A family of universal miniature autopilots - design solutions, characteristics, hardware/software-in-the-loop simulations

Kopecki, Grzegorz; Rzucidło, Paweł; Grzybowski, Piotr; Kordos, Damian

doi:10.2514/6.2016-3220

Cited by 4 publications

(4 citation statements)

References 8 publications

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“…Hardware in the loop simulations were realized for the system verification (Kopecki, 2016; Kopecki, 2018). For simulations, nonlinear aircraft model designed with the use of X-Plane was used, implemented in PC AC dynamics simulation and visualization computer.…”

Section: Simulation Resultsmentioning

confidence: 99%

Aircraft control with the use of model reference adaptive control

Kopecki

2021

AEAT

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Purpose Indirect (fly-by-wire) control systems for general aviation aircraft and unmanned aircraft vehicles (UAV) control systems enable the decoupling of control surfaces. This method of aircraft control is different from classical approach. The purpose of the article is to show the aircraft can be controlled even if the control control surfaces are blocked. Design/methodology/approach The concept discussed here relies on model reference adaptive control. The approach presented requires modifications of aircraft linearized model. In this paper, an example of roll angle control is shown. Findings During simulations the system worked properly with control surfaces partially blocked, if the blockage appeared close to neutral position. Exemplary simulations are shown in the text. Practical implications The solution presented was implemented on a UAV autopilot. Hardware in the loop simulations were performed, which shows the potential of practical usage. Originality/value Aircraft control, as discussed in this paper, gives the possibility of aircraft control and stable flight before a fault is detected, which increases the safety level.

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Section: Simulation Resultsmentioning

confidence: 99%

Aircraft control with the use of model reference adaptive control

Kopecki

2021

AEAT

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“…The results made available in this article constitute preliminary work and can be developed in several directions. A further objective is to implement a designed control system in a missile using different autopilot systems and put it to tests in a real environment [8,9] and different missile configurations [10]. Another task is implementation of different control algorithms.…”

Section: Discussionmentioning

confidence: 99%

“…Another task is implementation of different control algorithms. The presented stand can also be used for hardware in loop simulation [8].…”

Section: Discussionmentioning

confidence: 99%

Laboratory Stand for Simplified Verification of Missile Dynamics for Didactic Purposes

Rowicki

Kopecki

2021

Advances in Manufacturing Science and Technology

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The purpose of this study was to describe dynamics of missile based on bibliography, simplify the model to the easiest form, and verify it with the use of a designed laboratory stand. Next, a simple control system of the missile was designed. The stand is prepared for didactic purposes. A mathematical model was derived by applying Newton's second law together with the earth's coordinate system and the base coordinate system. Parameters of the actual rocket model were determined using the created laboratory stand. Synthesis of the rocket roll system was designed using Simulink PID Tuner application (MathWorks, Inc. Natick, Massachusetts, USA). A control system was based on a proportional-integral (PI) regulator. The designed control system was subjected to simulated tests in MATLAB Simulink (MathWorks, Inc. Natick, Massachusetts, USA).

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“…Unfortunately, some categories of flight tests have limited application in ultra-light (UL) and remotely piloted aircraft system (RPAS) systems because of weight limitations and the complexity of data collection systems (Bakunowicz and Meyer, 2016; Blachuta et al , 2014; Brzozowski et al , 2017; Majka, 2014; Nowak et al , 2014; Kopecki and Rzucidlo, 2016). Another challenge is the flexibility of systems in terms of signal redundancy, multiple measurement points (Krichen et al , 2017), capability and integration issues (Chudy et al , 2013; Kopecki et al , 2016; Majka, 2017). Moreover, flight test costs are increased by the necessity of complex processing and interpretation of collected data, as well as limitations driven by regulations (Szewczyk et al , 2017; Rzucidlo et al , 2016).…”

Section: Introductionmentioning

confidence: 99%

Distributed measurement system based on CAN data bus

Grzybowski

Klimczuk

Rzucidło

2018

AEAT

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Purpose This paper aims to describe the idea behind and design of a miniaturized distributed measurement system based on a controller area network (CAN) data bus. Design/methodology/approach The intention of the designers was to build a light and modular measurement system which can be used in remotely piloted aircraft systems and ultra-light aircraft during flight tests, as well as normal operation. The structure of this distributed measurement system is based on a CAN data bus. The CAN aerospace standard has been applied to the software as well as the hardware comprising this system. PRP-W2 software designed for PCs is an additional component of the proposed measurement system. This software supports data acquisition from a recorder unit and allows for preliminary data analysis, as well as data conversion and presentation. Findings The system, complete with a high-speed data recorder, was successfully installed on board of an MP-02 Czajka aircraft. A research experiment using the system and oriented on airframe high frequency vibration analysis is presented in the final part of this paper. Research limitations/implications This measurement system allows analysis of high-frequency vibrations occurring at selected points of the aircraft. A data set is recorded by three-axis accelerometers and gyroscopes at frequencies up to 1 kHz. Practical implications The use of a miniature and lightweight modular measurement system will, in many cases, be faster and less expensive than full-scale measurement and data acquisition systems, which often require a lengthy assembly process. The implementation of this class of lightweight flight test systems has many advantages, in particular to the operation of small aircraft. Such solutions are likely to become increasingly common in unmanned aerial vehicles and in other light aircraft in the future. Originality/value The adaptation of a distributed measuring system with a high frequency of measurements for purposes of small and miniature aircraft.

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A family of universal miniature autopilots - design solutions, characteristics, hardware/software-in-the-loop simulations

Cited by 4 publications

References 8 publications

Aircraft control with the use of model reference adaptive control

Aircraft control with the use of model reference adaptive control

Laboratory Stand for Simplified Verification of Missile Dynamics for Didactic Purposes

Distributed measurement system based on CAN data bus

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