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Module Code: ACD505

Module Title: Aircraft Performance and Flight DynamicsModule Leaders: M. Sivapragasam and Dr. H. K. Narahari

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologyModule Details

Course: M. Tech. in ACDDepartment: Automotive & Aeronautical EngineeringHead of the Department: Dr. S. Srikari (hod.aae.et@msruas.ac.in) Faculty: Engineering & TechnologyDean: Prof. H. K. Narahari (dean.et@msruas.ac.in)

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologyWhy this ModuleThe objectives of the course are to enable the students to:1. Explain the construction, working principles and functional requirements of aircraft systems with respect to their performance2. Convert the customer requirements to viable design specifications and evolve conceptual design3. Model, simulate, analyse and validate aircraft conceptual design to meet operational requirements using commercially available tools4. Demonstrate Critical, analytical, problem solving and research skills in the domain of Aeronautical Engineering5. Develop a career in Aeronautical Engineering6. Practise Teamwork, lifelong learning and continuous improvementThe module is being delivered to meet the above highlighted objectives of the course.M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologyModule Aim and SummaryThis module intends to prepare students for evaluating the stability and control parameters of an aircraft using linear methods. Students are taught basics of static stability and control for the following modes: longitudinal, lateral and directional. Students are taught dynamical equations governing the motion of aircraft in space. They are trained to solve linearised equations of motion and compute stability margins.M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologyModule Intended Learning OutcomesAfter undergoing this module students will be able to: Explain the influence of aerodynamic characteristics, weight, engine performance and flight altitude on the aircraft performanceDistinguish performance requirements between different class of aircraftAnalyse and evaluate aeroplane performance for different phases of flight, Level flight, Turning, Gliding, climb, takeoff and landing through solution of available standard mathematical modelsCalculate size and evaluate control surfaces using standard correlationsCritically evaluate the stability derivatives and establish flight boundaries such as range and endurance, payloadrange, Vn diagram and turn performanceM. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologyIndicative ContentSystems of axes and notation: Earth, body axes, Euler angles and transformationsStability and Control : Static equilibrium and trim, wing location, tail plane sizing, CG travel,Longitudinal : Stability : Sizing of Controls surfaces Neutral Point : Stick Fixed and FreeLateral and Directional Stability : Coupling between the two , Sizing of Controls surfacesEquations of motion of a rigid aircraft in space: Linearisations , flat earth simplifications.Decoupled equations

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & Technology6Indicative ContentSolution techniques: State space approach, Matrix methods, Transfer functionLongitudinal Dynamics : Modes of a typical Aircraft, Short period, long periodLateral and directional dynamics : Modes of a typical Aircraft, rolling, Dutch, spiralStability and control derivatives turning flight: Turning flight in general, Maximum loadfactor and bank angle, Fastest and tightest turn, sustained and attained turn rates, V-nDiagram

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & Technology7Teaching and Learning MethodsLecture SessionsLaboratory practiceM. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologyMethod of AssessmentA module assessment will have two components: Component - 1: 50% weight Assignment (30% weight) followed by a presentation on the assignment (10% weight) and a laboratory examination (10% weight). A word processed assignment is to be submitted followed by a presentation by the students. In case there is no laboratory examination, the assignment (40% weight) followed by a presentation on the assignment (10% weight) - applicable only for those modules where it is not possible to have laboratory examination.

Component - 2 : 50% weight Written Examination (50% weight).

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologyMethod of Assessment Contd.. The assessment questions are set to test the learning outcomes. In each component certain learning outcomes are assessed. The following table illustrates the focus of learning outcome in each component assessed:

Both components will be moderated by a second examiner.A student is required to score a minimum of 40% in each of the components and an overall 40% for successful completion of a module and earning the credits.

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySoftware tool and ResourcesMATLABPiano-XM. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologyModule DeliveryTheoryM. SivapragasamDr. H. K. Narahari

PracticeMr. M. SivapragasamM. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologyReferencesEssential Reading 1. Class Notes2. M.V. Cook. Flight Dynamics Principles, 2nd Edition, 2007, Elsevier3. J.B. Russel, Performance and Stability of Aircraft,2003, Butterworth

b. Recommended Reading:1. Ashish Tewari. (2007) Atmospheric and Space Flight Dynamics- Modeling and Simulationwith MATLAB and Simulink, 2007, Birkhauser2. Ilan Kroo Aircraft Design: Synthesis and Analysis, 20113. John D. Anderson. (1999) Aircraft Performance and Design, McGraw-Hill4. Nelson, R.C. (1998) Flight Stability and Automatic Control, 2nd Edition, McGraw Hill5. AIAA Aerospace Design Engineers Guide, 2003, 5th Edition

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologyModule Delivery Schedule (Theory) Session No.DateTimeDayTopicDelivered ByAdditional Activity101-06-201509:30 AM -1:00 PMMondayAircraft Steady and Level Flight-1M. Sivapragasam202-06-201509:30 AM -1:00 PMTuesdayAircraft Steady and Level Flight-2M. Sivapragasam303-06-201509:30 AM -1:00 PMWednesdayAircraft Accelerated Flight-1M. Sivapragasam404-06-201509:30 AM -1:00 PMThursdayAircraft Accelerated Flight-2M. Sivapragasam505-06-201509:30 AM -1:00 PMFridayAircraft Equilibrium, Stability and ControlM. Sivapragasam608-06-201509:30 AM -1:00 PMMondayAircraft Longitudinal Static StabilityM. Sivapragasam709-06-201509:30 AM -1:00 PMTuesdayAircraft Lateral Static Stability M. Sivapragasam810-06-201509:30 AM -1:00 PMWednesdayAircraft ManoeuvrabilityM. Sivapragasam911-06-201509:30 AM -1:00 PMThursdayAircraft Flight Dynamics - 1Dr. H. K. Narahari 1012-06-201509:30 AM -1:00 PMFridayAircraft Flight Dynamics - 2Dr. H. K. Narahari M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologyModule Delivery Schedule (Laboratory) Session No.DateTimeDayTopicDelivered ByAdditional Activity101-06-20152:00 PM -5:30 PMMondayPerformance calculations using MATLABM. Sivapragasam202-06-20152:00 PM -5:30 PMTuesdayPerformance calculations using MATLABM. Sivapragasam303-06-20152:00 PM -5:30 PMWednesdayPerformance calculations using MATLABM. Sivapragasam404-06-20152:00 PM -5:30 PMThursdayPerformance calculations using MATLABM. Sivapragasam505-06-20152:00 PM -5:30 PMFridayPerformance calculations using MATLABM. Sivapragasam608-06-20152:00 PM -5:30 PMMondayPerformance calculations using Piano-XM. Sivapragasam709-06-20152:00 PM -5:30 PMTuesdayPerformance calculations using Piano-XM. Sivapragasam810-06-20152:00 PM -5:30 PMWednesdayStatic stability calculations using MATLABM. Sivapragasam911-06-20152:00 PM -5:30 PMThursdayStatic stability calculations using MATLABM. Sivapragasam 1012-06-20152:00 PM -5:30 PMFridayDynamic stability calculations using MATLABM. SivapragasamM. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologyTheory SessionsM. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySession No. 1Aircraft Steady and Level Flight 1

At the end of this session, students will be able to :Explain the absolute and functional performance of an aircraftList the crucial aircraft and propulsion parameters influencing the performance characteristics of an aircraftShow the forces acting on an aircraft in steady level flight and derive the equations of motionCalculate the thrust required and available for steady level flight for jet aircraftCalculate the power required and available for steady level flight for propeller-driven aircraftAssess the importance of maximum velocity on aircraft design

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologyAt the end of the session, students will be able to :Differentiate range and enduranceCalculate the range and endurance of a propeller-driven aircraftCalculate the range and endurance of a jet aircraftApply the Breguet equations for propeller-driven and jet aircraftIdentify the parameters to maximise range and endurance for propeller-driven and jet aircraftDescribe the propulsion, aerodynamics and structural aspects in maximising range and enduranceSession No. 2 Aircraft Steady and Level Flight 2M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologyAt the end of the session, the students will be able to :Discuss the G-force and its types in relation to aircraft performanceCalculate the level turn performance of an aircraftExplain the effect of load factor on aircraft turn performanceCalculate the pull-up and pull-down performance of an aircraftConstruct the V-n diagram and explain its importance in aircraft performance and design

Session No. 3 Aircraft Accelerated Flight 1

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySession No. 4 Aircraft Accelerated Flight 2 At the end of the session, the students will be able to :Differentiate take off and landing requirements of different types of aircraftCalculate the take off performance of an aircraftExplain balanced field length requirements for aircraft take offCalculate the landing performance of an aircraftCalculate the climb performance of an aircraft

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologyAt the end of the session, the students will be able to :Distinguish equilibrium and stability of an aircraftExplain the six degrees of freedom of an aircraft in flightDescribe the conditions for static stability of an aircraftExplain the necessity of trimming an aircraft for stabilityEstimate the stability characteristics of an aircraft Derive the relationship between neutral point and static margin

Session No. 5 Aircraft Equilibrium, Stability and Control

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySession No. 6Aircraft Longitudinal Static Stability

At the end of this session the students will be able to :Classify the various aircraft control surfacesDifferentiate handling qualities of conventional and fly-by-wire aircraftCategorise the forces and moments acting on an aircraftDerive the conditions for longitudinal static stability of an aircraftEstimate the hinge moment coefficientAnalyse the longitudinal static stability of an aircraft with canard configuration Analyse the longitudinal static stability of tailless aircraft

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySession 7Aircraft Lateral Static Stability

At the end of this session the students will be able to :Differentiate two types of lateral motion of an aircraftDerive the conditions for yaw stability of an aircraftEstimate the hinge moment coefficient of rudderExplain the requirements of rudder sizingDerive the conditions for roll stability of an aircraftDescribe the effects of yaw-roll couplingExplain directional stability of an aircraft

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySession 8Aircraft Manoeuvrability

At the end of this session the students will be able to :Define manoeuvrability of an aircraftExplain the handling characteristics of an aircraftEstimate control surface effectivenessEstimate hinge momentsEstimate stick forcesDescribe control reversalM. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySession 9Aircraft Flight Dynamics 1

At the end of this session the students will be able to :Describe the axes and notation for the analysis of dynamic stability of an aircraftDerive the generalised set of equations of motion for a rigid aircraftConstruct the linearised form of equations of motion

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySession 10Aircraft Flight Dynamics 2

At the end of this session the students will be able to :Derive the three degree of freedom equations of motion for an aircraftConstruct the linearised form of equations of motionFormulate the equations of motion in state space form

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologyLaboratory SessionsM. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySession No. 1 Performance calculations using MATLABAt the end of this session, students will be able to :Calculate the thrust required of a jet aircraft using MATLAB Calculate the thrust available in a jet aircraft using MATLAB

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySession No. 2 Performance calculations using MATLABAt the end of this session, students will be able to :Calculate the power required of a propeller-driven aircraft using MATLAB Calculate the power available in a propeller-driven aircraft using MATLAB

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySession No. 3 Performance calculations using MATLABAt the end of this session, students will be able to :Calculate the turn performance characteristics of an aircraft using MATLAB

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySession No. 4 Performance calculations using MATLABAt the end of this session, students will be able to :Calculate the pull-up and pull-down performance characteristics of an aircraft using MATLABCalculate the climb performance characteristics of an aircraft using MATLAB

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySession No. 5 Performance calculations using MATLAB

At the end of this session, students will be able to :Calculate the take off and landing performance characteristics of an aircraft using MATLAB

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySession No. 6 Performance calculations using Piano-X

At the end of this session, students will be able to :Evaluate the detailed performance characteristics of Fokker 70, a narrow body, twin-engined, medium-range, turbofan aircraft using Piano-X

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySession No. 7 Performance calculations using Piano-X At the end of this session, students will be able to :Evaluate the detailed performance characteristics of Airbus A380, a double-deck, wide-body and four-engined aircraft using Piano-X

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySession No. 8Static stability calculations using MATLABAt the end of this session, students will be able to :Estimate the longitudinal static stability characteristics of an aircraft using MATLAB

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySession No. 9 Static stability calculations using MATLABAt the end of this session, students will be able to :Estimate the lateral static stability characteristics of an aircraft using MATLAB

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & TechnologySession No. 10 Dynamic stability calculations using MATLABAt the end of this session, students will be able to :Estimate the dynamic stability characteristics of an aircraft using MATLAB

M. S. Ramaiah University of Applied Sciences#Faculty of Engineering & Technology