ENHANCEMENTS IN UAV FLIGHT CONTROL AND SENSOR ORIENTATION

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1 Heinz Jürgen Przybilla Manfred Bäumker, Alexander Zurhorst ENHANCEMENTS IN UAV FLIGHT CONTROL AND SENSOR ORIENTATION

2 Content Introduction Precise Positioning GNSS sensors and software Inertial and augmentation sensors Investigation of Orientation Quality 3D positioning accuracy Accuracy of orientation angles Conclusions

3 Introduction Direct georeferencing of mobile sensor data is a major subject of the geodetic community. The hardware components of these high sophisticated systems are not suited for UAVapplications, due to their costs and weight.

4 Introduction The development of inertial sensors and microcontrollers in the last five years meanwhile led to miniaturized systems, which match requirements for flight control and navigation of UAV. Examinations to use this data for direct georeferencing of mobile sensor data are in progress since several years.

5 Introduction The use of UAV for mobile applications has to concern the following subjects: the availability of light weighted hardware, the positioning, orientation and stabilization of the image sensor at the predefined sites, the synchronised release of the camera, the acquisition of the position and orientation data for the post processing to perform the direct georeferencing.

6 Hardware aspects of current UAV navigation systems Navigation of an UAV is based on DGPS / PDGPS with single or dual frequency GPS RTK receivers magnetic sensors and barometric altitude sensors. Control and stabilization of position and altitude of the UAV / sensor are performed by means of MEMS gyroscopes and accelerometers other sensors to determine data of its orientation angles, its course (three axes magnetometer) and altitude (barometric sensor).

7 Hardware aspects of current UAV navigation systems Single frequency receiver: u blox NEO 6M Default GNSS sensor: small, lightweight and cost effective L1 single frequency receivers: data rate of up to 10 Hz positioning accuracy of up to 1 m under good conditions possible flight guidance under favorable weather conditions in the range of approximately ±5 m

8 Software requirements MultiWii User Interface Parameters of all connected sensors can be visualized, as well as variations of sensor values are shown and logged in real time. Freely available under GNU GPL v3 license terms Software written in C can be used on different microcontrollers can be adapted to own requirements and applications further improvements are possible

9 Precise positioning: GNSS Sensors Higher accuracy up to centimeter is accessible only by use of RTK capable dual frequency GNSS sensors. A first solution found consists of a dual frequency GNSS receiver OEM1 of TOPCON (size: 60 x100 x 13 mm) in connection with an airworthy dual frequency antenna Maxtena M1227 HCTA

10 Precise positioning: GNSS Sensors Dual frequency GNSS receiver TOPCON OEM1 with dual frequency antenna Maxtena M1227 HCTA The OEM1 receiver circuit integrates 72 universal channels: GPS: L1 (C/A & P), L2, L2C; GLONASS: L1 (C/A & P), L2 (C/A & P); SBAS: WAAS/EGNOS/MSAS). 3 serial ports, 1 USB, 1 CAN interface data rates of up to 100 Hz data can be additionally logged in an NMEA format.

11 Precise positioning: GNSS Sensors As a result of a further miniaturization Topcon recently developed the B110 receiver board (size: 40 x 55 x 10 mm), distributed for a few months. This ultra compact positioning engine is capable of providing scalable positioning from sub meter DGPS positioning to sub centimeter RTK positioning.

12 Precise positioning: GNSS Sensors Dual frequency GNSS receiver TOPCON B110, dual frequency antenna Maxtena M1227 HCTA and XBEE radio transmitter All GNSS systems are supported, as well as the prospective Galileo and COMPASS. SD/MMC card interface supports data logging with 20 Hz writing rate and up to 2 GByte capacity (a fundamental need for postprocessing). A major feature is the direct disposability of an event signal which can be used to synchronise the exposure time with the GNSS time (time stamp).

13 Precise positioning: GNSS Sensors B110 receiver mounted to a Quadrocopter platform

14 Precise positioning: GNSS Software For precise georeferencing improved position data can be calculated in postprocessing using the GNSS raw data, data of a reference station. For this purpose the RTKLIB program library is used. Source code is available in C++ for own developments. UI of the real time module RTKNAVI

15 Inertial and augmentation Sensors The terms inertial and augmentation sensors subsume all sensors which are necessary to determine the orientation of an UAV and a mounted (image) sensor.

16 Inertial and augmentation Sensors Stabilization of the Multicopter Primarily occurs by means of the rotation rate measurements of the MEMS gyroscopes. Position control (leveling) and determination of roll and pitch angles Three axes accelerometer

17 Inertial and augmentation Sensors Waypoint navigation (coming home) Primarily occurs by means of GPS position and velocities the static pressure sensor (barometric altitude) Compass module (three axes magnetometer)

18 Inertial and augmentation Sensors Barometric height Air pressure sensor Position hold / altitude hold Air pressure sensor together with the coordinates of GNSS

19 Inertial and augmentation Sensors MEMS sensors, originally developed for playstations and smartphones, have also influenced geodetic applications. The integration of sensors on a single board results in: cost effective manufacturing and mass production, offers the use in accordance with small and lightweight UAV's.

20 Inertial and augmentation Sensors All in one board Dimension: 50 mm x 50 mm Combines sensors and the microcontroller for the flight control and air navigation. To improve reliability a combination with a second sensor board is possible (adaption via I²C bus to main board). Result: the data of the redundant sensors can be compared continuously and validated.

21 Investigation of orientation quality Test: 3D position accuracy Miniprism additionally installed beneath the UAV. Real time tracking of the UAV during the flight via miniprism (up to 10 Hz) by a tachymeter equipped with an automatic target acquisition system (LEICA TS15). Comparison of calculated RTK positions with the coordinates derived from the tachymeter measurements. Accuracy of the RTK positions mainly depends on the method, whether the ambiguities could be fixed or only a float solution could be calculated.

22 Investigation of orientation quality Result: 3D position accuracy Differences RTK via Tachymetre fixed solution: < 0.1 m float solution: < 0.5 m Systematic differences are caused by the different mounting position of prism and GPS antenna

23 Investigation of orientation quality Test: 3D position accuracy Kinematic RTK measurements with the Topcon OEM1 board on the roof of Bochum University of Applied Sciences. The receiver had been positioned along a linear handrail with data logged at a rate of 10 Hz. For this investigation the handrail could be used as a nearly error free reference track.

24 Investigation of orientation quality Result: 3D position accuracy Achieved accuracies for the GNSS positions fixed solution: < 0.05 m float solution: < 0.05 m green: fixed solution orange: float solution

25 Investigation of orientation quality Test: Accuracy of orientation angles Accuracy of the attitude angles depends on the stability of the accelerometer bias Accuracy of the heading angles depends on the measurements of the three axes magnetometer its sophisticated calibration due the disturbances of the environment by hard iron and soft iron the modelling of the magnetic variation

26 Investigation of orientation quality Test: Accuracy of orientation angles Lab tests to achieve the accuracy of the accelerometers in respect to their biases and resolution. The equipment under test had been fixed on a board which could be tilted via a micrometer gauge. Comparison of attitude angles of the accelerometers (positioned under diametrical and opposite orientations: 0, 180, upside, upside down) with those of the gauge.

27 Investigation of orientation quality Result: Accuracy of orientation angles Delta = IMU Gauge [deg] Accelerometer Test 0,4 0,3 0,2 0,1 0,0 0,1 0,2 0,3 2,0 1,5 1,0 0,5 0,0 0,5 1,0 1,5 2,0 Attitude Angle [deg] Upside 0 Upside 180 Upside down 0 Upside down 180 The saw tooth pattern shows, as a typical effect, the resolution of the attitude angles. The systematic differences between the upside and upsidedown positions are caused by the non parallel installation of the IMU and the tilt board.

28 Investigation of orientation quality Result: Accuracy of orientation angles Delta = IMU Gauge [deg] Accelerometer Test 0,4 0,3 0,2 0,1 0,0 0,1 0,2 0,3 2,0 1,5 1,0 0,5 0,0 0,5 1,0 1,5 2,0 Attitude Angle [deg] Upside 0 Upside 180 Upside down 0 Upside down 180 Accuracy of attitude angles (during unaccelerated flight phases) 0.1 to 0.2 can be achieved.

29 Investigation of orientation quality Accuracy of orientation angles The heading ψ is derived from the three measurements of the magnetometer (m x, m y, m z ) Measurements have to be transformed into their horizontal components (m hx, m hy ) by using the g vector Horizontal components are used to calculate mag. heading ψ mag. ψ mag has to be corrected in respect to the magnetic variation (declination δ).

30 Investigation of orientation quality Result: Accuracy of orientation angles Under ideal conditions an accuracy of the heading angle ψ of 0.1 to 0.5 can be achieved.

31 Investigation of orientation quality Result: Accuracy of orientation angles Further improvements by using the Topcon GNSS receiver, which can be equipped with a second (single frequency) antenna. This results in a heading accuracy of 0.1 per meter antenna distance (the typical diameter of a Multicopter matches 0.8 m).

32 Conclusions Navigation accuracy is a critical parameter for a successful operation of UAVs. Comparing with high sophisticated systems actually a loss of accuracy is unavoidable. The quality of the used L1 GNSS sensors is sufficient for flight control and standard navigation (5m to 15m). The investigations show that a kinematic GPS solution with accuracies within the cm level is possible.

33 Conclusions The calculation of the orientation angles is still a challenge. The examinations show that the attitude could be calculated with an accuracy of 0.1 to 0.2 and the heading angle with 0.1 to 0.5 Improvements using a GNNS receiver with two antennas are realistic. It can be expected that the accuracy of the inertial sensors will increase in the nearby future.

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