CN113839378A - Electric starting control method for aviation auxiliary power device - Google Patents
Electric starting control method for aviation auxiliary power device Download PDFInfo
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- CN113839378A CN113839378A CN202111160747.XA CN202111160747A CN113839378A CN 113839378 A CN113839378 A CN 113839378A CN 202111160747 A CN202111160747 A CN 202111160747A CN 113839378 A CN113839378 A CN 113839378A
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- 238000000034 method Methods 0.000 title claims abstract description 18
- 238000004353 relayed correlation spectroscopy Methods 0.000 claims description 13
- 101150039658 Prrc2a gene Proteins 0.000 claims description 7
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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
- H02J1/00—Circuit arrangements for dc mains or dc distribution networks
- H02J1/10—Parallel operation of dc sources
- H02J1/109—Scheduling or re-scheduling the operation of the DC sources in a particular order, e.g. connecting or disconnecting the sources in sequential, alternating or in subsets, to meet a given demand
Abstract
The application belongs to the technical field of aviation power distribution, and particularly relates to an electric starting control method for an aviation auxiliary power device. The method comprises the following steps: when the starting instruction of the auxiliary power device is received to be effective, if the direct-current ground power supply DCGPU is electrified, the first switch contactor DCEPC, the second switch contactor ASC and the third switch contactor Bat2C are closed, the auxiliary power device is started by the direct-current power supply, and the storage battery is used for supplying power to the bus bar on the device; if the direct-current ground power supply DCGPU is not electrified, the second switch contactor ASC and the fourth switch contactor BSC are closed, other contactors are disconnected, the auxiliary power device is started by the storage battery, and the storage battery does not supply power to the bus bar on the machine. The direct-current starting control of the auxiliary power device is realized by depending on a hardware circuit, the direct-current starting control can be realized by only acquiring the state of the auxiliary contact of the existing contactor and adding a small amount of relays, and the method is simple, low in cost and high in reliability.
Description
Technical Field
The application belongs to the technical field of aviation power distribution, and particularly relates to an electric starting control method for an aviation auxiliary power device.
Background
The civil aviation market in China is a market with lower international development degree and higher growth speed at present, and along with the development of the overall technology of airplanes, particularly the development of large passenger planes towards the trend of being safer, more economical, more comfortable, more environment-friendly and more efficient, various electric equipment is greatly increased, so that the control scale of the power distribution technology is larger and larger, and the complexity is higher and higher. In this situation, the electric starting potential of the auxiliary power unit is imperative. At present, the control of the electric starting of the auxiliary power device is mainly realized by controlling the action of a corresponding contactor by software through a controller.
Aircraft engine starting modes generally include several: (1) starting by only the auxiliary power device; (2) the battery and the DC bus bar are jointly electrically started; (3) the generator of the auxiliary power device is electrically started, except for the bleed-off starting of the auxiliary power device, most airplanes use a controller to control the action of the contactor to realize the electric starting in order to control the action of the corresponding contactor in the distribution box, the misoperation of the contactor is easily caused by software faults, and the reliability is low.
Disclosure of Invention
In order to solve the technical problem, the application provides an electric starting control method for an aviation auxiliary power device, which mainly comprises the following steps:
a first switch contactor DCEPC and a second switch contactor ASC are arranged between a direct current ground power supply DCGPU and an auxiliary power device, the first switch contactor DCEPC is close to the direct current ground power supply DCGPU, the second switch contactor ASC is close to the auxiliary power device, and a node STARTBUS is arranged between the first switch contactor DCEPC and the second switch contactor ASC;
a third switch contactor Bat2C is arranged between the storage battery Bat2 and the onboard bus bar, and the third switch contactor Bat2C and the storage battery Bat2 are connected to a node STARTBUS through a fourth switch contactor BSC;
the electric start control method includes:
when the starting instruction of the auxiliary power device is received to be effective, if the direct-current ground power supply DCGPU is electrified, the first switch contactor DCEPC, the second switch contactor ASC and the third switch contactor Bat2C are closed, the auxiliary power device is started by the direct-current power supply, and the storage battery is used for supplying power to the bus bar on the device;
if the direct-current ground power supply DCGPU is not electrified, the second switch contactor ASC and the fourth switch contactor BSC are closed, other contactors are disconnected, the auxiliary power device is started by the storage battery, and the storage battery does not supply power to the bus bar on the device;
the first switch contactor DCEPC is driven by the controller, and the second switch contactor ASC, the third switch contactor Bat2C and the fourth switch contactor BSC are controlled by hardware.
Preferably, the driving of the first switch contact DCEPC by the controller includes:
the quality of the direct-current ground power supply meets the requirement that the command signal is effective, and after the switch DCGPU SW on the top hole plate is closed, the first switch contactor DCEPC is driven to be closed through control.
Preferably, the second switching contactor ASC is arranged to:
the positive pole of the ASC coil is divided into two paths through a node, the first path is connected with the storage battery BATT2, the second path is connected with the direct-current ground power supply DCGPU, the negative pole of the ASC coil is grounded, when the auxiliary power device is started by the ground power supply, the positive pole of the ASC coil is powered by the direct-current ground power supply DCGPU, when the auxiliary power device is started by the storage battery BATT2, the positive pole of the ASC coil is powered by the storage battery BATT 2.
Preferably, the third switch contact Bat2C is configured to:
the negative electrode of the coil of the third switch contactor Bat2C is grounded, and the positive electrode of the coil of the third switch contactor Bat2C is powered by the storage battery BATT2 after passing through the normally closed contact of the fourth switch contactor BSC and the main contact of the RELAY RELAY 11; the closing conditions of the third switch contact Bat2C are: the fourth switch contactor BSC is open and the battery BATT2 on the top control board controls the switch to close.
Preferably, the fourth switch contact BSC is arranged to:
the positive pole of the fourth switch contactor BSC is powered by a storage battery BATT2 through a RELAY RELAY10 main contact, the positive end of a starting instruction of the auxiliary power device controls the positive pole of a coil of the RELAY, and the negative end of the starting instruction of the auxiliary power device controls the negative pole of the coil of the RELAY; the closing condition of the fourth switch contactor BSC is as follows: if battery BATT2 is energized and first switch contact DCEPC is open.
The direct-current starting control of the auxiliary power device is realized by depending on a hardware circuit, the direct-current starting control can be realized by only acquiring the state of the auxiliary contact of the existing contactor and adding a small amount of relays, and the method is simple, low in cost and high in reliability.
Drawings
FIG. 1 is a block diagram of an arrangement on a starter of an auxiliary power unit according to the present application.
Fig. 2 is an ASC control schematic diagram of the present application.
Fig. 3 is a BSC control scheme of the present application.
Fig. 4 is a control schematic diagram of BAT2C according to the present application.
Fig. 5 is a schematic diagram of the DCEPC control of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The application provides an electric starting control method for an aviation auxiliary power device, which mainly comprises the following steps:
a first switch contactor DCEPC and a second switch contactor ASC are arranged between a direct current ground power supply DCGPU and an auxiliary power device, the first switch contactor DCEPC is close to the direct current ground power supply DCGPU, the second switch contactor ASC is close to the auxiliary power device, and a node STARTBUS is arranged between the first switch contactor DCEPC and the second switch contactor ASC;
a third switch contactor Bat2C is arranged between the storage battery Bat2 and the onboard bus bar, and the third switch contactor Bat2C and the storage battery Bat2 are connected to a node STARTBUS through a fourth switch contactor BSC;
the electric start control method includes:
when the starting instruction of the auxiliary power device is received to be effective, if the direct-current ground power supply DCGPU is electrified, the first switch contactor DCEPC, the second switch contactor ASC and the third switch contactor Bat2C are closed, the auxiliary power device is started by the direct-current power supply, and the storage battery is used for supplying power to the bus bar on the device;
if the direct-current ground power supply DCGPU is not electrified, the second switch contactor ASC and the fourth switch contactor BSC are closed, other contactors are disconnected, the auxiliary power device is started by the storage battery, and the storage battery does not supply power to the bus bar on the device;
the first switch contactor DCEPC is driven by the controller, and the second switch contactor ASC, the third switch contactor Bat2C and the fourth switch contactor BSC are controlled by hardware.
In some optional embodiments, the driving of the first switch contact DCEPC by the controller includes:
the quality of the direct-current ground power supply meets the requirement that the command signal is effective, and after the switch DCGPU SW on the top hole plate is closed, the first switch contactor DCEPC is driven to be closed through control.
In this embodiment, when the switch DC GPU SW on the top panel is closed, if the controller determines that the power quality of the DC external power DC GPU meets the requirement, a 28V/OPEN signal is output to drive the coil of the RELAY13 to be closed, the coil of the contactor DC EPC is powered by the DC GPU through the main contact of the RELAY13, and the hardware control principle is as shown in fig. 5.
In some alternative embodiments, the second switching contactor ASC is arranged to:
as shown in fig. 2, the positive pole of the ASC coil is divided into two paths by a node, the first path is connected with the battery BATT2, the second path is connected with the dc ground power supply DCGPU, the negative pole of the ASC coil is grounded, when the auxiliary power device is started by the ground power supply, the positive pole of the ASC coil is powered by the dc ground power supply DCGPU, and when the auxiliary power device is started by the battery BATT2, the positive pole of the ASC coil is powered by the battery BATT 2.
In the present embodiment, the closing conditions of the contactor ASC for controlling the starting of the starting bus bar starting auxiliary power unit are: the auxiliary power unit START command apustart CMD is received and DCEPC or BSC is closed.
In some alternative embodiments, the third switch contact Bat2C is configured to:
as shown in fig. 4, the negative electrode of the coil of the third switch contactor Bat2C is grounded, and the positive electrode of the coil of the third switch contactor Bat2C is powered by the battery Bat2 after passing through the normally closed contact of the fourth switch contactor BSC and the main contact of the RELAY 11; the closing conditions of the third switch contact Bat2C are: the fourth switch contactor BSC is open and the battery BATT2 on the top control board controls the switch to close.
In some alternative embodiments, the fourth switch contact BSC is arranged to:
as shown in fig. 3, the positive pole of the fourth switch contactor BSC is powered by the battery BATT2 through the main contact of the RELAY10, the positive end of the start instruction of the auxiliary power device controls the positive pole of the coil of the RELAY, and the negative end of the start instruction of the auxiliary power device controls the negative pole of the coil of the RELAY; the closing condition of the fourth switch contactor BSC is as follows: if battery BATT2 is energized and first switch contact DCEPC is open.
The direct-current starting control of the auxiliary power device is realized by depending on a hardware circuit, the direct-current starting control can be realized by only acquiring the state of the auxiliary contact of the existing contactor and adding a small amount of relays, and the method is simple, low in cost and high in reliability.
The above description is only for the specific embodiments of the present application, but the scope of the present application 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 application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. An electric start control method for an aviation auxiliary power device is characterized by comprising the following steps:
a first switch contactor DCEPC and a second switch contactor ASC are arranged between a direct current ground power supply DCGPU and an auxiliary power device, the first switch contactor DCEPC is close to the direct current ground power supply DCGPU, the second switch contactor ASC is close to the auxiliary power device, and a node STARTBUS is arranged between the first switch contactor DCEPC and the second switch contactor ASC;
a third switch contactor Bat2C is arranged between the storage battery Bat2 and the onboard bus bar, and the third switch contactor Bat2C and the storage battery Bat2 are connected to a node STARTBUS through a fourth switch contactor BSC;
the electric start control method includes:
when the starting instruction of the auxiliary power device is received to be effective, if the direct-current ground power supply DCGPU is electrified, the first switch contactor DCEPC, the second switch contactor ASC and the third switch contactor Bat2C are closed, the auxiliary power device is started by the direct-current power supply, and the storage battery is used for supplying power to the bus bar on the device;
if the direct-current ground power supply DCGPU is not electrified, the second switch contactor ASC and the fourth switch contactor BSC are closed, other contactors are disconnected, the auxiliary power device is started by the storage battery, and the storage battery does not supply power to the bus bar on the device;
the first switch contactor DCEPC is driven by the controller, and the second switch contactor ASC, the third switch contactor Bat2C and the fourth switch contactor BSC are controlled by hardware.
2. The aero-auxiliary power unit electric start control method as claimed in claim 1, wherein the first switch contact DCEPC being driven by the controller comprises:
the quality of the direct-current ground power supply meets the requirement that the command signal is effective, and after the switch DCGPU SW on the top hole plate is closed, the first switch contactor DCEPC is driven to be closed through control.
3. The aero-auxiliary power unit electric start control method as claimed in claim 1, wherein the second switch contactor ASC is configured to:
the positive pole of the ASC coil is divided into two paths through a node, the first path is connected with the storage battery BATT2, the second path is connected with the direct-current ground power supply DCGPU, the negative pole of the ASC coil is grounded, when the auxiliary power device is started by the ground power supply, the positive pole of the ASC coil is powered by the direct-current ground power supply DCGPU, when the auxiliary power device is started by the storage battery BATT2, the positive pole of the ASC coil is powered by the storage battery BATT 2.
4. The aviation auxiliary power unit electric start control method as defined in claim 1, wherein the third switch contactor Bat2C is configured to:
the negative electrode of the coil of the third switch contactor Bat2C is grounded, and the positive electrode of the coil of the third switch contactor Bat2C is powered by the storage battery BATT2 after passing through the normally closed contact of the fourth switch contactor BSC and the main contact of the RELAY RELAY 11; the closing conditions of the third switch contact Bat2C are: the fourth switch contactor BSC is open and the battery BATT2 on the top control board controls the switch to close.
5. An aero-auxiliary power unit electric start control method as claimed in claim 1 wherein a fourth switch contactor BSC is arranged to:
the positive pole of the fourth switch contactor BSC is powered by a storage battery BATT2 through a RELAY RELAY10 main contact, the positive end of a starting instruction of the auxiliary power device controls the positive pole of a coil of the RELAY, and the negative end of the starting instruction of the auxiliary power device controls the negative pole of the coil of the RELAY; the closing condition of the fourth switch contactor BSC is as follows: if battery BATT2 is energized and first switch contact DCEPC is open.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111160747.XA CN113839378A (en) | 2021-09-30 | 2021-09-30 | Electric starting control method for aviation auxiliary power device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111160747.XA CN113839378A (en) | 2021-09-30 | 2021-09-30 | Electric starting control method for aviation auxiliary power device |
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| CN113839378A true CN113839378A (en) | 2021-12-24 |
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| CN202111160747.XA Pending CN113839378A (en) | 2021-09-30 | 2021-09-30 | Electric starting control method for aviation auxiliary power device |
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Citations (5)
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|---|---|---|---|---|
| US20130334875A1 (en) * | 2012-06-19 | 2013-12-19 | Phuoc D. Nguyen | Dc power architecture for remote apu start |
| CN105429127A (en) * | 2015-11-17 | 2016-03-23 | 陕西航空电气有限责任公司 | Electric starting type power distribution system |
| CN109538358A (en) * | 2018-11-21 | 2019-03-29 | 中国商用飞机有限责任公司 | Starting circuit and control method for aviation APU |
| CN111244916A (en) * | 2020-03-08 | 2020-06-05 | 陕西航空电气有限责任公司 | Hardware interlocking method for key alternating current contactor in aviation power distribution system |
| CN112228221A (en) * | 2020-09-11 | 2021-01-15 | 中国航空工业集团公司成都飞机设计研究所 | Auxiliary power generation system driven by stamping turbine and use method |
-
2021
- 2021-09-30 CN CN202111160747.XA patent/CN113839378A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130334875A1 (en) * | 2012-06-19 | 2013-12-19 | Phuoc D. Nguyen | Dc power architecture for remote apu start |
| CN105429127A (en) * | 2015-11-17 | 2016-03-23 | 陕西航空电气有限责任公司 | Electric starting type power distribution system |
| CN109538358A (en) * | 2018-11-21 | 2019-03-29 | 中国商用飞机有限责任公司 | Starting circuit and control method for aviation APU |
| CN111244916A (en) * | 2020-03-08 | 2020-06-05 | 陕西航空电气有限责任公司 | Hardware interlocking method for key alternating current contactor in aviation power distribution system |
| CN112228221A (en) * | 2020-09-11 | 2021-01-15 | 中国航空工业集团公司成都飞机设计研究所 | Auxiliary power generation system driven by stamping turbine and use method |
Non-Patent Citations (1)
| Title |
|---|
| 杨娟、任仁良、韩勇: "飞机辅助动力装置电起动系统模型设计及仿真", 计算机仿真, vol. 35, no. 1, 31 January 2018 (2018-01-31), pages 61 - 65 * |
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