GB973364A - Fluid-pressure-operated-systems - Google Patents

Fluid-pressure-operated-systems

Info

Publication number
GB973364A
GB973364A GB3653861A GB3653861A GB973364A GB 973364 A GB973364 A GB 973364A GB 3653861 A GB3653861 A GB 3653861A GB 3653861 A GB3653861 A GB 3653861A GB 973364 A GB973364 A GB 973364A
Authority
GB
United Kingdom
Prior art keywords
valve
line
circuit
pressure
emergency
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.)
Expired
Application number
GB3653861A
Inventor
Derek Charles Noel Harris
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.)
Dowty Rotol Ltd
Original Assignee
Dowty Rotol Ltd
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 Dowty Rotol Ltd filed Critical Dowty Rotol Ltd
Priority to GB3653861A priority Critical patent/GB973364A/en
Publication of GB973364A publication Critical patent/GB973364A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B64C25/18—Operating mechanisms
    • B64C25/22—Operating mechanisms fluid
    • 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
    • F15B20/00—Safety arrangements for fluid actuator systems; Applications of safety devices in fluid actuator systems; Emergency measures for fluid actuator systems
    • F15B20/004—Fluid pressure supply failure

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Analytical Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluid-Pressure Circuits (AREA)

Abstract

973,364. Aircraft control systems. DOWTY ROTOL Ltd. Oct. 9, 1962 [Oct. 11, 1961], No. 36538/61. Heading B7G. An aircraft fluid pressure system comprises two normally separate fluid circuits, each comprising a fluid pressure generator, a motor, a " normal " selector valve which can connect one side of the motor either to the generator or to reservoir, a normally unpressurized emergency line connecting the circuit with the other circuit, and an " emergency " selector valve which, on loss of pressure in the other circuit, can be adjusted to permit pressure fluid from its circuit to pass through the emergency line to power the motor of the other circuit. In the Figure, a pump 13 in a line 12, driven by an electric motor (not shown), delivers fluid from a tank 11 through filter 15 to an undercarriage jack 20 through a two-position valve 16 operable by a solenoid 34. The valve connects one of the jack lines 18, 23 to line 12, and the other to a return line 31 in known manner. Line 18 contains a shuttle valve 19 with piston 19a. A pressure branch line 25 and return branch line 30 including a one-way valve 33 are connected to an " emergency " valve 26 operable by hand or by a solenoid. The second circuit, with primed references, is identical. A line 28 leads from valve 26 to shuttle valve 19<SP>1</SP>, and a line 28<SP>1</SP> from valve 26<SP>1</SP> to shuttle valve 19. With valves 26, 26<SP>1</SP> in the position shown, the two circuits are separate. The valves 16, 16<SP>1</SP> are shown in the undercarriage down position, being changed over for the undercarriage up position. Should pressure fail in, say, the first circuit, valve 26<SP>1</SP> can be changed over, to make pressure fluid available from pump 13<SP>1</SP> through line 28<SP>1</SP> and shuttle valve 19 (piston 19a being displaced), to extend jack 20. Equally, jack 20<SP>1</SP> can be extended should its normal supply fail, by operation of valve 26. The connections between the two circuits may be repeated to allow emergency contraction of both jacks, and emergency operation of undercarriage bay doors. Lines 28 and 28<SP>1</SP> may be vented during normal operation to prevent thermal pressure build-up.
GB3653861A 1961-10-11 1961-10-11 Fluid-pressure-operated-systems Expired GB973364A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3653861A GB973364A (en) 1961-10-11 1961-10-11 Fluid-pressure-operated-systems

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3653861A GB973364A (en) 1961-10-11 1961-10-11 Fluid-pressure-operated-systems

Publications (1)

Publication Number Publication Date
GB973364A true GB973364A (en) 1964-10-28

Family

ID=10389069

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3653861A Expired GB973364A (en) 1961-10-11 1961-10-11 Fluid-pressure-operated-systems

Country Status (1)

Country Link
GB (1) GB973364A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0155771A1 (en) * 1984-02-28 1985-09-25 Powell Duffryn Engineering Limited Improvements relating to hydraulic fluid supply systems
GB2265670A (en) * 1992-03-18 1993-10-06 Hoerbiger Ventilwerke Ag An hydraulic actuating arrangement
EP1495961A1 (en) * 2003-07-08 2005-01-12 Liebherr-Aerospace Lindenberg GmbH Retractable undercarriage actuation system
FR2907097A1 (en) * 2006-10-17 2008-04-18 Messier Bugatti Sa HYDRAULIC SYSTEM ARCHITECTURE OF AIRCRAFT AIRBORNE MANEUVER
FR2907096A1 (en) * 2006-10-17 2008-04-18 Messier Bugatti Sa HYDRAULIC SYSTEM ARCHITECTURE OF AIRCRAFT AIRBORNE MANEUVER
EP4006360A1 (en) * 2020-11-30 2022-06-01 Eaton Intelligent Power Limited Redundant hydraulic power pack architecture for aircraft main landing gear system

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0155771A1 (en) * 1984-02-28 1985-09-25 Powell Duffryn Engineering Limited Improvements relating to hydraulic fluid supply systems
GB2265670A (en) * 1992-03-18 1993-10-06 Hoerbiger Ventilwerke Ag An hydraulic actuating arrangement
GB2265670B (en) * 1992-03-18 1995-11-22 Hoerbiger Ventilwerke Ag An hydraulic actuating arrangement
EP1495961A1 (en) * 2003-07-08 2005-01-12 Liebherr-Aerospace Lindenberg GmbH Retractable undercarriage actuation system
DE10330805B4 (en) * 2003-07-08 2015-07-30 Liebherr-Aerospace Lindenberg Gmbh Aircraft landing gear control
EP1914164A1 (en) * 2006-10-17 2008-04-23 Messier-Bugatti Architecture of a hydraulic system for manoeuvring the landing gear of an aircraft
FR2907096A1 (en) * 2006-10-17 2008-04-18 Messier Bugatti Sa HYDRAULIC SYSTEM ARCHITECTURE OF AIRCRAFT AIRBORNE MANEUVER
EP1914163A1 (en) * 2006-10-17 2008-04-23 Messier-Bugatti Architecture of a hydraulic system for manoeuvring aircraft landing gear
US8028954B2 (en) 2006-10-17 2011-10-04 Messier-Bugatti Architecture for a hydraulic system for operating aircraft landing gear
US8136760B2 (en) 2006-10-17 2012-03-20 Messier-Bugatti-Dowty Architecture for a hydraulic system for operating aircraft landing gear
FR2907097A1 (en) * 2006-10-17 2008-04-18 Messier Bugatti Sa HYDRAULIC SYSTEM ARCHITECTURE OF AIRCRAFT AIRBORNE MANEUVER
EP4006360A1 (en) * 2020-11-30 2022-06-01 Eaton Intelligent Power Limited Redundant hydraulic power pack architecture for aircraft main landing gear system
US12049302B2 (en) 2020-11-30 2024-07-30 Eaton Intelligent Power Limited Redundant hydraulic power pack architecture for aircraft main landing gear system

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