GB749253A - Improvements in or relating to control system for an airplane - Google Patents

Improvements in or relating to control system for an airplane

Info

Publication number
GB749253A
GB749253A GB2713/53A GB271353A GB749253A GB 749253 A GB749253 A GB 749253A GB 2713/53 A GB2713/53 A GB 2713/53A GB 271353 A GB271353 A GB 271353A GB 749253 A GB749253 A GB 749253A
Authority
GB
United Kingdom
Prior art keywords
force
stick
aircraft
spring
control
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
GB2713/53A
Inventor
Irving L Ashkenas
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.)
Northrop Grumman Corp
Original Assignee
Northrop Grumman Corp
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 Northrop Grumman Corp filed Critical Northrop Grumman Corp
Priority to GB2713/53A priority Critical patent/GB749253A/en
Publication of GB749253A publication Critical patent/GB749253A/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
    • B64C13/24—Transmitting means
    • 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)
  • Mechanical Control Devices (AREA)

Abstract

749,253. Controlling aircraft. NORTHROP AIRCRAFT, Inc. Jan. 30, 1953, No. 2713/53. Class 4. A control system for an aircraft having an elevation controlling surface operated by a pilot's control element without exerting feelback forces on the element, includes means for creating a first force varying in accordance with airspeed, means for creating a second force varying with normal accelerations of the aircraft, means for applying the first force to centre the pilot's control element, and means for applying the second force to modify the effect of the first force in a direction tending to move the control element to reduce normal acceleration. As shown in Fig. 3, the control stick 6 pivots about an axis 13, and the lower end of a trunnion block 10 is connected to a support 26 having a forwardly extending leg carrying a bob weight 28. A balance spring assembly 29 is connected between the leg and a bracket 30 on the aircraft structure and comprises a tension rod 32 surrounded by a compression spring 33; the spring assembly is provided with adjustment fittings 40, 41 by means of which the pull of the spring may be adjusted to a predetermined value at a given control stick position. The angle A between the axis of the spring assembly and its movement arm about the stick pivot 13 is preferably designed to be 90 degrees at some position within the normal range of stick movement, and the combination of the spring and the bob weight serves to detect normal acceleration and apply a restoring force to the stick. Attached to the support 26 is a bracket 45 connected by a link 46 to a lever 47 pivoted at one end about a bracket secured to the aircraft structure and connected at the other end to a connecting rod 49 connected to a bellows shaft 50 of a force bellows. The bellows comprises a diaphragm 55 subjected at one side to static pressure and at the other to dynamic air pressure. Thus a force is applied to the control stick which varies approximately as the square of the airspeed and which increases with displacement of the stick from neutral position.
GB2713/53A 1953-01-30 1953-01-30 Improvements in or relating to control system for an airplane Expired GB749253A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2713/53A GB749253A (en) 1953-01-30 1953-01-30 Improvements in or relating to control system for an airplane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2713/53A GB749253A (en) 1953-01-30 1953-01-30 Improvements in or relating to control system for an airplane

Publications (1)

Publication Number Publication Date
GB749253A true GB749253A (en) 1956-05-23

Family

ID=9744488

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2713/53A Expired GB749253A (en) 1953-01-30 1953-01-30 Improvements in or relating to control system for an airplane

Country Status (1)

Country Link
GB (1) GB749253A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2953494A1 (en) * 2009-12-08 2011-06-10 Goodrich Actuation Systems Sas DEVICE FOR TESTING THE DETECTION OF THE EFFORT RESUME BY A SECONDARY PATH OF A FLIGHT CONTROL ACTUATOR, AND ASSOCIATED TEST METHOD
US10132724B2 (en) 2015-04-15 2018-11-20 Goodrich Actuation Systems Check device for flight actuator primary load path failure detection device

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2953494A1 (en) * 2009-12-08 2011-06-10 Goodrich Actuation Systems Sas DEVICE FOR TESTING THE DETECTION OF THE EFFORT RESUME BY A SECONDARY PATH OF A FLIGHT CONTROL ACTUATOR, AND ASSOCIATED TEST METHOD
EP2332838A1 (en) * 2009-12-08 2011-06-15 Goodrich Actuation Systems SAS Device for testing load bearing detection of a secondary channel of a flight control actuator, and associated testing method
US8702034B2 (en) 2009-12-08 2014-04-22 Goodrich Actuation Systems Sas Test device for the detection of the recovery effort by a secondary flight ordering actuator, and associated test method
US10132724B2 (en) 2015-04-15 2018-11-20 Goodrich Actuation Systems Check device for flight actuator primary load path failure detection device

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