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WO1997017252A1 - Systeme et procede de commande d'helice a pas variable et a retour d'asservissement - Google Patents

Systeme et procede de commande d'helice a pas variable et a retour d'asservissement Download PDF

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Publication number
WO1997017252A1
WO1997017252A1 PCT/RU1996/000352 RU9600352W WO9717252A1 WO 1997017252 A1 WO1997017252 A1 WO 1997017252A1 RU 9600352 W RU9600352 W RU 9600352W WO 9717252 A1 WO9717252 A1 WO 9717252A1
Authority
WO
WIPO (PCT)
Prior art keywords
vinτa
uπρavleniya
control system
lοπasτey
fact
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/RU1996/000352
Other languages
English (en)
Russian (ru)
Inventor
Jury Leonidovich Sukhorosov
Jury Nikolaevich Vronsky
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Otkrytoe Aktsionernoe Obschestvo 'nauchno-Proizvodstvennoe Predpryatie 'aerosila'
Original Assignee
Otkrytoe Aktsionernoe Obschestvo 'nauchno-Proizvodstvennoe Predpryatie 'aerosila'
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 Otkrytoe Aktsionernoe Obschestvo 'nauchno-Proizvodstvennoe Predpryatie 'aerosila' filed Critical Otkrytoe Aktsionernoe Obschestvo 'nauchno-Proizvodstvennoe Predpryatie 'aerosila'
Priority to AU12146/97A priority Critical patent/AU1214697A/en
Publication of WO1997017252A1 publication Critical patent/WO1997017252A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/38—Blade pitch-changing mechanisms fluid, e.g. hydraulic
    • B64C11/40—Blade pitch-changing mechanisms fluid, e.g. hydraulic automatic

Definitions

  • the invention is limited to aviation technology and, in particular, to electric-hydraulic systems and automatic air-drive systems.
  • the aforementioned area of the system is known to have a system for controlling the air rotors of a screw due to the inoperative condition of the inverter.
  • the availability of electronic communication with the user allows the user to share current / mains / installations of the equipment for the subsequent transmission of information to the computer for the removal of data from the computer;
  • the system of control of the air rotor of a variable circuit of the circuit is known, which contains an electric unit of control of the frequency of rotation of the rotor of a screw that is electrically volatile. ⁇ 97/17252 ⁇ 96 / 00352
  • U ⁇ azannye ⁇ itsa ⁇ elnye ⁇ a ⁇ y giving summa ⁇ nuyu ⁇ g ⁇ eshn ⁇ s ⁇ susches ⁇ venn ⁇ y value not ⁇ zv ⁇ lyayu ⁇ is ⁇ lz ⁇ va ⁇ signal ⁇ e ⁇ uscheg ⁇ ugl ⁇ v ⁇ g ⁇ ⁇ l ⁇ zheniya l ⁇ as ⁇ ey for ⁇ ganizatsii zaschi ⁇ ny ⁇ s ⁇ eds ⁇ v vin ⁇ a ⁇ i ⁇ aza ⁇ , ⁇ a ⁇ ⁇ a ⁇ v ⁇ zm ⁇ zhn ⁇ l ⁇ zhn ⁇ e i ⁇ s ⁇ aba ⁇ yvanie.
  • the means of controlling the variable pitch air rotor with the electronic communication equipped with an electronic speed control and hydraulic ⁇ ⁇ 97/17252 ⁇ / ⁇ 96 / 00352
  • Fig. 2 an air screw of a variable pitch at a larger scale
  • Fig. 3 a node of a sensor for supplying rotor parts of a screw on an increased scale
  • FIG. 4 is a structural block diagram of the control system.
  • Beta-Tube 6 combined with T-10 and T-5, its final end is associated with an oil-fused unit ⁇ 97/17252 ⁇ 96 / 00352
  • ⁇ ⁇ ezul ⁇ a ⁇ e ⁇ a ⁇ g ⁇ is ⁇ lneniya communication be ⁇ a- ⁇ ub ⁇ i 6 se ⁇ dechni ⁇ m 13 izbegayu ⁇ v ⁇ ascheniya ⁇ sledneg ⁇ , ⁇ a ⁇ ⁇ a ⁇ ⁇ us 16 da ⁇ chi ⁇ a za ⁇ i ⁇ si ⁇ van ⁇ n ⁇ si ⁇ eln ⁇ s ⁇ a ⁇ a ⁇ edu ⁇ a dviga ⁇ elya ⁇ s ⁇ eds Your current item.
  • ⁇ a ⁇ uzhnaya ⁇ ub ⁇ a 6 provided ⁇ s ⁇ av ⁇ y 22 u ⁇ l ⁇ neniyami ⁇ tsen ⁇ i ⁇ uyuschim ⁇ yas ⁇ am and sluzhi ⁇ for ⁇ dv ⁇ da ⁇ l ⁇ s ⁇ b ⁇ lsh ⁇ g ⁇ oil in step 23.
  • P ⁇ i e ⁇ m ⁇ us 16 da ⁇ chi ⁇ a ⁇ s ⁇ yann ⁇ ⁇ dzha ⁇ ⁇ v ⁇ ul ⁇ e node 26 be ⁇ a- ⁇ ub ⁇ i ⁇ uzhin ⁇ y 27 and vmes ⁇ e with uzl ⁇ m ⁇ dshi ⁇ ni ⁇ a 25, 28 and shlitsev ⁇ y v ⁇ ul ⁇ y ⁇ mezhu ⁇ chn ⁇ y gilz ⁇ y 29 ⁇ b ⁇ azuyu ⁇ single me ⁇ aniches ⁇ i connected in ⁇ sev ⁇ m na ⁇ avlenii ⁇ a ⁇ e ⁇ de ⁇ aley, ⁇ i ⁇ e ⁇ lenny ⁇ ⁇ usu 1 vin ⁇ a Bolshety 30, extension 25, by performing the conversion of the spare parts to the rotary, ensures the availability of the specified product.
  • the control channels are equipped with a step-by-step screw and a 40-port I vin ⁇ a ⁇ ⁇ g ⁇ anichi ⁇ elya ma ⁇ simaln ⁇ y chas ⁇ y v ⁇ ascheniya with ele ⁇ magni ⁇ nym ⁇ la ⁇ an ⁇ m 41 ele ⁇ iches ⁇ i related da ⁇ chi ⁇ m 7 ugl ⁇ v ⁇ g ⁇ ⁇ l ⁇ zheniya l ⁇ as ⁇ ey che ⁇ ez ele ⁇ nny bl ⁇ 32 (usl ⁇ vn ⁇ e iz ⁇ b ⁇ azhenie u ⁇ myanu ⁇ y ⁇ azan ⁇ communication line 42) .Ene ⁇ ge ⁇ iches ⁇ e ⁇ i ⁇ anie elemen ⁇ v sis ⁇ emy and vin ⁇ a ⁇ bes ⁇ echen ⁇ ⁇ s ⁇ eds ⁇ v ⁇ m masl ⁇ nas ⁇ s ⁇ v: ⁇ sn ⁇ vn ⁇ g ⁇ ⁇ lyuge ⁇ n ⁇ g ⁇ 43 and 44.
  • the changing magnetic field after the working process leads the emf in the measurement compartment of the probes, the electrical signal is removed from the outputs of the probes, and the mains is connected to the angle of the mains drive.
  • the last, interrupting the communication channels 46 and 47, is to proceed from the installation of the screw from the electrical unit 32 to the installation of the hydraulic proprietary 34 Nia, ⁇ y ⁇ ⁇ analu 48 ⁇ adae ⁇ vys ⁇ e pressure ⁇ ab ⁇ chey zhid ⁇ s ⁇ i che ⁇ ez z ⁇ l ⁇ ni ⁇ i 40 and 36 in ⁇ anal mal ⁇ g ⁇ step.
  • control system also has a whole range of friends, for example:
  • the control system also implements the minimum clearance angle on the base of the monitoring system: sleeve 26 - 19 19 in the beta unit.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Wind Motors (AREA)
  • Nitrogen And Oxygen Or Sulfur-Condensed Heterocyclic Ring Systems (AREA)

Abstract

Cette invention se rapporte au domaine de l'aéronautique et son résultat technique consiste en une meilleure précision dans la mesure des angles courants de calage des pales. Ce résultat consiste également en une plus grande fiabilité du fonctionnement du système, ceci grâce à des dispositifs de protection contre les écarts incontrôlables de l'hélice à des angles élevés de calage des pales, et à l'aide d'un signal indiquant la position courante des pales. A cette fin, le système de commande de l'hélice à pas variable et à retour d'asservissement se présente sous forme d'un tube bêta (6) se trouvant en coopération avec un capteur (7) de la position angulaire des pales (2). Ce système comprend une unité de commande électronique (32), un convertisseur électro-hydraulique (33), un limiteur hydromécanique à maximum de fréquence (34), ainsi que des canaux de commande de l'hélice comportant un élément de régulation qui se présente sous forme, par exemple, de clapets à tiroir. Ce système se caractérise par la liaison mécanique, dans le sens axial, du corps (16) du capteur (7) au corps (1) de l'hélice ou à l'arbre d'entraînement de l'hélice par une unité de type palier (25). Ce système se caractérise en outre par le fait que les canaux de commande comportent un clapet à tiroir (40) qui est actionné par un clapet électromagnétique (41) et qui permet de passer d'un mode de commande par l'unité électronique en un mode de commande par le limiteur hydromécanique à maximum de fréquence de rotation. L'électro-aimant (41), enfin, est connecté électriquement au capteur de position angulaire des pales par l'intermédiaire de l'unité de commande électronique.
PCT/RU1996/000352 1996-10-17 1996-12-23 Systeme et procede de commande d'helice a pas variable et a retour d'asservissement Ceased WO1997017252A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU12146/97A AU1214697A (en) 1996-10-17 1996-12-23 System and method for adjusting a variable-step propeller with feedback

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU96120109 1996-10-17
RU96120109A RU2108268C1 (ru) 1996-10-17 1996-10-17 Система и способ управления воздушным винтом изменяемого шага с обратной связью

Publications (1)

Publication Number Publication Date
WO1997017252A1 true WO1997017252A1 (fr) 1997-05-15

Family

ID=20186353

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU1996/000352 Ceased WO1997017252A1 (fr) 1996-10-17 1996-12-23 Systeme et procede de commande d'helice a pas variable et a retour d'asservissement

Country Status (3)

Country Link
AU (1) AU1214697A (fr)
RU (1) RU2108268C1 (fr)
WO (1) WO1997017252A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008147451A3 (fr) * 2007-01-15 2009-03-19 Sikorsky Aircraft Corp Système de poussée en translation pour un aéronef à voilure tournante
EP3354562A1 (fr) * 2017-01-30 2018-08-01 Ge Avio S.r.l. Dispositif d'écrasement de palier de transfert
US10850831B2 (en) * 2018-12-21 2020-12-01 Honeywell International Inc. Propeller pitch control system for aircraft turboprop engines

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3011048B1 (fr) * 2013-09-24 2016-05-13 Snecma Dispositif d'alimentation en fluide hydraulique d'un verin et mecanisme de commande de pas des pales d'une helice de turbomoteur comportant le verin

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4523891A (en) * 1983-06-15 1985-06-18 United Technologies Corporation Propeller pitch change actuation system
EP0311277A2 (fr) * 1987-10-03 1989-04-12 Dowty Rotol Limited Dispositif pour pale d'hélice
US5174718A (en) * 1991-08-12 1992-12-29 United Technologies Corporation Blade pitch change control system
EP0652154A1 (fr) * 1993-11-10 1995-05-10 Hispano-Suiza Procédé et dispositif de commande de variation du pas des pales d'un rotor

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4523891A (en) * 1983-06-15 1985-06-18 United Technologies Corporation Propeller pitch change actuation system
EP0311277A2 (fr) * 1987-10-03 1989-04-12 Dowty Rotol Limited Dispositif pour pale d'hélice
US5174718A (en) * 1991-08-12 1992-12-29 United Technologies Corporation Blade pitch change control system
EP0652154A1 (fr) * 1993-11-10 1995-05-10 Hispano-Suiza Procédé et dispositif de commande de variation du pas des pales d'un rotor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
TEKHNICHESKOE OPISANIE, 1959, GOSUDARSTVENNOE IZDATELSTVO OBORONNOI PROMYSHLENNOSTI (Moscow), "Aviatsionny Turbovintovoi Dvigatel AI-20", pages 103-112. *

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008147451A3 (fr) * 2007-01-15 2009-03-19 Sikorsky Aircraft Corp Système de poussée en translation pour un aéronef à voilure tournante
US7758310B2 (en) 2007-01-15 2010-07-20 Sikorsky Aircraft Corporation Translational thrust system for a rotary wing aircraft
EP3354562A1 (fr) * 2017-01-30 2018-08-01 Ge Avio S.r.l. Dispositif d'écrasement de palier de transfert
WO2018138295A1 (fr) * 2017-01-30 2018-08-02 Ge Avio S.R.L. Dispositif de pliage de support de transfert
CN110300702A (zh) * 2017-01-30 2019-10-01 通用电气阿维奥有限责任公司 传动轴承伸缩装置
US11161598B2 (en) 2017-01-30 2021-11-02 Ge Avio S.R.L. Transfer bearing collapsing device
US10850831B2 (en) * 2018-12-21 2020-12-01 Honeywell International Inc. Propeller pitch control system for aircraft turboprop engines

Also Published As

Publication number Publication date
AU1214697A (en) 1997-05-29
RU2108268C1 (ru) 1998-04-10

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