Temperature sensitivity compensation of pressure sensor considering its nonlinearity is crucial to obtain a highly accurate measurement. Unfortunately, various software methods are known to have some drawbacks, thus a large number of calibration points is necessary to model the sensor response properly. This paper aims to present a new compensation method that features the utilization of common response of the given type of sensors and the reduction of particular sensor calibration data set, which subsequently reduces the duration of necessary experiments. Mathematical formulas, which are the basis of a solution, are derived from the sensor general model. Two cases have been considered and analyzed theoretically: iterative solution with sensor response, and noniterative with sensor reproducing function. The method is experimentally verified using two sets of sensors. There is a tenfold increase in accuracy after compensation. In addition, the practical limitation of achievable accuracy by full individual calibration in the given instrumentation is estimated. The cost of simplification increases the remaining error by about 50%. Hence, the advantage is the reduction of acquisition time more than by half. The achievable accuracy is about 0.01% full scale (FS). The results demonstrate that the proposed compensation method is valid for high-accuracy measurements. Furthermore, the comparison of various cases confirms the validity of sensors similarity assumption and correctness of a theoretical analysis presented in this paper.

Purpose: This paper aims to present a vision-based method for determination of the position of a fixed-wing aircraft that is approaching a runway.Design methodology/approach: The method determines the location of an aircraft based on positions of precision approach path indicator lights and approach light system with sequenced flashing lights in the image captured by an on-board camera.Findings: As the relation of the lighting systems to the touchdown area on the considered runway is known in advance, the detected lights, seen as glowing lines or highlighted areas, in the image can be mapped onto the real-world coordinates and then used to estimate the position of the aircraft. Furthermore, the colours of lights are detected and can be used as auxiliary information.Practical implications: The presented method can be considered as a potential source of flight data for autonomous approach and for augmentation of manual approach.Originality/value: In this paper, a feasibility study of this concept is presented and primarily validated.

This paper presents an attempt to determine the dynamic properties of a measuring system based on total pressure measurement with the use of a Pitot tube and a semiconductor pressure transducer. The presented research uses computed fluid dynamics (CFD) simulation and real data from the pressure measurement system for determination of the dynamical model of the Pitot tube with the transducer. An identification algorithm is applied to the data from the simulation, and the model in the form of a transfer function is an identification result. The oscillatory behavior is detected, and this result is confirmed by frequency analysis of the recorded pressure measurements. One of the resonant frequencies is the same in both experiments, but the second is slightly different. The identified dynamical models permit the possibility to predict deviations caused by dynamics and to select the appropriate tube for a particular experiment.

The main subject of the paper is calibration of the sensor by learning method of the fuzzy system. Fuzzy system is used for simultaneous compensation of the nonlinearity and temperature sensitivity. The compensation of pressure sensors is intended for application in the Air Data Computer. The results obtained experimentally show that fuzzy system is superior to the polynomial regressions because it is not necessary to compute high degree polynomials. After the compensation it is supposed measurement device can be periodically verified and if necessary corrected. General property of two-point correction is presented. In the case of tested sensor two-point re-calibration is assumed as being effective because of one-side nonlinearity.

In the paper is described the integrated measurement system designed for the cooperation with the UAV's control system and also for another research with flying vehicles. The presentation mainly considers the measurement accuracy and the calibration considering temperature effect. On the example of the pressure sensors the calibration of many systems is presented. The results show effectiveness and also time reduction. Presented methodology is better in comparison to traditional solution of this problem.

The paper describes a measurement system made for registering data from the static tests of motor glider AOS-71 (the motor glider was designed in Rzeszów and Warsaw Universities of Technology). The experiment was an evidence part leading to obtaining the acceptance of the aircraft flight worthiness. The characteristic feature of the described studies was the necessity of running the strength tests in higher temperature.