GB722556A - Improvements in or relating to stabilisers for rotary wing aircraft - Google Patents

Improvements in or relating to stabilisers for rotary wing aircraft

Info

Publication number
GB722556A
GB722556A GB17007/52A GB1700752A GB722556A GB 722556 A GB722556 A GB 722556A GB 17007/52 A GB17007/52 A GB 17007/52A GB 1700752 A GB1700752 A GB 1700752A GB 722556 A GB722556 A GB 722556A
Authority
GB
United Kingdom
Prior art keywords
aerofoil
aerofoils
fuselage
tail
cone
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
GB17007/52A
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.)
Raytheon Technologies Corp
Original Assignee
United Aircraft 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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB722556A publication Critical patent/GB722556A/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
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8263—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like
    • B64C2027/8281—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like comprising horizontal tail planes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8263—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like
    • B64C2027/829—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like comprising a V-tail units

Landscapes

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

Abstract

722,556. Helicopters. UNITED AIRCRAFT CORPORATION. July 7,1952, [Sept. 20,1951], No. 17007/52. Class 4. A stabilizer positioned on the aft portion of the fuselage of a helicopter has an aspect ratio of not more than 3, is of generally triangular planform and of aerofoil configuration, and has its surface generally symmetrical about a fore and aft line. An aerofoil 34 of triangular planform is mounted on a shaft 38 pivotally supported in brackets 36 attached to the rear end of the fuselage, the shaft carrying a depending arm 40 to the lower end of which is connected the operating rod 44 of a servo mechanism 42. A transmitter 48 for an indicator in the pilot's cockpit to show the attitude of the aerofoil, is connected also to the arm 40 by a rod 50. In the embodiment shown the aerofoil is mounted on the side of the tail cone opposite to the stabilizing rotor 20, and it may carry upper and lower vertical fins, Fig. 8 (not shown). Alternatively, an aerofoil may be mounted centrally on the rear end of the tail cone at the base of an upwardly and rearwardly inclined pillar for the tail rotor Fig. 9 (not shown), or a pair of aerofoils may be mounted on either side of the rear cone either directly or by means of intermediate stays Figs. 6 and 7 (not shown). In the latter embodiments the aerofoils may be fixed in optimum positions.
GB17007/52A 1951-09-20 1952-07-07 Improvements in or relating to stabilisers for rotary wing aircraft Expired GB722556A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US722556XA 1951-09-20 1951-09-20

Publications (1)

Publication Number Publication Date
GB722556A true GB722556A (en) 1955-01-26

Family

ID=22106488

Family Applications (1)

Application Number Title Priority Date Filing Date
GB17007/52A Expired GB722556A (en) 1951-09-20 1952-07-07 Improvements in or relating to stabilisers for rotary wing aircraft

Country Status (1)

Country Link
GB (1) GB722556A (en)

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