WO1998034318A1 - Systeme et procede de radiocommande pour relais de distribution electrique d'aeronefs - Google Patents

Systeme et procede de radiocommande pour relais de distribution electrique d'aeronefs Download PDF

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Publication number
WO1998034318A1
WO1998034318A1 PCT/US1998/001839 US9801839W WO9834318A1 WO 1998034318 A1 WO1998034318 A1 WO 1998034318A1 US 9801839 W US9801839 W US 9801839W WO 9834318 A1 WO9834318 A1 WO 9834318A1
Authority
WO
WIPO (PCT)
Prior art keywords
electric power
switching means
information
control
distribution
Prior art date
Application number
PCT/US1998/001839
Other languages
English (en)
Other versions
WO1998034318B1 (fr
Inventor
Roy S. Baker
Original Assignee
Sundstrand Corporation
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Sundstrand Corporation filed Critical Sundstrand Corporation
Priority to CA002281711A priority Critical patent/CA2281711A1/fr
Publication of WO1998034318A1 publication Critical patent/WO1998034318A1/fr
Publication of WO1998034318B1 publication Critical patent/WO1998034318B1/fr

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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
    • H02J4/00—Circuit arrangements for mains or distribution networks not specified as ac or dc
    • 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
    • H02J13/00—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
    • H02J13/00006—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network characterised by information or instructions transport means between the monitoring, controlling or managing units and monitored, controlled or operated power network element or electrical equipment
    • H02J13/00022—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network characterised by information or instructions transport means between the monitoring, controlling or managing units and monitored, controlled or operated power network element or electrical equipment using wireless data transmission
    • 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

Definitions

  • the instant invention relates generally to aircraft electric power distribution systems
  • a typical aircraft electric power generation and distribution system for use on large commercial aircraft has from two to four main generators, depending on the number of engines and system electrical load requirements. Each of these generators are coupled to various load
  • individual generators may also be coupled together through bus tie breakers (BTBs) on a tie bus to allow parallel operation.
  • BTBs bus tie breakers
  • at least one auxiliary source of power is typically provided on the aircraft to supply power in case of main generator failure, or on the ground with main engines shut down.
  • This auxiliary source of power is coupled either directly to each of the individual generator busses through individual auxiliary power breakers (APBs), or to the tie bus through a single auxiliary power breaker (APB).
  • APBs auxiliary power breakers
  • APIB auxiliary power breaker
  • tie bus is separated into two halves by a cross tie breaker (XTB).
  • XTB cross tie breaker
  • ground power may be coupled separately to each half of the tie bus by two APBs. While on the ground at the terminal, ground power may be provided to the aircraft through an external APBs.
  • EPB power breaker
  • Control for this distribution system is effected through several control units.
  • GCU generator control unit
  • the GCU In addition to providing voltage and frequency output regulation of its generator, the GCU also coordinates the configuration of its channel by sensing and controlling the GCB and BTB for its channel. Coordination of the configuration of the APBs, the EPB, and the XTB is accomplished by a bus power control unit (BPCU) which senses and controls these breakers. Additionally, since the BPCU is responsible for the coordination of multichannel operation, it is responsible for the coordination of multichannel operation, it
  • auxiliary contacts within the breaker housing. These auxiliary contacts are actuated by a
  • the control units use an open/ground sense type circuit to detect whether the auxiliary contact is open, indicating the breaker is open, or whether the auxiliary contact is closed, indicating the breaker is closed. Due to the high intensity radiated fields (HIRF) and lightning strikes to which the aircraft may be subjected during flight, two wires (a positive and a return) are used to sense each auxiliary contact to prevent coupling of the electromagnetic energy into the control units.
  • HIRF high intensity radiated fields
  • two wires a positive and a return
  • control lines are also coupled to the breakers. To conserve energy on the
  • the breakers are typically latching type cut-throat relays requiring both a trip and a
  • radio remote control One method used in other industries to substantially eliminate the need for sense and control wires is radio remote control.
  • An early system of radio remote control for aircraft is illustrated in U.S. Patent No. 2,580,453, entitled “Remote-Control System for Aircraft", granted on January 1, 1952 to Murray et al. This early system transmits control information
  • U.S. Patent No. 3,403,381 entitled “System of Radio Communication by Asynchronous Transmission of Pulses Containing Address Information and Command Information", granted on September 24, 1968 to Haner.
  • This system uses a single carrier frequency to control multiple vehicles. This control is accomplished by transmitting pulses random in time, each pulse containing a single address to identify each individual vehicle. The control information for the vehicle is delayed for a period of time after the address is transmitted to avoid inadvertent control of a non-addressed vehicle.
  • Aircraft control unlike the locomotive control of the Haner '381 system, requires the ability for continuous control. Only being able to transmit control signals randomly in time, and being required to delay the
  • control information for a fixed period is wholly unacceptable for application on a commercial
  • This remote control system also uses a central transmitter to signal individual load controllers which connect and disconnect various loads to
  • the instant invention to provide a radio frequency control system for an airborne electric power
  • HIRF high intensity radiated electromagnetic fields
  • an aircraft electric power distribution system comprises two electric power generators each producing output electric
  • switching devices interposed therein. These switching devices are operative to interrupt and
  • control information is transmitted to the switching devices individually through the use of contactor addressing information to command interruption or enablement of the electric power distribution.
  • status information is transmitted from the switching devices to the controllers, either individually through controller addressing or collectively.
  • the switching devices are smart
  • contactors which include a digital signal processor and a logic processor for receiving, decoding, conditioning, and controlling the main contactor portion of the device.
  • the smart contactors include current sensing capability for sensing, scaling, and transmitting the current flow information to the controllers for use thereby.
  • the position of the main contactor portion of the smart contactor is also monitored and transmitted for use by the controllers.
  • FIG. 1 is a single line interconnect diagram of an electric power generation
  • FIG. 2 is a block diagram of a smart contactor comprising an aspect of the instant
  • FIG. 3 is a communication and control block diagram of the contactors of the instant
  • FIG. 4 is a flow diagram of the digital signal processor (DSP) logic of the instant invention.
  • FIG. 5a illustrates an exemplary control word bit pattern in accordance with an aspect
  • FIG. 5b illustrates an exemplary status word bit pattern in accordance with an aspect of
  • FIG. 5c illustrates an alternative exemplary status word bit pattern in accordance with
  • an exemplary embodiment of an aircraft electric power generation and distribution system 10 in accordance with the instant invention typically uses
  • Each channel is comprised of a generator
  • a typical system 10 also includes an auxiliary power unit generator 28 and provision for connection of a source of external power 30, although these need not be provided if not required by the particular system
  • Each of the generating channels 12, 14 are controlled by a controller, such as
  • GCU generator control unit 46, 48.
  • GCU generator control unit 46, 48.
  • This control typically combines voltage regulation, control, protection, and switching functions.
  • a bus power control unit (BPCU) 50 is also included to control the bus transfer functions including application of external and auxiliary power to the system.
  • control of the switching means is effected through the use of radio frequency command and status
  • EMI electromagnetic interference
  • HIRF high intensity radiated fields
  • the instant invention contemplates a smart contactor 52 to be included in the electric power distribution system as the electric power switching means 32-44 of FIG. 1
  • These smart contactors 52 comprise a typical switching mechanism 54 which may be of any typical technology as discussed above
  • the control for the switching mechanism is provided by a contactor control module
  • the contactor control module 56 which drives a control coil 58 to close a control contactor 60 which energizes the main contactor coil 62 to trip or close the main contacts 64a-c
  • the contactor control module 56 receives and transmits control and status information via an antenna 66 which may be
  • the smart contactor 52 also includes current sensing means, such as current transformers 68a-c, for providing current flow information to the contactor control module 56
  • the contactor control module 56 may use this information for internal protection, e.g., overcurrent protection of the smart contactor, as well as transmitting this information to its associated control unit (46, 48, or 50).
  • the contactor control module 56 comprises a receiver 70 coupled through a digitizer 72 to a digital signal processor (DSP) 74 This DSP 74
  • the coil driver 76 preferably utilizes the aircraft 28 volt supply 80 to drive the control coil 58 (see FIG. 2)
  • the logic processor 78 also receives status information from the coil driver 76, from the current sensors 68a-c, and from auxiliary contacts 82 which transition with the main contacts 64a-c (see FIG. 2).
  • the logic processor also outputs control information to the coil driver 76, as well as status
  • control word control signal
  • the encrypted control word is then decoded 92 and analyzed. If the control word is not intended for this particular contactor 94 (as will be described more fully below), the algorithm returns to wait for another signal If it is determined to be a control signal for this contactor, the control word is analyzed to determine if it is a control command 96 If it is a control command, the
  • the word does not contain a control command, the word is analyzed to determine if it contains a
  • the control signal is carried by a carrier waveform which may be modulated using a variety of techniques known in the art, such as amplitude modulation, frequency modulation, quadrature amplitude modulation, or quadrature digital phase shift keying to name a few. If
  • the carrier frequency may be advantageously
  • the actual amplitude or frequency modulation transmission frequency would be in the range of 20 to 30 kHz. This frequency is determined by the control signal or control word bit structure as described more fully below.
  • FIGs. 5a-c different addressable aircraft should be sufficient as illustrated in FIGs. 5a-c. However, if more
  • control word For a system such as is illustrated in FIG. 1, a three (3) bit contactor address
  • controller 46, 48, 50 may be addressed 114 as illustrated in FIG. 5c, or all controllers may
  • the type of word to follow must be identified. Since the exemplary embodiment of the invention includes only control words and status words, a single word type bit 116 is needed. If more word types are included, more word type bits must be included to identify each type so that proper decoding
  • FIG. 5 a the actual control portion of the control word may follow.
  • the use of two control bits 118 are sufficient. If the word type bit 116 indicates that a status word is being transmitted, the status information will follow (see FIG. 5b or FIG. 5c). Since a contactor may either be open or closed, a single status bit 120 is sufficient to indicate its status. For the monitored current information, the number of current status bits 122 are dependant on the desired resolution needed for the system. As an example, if the system current were to vary from 0 amps to 1000 amps and 8 bits were used, the resolution of the current transition is approximately 4 amps. Depending on the needs of the system, more or fewer bits may be
  • Patent Number 5,466,974 Aircraft Electric Power Distribution Center, or of U.S. Patent
  • the transmission power required may be greatly reduced. This has a double benefit in that it conserves power and that it dramatically reduces the possibility that another aircraft will pick up the control transmissions for the subject aircraft. Utilization of the low power transmission may eliminate

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  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Remote Monitoring And Control Of Power-Distribution Networks (AREA)

Abstract

L'invention concerne un système de distribution électrique pour aéronef comprenant deux générateurs électriques produisant chacun de l'électricité qui est couplée aux charges électriques de l'aéronef par des câbles de distribution séparés par des dispositifs de commutation électrique. Ces dispositifs peuvent être actionnés pour interrompre et valider la distribution d'électricité aux charges de l'aéronef. Le système de la présente invention comprend également des régulateurs de distribution électrique qui sont en communication radio avec chacun des dispositifs de commutation. De préférence, les informations de commande sont émises séparément les unes des autres à destination des dispositifs de commutation en utilisant des informations d'adressage du contacteur pour commander l'interruption ou la mise hors service de la distribution électrique. En outre, des informations d'état sont émises à partir des dispositifs de commutation vers les régulateurs, soit individuellement par adressage du régulateur soit en bloc. On évite les interférences entre avions en utilisant de l'information d'adressage véhicule et/ou des commandes à faible puissance et en émettant un signal d'état. Les dispositifs de commutation comportent un processeur de signal numérique et un processeur logique capables de recevoir, de décoder, de conditionner et de surveiller le bloc contacteur principal du dispositif. En outre, ces dispositifs ont aussi une aptitude à la détection de courant si bien qu'ils peuvent détecter, évaluer et transmettre les informations de flux de courant aux régulateurs pour qu'ils les utilisent. La position du bloc relais principal du relais intelligent est également surveillée et transmise afin d'être utilisée par les régulateurs.
PCT/US1998/001839 1997-01-31 1998-01-30 Systeme et procede de radiocommande pour relais de distribution electrique d'aeronefs WO1998034318A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CA002281711A CA2281711A1 (fr) 1997-01-31 1998-01-30 Systeme et procede de radiocommande pour relais de distribution electrique d'aeronefs

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US79250097A 1997-01-31 1997-01-31
US08/792,500 1997-01-31

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WO1998034318A1 true WO1998034318A1 (fr) 1998-08-06
WO1998034318B1 WO1998034318B1 (fr) 1998-10-15

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008107764A3 (fr) * 2007-03-02 2008-11-06 Axa Power Aps Interconnexion sans fil de signaux de commande pour un groupe de parc
US7626798B2 (en) 2008-01-24 2009-12-01 Honeywell International Inc. Electronic load control unit (ELCU) used as bus tie breaker in electrical power distribution systems
EP2300968A1 (fr) * 2008-01-30 2011-03-30 The Boeing Company Ordinateur portable pour la maintenance d'aéronef
US8148848B2 (en) 2008-01-24 2012-04-03 Honeywell International, Inc. Solid state power controller (SSPC) used as bus tie breaker in electrical power distribution systems
CN112600195A (zh) * 2020-12-01 2021-04-02 陕西航空电气有限责任公司 一种基于汇流条功率控制器的飞机配电系统控制架构
EP3895994A1 (fr) * 2020-04-16 2021-10-20 Honeywell International Inc. Système adaptatif de distribution d'énergie électrique d'aéronef

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4682294A (en) * 1983-10-18 1987-07-21 Automobiles Citroen Electric energy distributing devices comprising microprocessors
EP0267398A2 (fr) * 1980-09-02 1988-05-18 Deutsche Airbus GmbH Dispositif de transmission de signaux de commande, notamment pour avions
US5386363A (en) * 1990-08-16 1995-01-31 Sundstrand Corporation Aircraft load management center
GB2288291A (en) * 1994-04-05 1995-10-11 Smiths Industries Plc Electrical systems and connectors
US5531402A (en) * 1995-03-23 1996-07-02 Dahl; Robert M. Wireless flight control system
US5594285A (en) * 1993-08-27 1997-01-14 Sundstrand Corporation Power distribution center

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0267398A2 (fr) * 1980-09-02 1988-05-18 Deutsche Airbus GmbH Dispositif de transmission de signaux de commande, notamment pour avions
US4682294A (en) * 1983-10-18 1987-07-21 Automobiles Citroen Electric energy distributing devices comprising microprocessors
US5386363A (en) * 1990-08-16 1995-01-31 Sundstrand Corporation Aircraft load management center
US5594285A (en) * 1993-08-27 1997-01-14 Sundstrand Corporation Power distribution center
GB2288291A (en) * 1994-04-05 1995-10-11 Smiths Industries Plc Electrical systems and connectors
US5531402A (en) * 1995-03-23 1996-07-02 Dahl; Robert M. Wireless flight control system

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008107764A3 (fr) * 2007-03-02 2008-11-06 Axa Power Aps Interconnexion sans fil de signaux de commande pour un groupe de parc
US7626798B2 (en) 2008-01-24 2009-12-01 Honeywell International Inc. Electronic load control unit (ELCU) used as bus tie breaker in electrical power distribution systems
US8148848B2 (en) 2008-01-24 2012-04-03 Honeywell International, Inc. Solid state power controller (SSPC) used as bus tie breaker in electrical power distribution systems
EP2300968A1 (fr) * 2008-01-30 2011-03-30 The Boeing Company Ordinateur portable pour la maintenance d'aéronef
EP3895994A1 (fr) * 2020-04-16 2021-10-20 Honeywell International Inc. Système adaptatif de distribution d'énergie électrique d'aéronef
US11448136B2 (en) 2020-04-16 2022-09-20 Honeywell International Inc. Adaptive aircraft electrical power distribution system
CN112600195A (zh) * 2020-12-01 2021-04-02 陕西航空电气有限责任公司 一种基于汇流条功率控制器的飞机配电系统控制架构
CN112600195B (zh) * 2020-12-01 2023-04-28 陕西航空电气有限责任公司 一种基于汇流条功率控制器的飞机配电系统控制架构

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Publication number Publication date
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