GB2290424A - Power supply systems for aircraft - Google Patents
Power supply systems for aircraft Download PDFInfo
- Publication number
- GB2290424A GB2290424A GB9508665A GB9508665A GB2290424A GB 2290424 A GB2290424 A GB 2290424A GB 9508665 A GB9508665 A GB 9508665A GB 9508665 A GB9508665 A GB 9508665A GB 2290424 A GB2290424 A GB 2290424A
- Authority
- GB
- United Kingdom
- Prior art keywords
- power
- load
- power supply
- loads
- capacity
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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
-
- 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
- H02J3/00—Circuit arrangements for ac mains or ac distribution networks
- H02J3/12—Circuit arrangements for ac mains or ac distribution networks for adjusting voltage in ac networks by changing a characteristic of the network load
- H02J3/14—Circuit arrangements for ac mains or ac distribution networks for adjusting voltage in ac networks by changing a characteristic of the network load by switching loads on to, or off from, network, e.g. progressively balanced loading
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D2221/00—Electric power distribution systems onboard aircraft
-
- 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
- H02J2310/00—The network for supplying or distributing electric power characterised by its spatial reach or by the load
- H02J2310/40—The network being an on-board power network, i.e. within a vehicle
- H02J2310/44—The network being an on-board power network, i.e. within a vehicle for aircrafts
Abstract
The power supply system for controlling supply of power to several inductive loads 101 to 106, 201 to 206 has a power monitor 31, 32 and a processor 3 that determines when power consumed exceeds the capacity supplied by a.c. generators 10, 20. When overload is detected, rapidly disconnects loads of low priority. A software register in the processor is loaded with software controlling staggered reconnection of the loads when power capacity becomes sufficient again. If capacity is sufficient, all the loads may be reconnected together. The system may be used in an aircraft. <IMAGE>
Description
POWER SUPPLY SYSTEMS
This invention relates to power supply systems.
The invention is more particularly, but not exclusively, concerned with power supply systems for aircraft.
In an aircraft a.c. power supply system there is only a limited amount of power available from the aircraft generators. Inductive loads such as fans and pumps tend to draw high currents when first switched on, before settling to a lower steady value. When several of these loads are turned on at the same time, large and damaging currents can be drawn unless measures are taken to avoid this. One way of reducing the risk of damage is to increase the generator capacity but this leads to a consequent increase in the size, weight and expense of the generators. Alternatively, the system can be arranged to stagger the starting of large loads, and in particular, large inductive loads, such as hydraulic pumps.
Conventional systems have fixed time delay relays associated with the highly inductive loads. Each time delay is made different, with the highest priority loads having the shortest delays. In this way, if all the loads are commanded on simultaneously, the most important loads will be started first and the less important loads will be started after longer intervals. The problem with this arrangement, however, is that, if a low priority load is commanded on by itself, there will be a relatively long and unnecessary delay before power is supplied to the load.
Also, the arrangement does not entirely remove the risk that power could be supplied to several large inductive loads at the same time. For example, three hydraulic pumps A, B and C could be given different delays so that if switches controlling the operation of the three pumps were switched on at the same time, power would be supplied first to pump A, then to pump B and finally to pump C. However, if the switches controlling the pumps were turned on separately, one after the other, in the order C, B, A, this would reduce the time delay between power being supplied to the pumps and could lead to overloading of the generators.
Also, when the power source is only lightly loaded, it may not be necessary to stagger the switching of loads. If the system has lost one power source it will usually be necessary to stagger the application of loads onto the remaining power source, whereas, when both sources are operating, this may not be necessary. Current systems, however, are not sufficiently adaptable and cause staggering of the loads even when this may not be necessary.
It is an object of the present invention to provide an improved power supply system.
According to one aspect of the present invention there is provided a power supply system including a power supply, a plurality of loads, a plurality of switches connecting each respective one ofthe loads to the power supply, and processor means for controlling the operation of the switches, the processor means being arranged to delay closing of said switches when power is to be supplied to several of said loads such that there is a time delay between different ones ofthe loads being supplied with power, and the time delay for each load being variable such that the delay differs according to which combination of loads is to be supplied with power.
The system preferably includes a power monitor arranged to monitor the power consumed by the loads, means for detecting when the power consumed exceeds the capacity of the power supply, and hardware means for disconnecting a load when power consumed exceeds power supply capacity. The system may include means for supplying the contents of a software store to control reconnection of a load when power consumed becomes less than power supply capacity. The system may also include means for loading the software store with either software enabling supply of power to all the loads together or software for staggering reconnection of the loads. The software is preferably arranged to reconnect load without delay when there is sufficient power supply capacity.The system may include a software command register containing software information for control of reconnection of load, an output drive unit and a multiplexer having two inputs, one input ofthe multiplexer being connected to an output of the software command register, another input being connected to an off signal input, and the multiplexer being switched to supply the off signal to the output drive unit so as to turn off a load when the power consumption exceeds the capacity of the power supply and to switch the software information to the output drive unit when load is to be reapplied.
According to another aspect of the present invention there is provided a method of controlling connection and disconnection of a plurality of loads in a power supply system according to changes in the relationship between power consumption and the capacity of a power supply in the system, the method including the steps of monitoring the power consumption of the system, detecting when the consumption exceeds capacity, disconnecting load if consumption exceeds capacity, reconnecting load when capacity exceeds consumption and introducing a variable delay after connection of an inductive load before another load is connected.
The delay may be varied according to the inductive properties of the loads.
Consumption exceeding capacity is preferably detected by hardware so that load can be disconnected rapidly, the delay of connecting a load after connection of an inductive load being controlled by software. Preferably, commanding a load to be powered only causes powering of the load after a delay sufficient to enable disconnection of another, lower priority, load when there is insufficient power available in the system.
An aircraft power supply system according to the present invention, will now be described, by way of example, with reference to the accompanying drawings, in which:
Figure 1 shows the system schematically; and
Figure 2 shows a part of the system diagrammatically.
The power supply system has two a.c. power generators 10 and 20 connected to respective power buses 11 and 21. The buses 11 and 21 are electrically isolated from one another but can be interconnected via a tie 1 and a switch 2.
The system also includes various loads in the form of items of electrical equipment, of which only twelve are shown, six items 101 to 106 being connected to the left-hand bus 11 and the remaining six items 201 to 206 being connected to the right-hand bus 21. Each item of equipment is connected to its respective bus 11 or 21 via a respective relay or other remotelycontrolled switch 111 to 116 and 211 to 216. Each relay is connected to a processing unit 3, which provides appropriate control to maintain the relays open (of) ) or closed (on) as desired.
The processing unit 3 is also connected via line 30 to the tie switch 2 to control operation of this switch. The processing unit 3 receives various inputs, such as from power monitors 31 and 32 connected to the two respective buses 11 and 21, and from manually-operable switches 33 and 34.
With reference now also to Figure 2, the processing unit 3 includes a 4:1 multiplexer 35, which receives an output from the power monitors 31 or 32 and three inputs from BITE 36 (built-in test equipment). The power monitors 31 and 32 each take the form of a monitor that derives a voltage proportionally from the power supply bus feeding the loads. The multiplexer 35 also receives mode select inputs on lines 37 from software indicated by the numeral 38. The inputs on lines 37 instruct the multiplexer 35 to pass one ofthe inputs from the power monitors or BITE to a comparator 39. The comparator 39 also receives an input from a voltage reference source 40 and provides an output on line 41 indicative of whether or not power is available. The output on line 41 is supplied via a status register 42 to the software 38 and to the control input of a 2:1 multiplexer 43. The multiplexer 43 receives two inputs, one being an
OFF signal on line 44 and the other being the output of a software command register 45 that contains instructions supplied to it from the software 38.
The output of the multiplexer 43 is supplied via line 46 to an output drive unit 47 by which the relays 111 to 116 and 211 to 216 are controlled.
In normal operation, all the relays 111 to 116 and 211 to 216 are on so that any of the items of electrical equipment can be in operation if selected. In practice, the power supply of the aircraft need not be sufficient to power all the items of equipment because not all the items of equipment are in operation at any one time. In these circumstances, the power monitors 31 and 32 sense that the power drawn by the loads in operation is below the maximum capacity, and the comparator 39 provides an output on line 41 indicating that power is available for additional loads if required. This causes the multiplexer 42 to supply the output of the software command register 45 to the output drive 47, which enables all the relays.
During normal operation, all highly inductive loads, such as hydraulic pumps, are stagger started with a software-configurable delay between each start. An initial delay is applied prior to powering the first load, in order to give time for other, lower priority, loads to be shed, if necessary, to prevent the generators being overloaded. The processing unit 3 continually assesses the power available in the system and, as soon as the user commands another load to be connected, such as by actuating one of the switches 33 or 34, the processing unit determines whether or not sufficient power is available. If insufficient power is available, the delay enables the system to shed lower priority loads before power is supplied to the new load. If there is sufficient power available for the new load, the delay before it is powered is zero.The second load is powered with a delay after powering of the first load. The processing system computes this delay with knowledge of the inductive properties of the individual loads so that the delay is minimal but allows sufficient time for the current surge on starting to decay.
The time delay for each load is variable according to which combination of loads is to be supplied with power. For example, three identical inductive loads A, B and C might be commanded on at the same time but the sequence might typically be: A-lms after command, B2ms after command, and C-3ms after command. However, if the loads were commanded on by pressing switches associated with the loads in the sequence C, B, A, the delays might be: C-lms after its command, B-lms after its command, and A-lms after its command. In this way, the delays are kept to a minimum without there being a risk of excessive power consumption.
If a power interrupt should occur, such as caused by the failure of one of the generators 10 or 20, the output ofthe comparator 39 changes to indicate that power is no longer available.
The change in the output on line 41, therefore, causes the multiplexer 43 to supply the OFF signal to the output drive unit 47. This turns off those relays 111 to 116 and 211 to 216 associated with items of equipment that have a low priority, that is, those items of equipment that can be shut down without impairing the ability ofthe aircraft to fly safely. When the interrupt occurs, the hardware removes the power from the load with zero delay, thereby avoiding the delays inevitable with software control. If the power interrupt is only short, this is detected by the hardware in the processing unit 3 and indicated to the software 38 by a short duration pulsed input. This pulse is latched at the hardware-software interface until it is read and cleared by the software.The status register 42 is also changed to indicate to the software 38 that a power interrupt has occurred. The software 38 responds to this by reloading the software command register 45 with a stagger start program for when power is subsequently available. There is no need for a delay after turning on power to a non-inductive load because it draws a steady current rather than an initially high current If the failed generator should later come back into operation, the comparator 39 signals that power is available and switches the multiplexer 43 to supply the contents of the software command register 45 to the output drive unit 47. The items of equipment that were previously powered are then stagger started.
The system ofthe present invention enables the starting of loads with a minimum delay whilst also ensuring that there is no risk of several inductive loads being started without a sufficient delay between them.
Where there is sufficient power available for the required loads to be connected without the need to stagger their connection, the system is able to recognise this and connect all the required loads at the same time, thereby minimizing the time for which loads are disconnected.
Claims (14)
1. A power supply system including a power supply, a plurality of loads, a plurality of
switches connecting each respective one ofthe loads to the power supply, and
processor means for controlling the operation ofthe switches, wherein the processor
means is arranged to delay closing of said switches when power is to be supplied to
several of said loads such that there is a time delay between different ones of the loads
being supplied with power, and wherein the time delay for each load is variable such
that the delay differs according to which combination of loads is to be supplied with
power.
2. A power supply system according to Claim 1, including a power monitor arranged to
monitor the power consumed by the loads, means for detecting when the power
consumed exceeds the capacity of the power supply, and hardware means for
disconnecting a load when power consumed exceeds power supply capacity.
3. A power supply system according to Claim 1 or 2, including means for supplying the
contents of a software store to control reconnection of a load when power consumed
becomes less than power supply capacity.
4. A power supply system according to Claim 3, including means for loading the software
store with either software enabling supply of power to all the loads together or
software for staggering reconnection of the loads.
5. A power supply system according to Claim 3 or 4, wherein the software is arranged to
reconnect load without delay when there is sufficient power supply capacity.
6. A power supply system according to any of Claims 3 to 5, including a software
command register containing software information for control of reconnection of load,
an output drive unit and a multiplexer having two inputs, wherein one input of the
multiplexer is connected to an output of the software command register, wherein
another input is connected to an off signal input, and wherein the multiplexer is
switched to supply the off signal to the output drive unit so as to turn off a load when
the power consumption exceeds the capacity of the power supply and to switch the
software information to the output drive unit when load is to be reapplied.
7. A power supply system substantially as hereinbefore described with reference to the
accompanying drawings.
8. A method of controlling connection and disconnection of a plurality of loads in a
power supply system according to changes in the relationship between power
consumption and the capacity of a power supply in the system, wherein the method
includes the steps of monitoring the power consumption of the system, detecting when
the consumption exceeds capacity, disconnecting load if consumption exceeds
capacity, reconnecting load when capacity exceeds consumption and introducing a
variable delay after connection of an inductive load before another load is connected.
9. A method according to Claim 8, wherein the delay is varied according to the inductive
properties of the loads.
10. A method according to Claim 8 or 9, wherein consumption exceeding capacity is
detected by hardware so that load can be disconnected rapidly, and wherein the delay
of connecting a load after connection of an inductive load is controlled by software.
11. A method according to any one of Claims 8 to 10, wherein commanding a load to be
powered only causes powering ofthe load after a delay sufficient to enable
disconnection of another, lower priority, load when there is insufficient power available
in the system.
12. A method substantially as hereinbefore described with reference to the accompanying
drawings.
13. A system for use in the method of any one of Claims 8 to 12.
14. Any novel feature or combination of features as hereinbefore described.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB9508665A GB2290424B (en) | 1994-06-18 | 1995-04-28 | Power supply systems |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB9412287A GB9412287D0 (en) | 1994-06-18 | 1994-06-18 | Power supply systems |
GB9508665A GB2290424B (en) | 1994-06-18 | 1995-04-28 | Power supply systems |
Publications (3)
Publication Number | Publication Date |
---|---|
GB9508665D0 GB9508665D0 (en) | 1995-06-14 |
GB2290424A true GB2290424A (en) | 1995-12-20 |
GB2290424B GB2290424B (en) | 1998-06-17 |
Family
ID=26305086
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB9508665A Expired - Lifetime GB2290424B (en) | 1994-06-18 | 1995-04-28 | Power supply systems |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB2290424B (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0884821A1 (en) * | 1996-05-03 | 1998-12-16 | DaimlerChrysler Aerospace Airbus Gesellschaft mit beschränkter Haftung | Arrangement for power distribution, in particular for an aircraft |
GB2449966A (en) * | 2007-06-05 | 2008-12-10 | Boeing Co | Aircraft power management having prioritized subsystems |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1545006A (en) * | 1976-08-26 | 1979-04-25 | Arn Fritz | Monitoring apparatuses for maintaining mean maximum power consumption in electrical plants |
US4216384A (en) * | 1977-12-09 | 1980-08-05 | Directed Energy Systems, Inc. | System for monitoring and controlling electric power consumption |
-
1995
- 1995-04-28 GB GB9508665A patent/GB2290424B/en not_active Expired - Lifetime
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1545006A (en) * | 1976-08-26 | 1979-04-25 | Arn Fritz | Monitoring apparatuses for maintaining mean maximum power consumption in electrical plants |
US4216384A (en) * | 1977-12-09 | 1980-08-05 | Directed Energy Systems, Inc. | System for monitoring and controlling electric power consumption |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0884821A1 (en) * | 1996-05-03 | 1998-12-16 | DaimlerChrysler Aerospace Airbus Gesellschaft mit beschränkter Haftung | Arrangement for power distribution, in particular for an aircraft |
GB2449966A (en) * | 2007-06-05 | 2008-12-10 | Boeing Co | Aircraft power management having prioritized subsystems |
GB2449966B (en) * | 2007-06-05 | 2009-09-09 | Boeing Co | Battery network system with life-optimal power management and operating methods thereof |
US8010250B2 (en) | 2007-06-05 | 2011-08-30 | The Boeing Company | Life-optimal power management methods for battery networks system |
US8406936B1 (en) | 2007-06-05 | 2013-03-26 | The Boeing Company | Modular battery network system with life-optimal power management |
Also Published As
Publication number | Publication date |
---|---|
GB2290424B (en) | 1998-06-17 |
GB9508665D0 (en) | 1995-06-14 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US5583419A (en) | Power supply systems | |
US7456520B2 (en) | Control system, method and product for uninterruptible power supply | |
US6153947A (en) | Dual feed hot swap battery plant controller for power supplies | |
JP3114673B2 (en) | Uninterruptible power supply with redundant function | |
US3778634A (en) | Power supply with battery backup | |
US5604421A (en) | Electrical systems | |
US4520275A (en) | Master and slave power supply control circuits | |
US6031298A (en) | 2N redundant power system and method using cross-coupled AC power transfer | |
EP3691068B1 (en) | Control system | |
US5606245A (en) | Power supply systems | |
US5635772A (en) | Method and apparatus for transferring between electrical power sources which adaptively blocks transfer until load voltage decays to safe value | |
EP3282584B1 (en) | Power distribution system and method | |
CN113022313B (en) | VCU power-off protection circuit, power-off control method, system and engineering machinery | |
CN111038264B (en) | Delayed power-off control system and control method for vehicle | |
GB2290424A (en) | Power supply systems for aircraft | |
CN116436149A (en) | Uninterruptible power supply, system including a plurality of uninterruptible power supplies, and control method | |
US6483682B1 (en) | Electric power distribution system employing a fight-through switch | |
US5272387A (en) | Connecting device of an external electrical power supply source to an aircraft on the ground | |
JP7002803B1 (en) | Power factor improvement method and power factor improvement system | |
JP2500592B2 (en) | Uninterruptible power system | |
WO2001039346A1 (en) | Integrated fault protection for switched electronic systems for satellite applications | |
CN216086256U (en) | Automatic power switching system | |
JP2002186259A (en) | Hot line inserting/extracting circuit and single weight drive system | |
EP3879659A1 (en) | Ac essential bus delta current and overcurrent protection scheme | |
RU2080727C1 (en) | Method for raising power system stability and life expectancy |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
732E | Amendments to the register in respect of changes of name or changes affecting rights (sect. 32/1977) | ||
PE20 | Patent expired after termination of 20 years |
Expiry date: 20150427 |