redundancy electric brake device |
| CN102700706A (en) * | 2012-05-31 | 2012-10-03 | 西北工业大学 | Dual-redundancy actuator system and control method |
| CN102700530A (en) * | 2012-05-31 | 2012-10-03 | 西北工业大学 | Redundant driving electric brake of airplane and control method for redundant driving electric brake |
| CN102700542B (en) * | 2012-05-31 | 2014-06-11 | 西北工业大学 | Dual-redundancy electric brake device of airplane and control method for dual-redundancy electric brake device |
| CN102700530B (en) * | 2012-05-31 | 2014-11-05 | 西北工业大学 | Redundant driving electric brake of airplane and control method for redundant driving electric brake |
| CN103332296A (en) * | 2013-07-17 | 2013-10-02 | 国家电网公司 | Power supply for unmanned aerial vehicle |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20120509 |
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| CX01 | Expiry of patent term |