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The invention relates to a system for controlling a plurality of actuators (15) that can displace a mobile panel (13, 17) pertaining to a nacelle (1) of an aircraft, said system comprising at least two motors (16) that can drive the actuators (15). The system also comprises two separate control units (33, 35), each unit being configured in such a way as to control and feed at least one motor that is not fed or controlled by the other control unit. The invention also relates to a nacelle comprising such a system.

Titel:	Control system for a turboreactor nacelle
Autor/in / Beteiligte Person:	Maalioune, Hakim ; Le-Coq, Vincent ; Moradell-Casellas, Pierre ; Hadjidj, Djemouai ; Garcia Soto, Guillermo
Link:	View record in USPTO Patent Grants (Volltext)
Veröffentlichung:	2015
Medientyp:	Patent
Sonstiges:	Nachgewiesen in: USPTO Patent Grants Sprachen: English Patent Number: 9,057,342 Publication Date: June 16, 2015 Appl. No: 13/264893 Application Filed: April 06, 2010 Assignees: AIRCELLE (Gonfreville l'Orcher, FR), HISPANO SUIZA (Colombes, FR) Claim: 1. A system comprising: at least one mobile panel belonging to an aircraft nacelle; a plurality of actuators on each of said at least one mobile panel; at least two motors driving said plurality of actuators, wherein each one of said plurality of actuators is controlled by its own motor from said at least two motors; and first and second control units, wherein the first control unit controls and powers at least one of said at least two motors, wherein the second control unit controls and powers others of said at least two motors, and wherein said at least two motors are neither powered nor controlled by other one of said first and second control units. Claim: 2. The system according to claim 1 , wherein the first and second control units are separate and each powered by a power source, the power sources being independent of one another. Claim: 3. The system according to claim 1 , wherein the first and second control units are grouped together within one primary unit. Claim: 4. The system according to claim 1 , wherein each of the first and second control units delivers sufficient power for a single motor configured to actuate said plurality of actuators. Claim: 5. The system according to claim 1 , further comprising locking means immobilizing said plurality of actuators. Claim: 6. The system according to claim 5 , wherein the locking means are primary bolts associated with a tertiary bolt powered by a power source separate from the first and second control units. Claim: 7. The system according to claim 6 , wherein the first and second control units each comprise an internal stop means configured to stop the power supply of the locking means, the two internal stop means being connected to each other and an external stop means controlled independently of the first and second control units. Claim: 8. The system according to claim 7 , wherein each internal stop means is controlled by an aircraft computer configured to process data coming from an aircraft and by a nacelle computer configured to process data coming from a turboreactor, said nacelle computers being separate and independent. Claim: 9. The system according to claim 8 , wherein the external stop means is controlled by the aircraft computer. Claim: 10. The system according to claim 9 , wherein the nacelle computer includes electrical synchronization means of said at least two motors. Claim: 11. The system according to claim 8 , wherein signals of the states of the locking means are managed by the nacelle computer. Claim: 12. The system according to claim 8 , wherein the nacelle computer is powered by two separate electrical power systems that are powered or cut on during flight of the aircraft. Claim: 13. The system according to claim 7 , wherein each of the first and second control units has a logic synchronization means connected to the internal stop means and an input of a computer of a turboreactor. Claim: 14. The system according to claim 13 , wherein each of the internal and external stop means comprises a switch and a control device. Claim: 15. A nacelle for a dual-flow turboreactor having an outer structure defining an annular flow channel for a cold air flow, said outer structure comprising at least one mobile panel equipped with the system according to claim 1 . Claim: 16. The nacelle according to claim 15 , wherein the at least one mobile panel is a thrust reversal cowl configured to move substantially laterally. Claim: 17. The nacelle according to claim 15 , wherein the at least one mobile panel is a jet nozzle flap pivotably mounted so as to reduce a width of the annular flow channel. Claim: 18. The nacelle according to claim 15 , further comprising at least one thrust reversal cowl and at least one jet nozzle panel. Patent References Cited: 6439504 August 2002 Ahrendt ; 6681559 January 2004 Johnson ; 7370468 May 2008 Colotte et al. ; 7673442 March 2010 Seda et al. ; 2003/0101712 June 2003 Johnson et al. ; 1413735 April 2004 ; 1413736 April 2004 ; 1413737 April 2004 ; 2882097 August 2006 ; 2372729 September 2002 Other References: International Search Report issued Oct. 5, 2010 by European Patent Office re: International Application No. PCT/FR2010/050662; citing EP 1 413 736 A, EP 1 413 735 A, FR 2 882 097 A, GB 2 372 729 A, US 2003/101712 A1 and EP 1 413 737 A. cited by applicant Assistant Examiner: Goyal, Arun Primary Examiner: Rodriguez, William H Attorney, Agent or Firm: Brinks Gilson & Lione

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Control system for a turboreactor nacelle