A.I. Rysin1
1Ulyanovsk State Technical University (Ulyanovsk, Russia)
1rysin88@mail.ru
In the article the problem of ensuring the accuracy of the output navigation information of a free-form inertial navigation system is considered in relation to the typical composition of the onboard equipment of a general-purpose helicopter.
At the beginning of the article, the author notes that along with the advantages of the INS, which determined its choice as the main navigation system, the errors of the navigation parameters measured by it increase over time, which determines the need to correct them on measurements from other navigation systems. As the author points out, different methods that can be used for a helicopter only in a limited way were previously proposed. For example, they did not fully take into account the INS error model, the specifics of the object movement, and also required significant hardware costs. Next, the author examines the main navigation systems from the onboard equipment installed on general-purpose helicopters, gives their advantages and disadvantages. The main task, according to the author, is the possibility on board the aircraft of continuous assessment and correction of INS errors by external measurements. To solve this problem, the author presents a basic algorithm for estimating and subsequent correction of measurement errors of the INS by measurements of the satellite radio navigation system or the Doppler speed sensor from the helicopter's onboard equipment and provides restrictions on the solution being developed. At the same time, A.I. Rysin notes that it is also necessary to evaluate the accuracy of the solution obtained based on flight data and make a conclusion about its applicability on board the aircraft.
A.I. Rysin presents a complete stochastic INS error model, the state vector of which consists of 18 elements, and an observation model based on difference measurements of the INS and either a satellite navigation system (SNS) or a Doppler speed sensor. The presented models and correction algorithm, the author notes, firstly, make it possible to obtain a general solution for positional and high-speed channels for navigation information, and secondly, they are implemented as part of on-board digital computers. The author of the article confirms these provisions by presenting the results of mathematical modeling using registered flight data.
In conclusion, A.I. Rysin presents results of the statistical analysis of the errors in measuring the coordinates and speed of the integrated navigation complex and a comparative analysis of the accuracy of the results of various integration algorithms, This data allow us to talk about ensuring the required accuracy of determining the speed formed by the integrated navigation complex of a helicopter consisting of free-form INS and SNS or Doppler speed sensor equipment.
Rysin A.I. Algorithm of continuous error correction of the free-form inertial navigation system (INS) as part of the on-board equipment of a general-purpose helicopte. Information-measuring and Control Systems. 2024. V. 22. № 1. P. 51−66. DOI: https://doi.org/10.18127/j20700814-202401-06 (in Russian)
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