Possibilities of using software redundancy in low cost aeronautical control systems

Dołęga, B.; Kopecki, Grzegorz; Tomczyk, Andrzej

doi:10.1109/metroaerospace.2016.7573181

Cited by 11 publications

(4 citation statements)

References 7 publications

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“…While such information may be relevant to adjusting the mode and parameters of the control system, restrictions on the size and weight of those aircraft do not allow the installation of physical systems, practically. So, virtual sensors do appear a viable solution, as widely reported in the literature [8][9][10].…”

Section: Introductionmentioning

confidence: 83%

Preliminary Assessment of an FBG-Based Landing Gear Weight on Wheel System

et al. 2022

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Weight-on-Wheels (WoW) systems are aimed at indicating if the aircraft weight is loading onto the landing gear and its wheels, even partially. These systems are an integral part of the actuation system for safety-critical applications and shall provide reliable information on the actual operational status of the LG. That information reveals if the vehicle is in flight or on the ground. In this way, several kinds of accidents may be prevented, relating for instance, to the incorrect deployment of the landing gear, or even manoeuvres to a certain extent, therefore protecting the aircraft from dangerous damage. There are different architectures that have been proposed in the bibliography, some of them based on strain gauges deployed on the structure, or on proximity sensors installed on the wheels. Being this device and considered critical for safety, it is convenient to couple it with complementary measurements, recorded and processed by different sources. In general, it can be stated that such an intelligent sensor network may be seen as a fundamental support for proper landing gear deployment. The presented paper reports the results of a preliminary investigation performed by the authors to evaluate the possibility of deploying fibre optics on the landing gear structure as part of a WoW system to retrieve the required information. This choice would have a remarkable effect in terms of significant cabling reduction (a single array of sensing elements could be deployed over a single line), and cost abatement from both a manufacturing and operational point of view. There are many other benefits also when referring to an optical instead of a standard electrical sensor system. Due to its small size and ease of integration into different families of materials, it could be considered a system for monitoring the operating status of most actuators on board modern aircraft.

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Section: Introductionmentioning

confidence: 83%

Preliminary Assessment of an FBG-Based Landing Gear Weight on Wheel System

et al. 2022

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“…Measurement of aircraft attitude and heading angles is one of the primary tasks of airborne systems. These data are necessary for aircraft control (Nowak, 2014) and frequently used for the analysis of other measurements (Bakunowicz and Rzucidlo, 2017; Kopecki and Rzucidlo, 2016; Dolega, 2016). Figure 1 presents the general scheme of the AHRS control systems.…”

Section: Introductionmentioning

confidence: 99%

A proposal of AHRS yaw angle correction with the use of roll angle

Kopecki

Banicki

2023

AEAT

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Purpose Attitude and heading are very important measurements on board aircraft. In modern solutions they are measured by the attitude and heading reference system (AHRS). In some small unmanned systems, the GPS track angle is used for heading corrections instead of the magnetometer; then, the system measures the track angle instead of heading. With a temporary lack of correction signals, the measurement error increases very quickly. Similarly, a quick increase in the measurement error is observed when a magnetic heading sensor used for correction stops working properly. This study aims to propose measurement of the roll angle for yaw angle correction. Design/methodology/approach AHRS algorithms were designed; typical maneuvers were analyzed. The method was verified by simulation and in flight testing analysis. For quantitative analyses, a performance index was proposed. Findings The method enables reduction of the yaw angle error caused by the gyros bias error. This study presents the idea, results of simulations and flight testing data analysis and discusses advantages and limitations of the presented method. Practical implications The presented methodology can be implemented in AHRS systems for manned and unmanned aircraft. Originality/value This study enables more accurate measurement of the yaw angle in the case of missing correction signals.

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“…They can be defined as sensors measuring at a location where the sensor should physically be placed, but it is not. Examples of such solutions from various fields are presented in the works [ 8 , 9 , 10 ]. Virtual measurement methods enable the determination of specific quantities based on measurements from other physically available sensors.…”

Section: Introductionmentioning

confidence: 99%

Detection of Aircraft Touchdown Using Longitudinal Acceleration and Continuous Wavelet Transformation

Bakunowicz

Rzucidło

2020

Sensors

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The paper presents a methodology enabling the detection of aircraft touchdowns based on data obtained from accelerometers attached to the structural parts of the airframe in the cockpit or passenger compartment. Precise determination of the moment and place of touchdown of the main landing gear is challenging when analysing parameters such as height, flight speed and rate of descent. During the tests of the I-31T aircraft, it turned out that vibrations of the aircraft structure caused by the contact of the front and main landing gear with the ground have a repetitive character. In particular, this applies to longitudinal acceleration. The use of continuous wavelet analysis (CWT) allowed finding unique periodic features of the landing phenomenon that distinguish it from other forms of vibration occurring in individual flight phases. Ground and flight observations of experimental aeroplane MP-02 Czajka verified the proposed method of virtual touchdown detection. The results presented in this paper justify that this method may find broader application, especially for the light aircraft class.

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Possibilities of using software redundancy in low cost aeronautical control systems

Cited by 11 publications

References 7 publications

Preliminary Assessment of an FBG-Based Landing Gear Weight on Wheel System

Preliminary Assessment of an FBG-Based Landing Gear Weight on Wheel System

A proposal of AHRS yaw angle correction with the use of roll angle

Detection of Aircraft Touchdown Using Longitudinal Acceleration and Continuous Wavelet Transformation

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