Wyniki wyszukiwania - BazTech

1

Operation and reliability of an onboard GNSS receiver during an in-flight test

Krasuski Kamil, Bakuła Mieczysław

Zeszyty Naukowe. Transport / Politechnika Śląska

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2021

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z. 111

75--88

EN

This article presents and describes the operational capabilities of an onboard GNSS receiver to determine the reliability of the in-flight navigation parameters. An analysis was made of the operation reliability of an autonomous single-frequency Thales Mobile Mapper receiver in air navigation as compared to the technical operation of a dual-frequency Topcon HiperPro receiver. To this end, this work contains a comparison of the aircraft flight navigation parameters based on readings obtained from the Thales Mobile Mapper and Topcon HiperPro receivers. In particular, the comparison concerned the reliability of coordinate determination and flight speed parameters of an aircraft. The research experiment was conducted using a Cessna 172 aircraft, a property of the Military University of Aviation in Dęblin, Poland. Technical operation of the GNSS satellite receivers was tested in the flights of the Cessna 172 aircraft around the EPDE military airport in Dęblin. Based on the results obtained from the tests, it was found that the operational reliability of the Thales Mobile Mapper in the operational phase of the in-flight test ranged from -3.8 to +6.9 m in the XYZ geocentric frame and from -2.2 to +8.1 m in the BLh ellipsoidal frame, respectively. On the other hand, the accuracy of the Cessna 172 aircraft positioning when using the Thales Mobile Mapper receiver was higher than 1.7 m in the XYZ geocentric frame and higher than 2 m in the BLh ellipsoidal frame, respectively. Furthermore, the reliability of the Cessna 172 flight speed determination was from -3.4 to +2.4 m/s.

2

On board data acquisition system with intelligent transducers for unmanned aerial vehicles

Rochala Z.

Archives of Transport

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2011

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Vol. 23, iss. 4

521-529

EN

This report presents conc1usions from research project no. ON50900363 conducted at the Mechatronics Department, Military University of Technology in the years 2007-2010. As the main object of the study involved the preparation of a concept and the implementation of an avionics data acquisition system intended for research during flight of unmanned aerial vehicles of the mini class, this article presents a design of an avionics system and describes equipment solutions of a distributed measurement system intended for data acquisition consisting of intelligent transducers. The data collected during a flight controlled by an operator confirmed proper operation of the individual components of the data acquisition system.

PL

W referacie przedstawiono wnioski z prowadzonego w Zakładzie Awioniki i Uzbrojenia Lotniczego Wydziału Mechatroniki Wojskowej Akademii Technicznej w latach 2007-2010 projektu badawczego nr ON50900363. Ponieważ głównym celem pracy było opracowanie koncepcji i realizacja systemu akwizycji danych przeznaczonego do badań w locie bezpilotowych statków powietrznych klasy "mini" w artykule zaprezentowano projekt systemu awionicznego oraz opisano rozwiązania sprzętowe rozproszonego systemu pomiarowego służącego do akwizycji danych z przetworników inteligentnych. Zgromadzone podczas lotu sterowanego przez operatora dane potwierdziły poprawności działania poszczególnych składowych systemu akwizycji danych.

3

Iskra II - a scaled remotely piloted vehicle research program

Szender M.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

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2001

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nr 12

105-108

EN

Cost effective and low risk research methods, employing small-scale Remotely Piloted Vehicles (RPV), are becoming an important part of the airplane design process. The research program into a powered RPV is being initiated at Warsaw University of Technology on a 1/5 scale model of the ISKRA II airplane to collect the flight data at low and high angles of attack. The similarity criterion employed and RPV dimensions will be discussed. The stages of the program, description of the vehicle considered, propulsion system, launch and landing techniques and air-data collecting system will be presented, as well Also, a method for verification of the expected results will be discussed.