Applications Of Mechatronics In Aviation Engineering Essay

Applications Of Mechatronics In Aviation Engineering EssayThe term Aviation covers all the activities involved building of flying descent ruse particularly air planes. The two major divisions are manufacturing of air craft and its components, and second airlines operation. This manufacturing includes of space craft, missiles and related electrical and electronic components. This aviation industry subdivided intoAir craft manufacturingGeneral aviation activitiesAirline operationAirport operationAviation support industriesApplications of Mechatronics in AviationThis essay will discuss about some(prenominal) of the components use in aviation industry which relates to applications of mechatronics.AileronFlaps and Actuator drive social unitPilot Static agreementFly by wire control remainsYaw damperPrimary flight control governanceInternal navigation systemUnder carriage beat of motor rpmMeasurement of air flow velocityAltitude measurement detectorAir speedAileronThis ailerons were mounted by the hinges in a reaction test frames and manikin of actuator configurations with adjustable links. Electro dynamic shaker attached with a bonded pad to the outboard closeout rib are used to apply various(a) frequencies and amplitude to the aileron. An accelerometer used to monitor the frequency responses. If the frequencies were comparable the flutter free performance of the composite aileron was predicted. A pair of actuators fixed by the pads to the rear of the ailerons. This is used to load and take in the chordwise refraction and torsional rigidity. The movement are measured at nine points on the ailerons were measured by two ways. The two ways are linear transducers and optical.FlapsThis flapping constructed with parametric computer model and actuator system. The overall model could moved the full range of flap rotation and deflections and it could represent the thermal expansion in twain vertical directions and longitudinal. The drive unit rotates in its mou nting axis to maintain tangency of the pinion gear and sector gear regardless of any shifts in the location of the flap hinge axis. The existing computer design model is used to square off the real movement at the bearing with the system in a thermally deflected and conform the required movement. This computer model is used to find the sources of interference and eliminates the source. This system is reliable as well as searing for real time determination of components locations in the vehicle. It is very difficult for proper alignment of the parts with out this computer model and drive unit.Actuator drive unitThis actuator drive unit is designed to create maximum torque and speed if any two electrical or controller failures. Due toweight fill mechanical redundancy is not provided too it will increase effect ofcomplexity and overall reliability. To resolve this issue the failsafe design were included into the individual components to better the reliability concerns. When the mot or channel fails the rest of the channel would drag along the failed motor.Pilot Static SystemThis pilot static system is or soly used in aircrafts to determine the aircrafts airspeed, Mach number, altitude and altitude trend. This system consists of pilot tube, a static port and pilot static instruments. This unit also measures the external forces playing on the aircraft like temperature, pressure, density and viscosity of the fluid while in operation. Rest of the instruments connected to monitoring computers and selective information recorders, altitude encoders, cabin pressure controllers and various speed switches. Most of the commercial aircraft disasters have been traced to a failure of the pilot.Fly by Wire control SystemsThis fly by wire control systems is most reliable than manual control of an aircraft. The changes in flight control components are converted to control request and transmitted to flight control computers by the wires to determine how to move the actuators at each control surface. This flight control computers gives feedback to stabilize the aircraft performance even without pilot knowledge.Yaw damperIn many air craft usually in jets and turboprobs to decrease the damper due to Dutch roll mode this Yaw damper is used. It includes Yaw rate sensors and processor. This overall unit gives signal to an actuator which is connected to the rudder. The purpose of this yaw damper is to give solution for the better ride to passengers. This component is required in aircraft to ensure the stability remain with in the certified values.Primary flight control systemThis mechanically controlled system design is to provide responds to primary flight control system. For flight gasbag protection this electronically system is used. This control system is split into two levels, the four actuator controls and three primary flight computers. This gives warnings to pilot.In internal navigation system includes motion sensors (accelerometers) and rotation sen sors (gyroscopes). This setup is continuously calculating the reckoning position, orientation, and velocity of an aircraft and space craft.UndercarriageWhen take off and landing it allows the aircraft to move as a taxi. This complex body part compile with wheels, floats and landing gear system. The landing gear is hydraulically rotated forward and up during the ground operations until it engages an uplock hook. This landing gear doors having high temperature recyclable surface insulation thermal protection systems tiles joined together with their outer surface.Characterization setup of motors, batteries and propellerIn Mini and Micro air vehicles the delineation setup module has been using. This set up having motors, batteries and propellers, computer, multifunction I/O card, tachometer, current sensor, air velocity transducer, thermocouple with conditioner and necessary hardware interface. The DC voltage apply to the motor is controlled by LabVIEW based software. This software continuously collects the six channels data, calculates the engineering inputs, as well as keep updating the screen readout and displays the data also save the data into ASCII spreadsheet file. The collected and displayed data includes motor current, voltage, temperature, RPM, air velocity, thrust, calculated instantaneous power and calculated torque.Measurement of motor RPMIt is authorized to measure most efficiently motor, propeller and gear box combination RPM. Motors rpm based on varying the combinations of the propulsion systems components. Another important operation is to detect when motor failure happen. For this detection this system applies two rules to design Tachometer. In first method a wiring harness to connect to the existing real time system, magnets and student residence effect sensor on the gears or motor fan. When the fan start to rotates, the Hall effect sensor detects the field magnetism which is developed due to rotation and sends a signal to the board that is having capability to count the pulses. In second method an optics module is focused to illuminate the spinner from the side. When light reflects off a white stripe on the spinner is detected by the photo sensor for each revolution.Measurement of air flow velocityBy using the thermal anemometry the air velocity transducer measures velocities. This method of measurements offers flexibility with wide ranges for accurate measurements. The dim-witted operation of this arrangement is an electric current passed through in a fine filament which is open to the elements to cross flow. When the air flow varies the transferring heat also varies and it causes a variation in the heat balance of the filament. The fine filament material having a property to hold the temperature co-efficient resistance. This change is monitored via electronic methods and communicate the signal to corresponding flow velocity or flow temperature. This method also used for instantaneous velocities and temperature m easurement.Aircraft altitude measurement sensorFor altitude measurement Piezoresistive te sensors are mostly used. Due to high accuracy requirement the monolithic silicon pressure sensors are used and it delivers high level analog getup signal is proportional to the applied pressure. In case of change in temperature the silicon sensors are compensated due to these are temperature dependent. This altimeter is used as an coercive sensor. The outcome of the sensor is directed to an operational amplifier. The gain and offset of the amplifier circuit is modifying by two trimmers, so that it can be calibrated.Air SpeedThis differential airspeed pressure sensor output is connected to an operational amplifier. To calibrate the signal gain one of the trimmer is used. The ports of silicon based sensors are static and variable. To determine the outside air pressure Mensor pressure controller was used to apply a standalone pressure to the static port. When increase in the pressure differenc e mingled with two ports it generates the output voltage. The output voltage are lowest when the pressure is equal also it offset the voltage.