Use Of Inertial And Satellite Navigation Systems For Time Reduction Of The Space Satellite Initial Attitude

Paper number

IAC-07-C1.8.08

Author

Dr. Anatoliy Alpatov, Institute of Technical Mechanics of the National Academy of Science and National Space Agency of Ukraine, Ukraine

Coauthor

Dr. Vjacheslav Gusinin, Ukraine

Coauthor

Mr. Alexander Makarov, Yuzhnoye State Design Office, Ukraine

Coauthor

Mr. Aleksey Tykhonov, Institute of Technical Mechanics of the National Academy of Science and National Space Agency of Ukraine, Ukraine

Year

2007

Abstract

After insertion of space satellite into an orbit the first session of attitude is the mode of a dampening in which high by value components of a space satellite angular velocity are blanked to prefixed values. At once after separation from the launch vehicle of a space satellite its motion has the complex rotational character coupled to in advance unknown vector of moment of a momentum, which applies to it by the launch vehicle and the separation system. The mode of a dampening practically is not separable from a mode of orientation putting to prefixed attitude.

Energy and time resources are spent at first for decrease of initial angular velocities, and then for providing of the prefixed orientation (impart of the angular velocities ensuring preset angular orientation).
With the purpose of decrease of these expenditures the way of orientation and angular velocities determination of a space satellite at the moment of separation from the launch vehicle by use of inertial navigation system (INS) of a space satellite which includes sensor units of an angular velocity and accelerometers, and results of the navigation problem solution by satellite navigation equipment is researched.

As the instrument of the vector matching the Kalman filter is used.

As a vector of observation the difference between the components of a state vector evaluated according to INS and satellite navigation equipment is used. Angles of orientation and a projection of angular-velocity vector of space satellite around of each of axes of an inertial system of coordinates are determined. The Kalman filter determines current values of the given parameters.
The equations of errors of orientation determination of orientation by space vehicle INS and satellite navigation equipment are gained. These equations are used for prediction of current parameters of space satellite orientation.

The comparative analysis of determination of orientation and mode of decrease of initial angular velocities of space vehicle is conducted by a traditional way and by use of the offered method.

Abstract document

IAC-07-C1.8.08.pdf

Manuscript document

IAC-07-C1.8.08.pdf (🔒 authorized access only).

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