IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0120662
(2008-05-15)
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등록번호 |
US-8170728
(2012-05-01)
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우선권정보 |
FR-07 03616 (2007-05-22) |
발명자
/ 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
12 인용 특허 :
12 |
초록
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A system (100) for controlling a rotorcraft (1) including a rotor (10), at least one variable-pitch propulsion propeller (6L, 6R), and a motor (5) for driving the rotor and the propeller(s), the system includes: a member (101, 101A, 102, 103, 104) for generating a propeller pitch setpoint (θp*+θd*,
A system (100) for controlling a rotorcraft (1) including a rotor (10), at least one variable-pitch propulsion propeller (6L, 6R), and a motor (5) for driving the rotor and the propeller(s), the system includes: a member (101, 101A, 102, 103, 104) for generating a propeller pitch setpoint (θp*+θd*, θp*−θd*) as a function at least of a thrust variation command (TCL);a member (105, 105A) for generating a setpoint (RPM*) for the drive speed (RPM) of the rotor and the propeller(s), as a function at least of the travel speed (VTAS) of the rotorcraft; anda member (106) for generating a setpoint (NG*) for the engine speed as a function at least of the thrust command (TCL), of the drive speed setpoint (RTM*), and of a rotor collective pitch command (θ0).
대표청구항
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1. A system for controlling a rotorcraft having a rotor, at least one variable-pitch propulsion propeller, and a motor for driving the rotor and the at least one variable-pitch propulsion propeller, the system comprising: a member (101, 101A, 102, 103, 104) configured to generate a propeller pitch s
1. A system for controlling a rotorcraft having a rotor, at least one variable-pitch propulsion propeller, and a motor for driving the rotor and the at least one variable-pitch propulsion propeller, the system comprising: a member (101, 101A, 102, 103, 104) configured to generate a propeller pitch setpoint (θp*+θd*, θp*−θd*) as a function at least of a variation thrust command (TCL);a member (105, 105A) configured to generate a drive speed setpoint (RPM*) for a drive speed (RPM) of the rotor and the at least one variable-pitch propulsion propeller, as a function at least of a travel speed (VTAS) of the rotorcraft and where appropriate as a function of ambient temperature; anda member (106) configured to generate an engine speed setpoint (NG*) for an engine speed as a function at least of the variation thrust command (TCL), of the drive speed setpoint (RPM*), and of a rotor collective pitch command (θ0);wherein the member (106) configured to generate the engine speed setpoint (NG*) includes: a member (109) configured to generate a first anticipated command for varying engine speed as a function of the rotor collective pitch command (θ0);a member (110) configured to generate a second anticipated command for varying engine speed as a function of the variation thrust command (TCL);a first summing circuit (111) for adding together the first and second anticipated commands for varying engine speed, and for outputting a first component (NG1*) of the engine speed setpoint (NG*); anda unit (112, 113, 114) configured to generate the engine speed setpoint (NG*) as a function of the first component (NG1*), of the drive speed setpoint (RPM*), and of a measurement of the drive speed (RPM). 2. The system according to claim 1, in which the member (105, 105A) configured to generate the drive speed setpoint (RPM*) for the drive speed (RPM) comprises: a member (107) configured to generate a reference drive speed (RPMref) as a function of the travel speed (VTAS) of the rotorcraft; anda limiter (108) sensitive to the reference drive speed (RPMref) and delivering the drive speed setpoint (RPM*). 3. The system according to claim 1, for a rotorcraft having two variable-pitch propulsion propellers that are disposed on either side of the fuselage of the rotorcraft, the system comprising: a member (101, 101A) configured to generate a mean pitch setpoint (θp*) for the mean pitch (θp) of the two variable-pitch propulsion propellers as a function of the variation thrust command (TCL);a member (102) configured to generate a pitch difference setpoint (θd*) for half the difference in pitch (θd) between the two variable-pitch propulsion propellers as a function of the rotor collective pitch variation command (θ0) and of a heading/yaw variation command (Pal);a summing circuit (103) for adding together the mean pitch setpoint (θp*) and the pitch difference setpoint (θd*), and for delivering the resulting setpoint (θp*+θd*) to a member for controlling the pitch of a first one of the two propellers; anda summing circuit used as a subtracter (104) for subtracting the pitch difference setpoint (θd*) from the mean pitch setpoint (θp*) and for delivering the resulting setpoint (θp*−θd*) to a pitch control member of the second propeller. 4. The system according to claim 3, in which the member (102) configured to generate a pitch difference setpoint (θd*) for half the pitch difference comprises: a decoupling unit (141) for collective-yaw decoupling, which decoupling unit receives the rotor collective pitch variation command (θ0);a processor unit (142) for processing a heading variation command (Pal);a summing circuit (143) connected to the decoupling unit and to the processor unit; anda lowpass filter (144) receiving as input the sum delivered by the summing circuit and delivering as output the pitch difference setpoint (θd*) for half the pitch difference. 5. The system according to claim 2, in which the member (105) configured to generate the drive speed setpoint (RPM*) for the drive speed (RPM) further comprises: a member (115) configured to generate a transient variation (RPMper) in the drive speed setpoint (RPM*) as a function of the variation thrust command (TCL); anda summing circuit (116) for adding the transient variation (RPMper) for the drive speed setpoint (RPM*) to the reference drive speed (RPMref) and for delivering said sum to the limiter (108) that delivers the drive speed setpoint (RPM*). 6. A non-transitory computer readable medium for a rotorcraft having a rotor, at least one variable-pitch propulsion propeller, and a motor for driving the rotor and the at least one variable-pitch propulsion propeller, the non-transitory computer readable medium comprising: a code segment for generating a propeller pitch setpoint (θp*+θd*, θp*−θd*) as a function at least of a thrust variation command (TCL);a code segment for generating a drive speed setpoint (RPM*) for a drive speed (RPM) of the rotor and of the at least one variable-pitch propulsion propeller, as a function at least of a travel speed (VTAS) of the rotorcraft; anda code segment for generating an engine speed setpoint (NG*) for an engine speed, as a function at least of the variation thrust command (TCL), of the drive speed setpoint (RPM*), and of a rotor collective pitch command (θ0);wherein the code segment for generating the engine speed setpoint (NG*) includes: a code segment for generating a first anticipated command for varying engine speed as a function of the rotor collective pitch command (θ0);a code segment for generating a second anticipated command for varying engine speed as a function of the variation thrust command (TCL);a code segment for adding together the first and second anticipated commands for varying engine speed, and for outputting a first component (NG1*) of the engine speed setpoint (NG*); anda code segment for generating the engine speed setpoint (NG*) as a function of the first component (NG1*), of the drive speed setpoint (RPM*), and of a measurement of the drive speed (RPM). 7. The non-transitory computer readable medium according to claim 6, in which the code segment for generating the drive speed setpoint (RPM*) for the drive speed (RPM) comprises a code segment for generating a reference drive speed (RPMref) that decreases as a function of the travel speed (VTAS) of the rotorcraft when the travel speed VTAS exceeds a determined speed V1. 8. A rotorcraft including a rotor, at least one variable-pitch propulsion propeller, and a motor for driving the rotor and the at least one variable-pitch propulsion propeller, the rotorcraft including the control system according to claim 1. 9. The rotorcraft according to claim 8, including two variable-pitch propulsion propellers that are disposed on either side of the fuselage of the rotorcraft, which rotorcraft does not have an anti-torque rotor and does include a direct driving power transmission system between the engine and the rotor and the propellers. 10. A system for controlling a rotorcraft having a rotor, at least one variable-pitch propulsion propeller, and a motor for driving the rotor and the at least one variable-pitch propulsion propeller, the system comprising: a member (101, 101A, 102, 103, 104) configured to generate a propeller pitch setpoint (θp*+θd*, θp*−θd*) as a function at least of a variation thrust command (TCL);a member (105, 105A) configured to generate a drive speed setpoint (RPM*) for a drive speed (RPM) of the rotor and the at least one variable-pitch propulsion propeller, as a function at least of a travel speed (VTAS) of the rotorcraft and where appropriate as a function of ambient temperature; anda member (106) configured to generate an engine speed setpoint (NG*) for an engine speed as a function at least of the variation thrust command (TCL), of the drive speed setpoint (RPM*), and of a rotor collective pitch command (θ0);wherein the member (105, 105A) configured to generate the drive speed setpoint (RPM*) for the drive speed (RPM) includes: a member (107) configured to generate a reference drive speed (RPMref) as a function of the travel speed (VTAS) of the rotorcraft;a limiter (108) sensitive to the reference drive speed (RPMref) and delivering the drive speed setpoint (RPM*);a member (115) configured to generate a transient variation (RPMper) in the drive speed setpoint (RPM*) as a function of the variation thrust command (TCL); anda summing circuit (116) for adding the transient variation (RPMper) for the drive speed setpoint (RPM*) to the reference drive speed (RPMref) and for delivering said sum to the limiter (108) that delivers the drive speed setpoint (RPM*).
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