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WO1997017254A1 - Systeme de commande d'helice a mise en drapeau et a pas reversible pour avions moyen courriers - Google Patents

Systeme de commande d'helice a mise en drapeau et a pas reversible pour avions moyen courriers Download PDF

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Publication number
WO1997017254A1
WO1997017254A1 PCT/RU1996/000367 RU9600367W WO9717254A1 WO 1997017254 A1 WO1997017254 A1 WO 1997017254A1 RU 9600367 W RU9600367 W RU 9600367W WO 9717254 A1 WO9717254 A1 WO 9717254A1
Authority
WO
WIPO (PCT)
Prior art keywords
slide valve
propeller
blades
angle
valve
Prior art date
Application number
PCT/RU1996/000367
Other languages
English (en)
Russian (ru)
Inventor
Jury Leonidovich Sukhorosov
Jury Mikhailovich Gnidkin
Jury Nikolaevich Vronsky
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 AU13228/97A priority Critical patent/AU1322897A/en
Publication of WO1997017254A1 publication Critical patent/WO1997017254A1/fr

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 available for aviation and, in particular, for systems for controlling airborne-propeller air propellers for aircraft of local airlines.
  • Izves ⁇ na ⁇ a ⁇ zhe sis ⁇ ema u ⁇ avleniya ⁇ lyuge ⁇ n ⁇ - ⁇ eve ⁇ sivnym v ⁇ zdushnym vin ⁇ m ⁇ yam ⁇ y s ⁇ emy, s ⁇ de ⁇ zhaschaya gid ⁇ me ⁇ anizm with "be ⁇ a" - ⁇ ub ⁇ y, sis ⁇ emu gid ⁇ avliches ⁇ i ⁇ ⁇ anal ⁇ v, ⁇ ye ⁇ as ⁇ l ⁇ zheny in the drive sleeve ⁇ uchn ⁇ g ⁇ u ⁇ avleniya shag ⁇ m vin ⁇ a and gid ⁇ avliches ⁇ i s ⁇ edineny with ⁇ l ⁇ s ⁇ yami b ⁇ lsh ⁇ g ⁇ and mal ⁇ g ⁇ step and ⁇ a ⁇ zhe ⁇ egulya ⁇ vin ⁇ a with masl ⁇ nas ⁇ s ⁇ m , with an operating valve,
  • This ventilator air vent system is only suitable for variable motor drives that have an off-wheel drive ⁇ ⁇ 97/17254 ⁇ 7 ⁇ 96 / 00367
  • FIG. 1 ⁇ ⁇ WRITINGS. ⁇ . SUMMARY OF THE INVENTION is illustrated in FIG. 1, where the system for controlling a jet-powered air rotor for aircraft of local airlines is shown, including the air rotor, regulator of the rotor and elements of the power system.
  • ⁇ ⁇ l ⁇ s ⁇ i SB ⁇ azmeschena ⁇ uzhina ⁇ lyugi ⁇ vaniya 14.
  • ⁇ egulya ⁇ vin ⁇ a 4 s ⁇ de ⁇ zhi ⁇ masl ⁇ nas ⁇ s 15 ⁇ edu ⁇ tsi ⁇ nny ⁇ la ⁇ an 16 ⁇ uzhin ⁇ y 17 z ⁇ l ⁇ ni ⁇ tsen ⁇ bezhn ⁇ g ⁇ me ⁇ anizma 18 s ⁇ edinenny che ⁇ ez ⁇ b ⁇ a ⁇ ny ⁇ la ⁇ an 19 nas ⁇ s ⁇ m 15.
  • Access to the 29th side of the drive unit 23 is connected to the hydraulic channel 5 of the adjacent 31th vehicle and the vehicle is connected to the vehicle 5 Gid ⁇ tsilind ⁇ 6 sh ⁇ 8 and left 9 ⁇ ave ⁇ sy ⁇ ets u ⁇ avlyayuscheg ⁇ z ⁇ l ⁇ ni ⁇ a 23 ⁇ b ⁇ azuyu ⁇ ⁇ l ⁇ s ⁇ , ⁇ aya s ⁇ edinena s ⁇ sliv ⁇ m and ⁇ y s ⁇ sn ⁇ u ⁇ avlyayuschemu z ⁇ l ⁇ ni ⁇ u 23 ⁇ azmeschen ⁇ dvizhny ⁇ lunzhe ⁇ 32 ⁇ uzhin ⁇ y 33.
  • the lever for operating 41 is located in the pilot's cabin and is kinematically connected to the control of screw 4, as well as to the quick-loading unit.
  • the operation of the claimed system for controlling a fly-rotary 20 air rotor is operated by the following method.
  • the equipment of the control system is widely known, which ensures the unnecessary frequency of the rotation of the air through the screw by one step.
  • the central operating mechanism of regulator 4 is changed with a constant pressure of 18.
  • the value of the negative pressure does not take into account ⁇ 97/17254 ⁇ / ⁇ 96 / 00367
  • the screw spares are mounted on the corner of an intermediate unit.
  • thrust 35 through cam 37 places the occupant of withdrawal from unit 20 to the lower position.
  • step 7 last-minute effort of suppers
  • the 20 range of pressures in the screw cavity is at most 7 with a large discontinuous force and is intended to reduce the pitch of the blades to the maximum rotational angle.
  • the screw is operated by means of the forced shut-off of the 21-year-old male occupant at the end of the drive to the "no-go" cabin. Simultaneously with the shift lever 41 to the "flyugra” position, the engine is switched off and the fuel is turned off.
  • channel 5 of the working fluid to the screw is disconnected from the regulated pressure
  • the spare parts are installed at the end of the load due to the efforts developed by the body weights on the spare parts 3 and the spring 14.
  • the output from the plug is made by turning on the electric plug pump 22. With the engine off and
  • 25% of the operating speed of the rotational switch of the regulator is equal to zero or much lower than the equilibrium value;

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Nitrogen And Oxygen Or Sulfur-Condensed Heterocyclic Ring Systems (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Cette invention se rapporte au domaine de l'aéronautique et concerne notamment un système hydromécanique comportant un canal de commande d'hélice à mise en drapeau et à pas réversible pour des avions de type moyen courrier. Le système de commande de l'hélice comprend les éléments suivants situés dans le moyeu (1) de ladite hélice: un mécanisme hydraulique de changement de la position des pales (3), lequel comporte un piston (7), un ressort de mise en drapeau (14) ainsi qu'un clapet de commande (23) de l'hélice dont les alésages (25) et (26) sont en communication avec les chambres de pas élevé (12) et de pas réduit (13), ainsi qu'avec le canal de purge (27); un régulateur de l'hélice (4) comportant un clapet à mécanisme centrifuge (18) et un clapet de retrait des pales de la butée d'angle intermédiaire (20); et, enfin, une pompe à huile (15) avec un clapet réducteur (16), la butée d'angle intermédiaire se composant, quant à elle, d'un plongeur (32) et d'un ressort (33) situés devant le piston (7). Le clapet de commande de l'hélice (23) est fixé sur le piston (7) de manière à pouvoir effectuer un mouvement axial limité et entrer en interaction avec le plongeur (32) lorsque les pales sont en butée d'angle intermédiaire. L'extrémité du clapet de commande de l'hélice comporte en outre, du côté opposé à la butée, une chambre (29) dans laquelle un fluide de travail à pression variable est envoyé depuis le clapet à mécanisme centrifuge. Au dessus de ce dernier se trouve un piston de recalage (38) comportant une tige (39), lesquels vont interrompre, en fonction de la commande du clapet de retrait des pales de la butée d'angle intermédiaire (20), le fonctionnement du clapet à mécanisme centrifuge, et assurer l'alimentation en fluide de travail de la chambre (29) du clapet de commande de l'hélice directement depuis le clapet réducteur (16). Afin de régler l'angle de calage des pales de l'hélice en mode inversé, il est nécessaire d'augmenter le serrage du ressort du clapet réducteur par rapport à la manette des gaz de manière à exercer sur le clapet de commande de l'hélice une force capable de contrer celle du ressort (33) du plongeur (32).
PCT/RU1996/000367 1996-10-17 1996-12-30 Systeme de commande d'helice a mise en drapeau et a pas reversible pour avions moyen courriers WO1997017254A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU13228/97A AU1322897A (en) 1996-10-17 1996-12-30 System for controlling a feather-reversible propeller for local airline aircr aft

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU96120110A RU2099241C1 (ru) 1996-10-17 1996-10-17 Система управления флюгерно-реверсивным воздушным винтом для самолетов местных авиалиний
RU96120110 1996-10-17

Publications (1)

Publication Number Publication Date
WO1997017254A1 true WO1997017254A1 (fr) 1997-05-15

Family

ID=20186354

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU1996/000367 WO1997017254A1 (fr) 1996-10-17 1996-12-30 Systeme de commande d'helice a mise en drapeau et a pas reversible pour avions moyen courriers

Country Status (3)

Country Link
AU (1) AU1322897A (fr)
RU (1) RU2099241C1 (fr)
WO (1) WO1997017254A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6673108B2 (en) 1999-07-20 2004-01-06 Medtronic, Inc Transmural concentric multilayer ingrowth matrix within well-defined porosity

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU67587A1 (ru) * 1942-02-15 1945-11-30 Л.С. Файн Устройство дл реверсировани винта с автоматическим изменением шага
DE3733407A1 (de) * 1986-10-02 1988-04-14 United Technologies Corp Propellerverstelleinrichtung
US5037271A (en) * 1989-12-26 1991-08-06 United Technologies Corporation Pitch control system
US5141399A (en) * 1990-10-18 1992-08-25 United Technologies Corporation Pitch change control system
RU2030327C1 (ru) * 1991-06-28 1995-03-10 Гордеев Виктор Федорович Система флюгирования воздушного винта изменяемого шага

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU67587A1 (ru) * 1942-02-15 1945-11-30 Л.С. Файн Устройство дл реверсировани винта с автоматическим изменением шага
DE3733407A1 (de) * 1986-10-02 1988-04-14 United Technologies Corp Propellerverstelleinrichtung
US5037271A (en) * 1989-12-26 1991-08-06 United Technologies Corporation Pitch control system
US5141399A (en) * 1990-10-18 1992-08-25 United Technologies Corporation Pitch change control system
RU2030327C1 (ru) * 1991-06-28 1995-03-10 Гордеев Виктор Федорович Система флюгирования воздушного винта изменяемого шага

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 (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6673108B2 (en) 1999-07-20 2004-01-06 Medtronic, Inc Transmural concentric multilayer ingrowth matrix within well-defined porosity

Also Published As

Publication number Publication date
AU1322897A (en) 1997-05-29
RU2099241C1 (ru) 1997-12-20

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