GB703067A - Improvements in or relating to fluid reaction flying controls for aircraft - Google Patents

Improvements in or relating to fluid reaction flying controls for aircraft

Info

Publication number
GB703067A
GB703067A GB14392/50A GB1439250A GB703067A GB 703067 A GB703067 A GB 703067A GB 14392/50 A GB14392/50 A GB 14392/50A GB 1439250 A GB1439250 A GB 1439250A GB 703067 A GB703067 A GB 703067A
Authority
GB
United Kingdom
Prior art keywords
closures
ducts
intake
outlet
aircraft
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
GB14392/50A
Inventor
Albert Ronald Mettam
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.)
National Research Development Corp UK
Original Assignee
National Research Development Corp UK
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 National Research Development Corp UK filed Critical National Research Development Corp UK
Priority to GB14392/50A priority Critical patent/GB703067A/en
Publication of GB703067A publication Critical patent/GB703067A/en
Expired legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C23/00Influencing air-flow over aircraft surfaces, not otherwise provided for
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C21/00Influencing air-flow over aircraft surfaces by affecting boundary-layer flow
    • B64C21/02Influencing air-flow over aircraft surfaces by affecting boundary-layer flow by use of slot, ducts, porous areas, or the like
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2230/00Boundary layer controls
    • B64C2230/06Boundary layer controls by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2230/00Boundary layer controls
    • B64C2230/20Boundary layer controls by passively inducing fluid flow, e.g. by means of a pressure difference between both ends of a slot or duct
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/10Drag reduction

Abstract

703,067. Controlling aircraft. NATIONAL RESEARCH DEVELOPMENT CORPORATION. July 31, 1951 [June 9, 1950], No. 14392/50. Class 4 An aircraft flying control system comprises a duct which connects an outlet opening at the surface of an aerofoil with a forwardly directed intake which opens at or in advance of the leading edge part of the aerofoil so that air entering the intake in consequence of forward motion ot the aircraft issues trom the outlet and so produces a control force. In Fig. 6, the wing 50 comprises a pair of ducts 51, 52 which terminate in intake apertures in the wing leading edge and outlet apertures in the upper and lower surfaces. The intake apertures have pivoted closures 53, 54 and the outlet apertures sliding closures 55, 56. A mechanism for opening the closures, described for the duct 52 but applicable to both ducts, comprises a three-arm lever 57 fulcrumed about a vertical pivot 58 and having two opposed arms. connected by links 59, 60 with the intake and outlet closures 54, 56 respectively. A spring 61 holds both closures shut and an arm 63 on the three-arm lever is connected to an operating rod 62 which terminates adjacent a lever 64 mounted on a pivot 65 and connected by links 66, 68 and a pivoted lever 67 to a pilot's control column 69. A pivoted lever 71 having an extremity located in opposition to the end of the link 62, is connected by a rod 70 to the mechanism for operating the closures 53, 55. The closures normally maintain the continuity of the wing surface but lateral movement of the control column 69 in either direction will cause the closures 53, 55 or 54, 56 to open simultaneously to permit a flow of air through the ducts 51 or 52 to create a lateral control force. The ducts may be positioned side by side as shown or one above the other, Fig. 4, (not shown). In Fig. 8, the rear end of the fuselage 88 is surrounded by a cowl 87 having a forwardly directed annular intake and a rearward outlet which carries a closure 91. The ducts 81, 82 in the tail surfaces 89. 90 are connected to outlets 83, 84 and the intakes are closed by sliding closures 92, 93. In normal flight the closures 91, 92, 93 are located in the positions shown by dotted lines but when a controlling force has to be exerted the closure 91 is moved to its full-line position and the appropriate closure 92, 93 opened simultaneously. The outlets 83, 84 may have closures operatively connected with the closure members 91, 92, 93. According to the Provisional Specification, the device may be combined with normal control surfaces and trimming of the aircraft may be effected by displacement of one or more control ducts closures or by means of small auxiliary ducts and a gust detector may be associated with the device in order to increase or decrease the overall lift on a wing.
GB14392/50A 1950-06-09 1950-06-09 Improvements in or relating to fluid reaction flying controls for aircraft Expired GB703067A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB14392/50A GB703067A (en) 1950-06-09 1950-06-09 Improvements in or relating to fluid reaction flying controls for aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB14392/50A GB703067A (en) 1950-06-09 1950-06-09 Improvements in or relating to fluid reaction flying controls for aircraft

Publications (1)

Publication Number Publication Date
GB703067A true GB703067A (en) 1954-01-27

Family

ID=10040364

Family Applications (1)

Application Number Title Priority Date Filing Date
GB14392/50A Expired GB703067A (en) 1950-06-09 1950-06-09 Improvements in or relating to fluid reaction flying controls for aircraft

Country Status (1)

Country Link
GB (1) GB703067A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2129748A (en) * 1982-11-10 1984-05-23 Messerschmitt Boelkow Blohm Device for reducing squall loads on aircraft wings
US20130313355A1 (en) * 2012-05-22 2013-11-28 Eurocopter Pitching stabilization means and a rotary wing aircraft including such means
EP2692632B1 (en) * 2011-03-30 2019-09-04 The Society of Japanese Aerospace Companies High-lift device of flight vehicle

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2129748A (en) * 1982-11-10 1984-05-23 Messerschmitt Boelkow Blohm Device for reducing squall loads on aircraft wings
EP2692632B1 (en) * 2011-03-30 2019-09-04 The Society of Japanese Aerospace Companies High-lift device of flight vehicle
US20130313355A1 (en) * 2012-05-22 2013-11-28 Eurocopter Pitching stabilization means and a rotary wing aircraft including such means
US9302762B2 (en) * 2012-05-22 2016-04-05 Airbus Helicopters Pitching stabilization means and a rotary wing aircraft including such means

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