EP0068728A1 - Servosystem - Google Patents

Servosystem Download PDF

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Publication number
EP0068728A1
EP0068728A1 EP82303139A EP82303139A EP0068728A1 EP 0068728 A1 EP0068728 A1 EP 0068728A1 EP 82303139 A EP82303139 A EP 82303139A EP 82303139 A EP82303139 A EP 82303139A EP 0068728 A1 EP0068728 A1 EP 0068728A1
Authority
EP
European Patent Office
Prior art keywords
control
valve
jack
break
circuit
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.)
Withdrawn
Application number
EP82303139A
Other languages
English (en)
French (fr)
Inventor
Peter Arthur Henry Brammer
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.)
Westland Group PLC
Original Assignee
Westland PLC
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 Westland PLC filed Critical Westland PLC
Publication of EP0068728A1 publication Critical patent/EP0068728A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B18/00—Parallel arrangements of independent servomotor systems

Definitions

  • THIS INVENTION relates to a servo system and particularly to a servo system for use in positioning aircraft control surfaces or in adjusting the pitch of helicopter rotor blades.
  • the pitch of helicopter rotor blades can be controlled by hydraulic jacks.
  • Three such jacks may be provided and adapted respectively to cater for cyclic fore-and-aft, cyclic lateral and collective blade movements.
  • Each jack is controlled by a duplicated servo control system in order that adequate control is maintained in the event of a failure, such as seizure of a main spool valve, in one of the systems.
  • GB-A-2057718 describes a servo system in which duplicity is provided by identical servo valves 20a and 20b controlled by a single switching valve 22 to adjust the position of a servo motor 4.
  • the switching valve operates automatically to connect the remaining servo valve to the motor so that essential control is maintained; however it is to be noted that further movements of control rod 40 have to be accomplished against the loading imposed by the spring member 42a or 42b associated with the failed servo valve 20a or 20b.
  • the invention provides a servo system having a servo control circuit adapted to control the flow of pressurised fluid to a hydraulic control jack, the control circuit including a main spool valve for controlling the flow of pressurised fluid to chambers at each side of a piston in the jack in response to movement of a control means, a break-out valve operative in the event of a failure of the spool valve and in response to a subsequent movement of the control means to connect a source of pressurised fluid to operate a by-pass valve to open a circuit between the chambers of the jack.
  • the break-out valve includes isolating means adapted to isolate the valve from subsequent movements of the control means.
  • the isolating means may include a boss located in a chamber of the break-out valve and operatively associated with the control means, a sliding land located at each side of the boss, spring means normally operative to force the lands into contact with opposed surfaces of the boss and with a fixed abutment provided in the chamber, two pressurised fluid inlet conduits opening into the chamber so as to obturated by the respective lands during normal operation of the system, and an outlet conduit opening into the chamber between the lands and operatively connected to the by-pass valve.
  • the boss may be located intermediate the ends of an axially movable rod protruding from one end of the chamber of the break-out valve for pivotal connection to the control means.
  • the break-out valve outlet conduit may connect to a chamber at one side of a piston head of the by-pass valve, the piston head carrying a spool having spaced-apart lands controlling an interconnection between the chambers of the control jack.
  • a coil spring may act on the piston head in the same sense as pressurised fluid from the break-out valve outlet conduit and may be opposed by pressurised fluid acting on a reduced diameter of one of the lands.
  • the break-out valve outlet conduit may incorporate a non-return valve, and a pressure switch indicator may be adapted to provide an indication of fluid pressure in the outlet conduit.
  • the protruding end of the movable rod may be pivotally connected to one end of a lever the other end of which is pivotally connected to an end of an operating rod protruding from the spool valve, the control means being pivotally attached intermediate the ends of the lever.
  • the control means may comprise a control rod pivotally earthed to a moving body of the control jack.
  • control circuit may be duplicated to maintain operation of the jack in the event of a failure in one of the control circuits.
  • the invention provides a servo system including duplex servo control circuits each adapted during operation to control the flow of pressurised fluid to a common hydraulic jack, each circuit having a main spool valve for controlling the flow of pressurised fluid to chambers at each side of a piston in the jack in response to movement of a control means, a break-out valve operative in the event of a failure of the spool valve and in response to a subsequent movement of the control means to connect a source of pressurised fluid to operate a by-pass valve to open a circuit between chambers of the jack served by the failed circuit whereby continuous control of the position of the jack is provided by the second circuit, the break-out valve including isolating means adapted to isolate the valve from subsequent movements of the control means.
  • the invention provides in or for a helicopter powered flying control system, a servo system including duplex servo control circuits each adapted during operation to control the position of a common hydraulic jack, each circuit having a main spool valve for controlling the flow of pressurised fluid to chambers at each side of a piston in the jack in response to movement of a control stick, a break-out valve operative in the event of a failure of the spool valve and in response to a subsequent movement of the control stick to connect a source of pressurised fluid to operate a by-pass valve to open a circuit between the chambers of the jack served by the failed circuit whereby continued control of the position of the jack is provided by the second circuit.
  • duplex servo control circuits each adapted during operation to control the position of a common hydraulic jack, each circuit having a main spool valve for controlling the flow of pressurised fluid to chambers at each side of a piston in the jack in response to movement of a control stick, a break-out valve operative
  • a moving body control jack 11 is operationally connected to duplicated servo control circuits 12a and 12b which, in turn, are both operationally connected to control means comprising a control stick 13.
  • the control jack 11 comprises a body 14 formed with separated, longitudinally aligned chambers 15.
  • a piston 16 is located in each chamber 15, the pistons 16 being interconnected by a rod 17 and earthed to aircraft structure as indicated at 18.
  • Each of the pistons 16 subdivides its respective chamber 15 into chambers 15a and 15b.
  • Control stick 13 is pivotally attached to structure at 19 and is connected by rods 20a and 20b to pivotal attachments 21a and 21b intermediate the ends of input levers 22a and 22b respectively.
  • the structure for attachment 19 comprises the body 14 of control jack 11.
  • each of the control circuits 12a and 12b are identical, and the reference numerals in the following description are marked on the left hand circuit 12a only.
  • the letters P and R denote hydraulic pressure supplies and hydraulic return connections respectively.
  • lever 22a is connected through pivotal attachment 23 to an end of a rod 24 protruding axially from an end of a main spool valve 25.
  • the rod carries two lands 26 in a chamber of the valve 25, the axial position of the lands 26 serving to control the flow of pressurised hydraulic fluid from a pressure source to output conduits 27 and 28.
  • Conduits 27 and 28 are connected respectively to chambers 15a and 15b of one chamber 15 of control jack 11.
  • a branch conduit 29 connects conduit 27 to a chamber 30 formed in a by-pass valve 31 between two spaced-apart lands 32 and 33 of a spool attached to a piston head 34 having a larger diameter than that of the lands 32 and 33.
  • a coil spring 35 is located in a chamber 36 formed on the side of the piston head 34 opposite to that which carries the lands 32 and 33.
  • a branch conduit 37 connects conduit 28 also to the chamber 30, but at a position axially spaced from the connection of conduit 29, for a purpose to be explained.
  • lever 22a is connected through pivotal attachment 38 to a rod 39 protruding axially from one end of a break-out valve 40 having an internal chamber 41.
  • the rod 39 carries a fixed boss 42 between two sliding lands 43 and 44 which control the flow of hydraulic fluid between a bifurcated input conduit 45 and an output conduit 46.
  • a coil spring 47 is located in each end of chamber 41 and forces the lands 43 and 44 into a central position in the chamber 41 and in abutment with a stop 48 provided on the inner wall of chamber 41
  • Conduit 46 is filled with hydraulic fluid and connected to chamber 36 of by-pass valve 31.
  • a non-return valve 49 is fitted in conduit 46 and a branch conduit 50 downstream of non-return valve 49 includes a flow restrictor 51 and a pressure switch indicator 52.
  • control stick 13 through arc 53 is transmitted through rod 20a to pivot input lever 22a about a fixed pivot provided by connection 38 to adjust the position of lands 26 of the main spool valve 25 through the rod 24.
  • Movement of lands 26 from the illustrated null position serves to connect the supply of pressurised hydraulic fluid to one of the chambers 15a or 15b of one chamber 15 of control jack 11, thereby moving the body of jack 11 due to reaction with the fixed piston 16.
  • the preferred embodiment, with attachment 19 comprising the body 14 of control jack 11, provides an automatic feedback facility that is proportional to the input signal.
  • the pressurised fluid supply to by-pass valve 31 acts on the surface area of land 33 which overcomes the force of spring 35 acting on the larger surface area of piston 34 to retain the lands 32 and 33 in the position illustrated so as to prevent any flow of fluid between branch conduits 29 and 37.
  • Figure 2 illustrates operation of control circuit 12a in the event of a malfunction caused by sticking of the main spool valve 25.
  • Two failure cases will be described; namely, a case in which the main spool valve sticks with the lands 26 in the null position indicated in full line in Figure 2, and a case in which the lands 26 stick in a position other than the null position as indicated in broken line in Figure 2.
  • connection 23 becomes the fixed pivot and movement of control stick 13 acts to rock input lever 22a about this pivot to cause axial movement of rod 39 of break-out valve 40.
  • the axial spacing automatically established between the lands 43 and.44 of break-out valve 40 provides freedom of movement for the sliding rod 39 thereby effectively isolating the break-out valve 40 of the failed ciruit from further movements of the control stick, with the result that the valve 40 does not impose undesirable loadings on the control stick 13 which is therefore free to maintain control through the remaining operational circuit 12b.
  • Pressurised hydraulic fluid now flows through conduit 46 into chamber 36 of by-pass valve 31, and due to the larger area if the head of the piston 34, overcomes the pressure on the surface of land 33 to move the lands 32 and 33 to the position illustrated in Figure 2 to establish connection via chamber 30 of by-pass valve 31 between branch conduits 29 and 37.
  • the present invention provides a servo system which functions automatically in the event of a failure of the main spool valve in one of the duplex servo control circuits. Furthermore, apart from the initial load required to actuate the isolating means in the break-out valve 40 of the failed circuit by a subsequent movement of the control stick 13, the system ensures that no forces emanate from the failed circuit to hinder continued control by the remaining operational circuit.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluid-Pressure Circuits (AREA)
EP82303139A 1981-06-26 1982-06-16 Servosystem Withdrawn EP0068728A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB8119838 1981-06-26
GB8119838 1981-06-26

Publications (1)

Publication Number Publication Date
EP0068728A1 true EP0068728A1 (de) 1983-01-05

Family

ID=10522847

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82303139A Withdrawn EP0068728A1 (de) 1981-06-26 1982-06-16 Servosystem

Country Status (1)

Country Link
EP (1) EP0068728A1 (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0137052A1 (de) * 1983-09-07 1985-04-17 Feinmechanische Werke Mainz GmbH Prüfeinrichtung für redundante Flugsteuerung
EP0152714A1 (de) * 1984-01-09 1985-08-28 AEROSPATIALE Société Nationale Industrielle Flugsteuereinrichtung für Luftfahrzeuge
EP0546895A1 (de) * 1991-12-11 1993-06-16 AEROSPATIALE Société Nationale Industrielle Vorrichtung mit verminderter Störanfälligkeit zur Steuerung eines Hubschrauberrotors durch eine Taumelscheibe
EP0639499A1 (de) * 1993-08-20 1995-02-22 Lucas France Servosteuerungvorrichtung eines Steuerwerkes eines Flugzeuges
ES2156497A1 (es) * 1998-06-23 2001-06-16 Turbo Propulsores Ind Mejoras en el objeto de la patente 9801320, relativa a "sistema principal de servo-actuacion de piston con deteccion hidromecanica de fallos autocontenida.
EP3128216A1 (de) * 2015-08-07 2017-02-08 Claverham Limited Hydraulikventil
US20210139134A1 (en) * 2019-11-09 2021-05-13 Bell Textron Inc. Hydraulic cylinder with matching bias

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2006276A1 (de) * 1968-04-16 1969-12-26 Automotive Prod Co Ltd
DE1601713B2 (de) * 1967-12-22 1971-09-02 Dormer AG, 7990 Friedrichshafen Kontroll und scgalteinrichtungen an servosteuerungen
GB1306710A (en) * 1970-09-22 1973-02-14 Mainz Gmbh Feinmech Werke Hydraulic and pneumatic control systems
GB1327393A (en) * 1969-10-15 1973-08-22 Automotive Prod Co Ltd Fluid pressure control systems
GB1497594A (en) * 1974-10-23 1978-01-12 Messerschmitt Boelkow Blohm Hydraulic servodrive

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1601713B2 (de) * 1967-12-22 1971-09-02 Dormer AG, 7990 Friedrichshafen Kontroll und scgalteinrichtungen an servosteuerungen
FR2006276A1 (de) * 1968-04-16 1969-12-26 Automotive Prod Co Ltd
GB1327393A (en) * 1969-10-15 1973-08-22 Automotive Prod Co Ltd Fluid pressure control systems
GB1306710A (en) * 1970-09-22 1973-02-14 Mainz Gmbh Feinmech Werke Hydraulic and pneumatic control systems
GB1497594A (en) * 1974-10-23 1978-01-12 Messerschmitt Boelkow Blohm Hydraulic servodrive

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0137052A1 (de) * 1983-09-07 1985-04-17 Feinmechanische Werke Mainz GmbH Prüfeinrichtung für redundante Flugsteuerung
EP0152714A1 (de) * 1984-01-09 1985-08-28 AEROSPATIALE Société Nationale Industrielle Flugsteuereinrichtung für Luftfahrzeuge
EP0546895A1 (de) * 1991-12-11 1993-06-16 AEROSPATIALE Société Nationale Industrielle Vorrichtung mit verminderter Störanfälligkeit zur Steuerung eines Hubschrauberrotors durch eine Taumelscheibe
FR2684953A1 (fr) * 1991-12-11 1993-06-18 Aerospatiale Dispositif a vulnerabilite reduite pour la commande d'un rotor d'helicoptere par plateaux cycliques.
US5310315A (en) * 1991-12-11 1994-05-10 Aerospatiale Societe Nationale Industrielle Low-vulnerability device for the control of helicopter rotor by cyclic plates
EP0639499A1 (de) * 1993-08-20 1995-02-22 Lucas France Servosteuerungvorrichtung eines Steuerwerkes eines Flugzeuges
FR2709110A1 (fr) * 1993-08-20 1995-02-24 Lucas Air Equipement Dispositif de servocommande d'un organe de commande de vol d'aéronef.
US5600220A (en) * 1993-08-20 1997-02-04 Lucas France System for servo-controlling an aircraft flight control member
ES2156497A1 (es) * 1998-06-23 2001-06-16 Turbo Propulsores Ind Mejoras en el objeto de la patente 9801320, relativa a "sistema principal de servo-actuacion de piston con deteccion hidromecanica de fallos autocontenida.
EP3128216A1 (de) * 2015-08-07 2017-02-08 Claverham Limited Hydraulikventil
US10036408B2 (en) 2015-08-07 2018-07-31 Claverham Ltd. Hydraulic valve
US20210139134A1 (en) * 2019-11-09 2021-05-13 Bell Textron Inc. Hydraulic cylinder with matching bias

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PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

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STAA Information on the status of an ep patent application or granted ep patent

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Effective date: 19831211

RIN1 Information on inventor provided before grant (corrected)

Inventor name: BRAMMER, PETER ARTHUR HENRY