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This paper presents a technology demonstrator of a digital flight data recorder (FDR) used as a teaching aid for avionics. It demonstrates the technology and feasibility of designing a digital FDR for classroom teaching and training purposes. The paper also explores the synchronized operation of aircraft control surfaces and the analysis of FDR data. The hands-on practical knowledge gained from this teaching aid includes the application of transducers, sensors, digital electronics, and microprocessors in present-generation avionics.
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7th International Technology, Education and Development Conference March 4th-6th , 2013 Valencia, Spain TECHNOLOGY DEMONSTRATOR OF 7-CHANNEL DIGITAL FLIGHT DATA RECORDER AS AVIONICS TEACHING AID USING STATIC MODEL AIRCRAFT Authors 1. WgCdr Nikhil Verma, IAF Instructor Class-A Dept. of Aeronautical Engineering Military institute of Science and Technology 2. Md. Easir Arafat Papon Dept. of Aeronautical Engineering Military Institute of Science and Technology
Objectives To demonstrate technology and feasibility of designing digital FDR as a class-room teaching & training aid. To study the synchronized operation of aircraft control surfaces and analysis of FDR. Hands on practical knowledge on application of transducers, sensors, digital electronics and microprocessors in present generation avionics.
Flight Data Recorder Source : http://en.wikipedia.org/wiki/File:Fdr_sidefront.jpg An electronic system employed to record aircraft parameters from various sensors in all stages of flight. Generation of FDR is defined based on a. Data Storing b. Data recovery
Block Diagram of FDR Raw digital data is converted for graphical analysis based on respective data conversion and operating limits FDR output in terms of graphical format Analog Signal from sensors, for example Air Data sensor, is converted to digital FDR output in a text file Digital Signal is interpreted by FDR system Data is simultaneously stored in memory. Data Listing Data recorder Data Conversion & Transfer Data Acquisition Unit Sensors Display Figure : FDR MODEL
Steps in Design Model aircraft control surfaces are interfaced with motors connected to the microcontroller circuit. Analog inputs generated by surface movements is sampled and after ADC is stored for graphical display Theoritical Subjects Correlated Aircraft Instrumrntation Communication Engg Avionics Engg, Basic Electronics, Digital Electronics, Microprocessors & Programming MAT LAB Application Computer Interfacing Sensors, Control Surfaces Design steps require basic understanding and application of all major academic subjects involved in an undergraduate course of Avionics Engg. Analog Input Sampling Analog to Digital Conversion Data Storage Digital to Graphic Conversion Display
Flow Chart of FDR Model Power Supply 12V Temperature Sensor Voltage Regulator 5V Hands on Control Panel Central Processing Unit Aileron angle Aileron Up/Down Memory unit Elevator angle Elevator Up/Down Rudder angle Landing Gear angle Rudder Up/Down Temperature data L.G. Up/Down Engine-S RPM Engine-T RPM Engine-P Up/Down Engine-S Up/Down Elevator Computer Data Transfer Aileron Sensors like control surfaces, engine RPM, temperature sensor are connected to the processing unit. All sensors except temperature sensor are visible whereas temperature sensor is fitted inside the main circuit. All the sensors are connected through wire with a hand held control box and control of individual sensor is done from here. A pair of switch is used for each sensor to operate. All respective data is simultaneously stored in the memory device from the central processing unit. The data is stored as binary which is further converted into decimal value. Rudder MATLAB Software Central Processing Unit is the heart of designed FDR. 12V power supply is regulated down to 5V to operate the processing unit. Landing Gear Engine-P Graphical Display Engine-S
Graphical Display As in this profile there is no Roll or Yaw movement, so both Aileron and Rudder is unmoved, they have no deflection. This is the FDR output of a simple flight profile where aircraft takes off and then landed after a few moments. As aircraft is taking off so Engine RPM is Maximum , Landing Gear is being Folded and Elevator goes Up. After a while aircraft lands, so Elevator goes Down, Landing Gear is Down also Engine RPM keeps decreasing.
Advantages Low cost and developed with available technology. Hands on experience within classroom for variety of flight profiles that student can develop at own pace. Analysis and interpretation of control surfaces, electric sensors, application of microcontroller & digital circuits is very well demonstrated. Graphical or simulated animation do not provide the feel of operation of system which is achieved as control is with instructor/students.
Conclusion • Technology demonstrator for further development in real life application. • Radio Controlled Model Aircraft. • Static Real Design Aircraft. • Understanding flight profiles and analyzing FDR operation, design and output. • To develop concepts of all major subjects in Avionics Engineering. • Concepts of flight control laws is yet to be incorporated in the model FDR system. However, basic understanding and comprehension of control surfaces and relation with FDR output is achieved with this low cost model teaching aid.
