Nothing Special   »   [go: up one dir, main page]

RU95105180A - Method of inertial navigation - Google Patents

Method of inertial navigation

Info

Publication number
RU95105180A
RU95105180A RU95105180/28A RU95105180A RU95105180A RU 95105180 A RU95105180 A RU 95105180A RU 95105180/28 A RU95105180/28 A RU 95105180/28A RU 95105180 A RU95105180 A RU 95105180A RU 95105180 A RU95105180 A RU 95105180A
Authority
RU
Russia
Prior art keywords
coordinate system
accelerometers
signals
standard model
reading coordinate
Prior art date
Application number
RU95105180/28A
Other languages
Russian (ru)
Other versions
RU2107897C1 (en
Inventor
С.М. Якушин
Original Assignee
Пермский государственный технический университет
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Пермский государственный технический университет filed Critical Пермский государственный технический университет
Priority to RU95105180A priority Critical patent/RU2107897C1/en
Publication of RU95105180A publication Critical patent/RU95105180A/en
Application granted granted Critical
Publication of RU2107897C1 publication Critical patent/RU2107897C1/en

Links

Landscapes

  • Navigation (AREA)

Abstract

FIELD: inertial navigation, specifically determination of present values of coordinates of moving object. SUBSTANCE: increased accuracy of inertial navigation is achieved thanks to determination of angular drift of reading coordinate system of navigational system which operational mode corresponds to standard model. Relative angular mismatch of reading coordinate system and nominal reading coordinate system is determined by comparison of real signals from accelerometers of navigational system with signals of accelerometers computed on basis of usage of intermediate and output parameters of standard model of navigational system re-calculated into output signals from accelerometers corresponding to them using functional realization of standard model for reverse re-calculation of its output parameters to input ones corresponding to them. Reading coordinate system of standard model is turned with reference to reading coordinate system of navigational system through angles fixed in space. EFFECT: increased accuracy of determination of present coordinates of moving object.

Claims (1)

Область техники: относится к области инерциальной навигации, в частности к способам определения текущих значений координат движущегося объекта. Сущность: повышение точности инерциальной навигации достигается за счет определения углового дрейфа отсчетной системы координат навигационной системы, режим работы которой соответствует эталонной модели, определяют взаимное угловое рассогласование отсчетной системы координат и номинальной отсчетной системы координат путем сравнения реальных сигналов с акселерометров навигационной системы с вычисляемыми сигналами акселерометров на основе использования промежуточных и выходных параметров эталонной модели навигационной системы, пересчитываемых в соответствующие им выходные сигналы с акселерометров, используя функциональную реализацию эталонной модели для обратного пересчета ее выходных параметров в соответствующие им входные. Отсчетная система координат эталонной модели разворачивается относительно отсчетной системы координат навигационной системы на фиксированные углы в пространстве.Field of technology: relates to the field of inertial navigation, in particular to methods for determining the current coordinates of a moving object. Essence: increasing the accuracy of inertial navigation is achieved by determining the angular drift of the reference coordinate system of the navigation system, the operation mode of which corresponds to the reference model, determine the mutual angular mismatch of the reference coordinate system and the nominal reference coordinate system by comparing the real signals from the accelerometers of the navigation system with the calculated signals of the accelerometers on based on the use of intermediate and output parameters of the reference model of the navigation system, recalculated to the corresponding output signals from accelerometers, using the functional implementation of the reference model for the inverse conversion of its output parameters to the corresponding input ones. The reference coordinate system of the reference model is deployed relative to the reference coordinate system of the navigation system at fixed angles in space.
RU95105180A 1995-04-10 1995-04-10 Method of inertia navigation RU2107897C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU95105180A RU2107897C1 (en) 1995-04-10 1995-04-10 Method of inertia navigation

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU95105180A RU2107897C1 (en) 1995-04-10 1995-04-10 Method of inertia navigation

Publications (2)

Publication Number Publication Date
RU95105180A true RU95105180A (en) 1996-11-27
RU2107897C1 RU2107897C1 (en) 1998-03-27

Family

ID=20166457

Family Applications (1)

Application Number Title Priority Date Filing Date
RU95105180A RU2107897C1 (en) 1995-04-10 1995-04-10 Method of inertia navigation

Country Status (1)

Country Link
RU (1) RU2107897C1 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2509289C2 (en) * 2012-03-05 2014-03-10 Федеральное государственное военное образовательное учреждение высшего профессионального образования Военная академия Ракетных войск стратегического назначения имени Петра Великого МО РФ Azimuthal orientation of platform of triaxial gyrostabiliser by increments of angle of gyroblock precession
RU2577567C1 (en) * 2015-01-22 2016-03-20 Акционерное общество "Концерн "Центральный научно-исследовательский институт "Электроприбор" Method for strapdown inertial navigation on micromechanical sensitive elements
RU2658124C1 (en) * 2017-09-11 2018-06-19 Федеральное государственное бюджетное учреждение науки Институт проблем управления им. В.А. Трапезникова Российской академии наук Method of the object movement parameters measurement and system for its implementation

Also Published As

Publication number Publication date
RU2107897C1 (en) 1998-03-27

Similar Documents

Publication Publication Date Title
WO2003071692A3 (en) Device for use with a portable inertial navigation system (pins) and method for processing pins signals
ATE294981T1 (en) REAL-TIME DISTRIBUTED NAVIGATION METHODS
ATE386463T1 (en) MOTION TRACKING SYSTEM
ATE209336T1 (en) IMPROVED VEHICLE NAVIGATION SYSTEM AND METHOD
KR930022095A (en) Vehicle positioning device
WO2004015369A3 (en) Motion tracking system and method
RU2002107137A (en) The method of determining the sources of radio emissions
RU95105180A (en) Method of inertial navigation
DE69817617D1 (en) ANGLE SENSOR
AU6394798A (en) Method to determine correction parameters
SE9303808D0 (en) Method and apparatus for directional determination
DE602004002240D1 (en) Interpolation method for a high-resolution optical angle sensor and associated optical angle sensor
RU2085850C1 (en) System of course and vertical and method determining magnetic course
Gunnam et al. A DSP embedded optical navigation system
RU2784337C1 (en) Method for unipositional measurement of the coordinates of an optical emission source
RU2127867C1 (en) Method of dynamic measurement of angular displacements
RU2194250C1 (en) Method for controlling movable objects traveling route
RU93014137A (en) METHOD FOR DETERMINING PRESSURE LEVELS AND SPATIAL LOCATION OF SOURCES OF NOISE RADIATION OF MOVING OBJECT
Retscher Multi-sensor fusion using a Kalman filter and knowledge-based systems
JPS6435314A (en) On-vehicle navigation system
SU1377586A1 (en) Device for determining azimuth
RU2020111C1 (en) Device for detection of angular position of aircraft relative to earth magnetic field
JPS6435318A (en) On-vehicle navigation system
CN109186595A (en) A kind of indoor and outdoor combined navigation device based on STM32
RU94028538A (en) Method of determination of degree of non-linearity of primary navigational information sensors