IMPLEMENTATION OF INTERTIAL NAVIGATION SYSTEM MODEL DURING AIRCRAFT TESTING
Abstract
The flight subset control is required during the aviation equipment test flights. In order to achieve this objective the complex consisting of strap down inertial navigation system (SINS) and user equipment of satellite navigation systems (SNS) can be used. Such combination needs to be used for error correction in positioning which is accumulated in SINS with time. This article shows the research results of the inertial navigation system (INS) model. The results of the positioning error calculation for various INS classes are given. Each of the examined INS has a different accumulated error for the same time lag. The methods of combining information of INS and SRNS are covered. The results obtained can be applied for upgrading the aircraft flight and navigation complexes. In particular, they can allow to continuously determine speed, coordinates, angular situation and repositioning rate of change of axes of the instrument frame.
About the Authors
V. A. Borsoev
Institute of Air Navigation
Russian Federation
Moscow
Russian Federation
Moscow
A. V. Katsura
Siberian State Aerospace University
Russian Federation
Krasnoyarsk
Russian Federation
Krasnoyarsk
S. M. Stepanov
Ulyanovsk Higher Civil Aviation School
Russian Federation
Ul'yanovsk
Russian Federation
Ul'yanovsk
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Review
For citations:
Borsoev V.A., Katsura A.V., Stepanov S.M. IMPLEMENTATION OF INTERTIAL NAVIGATION SYSTEM MODEL DURING AIRCRAFT TESTING. Civil Aviation High Technologies. 2016;19(5):144-150. (In Russ.)
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