Control system and process for several actuators
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G05D-027/02
G05D-027/00
출원번호
US-0409761
(2003-04-08)
우선권정보
FR-02 04465(2002-04-10)
발명자
/ 주소
Foch,Etienne
Fleury,Christophe
출원인 / 주소
Airbus France
대리인 / 주소
Thelen Reid &
인용정보
피인용 횟수 :
4인용 특허 :
8
초록▼
This invention relates to a system for controlling several actuators (Al1, . . . , Anr), comprising at least two computers (L1, L2, . . . , Lk) and at least two means (C1, C 2, . . . , Cn) of controlling at least one actuator, each control module being capable of controlling at least one actuator th
This invention relates to a system for controlling several actuators (Al1, . . . , Anr), comprising at least two computers (L1, L2, . . . , Lk) and at least two means (C1, C 2, . . . , Cn) of controlling at least one actuator, each control module being capable of controlling at least one actuator through at least one first connection (16) and being capable of receiving information about this at least one actuator through at least one second connection (15), in which each control module is connected to at least two computers through at least two first communication buses (11, 12, 13).
대표청구항▼
The invention claimed is: 1. System for controlling the electrical generation system of an aircraft, said system comprising: a plurality of actuators for the electrical generation system of the aircraft, said actuators controlling distinct outputs; at least two computers; and at least two modules f
The invention claimed is: 1. System for controlling the electrical generation system of an aircraft, said system comprising: a plurality of actuators for the electrical generation system of the aircraft, said actuators controlling distinct outputs; at least two computers; and at least two modules for controlling at least one actuator, each control module being capable of controlling at least one actuator through at least one first connection and being capable of receiving information about said at least one actuator through at least one second connection, wherein each control module is connected to at least two computers through at least two first communication buses. 2. System according to claim 1, in which the computers are connected to each other through at least one second communication bus. 3. System according to claim 2, wherein each computer is connected to a communication bus through a connection. 4. System according to claim 1, wherein buses are CAN buses. 5. System according to claim 1, comprising electrical sources/generators, primary AC circuits of two contactors, controls for these contactors, and electrical distribution lines. 6. System according to claim 1, wherein the control modules are connected to communication networks, to which the computers are connected, the computers being connected to each other through an inter-computer network. 7. System according to claim 1, wherein actuators are electrical contactors. 8. System according to claim 1, wherein if a connection between a computer and an actuator is interrupted, said connection providing information concerning said actuator, said computer is capable of receiving the information concerning said actuator from another computer which is linked to said actuator. 9. Process for controlling the electrical generation system of an aircraft in a system comprising a plurality of actuators, at least two computers, and at least two modules for controlling at least one of said plurality of actuators for the electrical generation system of the aircraft, each control module being capable of controlling at least one actuator through at least one first connection and being capable of receiving information related to this at least one actuator through at least one second connection, wherein at least two control modules are used that make decisions related to control of the actuators that they control as a function of information received from several computers, and wherein each computer is capable of using information output from the control modules connected to it, calculates set values as a function of this information, and sends these set values to the said control modules, and wherein said actuators control distinct outputs of the electrical generation system of the aircraft. 10. Process according to claim 9, in which the computers work independently and asynchronously. 11. Process according to claim 9, wherein each computer is capable of accessing information originating from all actuators, even if connections between this computer and the actuator control modules are interrupted, and wherein said computer is capable of continuing to calculate set values corresponding to the different actuators and capable of sending set values related to actuators controlled by control modules for which the connection with said computer is not interrupted, on its communication bus. 12. Process according to claim 9, wherein if a connection between a computer and an actuator is interrupted, said connection providing information concerning said actuator, said computer is capable of receiving the information from another computer which is linked to said actuator. 13. Process for controlling the electrical generation system of an aircraft in a system comprising a plurality of actuators, at least two computers, and at least two modules for controlling at least one actuator, said process comprising: controlling, using the control module, at least one of said plurality of actuators for the electrical generation system of the aircraft through at least one first connection; receiving, at the control modules, information related to said at least one actuator through at least one second connection; making, using at least two control modules, decisions related to control of the actuators that they control, as a function of information received from several computers; calculating, at the computers, set values as a function of information output from the control modules connected thereto, sending the set values to the control modules; and controlling, using the actuators, distinct outputs of the electrical generation system of the aircraft. 14. Process according to claim 13, if a connection between a computer and an actuator is interrupted, said connection providing information concerning said actuator, said process further comprising: receiving, at said computer, the information concerning said actuator from another computer which is linked to said actuator.
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이 특허에 인용된 특허 (8)
Ejzak Richard P. (Rockford IL) Thom James B. (Rock City IL) Peterson William J. (Rockford IL) Glennon Timothy F. (Rockford IL), Control for an electrical generating and distribution system, and method of operation.
Pressnall Dana W. (Midland MI) Polishak Jeffery T. (Saginaw MI) Felix Bradley K. (Midland MI) Durisin Michael J. (Midland MI) Ellison Joseph (Detroit MI), Information display system for actively redundant computerized process control.
Jackson Douglas O. (Mercer Island WA), Method and apparatus for implementing a databus voter to select flight command signals from one of several redundant asy.
McTamaney Louis S. (Cupertino CA) Wong Yue M. (Saratoga CA) Chandra Rangasami S. (Pleasanton CA) Walker Robert A. (Sunnyvale CA) Lastra Jorge E. (San Jose CA) Wagner Paul A. (Cambridge MA) Sharma Uma, Multi-purpose autonomous vehicle with path plotting.
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