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Aircraft System Identification Theory And Practice

Aircraft attitude calculation with the use of aerodynamic flight data as correction signals

Integrated Smart Sensors: Design and Calibration

The article presents a measurement system for a micro UAV designed at the Department of Avionics and Control Systems of Rzeszow University of Technology. Since the project is based on earlier projects, e.g.[[[[1[[[1, the introduction begins with their short presentation [they are mentioned in the introduction firs. Then, the current project is discussed. The major objective of the project is to create a miniature autopilot cooperating with navigation units, data transmission units and measurement units. The system is based on Polish technological solutions. The autopilot is designed as a single unit, however the system is open and it allows you to use different elements. The system development is also possible. In-flight testing will be realized with the use of two unmanned flying platforms equipped with an electrical engine and a piston engine. The total mass of the platforms is 5 kg and 25 kg respectively. The article presents the structure of the control and navigation system and then, the structure of the measurement system. The measurement units consist of a GPS receiver, an attitude and heading reference system (AHRS) and an air data computer (ADC). Similar configuration is used in other micro UAV solutions, such as Micropilot or Kestrel. Then, algorithms of the measurement system are described. Navigation is based on GPS data with a DGPS (Differential GPS) advanced module. If the measurement information is complete, GPS data are used to correct measurements from other units. The system estimates wind disturbances and calculates accelerometers errors. In the case of missing GPS signals implementation of low-cost sensors may lead to significant measurement errors, and hence navigation only by means of the INS is impossible. In such a case, navigation is realized with the use of an inertial navigation system (INS), the magnetic heading measurement and ADC. AHRS unit algorithms use quaternion algebra for attitude calculation. For correction, complementary filtering is implemented [, [. The correction signal for the attitude (pitch and roll angles) is calculated with the use of acceleration measurements. Measurements of accelerations and yaw rates are used for the correction switching mechanism, since in dynamic states signals calculated from accelerations cannot be used for correction. Heading is corrected by means of magnetic heading measurement. ADC algorithms are based on typical aerodynamic dependences.

Algorithms of Measurement System for a Micro UAV

Convention on International Civil Aviation

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.

A vision-based method for supporting autonomous aircraft landing

The article presents the project of UAV control system realized at Department of Avionics and Control Systems of Rzeszow University of Technology. The project is based on earlier experiences. In the article general structure of the onboard control system is shown as well as the structure of control station. There are described in proposed control and navigation procedures as well as human factor, failure detection and system reconfiguration.

Proposal for navigation and control system for small UAV

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.

Temperature and Nonlinearity Compensation of Pressure Sensor With Common Sensors Response

Measurement of aircraft approach using airfield image

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.

Jacek Pieniazek

Papers

A vision-based method for supporting autonomous aircraft landing

Proposal for navigation and control system for small UAV

Temperature and Nonlinearity Compensation of Pressure Sensor With Common Sensors Response

Measurement of aircraft approach using airfield image

Integrated measurement system for UAV