RU2009145970A - INTEGRATED INERTIAL-SATELLITE ORIENTATION AND NAVIGATION SYSTEM - Google Patents
INTEGRATED INERTIAL-SATELLITE ORIENTATION AND NAVIGATION SYSTEM Download PDFInfo
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- RU2009145970A RU2009145970A RU2009145970/09A RU2009145970A RU2009145970A RU 2009145970 A RU2009145970 A RU 2009145970A RU 2009145970/09 A RU2009145970/09 A RU 2009145970/09A RU 2009145970 A RU2009145970 A RU 2009145970A RU 2009145970 A RU2009145970 A RU 2009145970A
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Abstract
Интегрированная инерциально-спутниковая система ориентации и навигации, содержащая бескарданный инерциальный измерительный модуль (БИИМ), включающий измерительный блок (ИБ) на «грубых» гироскопах и акселерометрах (например, на микромеханических гироскопах и микромеханических акселерометрах), блок выработки параметров ориентации (БВПО), блок выработки навигационных параметров (БВНП), блок комплексной обработки информации (БКОИ) и ПА СНС, включающую два или несколько приемных устройств с разнесенными на соответствующих базах антеннами и блок выработки вторых разностей фаз сигналов на несущей частоте, ! отличающаяся тем, что в состав БИИМ дополнительно введен блок формирования и разрешения неоднозначности разностных фазовых измерений (БФиРНРФИ), первый вход которого соединен с выходом ПА СНС по измеренным значениям вторых разностей фаз сигналов навигационных спутников, второй вход соединен с выходом ПА СНС по эфемеридной информации (координатам навигационных спутников), третий вход соединен с одним из выходов блока БВНП, четвертый вход соединен с одним из выходов блока БВПО, пятый вход соединен с третьим выходом блока БКОИ, а выход блока БФиРНРФИ соединен с третьим входом блока БКОИ, а ИБ БИИМ и опорная антенна ПА СНС установлены на максимально возможном отстоянии от центра масс объекта, при этом величина отстояния ограничивается размерами объекта и его конструктивными особенностями (ИБ БИИМ и опорную антенну ПА СНС размещают в одной точке объекта). An integrated inertial-satellite orientation and navigation system containing a gimballess inertial measuring module (BIIM), including a measuring unit (IS) on “rough” gyroscopes and accelerometers (for example, micromechanical gyroscopes and micromechanical accelerometers), a unit for generating orientation parameters (BVPO), a unit for generating navigation parameters (BVNP), a unit for complex information processing (BKOI) and PA SNA, including two or more receiving devices with antennas spaced at respective bases and a block generating second phase differences of the signals at the carrier frequency,! characterized in that the structure of BIIM additionally includes a unit for generating and resolving the ambiguity of difference phase measurements (BFiRNRFI), the first input of which is connected to the output of the PA SNA according to the measured values of the second phase differences of the signals of navigation satellites, the second input is connected to the output of the PA SNA by ephemeris information ( coordinates of navigation satellites), the third input is connected to one of the outputs of the BVNP unit, the fourth input is connected to one of the outputs of the BVPO block, the fifth input is connected to the third output of the BKOI unit, and the output is block and the BFIRNRFI is connected to the third input of the BKOI unit, and the ISBIIM and the reference antenna of the SNA SNA are installed at the maximum possible distance from the center of mass of the object, while the distance is limited by the size of the object and its design features (the BIIIM and the reference antenna of the SNA are placed at one point object).
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Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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RU2009145970/09A RU2009145970A (en) | 2009-12-08 | 2009-12-08 | INTEGRATED INERTIAL-SATELLITE ORIENTATION AND NAVIGATION SYSTEM |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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RU2009145970/09A RU2009145970A (en) | 2009-12-08 | 2009-12-08 | INTEGRATED INERTIAL-SATELLITE ORIENTATION AND NAVIGATION SYSTEM |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
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RU2011120316/28A Previously-Filed-Application RU2462690C1 (en) | 2011-05-13 | 2011-05-13 | Integrated inertial satellite system for orientation and navigation |
Publications (1)
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RU2009145970A true RU2009145970A (en) | 2011-06-20 |
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Application Number | Title | Priority Date | Filing Date |
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RU2009145970/09A RU2009145970A (en) | 2009-12-08 | 2009-12-08 | INTEGRATED INERTIAL-SATELLITE ORIENTATION AND NAVIGATION SYSTEM |
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RU (1) | RU2009145970A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2633034C2 (en) * | 2012-06-15 | 2017-10-11 | Зе Боинг Компани | Delay compensation |
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2009
- 2009-12-08 RU RU2009145970/09A patent/RU2009145970A/en not_active Application Discontinuation
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2633034C2 (en) * | 2012-06-15 | 2017-10-11 | Зе Боинг Компани | Delay compensation |
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Legal Events
Date | Code | Title | Description |
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FA92 | Acknowledgement of application withdrawn (lack of supplementary materials submitted) |
Effective date: 20110610 |