INTEGRATED INERTIAL-SATELLITE ORIENTATION AND NAVIGATION SYSTEM FOR OBJECTS MOVING ON BALLISTIC TRAJECTORY WITH ROTATION AROUND LONGITUDINAL AXIS
FIELD: physics; navigation. ^ SUBSTANCE: invention relates to navigation instrument making. The set problem is solved by that, conditions are created in which substantial connection appears and is used on a section of a ballistic trajectory between error models of inertial measurement modules when s...
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| creator | BLAZHNOV BORIS ALEKSANDROVICH EMEL'JANTSEV GENNADIJ IVANOVICH KOROTKOV ALEKSANDR NIKOLAEVICH NESENJUK LEONID PETROVICH STEPANOV ALEKSEJ PETROVICH |
| description | FIELD: physics; navigation. ^ SUBSTANCE: invention relates to navigation instrument making. The set problem is solved by that, conditions are created in which substantial connection appears and is used on a section of a ballistic trajectory between error models of inertial measurement modules when solving the problem of orientation and navigation. This connection appears and can be used in providing the following conditions: presence of fast rotation around a longitudinal axis and coning motion of precession of the control object about the centre of mass or only rotation of the object around a longitudinal axis on a ballistic trajectory; placing a unit of accelerometres of inertial measurement modules and a reception antenna for the satellite navigation system at a certain distance (basically on a transverse axis) from the centre of mass of the control object; solving the problem of orientation and navigation in the inertial measurement modules at the point of placing the unit of accelerometres at high frequency - approximately an order higher than frequency of rotation of the control object (due to necessity of generation of dynamic components in navigation parametres without distortions); formation of measured values of primary navigation parametres in the reception apparatus of the satellite navigation system where the reception antenna is placed using tracking measuring devices with bandwidth greater than the frequency of rotation of the control object. Also values of primary navigation parametres are calculated in the computer of the inertial measurement modules and these values are also used in the feedback in the reception apparatus of the satellite navigation system for narrowing the frequency band in tracking systems of carrier frequency and code delay. ^ EFFECT: increased accuracy and noise immunity of integrated systems of orientation and navigation (ISON), which have inertial measurement modules (IMM) on "rough" micromechanical gyroscopes and a miniature reception apparatus of satellite navigation systems (RA SNS), in generating orientation parametres of control objects (CO) on a section of its ballistic trajectory for a long period of time, ie provision for stationary character and limited level of errors of integrated systems of orientation and navigation in solving the problem of orientation of a control object on a ballistic trajectory, as well as high level of noise immunity. ^ 6 dwg
Изобретение относится к области навигационного приборост |
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| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_RU2375680C1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>RU2375680C1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_RU2375680C13</originalsourceid><addsrcrecordid>eNqNjEsKwkAQRLNxIeod-gIBP_jZdpIxtozd0NOJZiUi40pU0It4YyPq3lXxqKrXTZ7E5kpFcwUQOzVCn4YWvSdzIEqODY2EAbkAxprKD4YmmNvAUhQkW7vcAmykJi6hLTNs_8EoB1N8l6INbMlWoPLTqVSt0QuXZFVBjB5wR6GfdE6H8z0OvtlLYOksX6Xxdt3H--1wjJf42Gs1nsyns8UwH03-mLwAoUlBfQ</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>INTEGRATED INERTIAL-SATELLITE ORIENTATION AND NAVIGATION SYSTEM FOR OBJECTS MOVING ON BALLISTIC TRAJECTORY WITH ROTATION AROUND LONGITUDINAL AXIS</title><source>esp@cenet</source><creator>BLAZHNOV BORIS ALEKSANDROVICH ; EMEL'JANTSEV GENNADIJ IVANOVICH ; KOROTKOV ALEKSANDR NIKOLAEVICH ; NESENJUK LEONID PETROVICH ; STEPANOV ALEKSEJ PETROVICH</creator><creatorcontrib>BLAZHNOV BORIS ALEKSANDROVICH ; EMEL'JANTSEV GENNADIJ IVANOVICH ; KOROTKOV ALEKSANDR NIKOLAEVICH ; NESENJUK LEONID PETROVICH ; STEPANOV ALEKSEJ PETROVICH</creatorcontrib><description>FIELD: physics; navigation. ^ SUBSTANCE: invention relates to navigation instrument making. The set problem is solved by that, conditions are created in which substantial connection appears and is used on a section of a ballistic trajectory between error models of inertial measurement modules when solving the problem of orientation and navigation. This connection appears and can be used in providing the following conditions: presence of fast rotation around a longitudinal axis and coning motion of precession of the control object about the centre of mass or only rotation of the object around a longitudinal axis on a ballistic trajectory; placing a unit of accelerometres of inertial measurement modules and a reception antenna for the satellite navigation system at a certain distance (basically on a transverse axis) from the centre of mass of the control object; solving the problem of orientation and navigation in the inertial measurement modules at the point of placing the unit of accelerometres at high frequency - approximately an order higher than frequency of rotation of the control object (due to necessity of generation of dynamic components in navigation parametres without distortions); formation of measured values of primary navigation parametres in the reception apparatus of the satellite navigation system where the reception antenna is placed using tracking measuring devices with bandwidth greater than the frequency of rotation of the control object. Also values of primary navigation parametres are calculated in the computer of the inertial measurement modules and these values are also used in the feedback in the reception apparatus of the satellite navigation system for narrowing the frequency band in tracking systems of carrier frequency and code delay. ^ EFFECT: increased accuracy and noise immunity of integrated systems of orientation and navigation (ISON), which have inertial measurement modules (IMM) on "rough" micromechanical gyroscopes and a miniature reception apparatus of satellite navigation systems (RA SNS), in generating orientation parametres of control objects (CO) on a section of its ballistic trajectory for a long period of time, ie provision for stationary character and limited level of errors of integrated systems of orientation and navigation in solving the problem of orientation of a control object on a ballistic trajectory, as well as high level of noise immunity. ^ 6 dwg
Изобретение относится к области навигационного приборостроения. Техническим результатом изобретения является повышение точности и помехоустойчивости интегрированных систем ориентации и навигации (ИСОН), содержащей инерциальные измерительные модули (БИИМ) на «грубых» микромеханических гироскопах и миниатюрную приемную аппаратуру спутниковых навигационных систем (ПА СНС), в выработке параметров ориентации объектов управления (ОУ) на участке баллистической траектории его движения в течение длительного времени, т.е. обеспечение стационарного характера и ограниченного уровня погрешностей ИСОН в решении задачи ориентации ОУ на баллистической траектории, а также высокого уровня помехоустойчивости. Поставленная задача решается тем, что создаются условия, в которых появляется и используется существенная связь на участке баллистической траектории между моделями погрешностей БИИМ в решении задач ориентации и навигации. Данная связь появляется и может быть использована при обеспечении следующих условий: наличия быстрого вращения вокруг продольной оси и конического движения прецессии ОУ относительно центра масс или только вращения объекта вокруг продольной оси на баллистической траектории; размещении блока акселерометров БИИМ и приемной антенны СНС на некотором расстоянии (в основном по поперечной оси) от центра масс ОУ; решения задач ориентации и навигации в БИИМ в точке размещения блока акселерометров на высокой частоте - примерно на порядок больше частоты вращения ОУ (из-за необходимости выработки без искажений динамических составляющих в навигационных параметрах); формирования измеренных значен</description><language>eng ; rus</language><subject>GYROSCOPIC INSTRUMENTS ; MEASURING ; MEASURING DISTANCES, LEVELS OR BEARINGS ; NAVIGATION ; PHOTOGRAMMETRY OR VIDEOGRAMMETRY ; PHYSICS ; SURVEYING ; TESTING</subject><creationdate>2009</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20091210&DB=EPODOC&CC=RU&NR=2375680C1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25543,76293</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20091210&DB=EPODOC&CC=RU&NR=2375680C1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>BLAZHNOV BORIS ALEKSANDROVICH</creatorcontrib><creatorcontrib>EMEL'JANTSEV GENNADIJ IVANOVICH</creatorcontrib><creatorcontrib>KOROTKOV ALEKSANDR NIKOLAEVICH</creatorcontrib><creatorcontrib>NESENJUK LEONID PETROVICH</creatorcontrib><creatorcontrib>STEPANOV ALEKSEJ PETROVICH</creatorcontrib><title>INTEGRATED INERTIAL-SATELLITE ORIENTATION AND NAVIGATION SYSTEM FOR OBJECTS MOVING ON BALLISTIC TRAJECTORY WITH ROTATION AROUND LONGITUDINAL AXIS</title><description>FIELD: physics; navigation. ^ SUBSTANCE: invention relates to navigation instrument making. The set problem is solved by that, conditions are created in which substantial connection appears and is used on a section of a ballistic trajectory between error models of inertial measurement modules when solving the problem of orientation and navigation. This connection appears and can be used in providing the following conditions: presence of fast rotation around a longitudinal axis and coning motion of precession of the control object about the centre of mass or only rotation of the object around a longitudinal axis on a ballistic trajectory; placing a unit of accelerometres of inertial measurement modules and a reception antenna for the satellite navigation system at a certain distance (basically on a transverse axis) from the centre of mass of the control object; solving the problem of orientation and navigation in the inertial measurement modules at the point of placing the unit of accelerometres at high frequency - approximately an order higher than frequency of rotation of the control object (due to necessity of generation of dynamic components in navigation parametres without distortions); formation of measured values of primary navigation parametres in the reception apparatus of the satellite navigation system where the reception antenna is placed using tracking measuring devices with bandwidth greater than the frequency of rotation of the control object. Also values of primary navigation parametres are calculated in the computer of the inertial measurement modules and these values are also used in the feedback in the reception apparatus of the satellite navigation system for narrowing the frequency band in tracking systems of carrier frequency and code delay. ^ EFFECT: increased accuracy and noise immunity of integrated systems of orientation and navigation (ISON), which have inertial measurement modules (IMM) on "rough" micromechanical gyroscopes and a miniature reception apparatus of satellite navigation systems (RA SNS), in generating orientation parametres of control objects (CO) on a section of its ballistic trajectory for a long period of time, ie provision for stationary character and limited level of errors of integrated systems of orientation and navigation in solving the problem of orientation of a control object on a ballistic trajectory, as well as high level of noise immunity. ^ 6 dwg
Изобретение относится к области навигационного приборостроения. Техническим результатом изобретения является повышение точности и помехоустойчивости интегрированных систем ориентации и навигации (ИСОН), содержащей инерциальные измерительные модули (БИИМ) на «грубых» микромеханических гироскопах и миниатюрную приемную аппаратуру спутниковых навигационных систем (ПА СНС), в выработке параметров ориентации объектов управления (ОУ) на участке баллистической траектории его движения в течение длительного времени, т.е. обеспечение стационарного характера и ограниченного уровня погрешностей ИСОН в решении задачи ориентации ОУ на баллистической траектории, а также высокого уровня помехоустойчивости. Поставленная задача решается тем, что создаются условия, в которых появляется и используется существенная связь на участке баллистической траектории между моделями погрешностей БИИМ в решении задач ориентации и навигации. Данная связь появляется и может быть использована при обеспечении следующих условий: наличия быстрого вращения вокруг продольной оси и конического движения прецессии ОУ относительно центра масс или только вращения объекта вокруг продольной оси на баллистической траектории; размещении блока акселерометров БИИМ и приемной антенны СНС на некотором расстоянии (в основном по поперечной оси) от центра масс ОУ; решения задач ориентации и навигации в БИИМ в точке размещения блока акселерометров на высокой частоте - примерно на порядок больше частоты вращения ОУ (из-за необходимости выработки без искажений динамических составляющих в навигационных параметрах); формирования измеренных значен</description><subject>GYROSCOPIC INSTRUMENTS</subject><subject>MEASURING</subject><subject>MEASURING DISTANCES, LEVELS OR BEARINGS</subject><subject>NAVIGATION</subject><subject>PHOTOGRAMMETRY OR VIDEOGRAMMETRY</subject><subject>PHYSICS</subject><subject>SURVEYING</subject><subject>TESTING</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2009</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNjEsKwkAQRLNxIeod-gIBP_jZdpIxtozd0NOJZiUi40pU0It4YyPq3lXxqKrXTZ7E5kpFcwUQOzVCn4YWvSdzIEqODY2EAbkAxprKD4YmmNvAUhQkW7vcAmykJi6hLTNs_8EoB1N8l6INbMlWoPLTqVSt0QuXZFVBjB5wR6GfdE6H8z0OvtlLYOksX6Xxdt3H--1wjJf42Gs1nsyns8UwH03-mLwAoUlBfQ</recordid><startdate>20091210</startdate><enddate>20091210</enddate><creator>BLAZHNOV BORIS ALEKSANDROVICH</creator><creator>EMEL'JANTSEV GENNADIJ IVANOVICH</creator><creator>KOROTKOV ALEKSANDR NIKOLAEVICH</creator><creator>NESENJUK LEONID PETROVICH</creator><creator>STEPANOV ALEKSEJ PETROVICH</creator><scope>EVB</scope></search><sort><creationdate>20091210</creationdate><title>INTEGRATED INERTIAL-SATELLITE ORIENTATION AND NAVIGATION SYSTEM FOR OBJECTS MOVING ON BALLISTIC TRAJECTORY WITH ROTATION AROUND LONGITUDINAL AXIS</title><author>BLAZHNOV BORIS ALEKSANDROVICH ; EMEL'JANTSEV GENNADIJ IVANOVICH ; KOROTKOV ALEKSANDR NIKOLAEVICH ; NESENJUK LEONID PETROVICH ; STEPANOV ALEKSEJ PETROVICH</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_RU2375680C13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; rus</language><creationdate>2009</creationdate><topic>GYROSCOPIC INSTRUMENTS</topic><topic>MEASURING</topic><topic>MEASURING DISTANCES, LEVELS OR BEARINGS</topic><topic>NAVIGATION</topic><topic>PHOTOGRAMMETRY OR VIDEOGRAMMETRY</topic><topic>PHYSICS</topic><topic>SURVEYING</topic><topic>TESTING</topic><toplevel>online_resources</toplevel><creatorcontrib>BLAZHNOV BORIS ALEKSANDROVICH</creatorcontrib><creatorcontrib>EMEL'JANTSEV GENNADIJ IVANOVICH</creatorcontrib><creatorcontrib>KOROTKOV ALEKSANDR NIKOLAEVICH</creatorcontrib><creatorcontrib>NESENJUK LEONID PETROVICH</creatorcontrib><creatorcontrib>STEPANOV ALEKSEJ PETROVICH</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>BLAZHNOV BORIS ALEKSANDROVICH</au><au>EMEL'JANTSEV GENNADIJ IVANOVICH</au><au>KOROTKOV ALEKSANDR NIKOLAEVICH</au><au>NESENJUK LEONID PETROVICH</au><au>STEPANOV ALEKSEJ PETROVICH</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>INTEGRATED INERTIAL-SATELLITE ORIENTATION AND NAVIGATION SYSTEM FOR OBJECTS MOVING ON BALLISTIC TRAJECTORY WITH ROTATION AROUND LONGITUDINAL AXIS</title><date>2009-12-10</date><risdate>2009</risdate><abstract>FIELD: physics; navigation. ^ SUBSTANCE: invention relates to navigation instrument making. The set problem is solved by that, conditions are created in which substantial connection appears and is used on a section of a ballistic trajectory between error models of inertial measurement modules when solving the problem of orientation and navigation. This connection appears and can be used in providing the following conditions: presence of fast rotation around a longitudinal axis and coning motion of precession of the control object about the centre of mass or only rotation of the object around a longitudinal axis on a ballistic trajectory; placing a unit of accelerometres of inertial measurement modules and a reception antenna for the satellite navigation system at a certain distance (basically on a transverse axis) from the centre of mass of the control object; solving the problem of orientation and navigation in the inertial measurement modules at the point of placing the unit of accelerometres at high frequency - approximately an order higher than frequency of rotation of the control object (due to necessity of generation of dynamic components in navigation parametres without distortions); formation of measured values of primary navigation parametres in the reception apparatus of the satellite navigation system where the reception antenna is placed using tracking measuring devices with bandwidth greater than the frequency of rotation of the control object. Also values of primary navigation parametres are calculated in the computer of the inertial measurement modules and these values are also used in the feedback in the reception apparatus of the satellite navigation system for narrowing the frequency band in tracking systems of carrier frequency and code delay. ^ EFFECT: increased accuracy and noise immunity of integrated systems of orientation and navigation (ISON), which have inertial measurement modules (IMM) on "rough" micromechanical gyroscopes and a miniature reception apparatus of satellite navigation systems (RA SNS), in generating orientation parametres of control objects (CO) on a section of its ballistic trajectory for a long period of time, ie provision for stationary character and limited level of errors of integrated systems of orientation and navigation in solving the problem of orientation of a control object on a ballistic trajectory, as well as high level of noise immunity. ^ 6 dwg
Изобретение относится к области навигационного приборостроения. Техническим результатом изобретения является повышение точности и помехоустойчивости интегрированных систем ориентации и навигации (ИСОН), содержащей инерциальные измерительные модули (БИИМ) на «грубых» микромеханических гироскопах и миниатюрную приемную аппаратуру спутниковых навигационных систем (ПА СНС), в выработке параметров ориентации объектов управления (ОУ) на участке баллистической траектории его движения в течение длительного времени, т.е. обеспечение стационарного характера и ограниченного уровня погрешностей ИСОН в решении задачи ориентации ОУ на баллистической траектории, а также высокого уровня помехоустойчивости. Поставленная задача решается тем, что создаются условия, в которых появляется и используется существенная связь на участке баллистической траектории между моделями погрешностей БИИМ в решении задач ориентации и навигации. Данная связь появляется и может быть использована при обеспечении следующих условий: наличия быстрого вращения вокруг продольной оси и конического движения прецессии ОУ относительно центра масс или только вращения объекта вокруг продольной оси на баллистической траектории; размещении блока акселерометров БИИМ и приемной антенны СНС на некотором расстоянии (в основном по поперечной оси) от центра масс ОУ; решения задач ориентации и навигации в БИИМ в точке размещения блока акселерометров на высокой частоте - примерно на порядок больше частоты вращения ОУ (из-за необходимости выработки без искажений динамических составляющих в навигационных параметрах); формирования измеренных значен</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | GYROSCOPIC INSTRUMENTS MEASURING MEASURING DISTANCES, LEVELS OR BEARINGS NAVIGATION PHOTOGRAMMETRY OR VIDEOGRAMMETRY PHYSICS SURVEYING TESTING |
| title | INTEGRATED INERTIAL-SATELLITE ORIENTATION AND NAVIGATION SYSTEM FOR OBJECTS MOVING ON BALLISTIC TRAJECTORY WITH ROTATION AROUND LONGITUDINAL AXIS |
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