Please use this identifier to cite or link to this item: https://hdl.handle.net/20.500.11851/10384
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dc.contributor.authorAydın, B.-
dc.contributor.authorÜnver, H.Ö.-
dc.date.accessioned2023-04-16T10:02:11Z-
dc.date.available2023-04-16T10:02:11Z-
dc.date.issued2022-
dc.identifier.isbn9780791886670-
dc.identifier.urihttps://doi.org/10.1115/IMECE2022-95035-
dc.identifier.urihttps://hdl.handle.net/20.500.11851/10384-
dc.descriptionASME 2022 International Mechanical Engineering Congress and Exposition, IMECE 2022 -- 30 October 2022 through 3 November 2022 -- 186577en_US
dc.description.abstractMultiple rocket launcher systems have great strategic importance in today's defense systems. Therefore, the development and the quality of these strategically important systems are among the priorities of defense industry companies. The quality of the multiple launcher rocket systems is twofold. 1) Firing the ammunition with the appropriate time interval within the correct trajectories, 2) leaving the firing location quickly after completing the mission. In this study, stabilizer support legs were not used to increase vehicle mobility. The dynamics of a multiple rocket launch vehicle are modeled using rigid bodies and elastic elements with eight degrees of freedom in total. Since a 90-degree firing was performed relative to the longitudinal direction, half-vehicle modeling has been developed in the lateral direction of the vehicle. Firing tests had been executed without a support leg over a Multiple Launch Rocket System. During the firing, measurements were taken with a 3-axis accelerometer and gyroscope over the elevation and azimuth platforms. In addition, LPTs in vertical and lateral directions are placed on the superstructure. With these LPTs, the data obtained from the 3-axis accelerometer and gyroscope on the azimuth platform have been confirmed. The model parameters, stiffness/damping parameters of tires, suspensions, and hydraulic actuator, have been obtained using initial test results with MATLAB™ Parameter Estimator toolbox. The model's accuracy has been verified with a second firing test result. Copyright © 2022 by ASME.en_US
dc.language.isoenen_US
dc.publisherAmerican Society of Mechanical Engineers (ASME)en_US
dc.relation.ispartofASME International Mechanical Engineering Congress and Exposition, Proceedings (IMECE)en_US
dc.rightsinfo:eu-repo/semantics/closedAccessen_US
dc.subjectMLRSen_US
dc.subjectModelling Launching Dynamicsen_US
dc.subjectAccelerometersen_US
dc.subjectDegrees of freedom (mechanics)en_US
dc.subjectHydraulic actuatorsen_US
dc.subjectLaunchingen_US
dc.subjectNetwork securityen_US
dc.subjectRocketsen_US
dc.subject3-axis accelerometeren_US
dc.subject3-axis gyroscopesen_US
dc.subjectDefence systemsen_US
dc.subjectFiring testsen_US
dc.subjectLateral directionsen_US
dc.subjectMLRSen_US
dc.subjectModeling and verificationsen_US
dc.subjectModeling launching dynamicen_US
dc.subjectMultiple Launch Rocket Systemsen_US
dc.subjectMultiple rocket launcher systemsen_US
dc.subjectDynamicsen_US
dc.titleModeling and Verification of Firing Dynamics of a Multiple Launch Rocket Systemen_US
dc.typeConference Objecten_US
dc.departmentTOBB ETÜen_US
dc.identifier.volume5en_US
dc.identifier.scopus2-s2.0-85148331593en_US
dc.institutionauthor-
dc.identifier.doi10.1115/IMECE2022-95035-
dc.authorscopusid58107520300-
dc.authorscopusid6603873269-
dc.relation.publicationcategoryKonferans Öğesi - Uluslararası - Kurum Öğretim Elemanıen_US
item.openairecristypehttp://purl.org/coar/resource_type/c_18cf-
item.grantfulltextnone-
item.fulltextNo Fulltext-
item.openairetypeConference Object-
item.cerifentitytypePublications-
item.languageiso639-1en-
Appears in Collections:Scopus İndeksli Yayınlar Koleksiyonu / Scopus Indexed Publications Collection
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