GB872602A - Improvements in flying control systems for aircraft - Google Patents

Improvements in flying control systems for aircraft

Info

Publication number
GB872602A
GB872602A GB33437/57A GB3343757A GB872602A GB 872602 A GB872602 A GB 872602A GB 33437/57 A GB33437/57 A GB 33437/57A GB 3343757 A GB3343757 A GB 3343757A GB 872602 A GB872602 A GB 872602A
Authority
GB
United Kingdom
Prior art keywords
control
actuator
valve
aircraft
oct
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
GB33437/57A
Inventor
Roy Westbury
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.)
HM Hobson Ltd
Original Assignee
HM Hobson 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 HM Hobson Ltd filed Critical HM Hobson Ltd
Priority to GB33437/57A priority Critical patent/GB872602A/en
Publication of GB872602A publication Critical patent/GB872602A/en
Expired legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/0055—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements
    • G05D1/0077—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements using redundant signals or controls
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Fluid-Pressure Circuits (AREA)
  • Actuator (AREA)

Abstract

872,602. Fluid-pressure servo motor-control systems. HOBSON Ltd., H. M. Oct. 27, 1958 [Oct. 25, 1957], No. 33437/57. Class 135. [Also in Group XXXIII] In an aircraft flying control system a control surface is split into two sections, each section being provided with a pair of hydraulic actuators 10, 10A, the actuator control valves 13, 13A being coupled to a common pilot's control member by individual mechanical linkages 16, 16A, each linkage including a normally inoperative lost-motion connection, such as a spring box 17, permitting in an emergency, movement of the linkage in either direction in relation to the control valve. The actuator pistons 11, 11A are secured to the aircraft structure and the moving cylinders are attached to the control surface section. Floating lever type follow-up is provided for the control valves by means of levers 14, 14A. In order to prevent flutter in the event of a control valve seizing the supply line to each servo-control valve is provided with a non-return valve 20 to prevent movement of the jack due to aerodynamic forces. A restrictor 21 is placed in parallel with the non-return valve to permit the control surface to gradually assume a trailing position. The pistons 11, 11A may be of the differential area type. Each actuator may be supplied with motive fluid from an independent source.
GB33437/57A 1957-10-25 1957-10-25 Improvements in flying control systems for aircraft Expired GB872602A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB33437/57A GB872602A (en) 1957-10-25 1957-10-25 Improvements in flying control systems for aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB33437/57A GB872602A (en) 1957-10-25 1957-10-25 Improvements in flying control systems for aircraft

Publications (1)

Publication Number Publication Date
GB872602A true GB872602A (en) 1961-07-12

Family

ID=10352949

Family Applications (1)

Application Number Title Priority Date Filing Date
GB33437/57A Expired GB872602A (en) 1957-10-25 1957-10-25 Improvements in flying control systems for aircraft

Country Status (1)

Country Link
GB (1) GB872602A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2152244A (en) * 1983-12-30 1985-07-31 Brunswick Corp Integral valve and cylinder assembly for power steered marine drive
JP2012116466A (en) * 2010-11-29 2012-06-21 Nabtesco Corp Aircraft actuator hydraulic system

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2152244A (en) * 1983-12-30 1985-07-31 Brunswick Corp Integral valve and cylinder assembly for power steered marine drive
JP2012116466A (en) * 2010-11-29 2012-06-21 Nabtesco Corp Aircraft actuator hydraulic system

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