GB811062A - Attitude indicating instruments for aircraft - Google Patents
Attitude indicating instruments for aircraftInfo
- Publication number
- GB811062A GB811062A GB20546/55A GB2054655A GB811062A GB 811062 A GB811062 A GB 811062A GB 20546/55 A GB20546/55 A GB 20546/55A GB 2054655 A GB2054655 A GB 2054655A GB 811062 A GB811062 A GB 811062A
- Authority
- GB
- United Kingdom
- Prior art keywords
- pitch
- aircraft
- attitude
- craft
- roll
- 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
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C19/00—Gyroscopes; Turn-sensitive devices using vibrating masses; Turn-sensitive devices without moving masses; Measuring angular rate using gyroscopic effects
- G01C19/02—Rotary gyroscopes
- G01C19/04—Details
- G01C19/32—Indicating or recording means specially adapted for rotary gyroscopes
Landscapes
- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- A Measuring Device Byusing Mechanical Method (AREA)
Abstract
811,062. Attitude indicators for aircraft. SPERRY RAND CORPORATION. July 15, 1955 [Aug. 2, 1954], No. 20546/55. Class 4. An aircraft instrument for indicating both desired and actual course and attitude comprises a housing 12 provided with a viewing opening 13 for a pair of cross pointers 10, 11 respectively mounted on pivots 15, 16 for rotation by actuating means 17, 19 with respect to a fixed reference index 9 supported by a curved rod 8. The actuating means 17 for the azimuth guidance pointer 10 is energised by an electrical signal corresponding to the algebraic sum of signals proportional to the displacement of the craft from a radio course, the heading of the craft relative to the bearing of the course and the bank angle of the craft. The elevation guidance pointer actuator 19 is energised by a signal corresponding to the displacement of the craft from the glide slope beam of an I.L.S. system and a signal proportional to the pitch angle of the craft. The pointers 10 and 11 thereby provide an indication of a desired course and angle of pitch. The actual attitude of the aircraft is provided by a part-spherical member 25 which is divided into light and dark areas by a horizon-defining line 35 and has a divided scale 75 inscribed thereon to represent angles of pitch. The member 25 is mounted on a pivot 28 and it has an arm 47 fast therewith rocked by means of a crank 45 secured to one end of a push-rod 43. The rod 43 engages at its other end with a cam 42 operated through reduction gearing 57, 58 and 59 from a pitch motor 56 incorporated in a servo loop of a vertical gyro (not shown). The servo loop comprises a pitch synchro 55 driven by rod 43 and electrically coupled to a pitch signal generating device on the gyro so that a signal is generated corresponding to the error between the position of member 25 about axis 28 and the pitch attitude of the aircraft. This error signal is amplified and fed to motor 56 whereby the member 25 is positioned in accordance with the pitch attitude of the aircraft. The pivot 28 is mounted on a gimbal 27 secured to a rotatably mounted sleeve 29 having a toothed ring engaged by a gear train 39 driven by a roll motor 38 incorporated in a servo loop of the gyro. This servo loop comprises a roll synchro 37 driven by the toothed ring on gimbal 27 and as in the pitch servo, an error signal positions motor 38 in accordance with the roll attitude of the aircraft. The greater part of horizon-defining line 35 is located some distance behind the face of the instrument and to give a clearer and more exact indication of the angle of roll, a pointer 85 is mounted closely behind the face 34 for movement with respect to a fixed calibrated scale 86. The pointer 85 is secured to a ring 84 formed with a toothed periphery which meshes through gears with the gear train 39. It is stated that hemispherical member 25 may be formed in two overlapping parts, one fixed and light coloured, the other of dark colour having an edge corresponding to line 35. Specifications 690,985, 776,578 and 811,061 are referred to.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US811062XA | 1954-08-02 | 1954-08-02 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB811062A true GB811062A (en) | 1959-03-25 |
Family
ID=22162125
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB20546/55A Expired GB811062A (en) | 1954-08-02 | 1955-07-15 | Attitude indicating instruments for aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB811062A (en) |
-
1955
- 1955-07-15 GB GB20546/55A patent/GB811062A/en not_active Expired
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