Effects of angular vibration on the performance of a single-degree-of-freedom integrating gyroscope
| dc.contributor.advisor | Wrigley, Walter | |
| dc.contributor.author | Haff, William B. | |
| dc.contributor.author | Meltzer, Melvin | |
| dc.contributor.corporate | Massachusetts Institute of Technology | |
| dc.contributor.department | Aeronautics and Astronautics | |
| dc.date | May 1960 | |
| dc.date.accessioned | 2012-08-29T23:30:58Z | |
| dc.date.available | 2012-08-29T23:30:58Z | |
| dc.date.issued | 1960-05 | |
| dc.description | This thesis document was issued under the authority of another institution, not NPS. At the time it was written, a copy was added to the NPS Library Collection for reasons not now known. It has been included in the digital archive for its historical value to NPS. Not believed to be a CIVINS (Civilian Institutions) title. | |
| dc.description.abstract | Recent studies have shown that various inaccuracies occur when a single-degree-of-freedom gyroscope is subjected to an angular vibratory environment. Under such conditions the performance of the gyroscope has been analyzed and the nature of the inaccuracies investigated. Errors due to "coning", "dynamic unbalance", and "sculling" have been included in the investigation. Values of the inaccuracies representative of those expected from tests using the precision angular vibrator developed by the Instrumentation Laboratory of the Massachusetts Institute of Technology are presented. By reference to a dynamic model the equation of motion was obtained. A suitable solution to the equation was determined in series form for the case of sinusoidal inputs simultaneously applied about two axes. No restrictions are placed on the frequency of the applied motions. The terms in the series solution reveal the nature of the angular displacement of the float with respect to inertial space about the output axis for two cases: (1) zero elastic restraint, (2) finite elastic restraint. It is strongly recommended that correlation of actual experimental results with the developed theory be obtained prior to further theoretical considerations. | |
| dc.description.service | Lieutenant, United States Navy | |
| dc.description.service | Lieutenant, United States Navy | |
| dc.description.sponsorship | U.S. Navy Special Projects Office under Bureau of Ships Contract NObs 78136, Project 53-173. | |
| dc.description.uri | http://archive.org/details/effectsofngularv1094512078 | |
| dc.identifier.uri | https://hdl.handle.net/10945/12078 | |
| dc.language.iso | en_US | |
| dc.publisher | Cambridge, Massachusetts; Massachusetts Institute of Technology | en_US |
| dc.rights | This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States. | |
| dc.subject.lcsh | Aeronautics | en_US |
| dc.title | Effects of angular vibration on the performance of a single-degree-of-freedom integrating gyroscope | en_US |
| dc.type | Thesis | en_US |
| dspace.entity.type | Publication | |
| etd.thesisdegree.discipline | Aeronautics | |
| etd.thesisdegree.grantor | Massachusetts Institute of Technology | en_US |
| etd.thesisdegree.level | Masters | en_US |
| etd.thesisdegree.name | M.S. | en_US |
Files
Original bundle
1 - 1 of 1