GB1093550A - Gyroscopic inertial instruments and guidance systems - Google Patents
Gyroscopic inertial instruments and guidance systemsInfo
- Publication number
- GB1093550A GB1093550A GB29232/67A GB2923267A GB1093550A GB 1093550 A GB1093550 A GB 1093550A GB 29232/67 A GB29232/67 A GB 29232/67A GB 2923267 A GB2923267 A GB 2923267A GB 1093550 A GB1093550 A GB 1093550A
- Authority
- GB
- United Kingdom
- Prior art keywords
- inertial
- shaft
- elements
- axis
- orthogonal
- 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
- G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
- G01C21/10—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration
- G01C21/12—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning
- G01C21/16—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning by integrating acceleration or speed, i.e. inertial navigation
- G01C21/166—Mechanical, construction or arrangement details of inertial navigation systems
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T74/00—Machine element or mechanism
- Y10T74/12—Gyroscopes
- Y10T74/1261—Gyroscopes with pick off
- Y10T74/1268—Pneumatic
Landscapes
- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Automation & Control Theory (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Gyroscopes (AREA)
- Navigation (AREA)
- Surgical Instruments (AREA)
- Manufacture Of Motors, Generators (AREA)
- Accommodation For Nursing Or Treatment Tables (AREA)
Abstract
1, 093, 550. Gyroscopic apparatus; accelerometers. LITTON INDUSTRIES Inc. May 20, 1966 [May 21, 1965], No.29232/67. Divided out of 1, 093, 549. Headings G1C and G1K. A gyroscopic inertial instrument comprises two inertial ring-like elements 26, 26' mounted for rotation on a common shaft 20 at a rotational frequency N by means of a synchrous motor 16, each of the elements 26, 26' being also mounted for vibratory motion at a frequency N about torsion bars 28, 28', the torsion bars 28 being orthogonal to the bars 28', and both sets of bars being orthogonal to the shaft 20. E-shaped sensors 40, 40' are positioned to detect the vibratory motions of the inertial elements 26, 26'. It is shown in the Specification that the equation of motion for the inertial elements demonstrates that the angular displacement of the element about its torsional oscillation axis is proportional to the rotational displacement of the shaft 20 multiplied by a cosine term representing the vibrations. This cosine term contains phase information which can be extracted by means of a timing signal to yield the angle between the axis of the rotational displacement of the shaft 20 and a fixed co-ordinate system in the gyroscope casing. In practice this timing signal is generated by a signal generator 51 positioned a slightly ellipsoidal member 36 on the shaft 20. Electronic circuitry is described which enables the required displacement information to be obtained. It has been found that spurious output signals can be derived from an inherent shaft wobble of the shaft 20 at a frequency 2N due to bearing tolerances. These are eliminated in the construction of Fig. 1 since the torsion bars 28, 28' are orthogonal so that the error signals from the two inertial elements 26, 26' are out of phase and cancel each other. When these instruments are used in an inertial guidance system the vibratory motion is nulled by torquing the platform back to its stabilized attitude. However, when mounted fixedly in an aircraft the vibratory motion must be nulled in order that the sensing signal can be utilized. Torquers 62, 62' are provided to effect this and these are fed back from the above mentioned electronic circuitry. It has also been found that if the centre of mass of one of the inertial elements 26, 26' is displaced slightly from the oscillation axis defined by the torsion bar 28 or 28', then linear acceleration along an axis orthogonal to the axis of the shaft 20 produces a moment on the inertial element causing vibration of the element about its torsional axis. This will produce a further term in the equation of motion of the element, which can be resolved by electronic circuitry as before, for example by comparing the signals generated by two inertial elements as 26, 26' with their torsion bars 28, 28' disposed parallel, and only one of which has its centre of mass displaced from the torsional oscillation axis. Various forms of inertial element are described which enable both angular displacement and linear acceleration terms to be resolved, and a complete inertial guidance system is described utilizing three orthogonally disposed inertial instruments of the type referred to above and serving to completely stabilize the platform.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US457740A US3382726A (en) | 1965-05-21 | 1965-05-21 | Vibrating rotor gyroscope |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1093550A true GB1093550A (en) | 1967-12-06 |
Family
ID=23817923
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB22719/66A Expired GB1093549A (en) | 1965-05-21 | 1966-05-20 | Gyroscopic inertial instruments and guidance systems |
GB29232/67A Expired GB1093550A (en) | 1965-05-21 | 1966-05-20 | Gyroscopic inertial instruments and guidance systems |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB22719/66A Expired GB1093549A (en) | 1965-05-21 | 1966-05-20 | Gyroscopic inertial instruments and guidance systems |
Country Status (7)
Country | Link |
---|---|
US (1) | US3382726A (en) |
JP (1) | JPS4811257B1 (en) |
BE (1) | BE681307A (en) |
DE (1) | DE1523213B2 (en) |
GB (2) | GB1093549A (en) |
NL (1) | NL6607061A (en) |
SE (2) | SE359918B (en) |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3540289A (en) * | 1966-12-08 | 1970-11-17 | Gen Motors Corp | Tuned rotor gyro-accelerometer |
US3678764A (en) * | 1967-11-20 | 1972-07-25 | Litton Systems Inc | Gyroscope having vibrating gimbals |
US3678765A (en) * | 1969-12-15 | 1972-07-25 | Ambac Ind | Magnetically-tuned resonant gyroscope |
US3697968A (en) * | 1971-04-16 | 1972-10-10 | Nasa | Dual purpose momentum wheels for spacecraft with magnetic recording |
US3779087A (en) * | 1972-03-30 | 1973-12-18 | Singer Co | Gyroscope pickoff means |
US3805625A (en) * | 1973-02-21 | 1974-04-23 | Northrop Corp | Asymmetric gyroscope |
GB1599082A (en) * | 1978-02-27 | 1981-09-30 | Nat Res Dev | Gyroscopic apparatus |
JPS55155912A (en) * | 1979-05-20 | 1980-12-04 | Takao Ishii | Nut and washer structure |
US4445375A (en) * | 1981-02-27 | 1984-05-01 | General Electric Company | Tuned coriolis angular rate measuring device |
US4744249A (en) * | 1985-07-25 | 1988-05-17 | Litton Systems, Inc. | Vibrating accelerometer-multisensor |
US4841773A (en) * | 1987-05-01 | 1989-06-27 | Litton Systems, Inc. | Miniature inertial measurement unit |
US5007289A (en) * | 1988-09-30 | 1991-04-16 | Litton Systems, Inc. | Three axis inertial measurement unit with counterbalanced, low inertia mechanical oscillator |
CN109483394B (en) * | 2018-09-13 | 2023-12-12 | 西安航晨机电科技股份有限公司 | Ultra-precise spherical surface machining device and method for hemispherical harmonic oscillator |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2716893A (en) * | 1949-10-18 | 1955-09-06 | Gen Dynamics Corp | Means and apparatus for utilizing gyrodynamic energy |
US3077785A (en) * | 1959-09-09 | 1963-02-19 | Gen Precision Inc | Pivot spring suspended gyro |
US3147627A (en) * | 1959-11-19 | 1964-09-08 | Vickers Armstrongs Aircraft | Rate gyroscopes |
US3241377A (en) * | 1960-01-13 | 1966-03-22 | Jr George C Newton | Method of and apparatus for detecting angular motion |
-
1965
- 1965-05-21 US US457740A patent/US3382726A/en not_active Expired - Lifetime
-
1966
- 1966-05-18 SE SE06060/70A patent/SE359918B/xx unknown
- 1966-05-18 SE SE06938/66A patent/SE326838B/xx unknown
- 1966-05-20 BE BE681307D patent/BE681307A/xx unknown
- 1966-05-20 DE DE19661523213 patent/DE1523213B2/en not_active Withdrawn
- 1966-05-20 GB GB22719/66A patent/GB1093549A/en not_active Expired
- 1966-05-20 GB GB29232/67A patent/GB1093550A/en not_active Expired
- 1966-05-21 JP JP3208766A patent/JPS4811257B1/ja active Pending
- 1966-05-23 NL NL6607061A patent/NL6607061A/xx unknown
Also Published As
Publication number | Publication date |
---|---|
DE1523213A1 (en) | 1969-06-12 |
GB1093549A (en) | 1967-12-06 |
SE359918B (en) | 1973-09-10 |
BE681307A (en) | 1966-11-21 |
JPS4811257B1 (en) | 1973-04-12 |
NL6607061A (en) | 1966-11-22 |
US3382726A (en) | 1968-05-14 |
DE1523213B2 (en) | 1970-08-06 |
SE326838B (en) | 1970-08-03 |
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