GB1492671A - Helicopter rotor blade - Google Patents

Helicopter rotor blade

Info

Publication number
GB1492671A
GB1492671A GB23975A GB23975A GB1492671A GB 1492671 A GB1492671 A GB 1492671A GB 23975 A GB23975 A GB 23975A GB 23975 A GB23975 A GB 23975A GB 1492671 A GB1492671 A GB 1492671A
Authority
GB
United Kingdom
Prior art keywords
spar
aft
secured
skin
tip
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
GB23975A
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.)
Textron Inc
Original Assignee
Textron Inc
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 Textron Inc filed Critical Textron Inc
Publication of GB1492671A publication Critical patent/GB1492671A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/463—Blade tips
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • B64C2027/4733—Rotor blades substantially made from particular materials
    • B64C2027/4736—Rotor blades substantially made from particular materials from composite materials

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Wind Motors (AREA)
  • Toys (AREA)

Abstract

1492671 Helicopter rotor blades TEXTRON Inc 3 Jan 1975 [3 Jan 1974] 239/75 Heading B7W A helicopter rotor blade has a root portion formed with chordally spaced attachment fittings 40, 42 secured to the load-bearing structure by conventional starwise extending doubler plates (48-51), Fig. 2 (not shown) the structure comprising a torque box extending to a tip fairing member 22 with the aft blade profile being completed by a non-structural fairing structure. A leading edge star 12 of U-shape has a nose block 56, an upper rearwardly directed surface 58, a lower rearwardly directed surface 60 and a spanwise enclosure plate 62 forming a torque box 64 which is filled by a lightweight impact resistant metallic honeycomb 66. Further reinforcement is provided by upper and lower doubler members 68 and 70 secured to the aft side of spar 12. An aft spar 74, extending parallel to plate 62 extends from root to tip and is formed by an I-section which from the blade root to a position about 60% of the spar from the root includes a further member 76. Spin panels 14, 16, 18, 20 are provided. The aft upper panel 16 is secured to the trailing edge of 12 up to the 60% span position and between this position and the blade tip it extends only as forward as the spar 74 and is secured at its leading edge to the spar 74. The upper forward skin 20 becomes exposed from the 60% position to the tip. The trailing edge of the lower forward skin panel 18 is secured to the lower leading edge of spar 74 and the leading edge of lower aft skin panel 14 to the lower trailing edge of spar 74, the trailing edges of both panels 14 and 16 terminating at a trailing edge member 72. Spar 74 and plate 62 with skin panels 18 and 20 form an aft torque box 78 which is filled with a metallic honeycomb 80 extending to the blade tip. Cavities formed aft of spar 76 and between aft upper skin 16 and forward upper skin 20 are filled respectively with honeycombs 92 and 94. Chordwise and spanwise balance weights and electrostatic discharge elements are provided.
GB23975A 1974-01-03 1975-01-03 Helicopter rotor blade Expired GB1492671A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US43034474A 1974-01-03 1974-01-03

Publications (1)

Publication Number Publication Date
GB1492671A true GB1492671A (en) 1977-11-23

Family

ID=23707141

Family Applications (1)

Application Number Title Priority Date Filing Date
GB23975A Expired GB1492671A (en) 1974-01-03 1975-01-03 Helicopter rotor blade

Country Status (6)

Country Link
JP (1) JPS50117200A (en)
CA (1) CA1016524A (en)
DE (1) DE2461008C2 (en)
FR (1) FR2256868B1 (en)
GB (1) GB1492671A (en)
IT (1) IT1026166B (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3070371A1 (en) * 2017-08-31 2019-03-01 Airbus Helicopters BLADE, ROTOR WITH THIS BLADE AND AIRCRAFT PROVIDED WITH THIS ROTOR
CN110884684A (en) * 2019-12-04 2020-03-17 中国直升机设计研究所 Design method for strength test of helicopter after impact of bearingless tail blade
CN113165738A (en) * 2018-11-30 2021-07-23 列奥纳多股份公司 Rotor for an aircraft capable of hovering

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2507149A1 (en) * 1981-06-05 1982-12-10 Onera (Off Nat Aerospatiale) END OF BLADE FOR AN AIRCRAFT ROTARY SAIL AND ROTARY VESSEL PROVIDED WITH SUCH EXTREMITES OF BLADE
US4585086A (en) * 1983-08-18 1986-04-29 Honda Giken Kogyo Kabushiki Kaisha Motor vehicle frame material and frame construction using the same
FR2912990B1 (en) * 2007-02-23 2009-04-24 Eurocopter France ROTATING BLADE WITH RADIAL STRING AND AT LEAST ONE FRONT AND / OR REAR ARROW STRING

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2884078A (en) * 1953-10-21 1959-04-28 Parsons Corp Rotor blade structure having spanwise reinforcing members
DE1034985B (en) * 1953-10-21 1958-07-24 Parsons Corp Metallic rotating wing
US3155166A (en) * 1962-09-17 1964-11-03 Parsons Corp Rotor blade including improved attachment of filled aft structure
GB1082352A (en) * 1964-10-02 1967-09-06 Parsons Corp Improved airfoil construction
GB1214858A (en) * 1968-05-20 1970-12-09 Westland Aircraft Ltd Improvements in or relating to the construction of rotor blades for rotary wing aircraft

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3070371A1 (en) * 2017-08-31 2019-03-01 Airbus Helicopters BLADE, ROTOR WITH THIS BLADE AND AIRCRAFT PROVIDED WITH THIS ROTOR
CN113165738A (en) * 2018-11-30 2021-07-23 列奥纳多股份公司 Rotor for an aircraft capable of hovering
CN113165738B (en) * 2018-11-30 2024-04-02 列奥纳多股份公司 Rotor for a hovering aircraft
CN110884684A (en) * 2019-12-04 2020-03-17 中国直升机设计研究所 Design method for strength test of helicopter after impact of bearingless tail blade
CN110884684B (en) * 2019-12-04 2022-04-12 中国直升机设计研究所 Design method for strength test of helicopter after impact of bearingless tail blade

Also Published As

Publication number Publication date
JPS50117200A (en) 1975-09-12
CA1016524A (en) 1977-08-30
FR2256868B1 (en) 1979-04-27
IT1026166B (en) 1978-09-20
DE2461008A1 (en) 1975-07-17
DE2461008C2 (en) 1985-09-26
FR2256868A1 (en) 1975-08-01

Similar Documents

Publication Publication Date Title
US4022546A (en) Helicopter rotor blade
US3586460A (en) Rotor blade variable modulus trailing edge
US9884682B2 (en) Aircraft configuration
EP2418148B1 (en) Aircraft having a lambda-box wing configuration
GB1214858A (en) Improvements in or relating to the construction of rotor blades for rotary wing aircraft
GB1461723A (en) Helicopter blade structuren1461724chun cheng lin feeding bottles
EP2668094A2 (en) Laminar flow wing optimized for transonic and supersonic cruise aircraft
US2643076A (en) Improvement in aircraft of high aspect ratio
US3813186A (en) Rotor blade shear reinforcement
GB1492671A (en) Helicopter rotor blade
US10870488B2 (en) Braced wing aircraft
Purser et al. Experimental verification of a simplified vee-tail theory and analysis of available data on complete models with vee tails
Ahmadi et al. Energetics and optimum motion of oscillating lifting surfaces of finite span
GB1146699A (en) Compound rotorcraft
EP0221204B1 (en) Supersonic airplane
US1840643A (en) Airplane
US2609883A (en) Rotary wing blade
RU94017618A (en) Combination vertical take-off and landing rotary-wing aircraft and method of conversion of rotary-wing flying vehicle into aircraft configuration
GB1150123A (en) Improvements in or relating to the Construction of Rotor Blades for Rotary Wing Aircraft
US3259342A (en) Airplanes
Wood et al. Circulation control airfoils as applied to rotary-wing aircraft
Cohen et al. Theoretical investigation of the supersonic lift and drag of thin, sweptback wings with increased sweep near the root
US2165482A (en) Aircraft wing arrangement
Kentfield Aircraft with outboard horizontal stabilizers, history, current status, development potential
US3503575A (en) Helicopter

Legal Events

Date Code Title Description
PS Patent sealed
PE20 Patent expired after termination of 20 years

Effective date: 19950102