AE 1350 Lecture #2TOPICS ALREADY COVEREDVARIOUS DISCIPLINESAxes of an AirplaneRoll of an AirplaneYawPITCHAERODYNAMIC CONTROL SURFACESTOPICS TO BE COVEREDAEROSPACE ENGINEERING DISCIPLINESENGLISH UNITSS. I. UNITS Système International d’UnitesEnglish Units (Continued)CONVERSION FACTORSExamplesAEROSPACE TERMINOLOGYSlide 17TYPICAL WING LOADINGPRELIMINARY THOUGHTS ON DESIGNConceptual DesignConceptual DesignsSlide 22Preliminary DesignPreliminary Design AnalysisDetailed DesignSlide 26Slide 27Slide 28A380 ArrangementSPECIFICATION AND STANDARDSCUSTOMER SPECIFICATIONSTYPICAL GOVERNMENT STANDARDSSYSTEM INTEGRATIONA380 ProductionAEROSPACE DESIGN INVOLVESAE 1350Lecture #2TOPICS ALREADY COVERED•We reviewed the history of aeronautics and rocketry.•We discussed the parts of the airplane.•We discussed various ways an aircraft is graphically represented.VARIOUS DISCIPLINESAerodynamics &PerformanceStability & ControlPropulsionStructuresDesignAxes of an AirplaneRoll of an Airplane•The longitudinal axis extends lengthwise through the fuselage from the nose to the tail. •Movement of the airplane around the longitudinal axis is known as roll and is controlled by movement of the ailerons.Yaw•The vertical or normal axis passes vertically through the center of gravity. •Movement of the airplane around the vertical axis is yaw.• Yaw is controlled by movement of the rudder.PITCH•The lateral axis extends crosswise from wingtip to wing tip. •Movement of the airplane around the lateral axis is known as pitch.•Pitch is controlled by movement of the elevators.AERODYNAMIC CONTROL SURFACES•Elevators control pitch angle•Ailerons control roll angle•Rudder controls yaw angle•Flaps increase lift and drag•Leading edge slats increase lift•Drag brakes increase drag•Spoilers reduce lift.•Canard is a horizontal control surface placed near the nose.TOPICS TO BE COVERED•Roadmap of Disciplines•“English” to “S.I.” units•Common Aerospace Terminology•Preliminary Thoughts on Aerospace Design•Specifications (“Specs”) and Standards•System IntegrationAEROSPACE ENGINEERINGDISCIPLINES•Design, modeling, and testing aerospace vehicles requires knowledge and training in the areas of–Aerodynamics–Structures–Flight Mechanics, Stability & Control–Propulsion–Performance–Design - An integration of these disciplinesto come up with a new product or conceptENGLISH UNITS•U. S. aerospace industries use this convention.–mass : lbm or in slugs–Distance : feet–Time: seconds–Force: lbf (pronounced pound force)–Pressure: psi (pounds per square inch), or in atm–energy: Btu (British thermal units)–Power: HP–Temperature: Fahrenheit or degree Rankine ( R)S. I. UNITSSystème International d’Unites•Most other European and Asian nations use this.–mass - kg–Distance - m (pronounced meters)–Time - seconds–Force - N (pronounced Newtons)–Pressure - N/m2, or in atm–energy in Joules–Power in Watts (Joule/sec)–Temperature in Celsius or degree Kelvin ( K)English Units (Continued)•Note:–1 slug = 32.2 lbm–1 atm = 14.7 psi (14.7 pounds per square inch)–0 Degrees F = 460 Degrees Rankine–We convert Fahrenheit to Rankine by adding 460 to F–1 BTU = 778.15760 ft lb–1 HP = 550 ft.lb/sCONVERSION FACTORS•1 ft = 0.3048 m•1 slug = 14.594 kg•1 slug = 32.2 lbm•1 lbm = 0.4536 kg•1 lb = 4.448 N•1 atm = 114.7 psi = 2116 lb/ft2 = 1.01 x 105 N/m2•1degree K = 1.8 degree R• Convert Celsius to Kelvin by adding 273 to Celsius• 1HP = 745.69987 Watts•g = Acceleration due to gravity = 32.2 ft/s2 = 9.8 m/s2Examples•Wright Flyer weighed 340 kg–Its weight in English Units: • Its wing area was 46.5 m2–The area in English units:–Its speed = 56 km/h = 35mph (VFY: verify for yourself, please!)mmlblbkg 750slug 12.32kg 14.594slug 1340 2225003048.015.46 ftmftm AEROSPACE TERMINOLOGY•GW=Gross Weight= The nominal weight for a standard mission before the aircraft (or spacecraft) takes off.•Crew Weight: Weight of crew and associated equipment (parachute, oxygen, etc.)•P/L= Payload Weight = Weight the aircraft was designed to carry. (passengers weight, baggage for aircraft;satellites, imaging equipment etc. for spacecraft)•Fuel/Weight: That required to do the mission plus required reserves•Empty Weight = What the aircraft or spacecraft weighs when it is nominally empty (may include trapped fuel )•GW = Crew weight+ P/L + Fuel Weight + Empty WeightAEROSPACE TERMINOLOGY–Wing Loading = Aircraft Weight/Wing Area–Power Loading = Aircraft Weight/ Nominal Engine Power –Aspect ratio, AR = (Wing Span)2 / Wing Area–Taper ratio = Root Chord/ Tip Chord–Specific Fuel Consumption, sfc = (Fuel Weight)/ (Power x Hour)–Empty Weight Fraction = Empty Weight/ Gross Weight–Payload Fraction = Payload Weight/ Gross Weight22,mNftlbWattNHPlb,TYPICAL WING LOADING•Light Civil Aircraft: 10 to 30 lb/ft2•High Altitude Fighter 30 to 60 lb/ft2•Interceptor Fighter 120 to 350 lb/ft2•Long Range Transport 110 to 140 lb/ft2PRELIMINARY THOUGHTS ON DESIGN•Design is, in general,–a team effort–a large system integration activity–done in three stages–iterative–creative, knowledge based.•The three stages are:–Conceptual design–Preliminary design–Detailed designConceptual Design•What will it do?•How will it do it?•What is the general arrangement of parts?•The end result of conceptual design is an artist’s or engineer’s conception of the vehicle/product.•Example: Clay model of an automobile.Conceptual DesignsDan Raymer sketchConceptual Designs1988 Lockheed DesignPreliminary Design•How big will it be?•How much will it weigh?•What engines will it use?•How much fuel or propellent will it use?•How much will it cost?•This is what you will do in this course.Preliminary Design AnalysisWing sizing spreadsheetWritten by Neal Willford 12/29/03 for Sport AviationBased on methods presented in "Technical Aerodynamics" by K.D. Wood, "Engineering Aerodynamics" by W.S. Diehl, and "Airplane Performance, Stability and Control" by Perkins and HageThis spreadsheet is for educational purposes only and may contain errors. Any attempt to use the results for actual design purposes are done at the user's own risk.Input required in yellow cellsWing area sizingA/C weight:1150lbs Flaps up Clmax:1.42get from