gyroscopyГироскопия и навигацияGiroskopiya i Navigatsiya / Gyroscopy and Navigation0869-70352075-0927AO «Концерн «ЦНИИ «Электроприбор»gyroscopy-482Research ArticleСтатьиИнтегрированная навигационная система на основе МЭМС для адаптивного управления полетом беспилотного аппаратаФерсманП.

Ферсман Петер, профессор

КашвихК.

Кашвих Клаус, инженер 

КрюгерT.

Крюгер Томас, инженер

ШнеттерФ.

Шнеттер Филипп, инженер 

ВилкенсК.-С.

Вилкенс Клаус-Себастьян, инженер

Институт аэрокосмических систем Технического университета БрауншвейгаGermanyИнститут аэрокосмических систем Технического университета Брауншвейга (Брауншвейг)Germany201326022026211318Copyright © Ферсман П., Кашвих К., Крюгер T., Шнеттер Ф., Вилкенс К., 20262026Ферсман П., Кашвих К., Крюгер T., Шнеттер Ф., Вилкенс К.Ферсман П., Кашвих К., Крюгер T., Шнеттер Ф., Вилкенс К.Данная работа распространяется под лицензией Creative Commons Attribution 4.0.This work is licensed under a Creative Commons Attribution 4.0 License.https://www.gyroscopy.ru/jour/article/view/482

Рассматривается предназначенная для управления беспилотным летательным аппаратом (БПЛА) интегрированная навигационная система. Приводятся характеристики входящих в нее датчиков, а также их модели, определенные на основе вариации Аллана. Предлагается закон управления БПЛА адаптивный к неопределенностям условий полета и повреждениям исполнительных органов. Приводятся результаты моделирования, подтверждающие эффективность закона управления.

Статья по приглашенному докладу на XIX Санкт-Петербургской международной конференции по интегрированным навигационным системам.

The current development process especially of small unmanned aircraft systems from automatic to semi-autonomous or even fully autonomous behaviour demands for reliable and precise navigation solutions as well as robust control strategies. For a truly autonomous system adequate as well as secure reactions towards nonlinearities arising for example from unknown environmental conditions or system dam-ages are a prerequisite. An adaptive flight control system, which has to cancel the undesirable effects of such disturbances depends on constantly available accurate navigation data. To satisfy these boundary conditions, it is sensible to stronger intertwine the development process of miniaturised navigation systems and adaptive flight controllers. As the controller design and its validation is based on nonlinear simulations, it is advisable to model the integrated navigation system and its low-cost components in a detailed way, so that its distinct dynamic properties can already be taken into account during the development process of the controller. In this context, a tightly coupled integrated navigation scheme is presented, where the characteristics of the sensor components are identified and modelled using the Allan variance analysis. This information can be used during the validation process of the proposed adaptive flight control system, which is based on the concept of nonlinear dynamic inversion combined with artificial neural networks. This paper gives an overview on how miniaturised navigation systems can be modelled and utilised for adaptive flight control schemes of small unmanned aircraft.

 

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The authors declare that there are no conflicts of interest present.