BS-G-122-1949.pdf
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1、BRITISH STANDARD BS G 122:1949 Specification for Aircraft magnetic compass Remote-reading (gyro-stabilized) Licensed Copy: London South Bank University, London South Bank University, Sat Dec 09 02:22:47 GMT+00:00 2006, Uncontrolled Copy, (c) BSI BS G 122:1949 This British Standard, having been appro
2、ved by the Aircraft Industry Standards Committee and endorsed by the Chairman of the Engineering Divisional Council, was published under the authority of the General Council of the Institution on 15 December 1949 BSI 02-2000 ISBN 0 580 34522 X A British Standard does not purport to include all the n
3、ecessary provisions of a contract. Users of British Standards are responsible for their correct application. Compliance with a British Standard does not of itself confer immunity from legal obligations. Summary of pages This document comprises a front cover, an inside front cover, pages i and ii, pa
4、ges 1 and 2 and a back cover. This standard has been updated (see copyright date) and may have had amendments incorporated. This will be indicated in the amendment table on the inside front cover. Amendments issued since publication Amd. No.DateComments Licensed Copy: London South Bank University, L
5、ondon South Bank University, Sat Dec 09 02:22:47 GMT+00:00 2006, Uncontrolled Copy, (c) BSI BS G 122:1949 BSI 02-2000i Contents Page 1Definition1 2General construction1 3Detailed construction1 4Operating conditions2 5Accuracy2 6Vibration2 Licensed Copy: London South Bank University, London South Ban
6、k University, Sat Dec 09 02:22:47 GMT+00:00 2006, Uncontrolled Copy, (c) BSI ii blank Licensed Copy: London South Bank University, London South Bank University, Sat Dec 09 02:22:47 GMT+00:00 2006, Uncontrolled Copy, (c) BSI BS G 122:1949 BSI 02-20001 Preferred maximum size: Designs incorporating a g
7、yroscope of the direction indicator type for mounting on the flight instrument panel. Fixing holes: Four fixing holes spaced 4.75 in. vertically and 4.5 in. horizontally. 1 Definition For the purpose of this British Standard the term “remote-reading magnetic compass (gyro-stabilized)” denotes appara
8、tus for indicating the heading of the aircraft, utilizing the magnetic meridian as a datum, of the type in which virtually dead-beat indications are obtained on a master indicator (and repeater indicators, if any), by gyroscopic means, whether by stabilizing the magnetic detector element or by emplo
9、ying this element to monitor the gyroscope or the transmission therefrom. 2 General construction The construction of the instrument shall be mechanically sound, suitable for its purpose, and in accordance with the requirements laid down in BS G 100 “General requirements for indicating instruments an
10、d electrical apparatus”1), with respect to climatic proofing, temperature performance and ability to withstand aircraft vibration. 3 Detailed construction a) The detailed construction of the apparatus shall be in accordance with the relevant requirements laid down in BS G 100. b) The apparatus shall
11、 have a magnetic detector element designed for mounting in a favourable magnetic location, e.g. the wing or tail of the aircraft, and capable of transmitting data to an indicator or indicators suitably placed in the aircraft. c) The combination of the magnetic element, gyroscope and transmission sys
12、tem shall be such that errors due to acceleration or attitude of the aircraft are effectively reduced, thus affording a sensibly dead-beat and accurate indication on compass indicators provided in the system. d) The apparatus shall be driven electrically. The power supply shall be 400 cycles, 115 vo
13、lts. A.C. nominal. Alternatively or additionally, D.C. power may be used from a nominal 24-volt supply. e) The gyroscope shall start and run at a power supply of 80 per cent of normal voltage. f) The gyroscope shall possess a freedom of 85 in pitch or roll. g) The control precession rates of the gyr
14、oscope shall normally be not more than 8 per minute and should be as low as possible consistent with a high degree of reliability. h) In systems which utilize a directional gyro, provision shall be made for switching off the monitoring control at will. Indication shall be given of absence of monitor
15、ing control due to switching off or to failure of control in normal operation. A switch shall be provided to isolate the monitoring system leading the power supply to the directional gyro unit alone. In systems which utilize a vertical gyroscope, means shall be provided for clamping the gyroscope in
16、 the normal attitude for level flight and an indication of this condition shall be provided for the pilot. j) The course indicating dial(s) shall be calibrated over a range of 360 azimuth with markings at the intervals shown below, according to the size of the dial: The treated dial markings shall s
17、atisfy the requirements of BS G 100. k) A settable course-marker for the pilots compass dial shall be provided to indicate the course to be flown; and the preferred presentation shall be a vertical dial with a moving compass card. l) Means shall be provided for correcting the deviations of the compa
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