GB662110A - Improvements in aircraft propeller and rotor blades - Google Patents

Improvements in aircraft propeller and rotor blades

Info

Publication number
GB662110A
GB662110A GB1831149A GB1831149A GB662110A GB 662110 A GB662110 A GB 662110A GB 1831149 A GB1831149 A GB 1831149A GB 1831149 A GB1831149 A GB 1831149A GB 662110 A GB662110 A GB 662110A
Authority
GB
United Kingdom
Prior art keywords
rotor blades
aircraft propeller
sheathing
blade
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
GB1831149A
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.)
GUY CLAVELL INGE GARDINER
De Havilland Aircraft Co Ltd
Original Assignee
GUY CLAVELL INGE GARDINER
De Havilland Aircraft Co 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
Priority claimed from US534907A external-priority patent/US2453235A/en
Application filed by GUY CLAVELL INGE GARDINER, De Havilland Aircraft Co Ltd filed Critical GUY CLAVELL INGE GARDINER
Priority to GB1831149A priority Critical patent/GB662110A/en
Publication of GB662110A publication Critical patent/GB662110A/en
Expired legal-status Critical Current

Links

Classifications

    • H—ELECTRICITY
    • H01—BASIC ELECTRIC ELEMENTS
    • H01H—ELECTRIC SWITCHES; RELAYS; SELECTORS; EMERGENCY PROTECTIVE DEVICES
    • H01H73/00—Protective overload circuit-breaking switches in which excess current opens the contacts by automatic release of mechanical energy stored by previous operation of a hand reset mechanism
    • H01H73/22—Protective overload circuit-breaking switches in which excess current opens the contacts by automatic release of mechanical energy stored by previous operation of a hand reset mechanism having electrothermal release and no other automatic release
    • H01H73/24—Protective overload circuit-breaking switches in which excess current opens the contacts by automatic release of mechanical energy stored by previous operation of a hand reset mechanism having electrothermal release and no other automatic release reset by lever
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/20—Constructional features
    • B64C11/205—Constructional features for protecting blades, e.g. coating
    • H—ELECTRICITY
    • H01—BASIC ELECTRIC ELEMENTS
    • H01H—ELECTRIC SWITCHES; RELAYS; SELECTORS; EMERGENCY PROTECTIVE DEVICES
    • H01H71/00—Details of the protective switches or relays covered by groups H01H73/00 - H01H83/00
    • H01H71/10—Operating or release mechanisms
    • H01H71/12—Automatic release mechanisms with or without manual release
    • H01H71/46—Automatic release mechanisms with or without manual release having means for operating auxiliary contacts additional to the main contacts
    • H01H71/48—Automatic release mechanisms with or without manual release having means for operating auxiliary contacts additional to the main contacts with provision for short-circuiting the electrical input to the release mechanism after release of the switch, e.g. for protection of heating wire
    • H—ELECTRICITY
    • H01—BASIC ELECTRIC ELEMENTS
    • H01H—ELECTRIC SWITCHES; RELAYS; SELECTORS; EMERGENCY PROTECTIVE DEVICES
    • H01H71/00—Details of the protective switches or relays covered by groups H01H73/00 - H01H83/00
    • H01H71/74—Means for adjusting the conditions under which the device will function to provide protection
    • H01H71/7427—Adjusting only the electrothermal mechanism
    • H01H71/7436—Adjusting the position (or prestrain) of the bimetal

Abstract

662,110. Rotary wings; airscrews. DE HAVILLAND AIRCRAFT CO., Ltd., and GARDINER, G. C. 1. June 16, 1950 [July 11, 1949], No. 18311/49. Classes 4 and 114. An airscrew or rotor blade formed from light metal alloy has its leading edge covered with a thin steel sheathing 2 secured by a synthetic resin adhesive. The blade may be recessed to receive an electric heating de-icing device 4 prior to the application of the sheathing. Specification 577,823, [Group VIII], is referred to.
GB1831149A 1949-07-11 1949-07-11 Improvements in aircraft propeller and rotor blades Expired GB662110A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1831149A GB662110A (en) 1949-07-11 1949-07-11 Improvements in aircraft propeller and rotor blades

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US534907A US2453235A (en) 1944-05-10 1944-05-10 Nonfree-tripping overload circuit breaker
GB1172045A GB612110A (en) 1944-05-10 1945-05-10 Improvements in or relating to non-free-tripping overload circuit breakers
US1754248 US2506796A (en) 1944-05-10 1948-03-27 Nonfree-tripping overload circuit breaker
GB1831149A GB662110A (en) 1949-07-11 1949-07-11 Improvements in aircraft propeller and rotor blades

Publications (1)

Publication Number Publication Date
GB662110A true GB662110A (en) 1951-11-28

Family

ID=10110315

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1831149A Expired GB662110A (en) 1949-07-11 1949-07-11 Improvements in aircraft propeller and rotor blades

Country Status (1)

Country Link
GB (1) GB662110A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3123327A (en) * 1964-03-03 Figure
US3173491A (en) * 1963-11-21 1965-03-16 United Aircraft Corp Deicing system
US3200477A (en) * 1962-11-21 1965-08-17 Enstrom Corp Helicopter tail rotor structure and method of construction
US4784575A (en) * 1986-11-19 1988-11-15 General Electric Company Counterrotating aircraft propulsor blades
US4971641A (en) * 1988-11-14 1990-11-20 General Electric Company Method of making counterrotating aircraft propeller blades
USRE34207E (en) * 1986-11-19 1993-03-30 General Electric Company Counterrotating aircraft propulsor blades
CN104129496A (en) * 2013-05-03 2014-11-05 波音公司 Protective finish for wing tip devices
EP2322427B1 (en) 2009-11-17 2017-06-14 Hamilton Sundstrand Corporation Airfoil assembly and airfoil assembly wear indicating method

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3123327A (en) * 1964-03-03 Figure
US3200477A (en) * 1962-11-21 1965-08-17 Enstrom Corp Helicopter tail rotor structure and method of construction
US3173491A (en) * 1963-11-21 1965-03-16 United Aircraft Corp Deicing system
US4784575A (en) * 1986-11-19 1988-11-15 General Electric Company Counterrotating aircraft propulsor blades
USRE34207E (en) * 1986-11-19 1993-03-30 General Electric Company Counterrotating aircraft propulsor blades
US4971641A (en) * 1988-11-14 1990-11-20 General Electric Company Method of making counterrotating aircraft propeller blades
EP2322427B1 (en) 2009-11-17 2017-06-14 Hamilton Sundstrand Corporation Airfoil assembly and airfoil assembly wear indicating method
EP2322427B2 (en) † 2009-11-17 2020-07-29 Hamilton Sundstrand Corporation Airfoil assembly and airfoil assembly wear indicating method
CN104129496A (en) * 2013-05-03 2014-11-05 波音公司 Protective finish for wing tip devices
EP2799330A3 (en) * 2013-05-03 2014-12-17 The Boeing Company Protective finish for wing tip devices
US9845162B2 (en) 2013-05-03 2017-12-19 The Boeing Company Protective finish for wing tip devices
EP3366572A1 (en) * 2013-05-03 2018-08-29 The Boeing Company Protective finish for wing tip devices

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