robert f simmons and yeongho yu

... ⎥ B = axial force coefficient side force coefficient normal force coefficient ⎡ ⎣ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ C D C Y C L ⎡ ⎣ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ = drag coefficient side force coefficient lift coefficient ⎡ ⎣ ... y f z ⎡ ⎣ ⎢ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ ⎥ I = F gravity + F aerodynamics + F thrust ⎡ ⎣ ⎤ ⎦ I Rate of change of position! Rate of change of velocity! Vector of combined forces! Equations of Motion for ... Point-Mass Dynamics and Aerodynamic/Thrust Forces
 Robert Stengel, Aircraft Flight Dynamics, 
 MAE 331, 2012! •  Properties of the Atmosphere" •  Frames of reference" •  Velocity and momentum"

Ngày tải lên: 04/07/2014, 19:20

... Numerically" –  First differences in f(x,u,w)" •  Analytically" –  Symbolic evaluation of analytical models of F, G, and L" " ∂ f1 ∂ f1 $ ∂ u1 ∂ u2 $ ∂ f2 $ ∂ f2 ∂ u1 ∂ u2 =$ $ $ ∂ fn $ ∂ fn ∂ u1 ∂ ... effects " Effects of longitudinal perturbations on longitudinal motion" " FLon F = $ Lat−Dir $ FLon # Effects of longitudinal perturbations on lateral-directional motion" •  Effects of lateral-directional ... (0) & " N % ! f ∫# f N # " N tf $ & dt ⇒ & % ! x (t) $ # 1N & in !0,t $ " f% # x2 (t) & " N % !  Analytical evaluation of partial derivatives" ∂ f1 ∂ x1 = 0; ∂ f1 ∂ x2 = ∂ f1 ∂ f2 ∂ f2 ∂ x1 = −10

Ngày tải lên: 04/07/2014, 19:25

... Transfer Functions and Frequency Response
 Robert Stengel, Aircraft Flight Dynamics
 MAE 331, 2012" •  Frequency domain view of initial condition response" •  Response of dynamic ... Transfer Function Matrix" •  Frequency-domain effect of all inputs on all outputs" •  Assume control effects do not appear directly in the output: H u = 0" •  Transfer function ... # # $ % & & adj s − f 11 ( ) − f 12 − f 21 s − f 22 ! " # # $ % & & det s − f 11 ( ) − f 12 − f 21 s − f 22 ( ) ( ) * * + , - - g 11 g 12 g 21 f 22 ! " # # $ % &

Ngày tải lên: 04/07/2014, 19:27

... Control" •  Effect of control surface deflections on aircraft motions" –  Generation of control forces and rigid-body moments on the aircraft" –  Rigid-body dynamics of the aircraft" ... moment C H α : floating tendency C H command : pilot or autopilot input •  Hinge-moment coefficient, C H " –  Linear model of dynamic effects" Angle of Attack and Control Surface Deflection" ... Surface Types Elevator" •  Horizontal tail and elevator in wing wake at selected angles of attack" •  Effectiveness of low mounting is unaffected by wing wake at high angle of

Ngày tải lên: 04/07/2014, 19:28

... Models " Ordinary Differential... complex, integrated problems." !  Understanding of aircraft equations of motion, configuration aerodynamics, and methods for analysis of linear and nonlinear systems ... Electra" F-100" Flight Tests Using Balsa Glider and Cockpit Flight Simulator •  Flight envelope of full-scale aircraft simulation –  Maximum speed, altitude ceiling, stall speed, … •  Performance ... Aerodynamics of Airplane Configurations !  Cruising Flight Performance !  Gliding, Climbing, and Turning Performance !  Nonlinear, 6-DOF Equations of Motion !  Linearized Equations of Motion

Ngày tải lên: 04/07/2014, 19:19

... doubled (F4F vs. F8F)! •  Use of flaps means high power at low speed, increasing relative significance of thrust effects" •  Short-Takeoff-and-Landing (STOL) aircraft augment takeoff/landing ... compressibility effects on drag! •  Dramatic change in stability, control, and flying qualities! •  North American FJ-1 and FJ-4 Fury! •  Republic F-84B Thunderbird and F-84F Thunderstreak! •  Grumman F9F-2 ... Panther and F9F-6 Cougar! Toward Supersonic Flight and Stealth Fighter Jets of the 1950s! •  Emphasis on supersonic speed! Republic F-105! Lockheed F-104! Convair F-102! McDonnell F-101!North

Ngày tải lên: 04/07/2014, 19:21

... y ( ) c y ( ) q dy −b/2 b / 2 ∫ Effect of Aspect Ratio on Wing Lift Slope Coefficient (Incompressible Flow)" •  Airfoil section lift coefficients and lift slopes near wingtips are lower ... −2.58 flow ] Wetted Area: Total surface area of the wing or aircraft, subject to skin friction" * See Van Dyke, M., An Album of Fluid Motion, Parabolic Press, Stanford, 19 82" Effect of Streamlining ... Theory" •  Airfoil section may vary from tip-to-tip" –  Chord length" –  Airfoil thickness" –  Airfoil profile" –  Airfoil twist" •  Lift of a 3-D wing is found by integrating

Ngày tải lên: 04/07/2014, 19:22

... Vectors of the Airplane " ! f $ ! X # x & # B # fy & dx dy dz = # YB fB = ∫ Surface # & # # & " ZB " fz % $ & & & % fz # % ( yfz − zfy ) m = % ( zfx − xfz ) % % ( xf − yf ) y x $ = ( yfz − zfy ) ... zfx − xfz ) j + ( xfy − yfx ) k & # −z y & # fx & ( % ( ( = rf = % z −x ( % f (  % ( y ( % −y x ( % f ( ( '$ z ' $ % ( ' $ & & & % " $ ( yfz − zfy ) $ zf − xf mB = ∫ ( x z) Surface $ $ ( xf ... '$ VN ' ∂α ' Downwash effect on aft horizontal tail" Upwash effect on a canard (i.e., forward) surface" Effects of Static Margin and Elevator Deflection on Pitching Coefficient" •  Zero crossing

Ngày tải lên: 04/07/2014, 19:22

... far from disturbing effects of the aircraft" Air Data Instruments ( Steam Gauges ) " Modern Aircraft. ..Maximum Range of a Jet Aircraft Flying at Constant True Airspeed " Maximum Range of ... •  Satisfy necessary condition for a maximum" •  Lift-to-drag ratio" •  Lift coefficient for maximum L/D and minimum thrust are the same" Airspeed, Drag Coefficient, and Lift-to-Drag ... propeller efficiency η I = ideal propulsive efficiency η net max ≈ 0.85 − 0.9 •  Advance Ratio" J = V nD from McCormick! Propeller Efficiency, η P , and Advance Ratio, J" Effect of propeller-blade

Ngày tải lên: 04/07/2014, 19:24

... ' ( ) ) ) ) ) ) ) ) ) ) ) G = ∂ f 1 ∂δ E ∂ f 1 ∂δ T ∂ f 1 ∂δ F ∂ f 2 ∂δ E ∂ f 2 ∂δ T ∂ f 2 ∂δ F ∂ f 3 ∂δ E ∂ f 3 ∂δ T ∂ f 3 ∂δ F ∂ f 4 ∂δ E ∂ f 4 ∂δ T ∂ f 4 ∂δ F # $ % % % % % % % % % % & ... separately" F Lon = F Ph F SP Ph F Ph SP F SP ! " # # $ % & & Effects of phugoid perturbations on phugoid motion" Effects of phugoid perturbations on short-period motion" Effects ... = − ∂ f 2 ∂ V ∂ f 4 ∂γ = − ∂ f 2 ∂γ •  Coefficients in fourth row of F" Sensitivity of Angle of Attack Dynamics to State Perturbations " ∂ f 4 ∂ q = 1− ∂ f 2 ∂ q ∂ f 4 ∂α = − ∂ f 2 ∂α

Ngày tải lên: 04/07/2014, 19:26

... Stability-and-Control Derivatives" ∂ f 1 ∂ v ∂ f 1 ∂ p ∂ f 1 ∂ r ∂ f 1 ∂φ ∂ f 2 ∂ v ∂ f 2 ∂ p ∂ f 2 ∂ r ∂ f 2 ∂φ ∂ f 3 ∂ v ∂ f 3 ∂ p ∂ f 3 ∂ r ∂ f 3 ∂φ ∂ f 4 ∂ v ∂ f 4 ∂ p ∂ f 4 ∂ r ∂ f 4 ∂φ ... Equations?" F LD = F DR F RS DR F DR RS F RS ! " # # $ % & & = F DR small small F RS ! " # # $ % & & ≈ F DR 0 0 F RS ! " # # $ % & & Effects of Dutch roll ... ∂ f 1 ∂ p ∂ f 1 ∂ r ∂ f 1 ∂φ ∂ f 2 ∂ v ∂ f 2 ∂ p ∂ f 2 ∂ r ∂ f 2 ∂φ ∂ f 3 ∂ v ∂ f 3 ∂ p ∂ f 3 ∂ r ∂ f 3 ∂φ ∂ f 4 ∂ v ∂ f 4 ∂ p ∂ f 4 ∂ r ∂ f 4 ∂φ # $ % % % % % % % % % % % & ' ( ( (

Ngày tải lên: 04/07/2014, 19:26

... Control- and Disturbance-Effect Matrices" Γ = e F δ t − I ( ) F −1 G = I − 1 2! F δ t + 1 3! F 2 δ t 2 − 1 4! F 3 δ t 3 + $ % & ' ( ) G δ t Λ = e F δ t − I ( ) F −1 L = I − 1 2! F δ ... wave" •  Input and output amplitudes different! y C t ( ) = y C peak sin ω t Effect of Input Frequency on Output Amplitude and Phase Angle" •  With low input frequency, input and output ... & Δx 1 * Δx 2 * " # $ $ % & ' ' = − f 22 − f 12 − f 21 f 11 " # $ $ % & ' ' f 11 f 22 − f 12 f 21 ( ) g 1 g 2 ) * + + , - . . Δu *+ l 1 l 2 ) * + + , -

Ngày tải lên: 04/07/2014, 19:26

... Variation in aircraft aerodynamic configuration" –  Effect of feedback control, i.e., control of pitching moment (via elevator) that is proportional to pitch rate" Effect of Parameter Variations ... Root Locus Analysis of Parameter Variations
 Robert Stengel, Aircraft Flight Dynamics
 MAE 331, 2012" •  Effects of system parameter variations on modes of motion" •  Root locus ... http://www.princeton.edu/~stengel/FlightDynamics.html ! Characteristic Equation: A Critical Component of the Response’s Laplace Transform " sI − F [ ] −1 = Adj sI − F ( ) sI − F = C T s ( ) sI − F (n × n) 1×1

Ngày tải lên: 04/07/2014, 19:27

... from takeoff and landing" •  Suggestion: Follow the form of MIL-F-8785C, FAR Part 23, etc., but adapt to differences between manned and unmanned systems" Flight Testing for Certification ... •  Princeton Air Scooter! •  Hiller VZ-1 Flying Platform! •  Princeton 20-ft Ground Effect Machine " Short-Takeoff-and-Landing, Inflatable Plane, and the Princeton Sailwing" •  Pilatus ... Aircraft (Navion )" USAF/Calspan TIFS! USAF AFTI F-16! Princeton VRA!USAF/Calspan NT-33A! Cooper-Harper Handling Qualities 
 Rating Scale " NASA TN-D-5153,1969! Effect of Equivalent Time Delay

Ngày tải lên: 04/07/2014, 19:28

... Typically" L q and L  α have small effects for large aircraft* M q and M  α are same order of magnitude and have more significant effects !  Neglecting" L q and L  α * but not for small ... Condition for Level Flight " •  Specify desired altitude and airspeed, hN and VN! •  Guess starting values for the trim parameters, δT0, δE0, and θ0# •  Calculate starting values of f1, f2, and f3" ... ( Δ δ E Angle-of-Attack-Rate Effects Principally Affect the Short-Period Mode" !  Lift and pitching moment proportional to angle-of-attack rate" !  Bring effects to left side"

Ngày tải lên: 04/07/2014, 19:29

... from various departments and levels, and as a framework to categorize the findings. The model used in this study focuses on four issues: environment, process, form and content, and effects of ... number of different learning curves with respect to different ITs, as illustrated in Figure 2.3. In addition, it is now clear that different parts of a single organization may well be at different ... IT processes form parts of the two (left side) components. Together these two form the context of information strategy. In Sections 3.1, 3.2, 3.3 and 3.4 the aspects of the four components of the model and...

Ngày tải lên: 21/06/2014, 13:20

... have effective information strategy planning and effective information strategies, in order to obtain effective IT in organizations (Henderson and Sifonis, 1988; Fitzgerald, 1993; Premkumar and ... in organizational effectiveness, efficiency and performance, and full exploitation of information technology investment. Establishing the necessary alignment requires the involvement of and co- operation ... then, separate facilities for office automation have been added and a network of PCs and workstations has been installed. Recently, the data communication facilities with the offices of the partner-bank...

Ngày tải lên: 21/06/2014, 13:20

... leasing other kinds of equipment (e.g., forklifts and trucks) as well. The common belief was that the back office had been taken care of, and now the front office needed to be focused on. David ... could not be found. Actions by individuals seemed to strongly influence the creation and dissemination of vision, and vision itself was difficult for respondents to articulate, and difficult to ... and innovation do not differ from each other in terms of alignment with the other dimensions. Previous research has also found it difficult to separate alliance and growth, and differentiation and innovation...

Ngày tải lên: 21/06/2014, 13:20