GB1531157A - Aircraft tailplane including anti-icing device - Google Patents

Aircraft tailplane including anti-icing device

Info

Publication number
GB1531157A
GB1531157A GB2256076A GB2256076A GB1531157A GB 1531157 A GB1531157 A GB 1531157A GB 2256076 A GB2256076 A GB 2256076A GB 2256076 A GB2256076 A GB 2256076A GB 1531157 A GB1531157 A GB 1531157A
Authority
GB
United Kingdom
Prior art keywords
tailplane
icing
chord
including anti
leading edge
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
GB2256076A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to GB2256076A priority Critical patent/GB1531157A/en
Publication of GB1531157A publication Critical patent/GB1531157A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Fittings On The Vehicle Exterior For Carrying Loads, And Devices For Holding Or Mounting Articles (AREA)

Abstract

1531157 Preventing ice formation O K ANTONOV 1 June 1976 22560/76 Heading B7W An aircraft tailplane 2 has a de-icing member 4 spaced from its leading edge 5. The angle of incidence 9 of the member 4 is between 30 and 60 degrees and its spacing 11 from the leading edge of the tailplane is 1 to 3% of the tailplane chord. The chord length of the member is 3 to 8% of the tailplane chord. A hot air duct 17 delivers air to a space 20 in the tailplane and also, via pipes 19 to a chamber 18 within the de-icing member. The application of heat to the tailplane and de-icing member is controlled either automatically or by the pilot, and it is stated that in the event of heat not being applied, as a result of a malfunction or pilot error, the member 4 still maintains the tailplane ice-free.
GB2256076A 1976-06-01 1976-06-01 Aircraft tailplane including anti-icing device Expired GB1531157A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2256076A GB1531157A (en) 1976-06-01 1976-06-01 Aircraft tailplane including anti-icing device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2256076A GB1531157A (en) 1976-06-01 1976-06-01 Aircraft tailplane including anti-icing device

Publications (1)

Publication Number Publication Date
GB1531157A true GB1531157A (en) 1978-11-01

Family

ID=10181410

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2256076A Expired GB1531157A (en) 1976-06-01 1976-06-01 Aircraft tailplane including anti-icing device

Country Status (1)

Country Link
GB (1) GB1531157A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2116929A (en) * 1982-03-24 1983-10-05 Secr Defence Ice prevention devices
GB2518232A (en) * 2013-09-17 2015-03-18 Airbus Operations Ltd Ice accretion prevention

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2116929A (en) * 1982-03-24 1983-10-05 Secr Defence Ice prevention devices
GB2518232A (en) * 2013-09-17 2015-03-18 Airbus Operations Ltd Ice accretion prevention

Similar Documents

Publication Publication Date Title
FR2352256A1 (en) IMPROVEMENTS TO AIR CONDITIONING SYSTEMS, ESPECIALLY FOR AIRCRAFT CABINS
GB1183714A (en) Improvements in or relating to Boundary Layer Control Systems.
GB1398809A (en) Hinged control surface for aircraft
GB622627A (en) Means for preventing an internal-combustion turbine unit from icing
GB1196756A (en) Improvements in Aerofoils.
GB1531157A (en) Aircraft tailplane including anti-icing device
GB542878A (en) Improvements in means for preventing ice accumulation on aerofoil and like surfaces
FR1555531A (en)
GB536865A (en) Improvements in or relating to aircraft
SU1840518A1 (en) Flying vehicle
GB655089A (en) Improvements in or relating to the control of aircraft at low speeds
GB622778A (en) Improvements relating to the prevention of icing of aircraft
USD180341S (en) Pblotless propeller driven airplane
SHALLCROSS Military considerations for helicopter flight controls
AU140659B2 (en) Improvements in or relating to fuel control systems for aircraft gas-turbine powerplants
Dee et al. Flight determination of wing flow patterns and buffet boundaries for the Fairey Delta 2 aircraft at Mach numbers between 0. 4 and 1. 3, and comparison with wind tunnel results(Flight and wind tunnel tests compared to visualize wing flow patterns for Fairey Delta 2 aircraft between Mach numbers 0. 4 and 1. 3)
CARNEGIS Engine sensory requirements for energy management
AU1337752A (en) Improvements in or relating to systems for controlling the pressure in enclosed spaces e g. aircraft cabins
SCHMIDTLEIN Adaptation of a nonlinear attitude regulator developed for a V/STOL aircraft, to a helicopter(Attitude stabilization of Bell 47-G helicopter with adapted nonlinear V/STOL attitude regulator)
CURBILLON Aerospatial'es approach to the study of flutter at the design stage of the project
GB922900A (en) Improvements in or relating to aircraft
FR2272893A1 (en) Powered aircraft with small front wing - has freely rotating tabs on front wing forming elevators
BOUCHER et al. The sequential spark technique- A tool for wake velocity studies in ballistic ranges(Sequential electric spark technique for hypervelocity projectiles turbulent wake velocity measurements at ballistic ranges in free flight regime)
BERGMAN et al. Control authority with a flight performance controller(development of aircraft system for pilot control of aircraft bank angle and vertical speed)
AU146540B2 (en) Improvements in or relating to aircraft flight control systems

Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee