Essais & Simulations n°134

mesures mesures During

mesures mesures During the takeoff and landing phases, slat is extended with an extern al position given by the following Catia drawing: • during winter conditions on two German Routes at the shortest day of the year (worst conditions): > Hamburg - Oslo route 1h25 flight duration, five times a day > Frankfurt - Bergen route 3h flight duration, three times a day > With the worst weather case: Over cloudy under FL220 and Sunny above Figure 4 Camera system installed on the Aircraft Functional lay out and innovations Main functional requirements of the micro camera system Figure 2 Slat extended / retracted This micro camera system has to work for fourteen months under typical flight conditions of an A320 commercial Aircraft. It means: • a flight level up to 33 000 feet (FL330), • a Mach number of 0.78 which is about 220 m/s at cruise level, • a temperature range between - 40°C and +45°C • a pressure range between 250 hPa & 1500 hPa • a low impact on the aerodynamic flow The OWACSA autonomous micro camera system was split into: • An energy sub system with solar harvesting and super capacitors as energy storage. Indeed, on one hand, solar panel is the more productive harvesting system during the day and on the other hand, no COTS chemical battery allows to be charged under negative Celsius temperatures. • A camera with a dedicated control software sub system. Its hardware is a smartphone with a very high resolution camera. Its Li-ion battery is replaced by the energy sub system. Thanks to its internal sensors (GPS, accelerometer…), the control system gives the flight phases and defines the picture rate. • The CaptiFlex technology for embedding the previous sub systems. Embedded in CaptiFlex dimensions are: • 1300 x 670 mm² and 7 mm thick for energy system with its own protection against hail • 3000 x 163 mm² and 4 mm thick for the electrical connection • 530 x 426 mm² and 20 mm thick for camera system Characteristics of the system Camera and control software: the main camera characteristics are: • A 33 MPixels retina sensor with an over sampling system • An high quality 6 - lens, f2.2 and a 26 mm focal length with an added lens • A shooting time in less than 5 seconds • A 32 GB memory • GPS and other sensors such as accelerometer • Wifi 802.11 a/b/g/n Thanks to GPS and accelerometer, the control software can: • detect the sunrise and sun set at the real time aircraft location • define the ground and flight phases and for these latter the picture rate It has to take high quality pictures, only during the day time: • at a rate depending on the flight phase: > one picture on taxi out and taxi in > one picture every 10 seconds during takeoff and landing > one picture every minute during climb out > no picture during cruise > one picture every two minutes during descent • about 100 pictures by flight and 5 flights a day • a viewing area of about 800 mm to 1000 mm along the span and 250 mm • a minimal spatial resolution of 4 pixels by millimeter on the leading edge It has to operate: • fully autonomously without external source for two days at least • fully automatically for defining flight phases • with a sufficient storage for 1000 high resolution pictures at least • by wireless for downloading the pictures Figure 3 OWACSA functional lay out OWACSA proposal was graduate thanks to the two innovations identified by the C lean Sky experts: • Using super capacitors for the energy storage • Using CaptiFlex technology for installation onto outer skin of aircraft Micro camera system installation design on Aircraft and its reality For solar reasons, energy sub system was designed for setting up it on the fuselage crown. For picture and aerodynamic reasons, camera location was designed just in front of the Belly fairing at 4 m from the middle of the leading edge and at its level. Between the two latter there is an electrical connection. 56I ESSAIS & SIMULATIONS • N°134 • septembre 2018 ESSAIS & SIMULATIONS • N°134 • septembre 2018 I57