GB402225A - Apparatus for the automatic operation of the vertical and transverse stabilising of aircraft - Google Patents

Apparatus for the automatic operation of the vertical and transverse stabilising of aircraft

Info

Publication number
GB402225A
GB402225A GB28769/32A GB2876932A GB402225A GB 402225 A GB402225 A GB 402225A GB 28769/32 A GB28769/32 A GB 28769/32A GB 2876932 A GB2876932 A GB 2876932A GB 402225 A GB402225 A GB 402225A
Authority
GB
United Kingdom
Prior art keywords
disc
pointer
plane
magnet
vertical
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
GB28769/32A
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.)
MESSGERATE BOYKOW GmbH
Original Assignee
MESSGERATE BOYKOW GmbH
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 MESSGERATE BOYKOW GmbH filed Critical MESSGERATE BOYKOW GmbH
Publication of GB402225A publication Critical patent/GB402225A/en
Expired legal-status Critical Current

Links

Classifications

    • GPHYSICS
    • G05CONTROLLING; REGULATING
    • G05DSYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
    • G05D1/08Control of attitude, i.e. control of roll, pitch, or yaw
    • G05D1/0808Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
    • G05D1/0816Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft to ensure stability
    • G05D1/085Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft to ensure stability to ensure coordination between different movements

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Transmission And Conversion Of Sensor Element Output (AREA)

Abstract

402,225. Clinometers. MESSGERATE BOYKOW GES., Goerz Allee, Zehlendorf, Berlin. - (Assignees of Boykow, J. M. ; 2A, Fontanestrasse, West Lichterfelde, Berlin.) Oct. 14, 1932, No. 28769. Convention date, Oct. 14, 1931. [Class 97 (ii).] An aircraft is provided with two bodies each containing two symmetrically disposed nozzles, one pair being in a vertical plane and directed upwards and downwards and the other pair being in a horizontal plane, these nozzles through differential manometers automatically controlling the elevator and ailerons or adjusting an indicator on the dashboard. Two streamlined bodies having symmetrically disposed nozzle openings d<1>, d<11> are arranged on the wings, one with its plane ofsymmetry parallel to a horizontal plane and the other with its plane parallel to a vertical longitudinal plane. The nozzle throats are connected to capsules m<1>, m<2> which normally hold a pointer z in mid position between contact strips c, Fig. 3, carried by a spindle b which is constrained by a spring f, levers g, and a crank n to assume a normal position. Any movement of the pointer z energizes magnets e<1>, e<2> to move the spindle b in a direction to follow up the pointer, this motion being damped by a fluid friction device p, this friction device also resisting the return motion produced by the spring f. Simultaneously, rotary magnets control air-valves of cylinders acting upon the elevator or aileron controls. As applied to an indicating instrument, the pointers z act through devices similar to that shown in Fig. 3 upon rotary magnets T', T', Fig. 5. The magnet T' rotates a semicircular disc S, the top edge of which represents the horizon, by means of links r<1>, r<2>, r<3> in front of a disc representing the sky. The magnet T<1> raises and lowers the disc S by means of a lever u<3> link u<2> and angle lever u<1> centred on the axis of the magnet T2. In front of the disc S is a transparent disc having an outline of the bonnet g of the machine. The disc S may bear a photographic representation of the ground. A pointer may be moved transversely across the instrument in response to a turn indicator.
GB28769/32A 1931-10-14 1932-10-14 Apparatus for the automatic operation of the vertical and transverse stabilising of aircraft Expired GB402225A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE402225X 1931-10-14

Publications (1)

Publication Number Publication Date
GB402225A true GB402225A (en) 1933-11-30

Family

ID=6410180

Family Applications (1)

Application Number Title Priority Date Filing Date
GB28769/32A Expired GB402225A (en) 1931-10-14 1932-10-14 Apparatus for the automatic operation of the vertical and transverse stabilising of aircraft

Country Status (1)

Country Link
GB (1) GB402225A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2420932A (en) * 1943-08-11 1947-05-20 E H Johnson Control system for airplanes
US2621873A (en) * 1947-03-31 1952-12-16 North American Aviation Inc Aircraft control
US2626115A (en) * 1951-06-07 1953-01-20 North American Aviation Inc Aircraft controls

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2420932A (en) * 1943-08-11 1947-05-20 E H Johnson Control system for airplanes
US2621873A (en) * 1947-03-31 1952-12-16 North American Aviation Inc Aircraft control
US2626115A (en) * 1951-06-07 1953-01-20 North American Aviation Inc Aircraft controls

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