GB570030A - Improvements in and relating to aircraft controls - Google Patents

Improvements in and relating to aircraft controls

Info

Publication number
GB570030A
GB570030A GB113/44A GB11344A GB570030A GB 570030 A GB570030 A GB 570030A GB 113/44 A GB113/44 A GB 113/44A GB 11344 A GB11344 A GB 11344A GB 570030 A GB570030 A GB 570030A
Authority
GB
United Kingdom
Prior art keywords
aircraft
valve
piston
pipes
spring
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
GB113/44A
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.)
JOHN LESLIE HEWITT
Blackburn Aircraft Ltd
Original Assignee
JOHN LESLIE HEWITT
Blackburn Aircraft 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 JOHN LESLIE HEWITT, Blackburn Aircraft Ltd filed Critical JOHN LESLIE HEWITT
Priority to GB113/44A priority Critical patent/GB570030A/en
Publication of GB570030A publication Critical patent/GB570030A/en
Expired legal-status Critical Current

Links

Classifications

    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Fluid-Damping Devices (AREA)

Abstract

570,030. Controlling aircraft. BLACKBURN AIRCRAFT, Ltd., SMYT1-I, S. J., and HEWITT, J. L. Jan. 4, 1944, No. 113. [Class 4] A control system for aircraft having spring tab balanced control surfaces embodies means which progressively reduces the possible rate of movement of the control surfaces as the speed of the aircraft increases about a predetermined value. In the form shown, the control transmitting apparatus includes a piston rod 3 connected to a piston in a hydraulic cylinder 5, the ends of which are interconnected through pipes 6, 7, incorporating a throttling valve 9. The latter is provided with an elongated port 10 registering with the pipes 6, 7, and is moved against a spring 14 by pressure applied to a piston 11 from a pitot head, through a connection 13. The spring-engaging end of the valve 9 may be connected to a static head by a conduit 15, and a similar connection may be made to the low pressure side of the piston 11. Owing to the elongated form of the valve port 10, the valve 9 is permitted a predetermined axial movement, dependent upon the desired airspeed, before throttling of the fluid flow through the cylinder connecting pipes 6, 7, commences, with a consequent increase in the effort required to move the pilot's controls.
GB113/44A 1944-01-04 1944-01-04 Improvements in and relating to aircraft controls Expired GB570030A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB113/44A GB570030A (en) 1944-01-04 1944-01-04 Improvements in and relating to aircraft controls

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB113/44A GB570030A (en) 1944-01-04 1944-01-04 Improvements in and relating to aircraft controls

Publications (1)

Publication Number Publication Date
GB570030A true GB570030A (en) 1945-06-19

Family

ID=9698644

Family Applications (1)

Application Number Title Priority Date Filing Date
GB113/44A Expired GB570030A (en) 1944-01-04 1944-01-04 Improvements in and relating to aircraft controls

Country Status (1)

Country Link
GB (1) GB570030A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2548481A (en) * 1946-10-16 1951-04-10 Saunders Roe Ltd Flying control for aircraft
US2638289A (en) * 1949-02-05 1953-05-12 Northrop Aircraft Inc Hydraulic stick control
US2944770A (en) * 1954-08-04 1960-07-12 Ampatco Lab Corp Aircraft control system
US3807248A (en) * 1972-05-22 1974-04-30 R Hooper Variable speed drive control

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2548481A (en) * 1946-10-16 1951-04-10 Saunders Roe Ltd Flying control for aircraft
US2638289A (en) * 1949-02-05 1953-05-12 Northrop Aircraft Inc Hydraulic stick control
US2944770A (en) * 1954-08-04 1960-07-12 Ampatco Lab Corp Aircraft control system
US3807248A (en) * 1972-05-22 1974-04-30 R Hooper Variable speed drive control

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