WO1998005052A1 - Contacteur modulaire - Google Patents

Contacteur modulaire Download PDF

Info

Publication number
WO1998005052A1
WO1998005052A1 PCT/US1997/013176 US9713176W WO9805052A1 WO 1998005052 A1 WO1998005052 A1 WO 1998005052A1 US 9713176 W US9713176 W US 9713176W WO 9805052 A1 WO9805052 A1 WO 9805052A1
Authority
WO
WIPO (PCT)
Prior art keywords
contactor
module
auxiliary
status
modular
Prior art date
Application number
PCT/US1997/013176
Other languages
English (en)
Inventor
Darin R. Morman
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
Publication of WO1998005052A1 publication Critical patent/WO1998005052A1/fr

Links

Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01H—ELECTRIC SWITCHES; RELAYS; SELECTORS; EMERGENCY PROTECTIVE DEVICES
    • H01H50/00—Details of electromagnetic relays
    • H01H50/02—Bases; Casings; Covers
    • H01H50/04—Mounting complete relay or separate parts of relay on a base or inside a case
    • H01H50/041—Details concerning assembly of relays
    • H01H50/042—Different parts are assembled by insertion without extra mounting facilities like screws, in an isolated mounting part, e.g. stack mounting on a coil-support
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01H—ELECTRIC SWITCHES; RELAYS; SELECTORS; EMERGENCY PROTECTIVE DEVICES
    • H01H71/00—Details of the protective switches or relays covered by groups H01H73/00 - H01H83/00
    • H01H71/04—Means for indicating condition of the switching device
    • H01H2071/048—Means for indicating condition of the switching device containing non-mechanical switch position sensor, e.g. HALL sensor
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01H—ELECTRIC SWITCHES; RELAYS; SELECTORS; EMERGENCY PROTECTIVE DEVICES
    • H01H50/00—Details of electromagnetic relays
    • H01H50/08—Indicators; Distinguishing marks
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01H—ELECTRIC SWITCHES; RELAYS; SELECTORS; EMERGENCY PROTECTIVE DEVICES
    • H01H50/00—Details of electromagnetic relays
    • H01H50/54—Contact arrangements
    • H01H50/541—Auxiliary contact devices
    • H01H50/545—Self-contained, easily replaceable microswitches

Definitions

  • the present invention is directed to an improved contactor for making/breaking a main electrical circuit, coordinated switching of the solenoid coil, and communicating a contactor's status through a plurality of auxiliary outputs.
  • the contactor is useful in an aircraft.
  • the conventional contactor for use on an aircraft contains all the components which perform the functions of making/breaking a main electrical circuit, coordinated switching of the solenoid coil, and communicating the contactor's status through auxiliary outputs. Provisions for attaching a wiring harness to the auxiliary outputs and solenoid coil command lines and securing aircraft current-in and current-out feeder wires of the main electrical circuitry are also included as one contactor package.
  • the contactor 17 is in the form of a power relay with an electrically operated, magnetically latched three-pole, single throw, plunger actuated solenoid unit 18.
  • the solenoid unit comprises a coil 1 and a plunger 5 attached to the main actuating rod 4 which carries movable contacts 9 which are moved back and forth along the axis A-A in Fig. 2 into and out of contact with respective stationary contacts 10 in a main electrical circuit.
  • the relay 17 has seventeen auxiliary circuits which function to communicate the contactor's status, e.g. whether the main electrical circuit is open or closed by the contactor, through a plurality of auxiliary outputs in a connector 19.
  • the auxiliary circuits each include auxiliary contacts 3 inside auxiliary switches 20. Both normally opened and normally closed sides of the auxiliary switches are available at the relay connector. Switch screws 12 carried by the actuator plate 6 attached to the main actuating rod 4 of the solenoid unit 18 are moved to open and close the auxiliary switches 20 by pushing or releasing the switch button 1 3 with the making/breaking of the main electrical circuit with contacts 9 and 10.
  • the relay 17 has a coil transfer switch 7 to coordinate relay trip and close action in response to the command signal from an aircraft control unit, and to remove power from the trip and close coils of coil 1 after operation.
  • the main electrical power connections to the relay are made by six terminal studs. Normally, electrical power is connected to terminals T1 , T2 and T3 and the power leaves the relay through terminals L1 , L2 and L3. Connections for the auxiliary switches 20 and the coil transfer switch 7 are through the pins of the connector 19.
  • a close command signal from an aircraft control unit is applied through the coil transfer switch 7 to the close coil of coil 1 and sets up an electromagnetic flux in the same direction as the permanent magnet but through the solenoid plunger 5.
  • This flux overcomes the force of the main spring 21 and causes the solenoid plunger 5 to move downward.
  • the permanent magnet flux path, as the two air gaps are reduced to zero, will be through the plunger ring 23 and solenoid plunger 5 because of the lower reluctance of the plunger path.
  • the force of the permanent magnet flux is greater than the force of the main spring 21 and will hold the relay in the closed position or latched position after the close coil current is cut off by the coil transfer switch 7. While the relay is closing the main actuator 4 attached to the solenoid plunger 5, moves downward with the plunger 5. The main actuator rod 4 pulls the movable contacts 9 down onto the fixed contacts 10 to complete the main electrical power circuits through the relay. At the same time the auxiliary switches 20 and the coil transfer switch 7 are operated by switch screws 1 2 carried by the actuator plate 6.
  • a trip command signal from an aircraft control unit is applied through the coil transfer switch 7 to the relay trip coil in coil 1 which sets up an electromagnetic flux that opposes the permanent magnet latch flux.
  • the electromagnetic flux reduces the force of the permanent magnet flux and energy stored in the main spring 21 causes the solenoid plunger and the main actuating rod 4 to move upward.
  • the main actuating rod 4 pushes on the insulating bushing 14 causing the movable contacts 9 to move away from the stationary contacts 10 opening the main electrical power circuit through the relay.
  • the auxiliary switches 20 and coil switch 7 are released as the actuator plate 6 containing the switch screws 12 moves up.
  • the solenoid plungers moves upward, the air gap in the plunger flux circuit will increase causing a high reluctance path.
  • the permanent magnet flux path will be through the spacers 22, solenoid bases 25, and permanent magnets 24.
  • This conventional contactor is disadvantageous in that the contactor contains all the components which perform the functions of making/breaking the main electrical circuit, the coordinated switching of the solenoid coil, and the communication of the contactor's status through auxiliary outputs. Provision for attaching a wiring harness to the auxiliary outputs and the solenoid coil command lines at connector 19 and securing the aircraft current-in and current-out feeder wires are also included in the one contactor package. When any one of the these functions fails or the method for securing the wiring harness or current-in or current-out wires becomes worn or damaged, the entire contactor must be removed and replaced or repaired. Also, the number of auxiliary outputs varies for different aircraft applications which can require a change in the overall contactor design, performance characteristic and packaging envelope.
  • An object of the present invention is to provide an improved contactor which avoids the aforementioned disadvantages of the prior contactor. More specifically, an object of the invention is to provide an improved contactor which utilizes the traditional way to perform the function of making/breaking the main electrical circuit but a unique way of providing coordinated switching function of the solenoid coil and a unique way of providing the function of communicating the contactor's status through auxiliary outputs with two distinct modules on a common base instead of with all functions in one package.
  • This new approach allows the flexibility of providing any number of auxiliary outputs without affecting the performance and packaging of the module which performs the making/breaking in the main electrical circuit. Further, when one of the functions fails, only the defective module needs to be replaced or repaired. This decreases the replacement costs since the entire contactor does not have to be replaced.
  • a modular contactor for performing the function of making/breaking a main electrical circuit, and the function of coordinated switching of the solenoid coil and the function of communicating the contactor's status through a plurality of auxiliary outputs, comprises a contactor module having a means for making/breaking a main electrical circuit and a sensor providing an electrical signal of the contactor's status; and an auxiliary function module including means for providing a plurality of auxiliary outputs communicating the contactor's status and means for providing coordinated switching of the solenoid coil; and wherein the module contactor includes means for releasably electrically connecting the contactor module and the auxiliary function module for transmitting the electrical signal of the sensor of the contactor module to the means for providing auxiliary inputs communicating the contactor's status and transmitting the command signal through the auxiliary function module to the solenoid coil in the contractor module.
  • the modular contactor of the disclosed embodiment further comprises a mounting base to which the contactor module and the auxiliary function module are releasably mounted.
  • the mounting base comprises terminals in the form of threaded studs for attaching current-in and current-out feeder wires directly to the modular contactor.
  • the contactor module is electrically connected across the current-in and current-out terminals for making/breaking the electrical circuit through the modular contactor.
  • the means for releasably electrically connecting the contactor module and the auxiliary function module includes respective electrical connectors on the contactor module and the auxiliary function module which make electrical contact with one another when the modules are both releasably mounted on the mounting base.
  • the mounting base in turn includes through holes for securing the modular contactor to a support member of an aircraft.
  • the auxiliary function module in the disclosed embodiment includes a connector for mating with an aircraft wiring harness for outputting the plurality of auxiliary outputs communicating the contactor's status and for receiving the solenoid coil command signal from an aircraft control unit.
  • the means for providing the plurality of auxiliary outputs communicating the contactor's status includes a circuit board with multiplexing circuitry for providing the plurality of auxiliary outputs utilizing the electrical signal from the sensor from the contactor module.
  • the sensor located in the contactor module generates an electrical signal which is dependent on the contactor's actuator position and sends this signal to the auxiliary function module for interpretation.
  • the means for coordinated switching of the solenoid coil is provided by electronic switching circuitry that removes the command signal from the solenoid coil and also applies the proper electrical polarity across the solenoid coil for the next coil command signal.
  • a further advantage of the present invention resides in the elimination of the mechanical interface of the actuator and auxiliary switches and the mechanical interface of the actuator and coil transfer switch as in the prior art contactor referred to above.
  • the invention requires only an electrical interface between the auxiliary function module and the contactor module, not a mechanical interrelationship. That is, the auxiliary function according to the present invention is performed electronically instead of by contacts and that function is controlled by an electrical signal from the contactor module instead of a mechanical interface. Also, the coordinated switching function according to the present invention is performed electronically in the auxiliary function module instead of a mechanical interface.
  • the auxiliary function module also mounts to the mounting base instead of the contactor module.
  • the means for releasably electrically contacting the contactor module and the auxiliary function module includes respective electrical connectors on the contactor module and the auxiliary function module which make electrical contact with one another when the modules are both releasably mounted on the mounting base.
  • the present invention is also directed to an aircraft having the improved modular contactor of the present invention connected to a support member of the aircraft by way of the mounting base.
  • Fig. 1 is a perspective view of a prior art contactor in the form of a power relay for an aircraft;
  • Fig. 2 is a cross-sectional view of the prior art contactor of Fig. 1 taken along the line ll-ll;
  • Fig. 3 is a cross-sectional view of the prior art contactor of Fig. 1 taken along the line Ill-Ill;
  • Fig. 4 is a perspective view of a modular contactor of the present invention in a assembled form mounted as a power relay on a support member of an aircraft;
  • Fig . 5 is a perspective view of the several modules of the contactor of Fig. 4 shown in spaced relation to one another before assembly and mounting on an aircraft;
  • Fig . 6 is a schematic block diagram of a modular contactor of Fig. 4 depicting components of the contactor and their relationship to the auxiliary function module and the contactor module of the contactor.
  • a contactor 30 contains a contactor module 31 and an auxiliary function module 32 which both mount onto a common mounting base 33.
  • the contactor module 31 performs the function of making/breaking a main electrical circuit and contains a solenoid motor 36, a position sensor 37 and main electrical contacts 38.
  • the solenoid moves the main electrical contacts 38 by way of an actuator 45 for making/breaking the main electrical circuit which extends through the contactor module.
  • the position sensor 37 indicates the position of the actuator and, therefore, whether the main electrical power circuit is open or closed by the solenoid operated main contacts 38.
  • the type of sensor can be an optical sensor, a proximity sensor, Hall-effect sensor, or any other type that has an electrical output of at least two different voltage levels.
  • the auxiliary function module 32 contains a circuit board 39 with the necessary electronics to provide the appropriate number of auxiliary outputs from the output signal of the position sensor and the necessary solid state switching circuitry to provide the coordinated switching of the command signal to the solenoid coil.
  • This multiplexing circuitry and solid state switching circuitry are schematically depicted in Fig. 6. The multiplexing can be done by digital or analog methods using combinations of diodes, transistors, or microprocessor means and the coordinated switching of the coil command signal can be done by field-effect transistors, bipolar transistors, silicon controlled switches or any other solid state switching means, as will be readily understood by the skilled artisan.
  • a connector 40 which mates with aircraft wiring harness 41 is also part of the auxiliary function module 32.
  • the modular contactor mounting base 33 contains threaded terminal studs 42 for mounting the contactor module 31 and attaching the aircraft current-in and the current- out feeder wires.
  • Copper bus bars 47 are provided on the contactor module 31 and the bus bars 47 have apertures formed therein for receiving the terminal studs 42 in the assembled position of the contactors.
  • the current-in and current-out feeder wires have lugs, not shown, that have an aperture for receiving the terminal studs so the feeder wire lugs will be in direct contact with the copper bus bars 47 when installed in the aircraft.
  • Through holes 43 are provided in the mounting base 33 for mounting the contactor 30 on a support member of an aircraft 46 by suitable fasteners, not shown.
  • Through holes 34 in contactor module 31 and through holes 35 in auxiliary function module 32 are provided for mounting the modules 31 and 32 on the mounting base 33 using suitable fasteners, not shown.
  • auxiliary function module 32 gets secured to the mounting base 33, an electrical connection is also made with the contactor module via mating connectors 44 on opposed surfaces of the modules 31 and 32.
  • the mating connectors 44 contain electrical pins/sockets which contact one another. This electrical connection permits the output of the position sensor 37 in the contactor module 31 to reach the circuitry in the auxiliary function module 32. The connection also allows the power to the coil of the solenoid 36 in the contactor module 31 to be passed through and switched in the auxiliary function module as shown schematically in Fig. 6.
  • the present invention eliminates the mechanical interface of auxiliary switches by using a sensor located in the contactor module to generate an electrical signal which is dependent on the contactor's actuator position. This signal is sent to the auxiliary function module for interpretation.
  • the contactor of the present invention requires only an electrical interface between the auxiliary function module and the contactor module, not a mechanical interrelationship.
  • the auxiliary function module uses electronic circuitry instead of mechanical contacts for auxiliaries and coil switching.

Abstract

Un contacteur modulaire, particulièrement utile dans un aéronef, assure la fonction de fermeture/ouverture d'un circuit électrique principal, la fonction de commutation coordonnée de la bobine du solénoïde et la fonction de communication de l'état du contacteur pour une pluralité de sorties auxiliaires. Le contacteur comprend un support de montage sur lequel sont montés libérables un module contacteur et un module de fonction auxiliaire. Le module contacteur comprend au moins un contact qui permet de fermer/ouvrir un circuit électrique principal et un capteur qui fournit un signal électrique de l'état du contacteur. Le module de fonction auxiliaire comprend un circuit électrique qui fournit une pluralité de sorties auxiliaires communiquant l'état du contacteur et qui assure la commutation coordonnée de la bobine du solénoïde. Les conducteurs électriques du module contacteur et du module de fonction auxiliaire entrent en contact électrique quand ils sont montés libérables sur le support de montage, et ainsi transmettent le signal électrique du capteur du module contacteur au circuit du module de fonction auxiliaire, de façon à fournir une pluralité de sorties auxiliaires communiquant l'état du contacteur et à transmettre le signal de commande, par l'intermédiaire du module de fonction auxiliaire, à la bobine du solénoïde du module contacteur. Avantageusement, quand une fonction est défaillante, il suffit de remplacer ou de réparer le module défectueux. En outre, la souplesse du contacteur lui permet de fournir n'importe quelle quantité de sorties auxiliaires, à l'aide de différents modules de fonction auxiliaire, sans affecter les performances ou l'emballage mécanique du module assurant la fermeture/ouverture du circuit électrique principal. Les interfaces mécaniques au niveau des commutateurs auxiliaires et l'inverseur de la bobine du solénoïde sont également éliminés.
PCT/US1997/013176 1996-07-29 1997-07-28 Contacteur modulaire WO1998005052A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US68157996A 1996-07-29 1996-07-29
US08/681,579 1996-07-29

Publications (1)

Publication Number Publication Date
WO1998005052A1 true WO1998005052A1 (fr) 1998-02-05

Family

ID=24735888

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1997/013176 WO1998005052A1 (fr) 1996-07-29 1997-07-28 Contacteur modulaire

Country Status (1)

Country Link
WO (1) WO1998005052A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008034395A1 (fr) * 2006-09-21 2008-03-27 Siemens Aktiengesellschaft Appareillage de commutation avec prélèvement de voie de courant principale intégré
WO2008087074A2 (fr) * 2007-01-15 2008-07-24 Siemens Aktiengesellschaft Dispositif de détection destiné à la détection de l'état de commutation d'un commutateur électromagnétique
WO2015084711A1 (fr) * 2013-12-04 2015-06-11 Labinal, Llc Procédé et appareil permettant de détecter l'état d'un interrupteur de circuit
FR3028100A1 (fr) * 2014-11-05 2016-05-06 Schneider Electric Ind Sas Systeme comprenant une embase et un module debrochable a chaud

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0189924A1 (fr) * 1985-01-31 1986-08-06 Siemens Aktiengesellschaft Dispositif pour accoupler un interrupteur auxiliaire
DE8906072U1 (fr) * 1988-05-20 1989-10-05 Telemecanique, Rueil-Malmaison Cedex, Fr
EP0354575A2 (fr) * 1988-08-10 1990-02-14 Fuji Electric Co., Ltd. Contacteur électromagnétique
US5486972A (en) * 1993-12-30 1996-01-23 Eaton Corporation AC powered electrical control device with logic level control

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0189924A1 (fr) * 1985-01-31 1986-08-06 Siemens Aktiengesellschaft Dispositif pour accoupler un interrupteur auxiliaire
DE8906072U1 (fr) * 1988-05-20 1989-10-05 Telemecanique, Rueil-Malmaison Cedex, Fr
EP0354575A2 (fr) * 1988-08-10 1990-02-14 Fuji Electric Co., Ltd. Contacteur électromagnétique
US5486972A (en) * 1993-12-30 1996-01-23 Eaton Corporation AC powered electrical control device with logic level control

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008034395A1 (fr) * 2006-09-21 2008-03-27 Siemens Aktiengesellschaft Appareillage de commutation avec prélèvement de voie de courant principale intégré
WO2008087074A2 (fr) * 2007-01-15 2008-07-24 Siemens Aktiengesellschaft Dispositif de détection destiné à la détection de l'état de commutation d'un commutateur électromagnétique
WO2008087074A3 (fr) * 2007-01-15 2009-01-22 Siemens Ag Dispositif de détection destiné à la détection de l'état de commutation d'un commutateur électromagnétique
US8289026B2 (en) 2007-01-15 2012-10-16 Siemens Aktiengesellschaft Recording device for recording the switch state of an electromagnetic switch device
WO2015084711A1 (fr) * 2013-12-04 2015-06-11 Labinal, Llc Procédé et appareil permettant de détecter l'état d'un interrupteur de circuit
US9720044B2 (en) 2013-12-04 2017-08-01 Labinal, Llc Method and apparatus for sensing the status of a circuit interrupter
FR3028100A1 (fr) * 2014-11-05 2016-05-06 Schneider Electric Ind Sas Systeme comprenant une embase et un module debrochable a chaud
CN105576452A (zh) * 2014-11-05 2016-05-11 施耐德电器工业公司 包括基座和热插接模块的系统
EP3018689A1 (fr) * 2014-11-05 2016-05-11 Schneider Electric Industries SAS Système comprenant une embase et un module débrochable à chaud
US9548561B2 (en) 2014-11-05 2017-01-17 Schneider Electric Industries Sas System comprising a base and a hot unpluggable module

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