Aircraft Flight Dynamics Robert F Stengel Lecture9 Aircraft Equations of Motion 2

... sin γ ! " # # # $ % & & & Relationship of Inertial Axes to Velocity Axes" Aircraft Equations of Motion - 2 Robert Stengel, Aircraft Flight Dynamics, MAE 331, 20 12 " •  Rotating frames of reference" •  Combined equations ... of Reference" •  Orthonormal transformations connect all reference frames" Next Time: Linearization...

Ngày tải lên: 04/07/2014, 19:25

... Construct aircraft moments and products of inertia from components using parallel-axis theorem" •  Model in Pro/ENGINEER, etc." Aircraft Equations of Motion - 1
 Robert Stengel, Aircraft ... have a set of principal axes" Ellipsoid of Inertia! € I xx x 2 + I yy y 2 + I zz z 2 = 1 Inertia Matrix of an Aircraft with Mirror Symmetry" I =...

Ngày tải lên: 04/07/2014, 19:25

... A −1 = a 22 −a 21 −a 12 a 11 ! " # # $ % & & T a 11 a 22 − a 12 a 21 = a 22 −a 12 −a 21 a 11 ! " # # $ % & & a 11 a 22 − a 12 a 21 A = a 11 a 12 a 13 a 21 a 22 a 23 a 31 a 32 a 33 ! " # # # $ % & & & ; ... entire system " F( t) = ∂ f 1 ∂ x 1 ∂ f 1 ∂ x 2 ∂ f 1 ∂ x 12 ∂ f 2 ∂ x 1 ∂ f 2 ∂ x 2...

Ngày tải lên: 04/07/2014, 19:25

... ratio" Root Locus Analysis of Parameter Variations
 Robert Stengel, Aircraft Flight Dynamics MAE 331, 20 12& quot; •  Effects of system parameter variations on modes of motion& quot; •  Root locus ... Effect of a 0 Variation" Δ(s) = s 4 + a 3 s 3 + a 2 s 2 + a 1 s + a 0 = s 4 + a 3 s 3 + a 2 s 2 + a 1 s ( ) + k = s s 3 + a 3 s 2 + a 2 s + a 1 ( ) +...

Ngày tải lên: 04/07/2014, 19:27

... Larrabee, 20 02! Boeing 777 Fly-By-Wire Control System" Aircraft Control Devices and Systems 
 Robert Stengel, Aircraft Flight Dynamics, MAE 331, 20 12& quot; Copyright 20 12 by Robert Stengel. ... Normal load factor" –  Pitch-command/attitude-hold" –  Flight path angle" USAF F- 15 IFCS! Princeton Variable-Response Research Aircraft! USAF AFTI /F- 1...

Ngày tải lên: 04/07/2014, 19:28

... Aerodynamics of Airplane Configurations !  Cruising Flight Performance !  Gliding, Climbing, and Turning Performance !  Nonlinear, 6-DOF Equations of Motion !  Linearized Equations of Motion !  ... vehicles. !  Understanding of aircraft equations of motion, configuration aerodynamics, and methods for analysis of linear and nonlinear systems. !  Appreciation of...

Ngày tải lên: 04/07/2014, 19:19

... F aerodynamics + F thrust ⎡ ⎣ ⎤ ⎦ I Rate of change of position! Rate of change of velocity! Vector of combined forces! Equations of Motion for a Point Mass "  ˙ x (t) = dx(t) dt = f[ x(t) ,F] •  ... Frame" C X C Y C Z ⎡ ⎣ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ B = axial force coefficient side force coefficient normal force coefficient ⎡ ⎣ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ C D C Y C L ⎡ ⎣ ⎢ ⎢ ⎢ ⎤...

Ngày tải lên: 04/07/2014, 19:20

... doubled (F4 F vs. F8 F)! •  Use of flaps means high power at low speed, increasing relative significance of thrust effects" •  Short-Takeoff-and-Landing (STOL) aircraft augment takeoff/landing ... metres (3,8 92 sq!ft) 3,501!sq!ft ( 325 m 2 ) Tail height 42 ft 5 in ( 12. 93 m) 16.85!metres (55!ft!3!in) 55!ft!6!in (16.9 m) Fuselage width 12! ft 4 in (3.76 m) 5.64!metres (18!f...

Ngày tải lên: 04/07/2014, 19:21

... Axes" f B = X B Y B Z B ! " # # # $ % & & & m B = L B M B N B ! " # # # $ % & & & Force Vector" Moment Vector" r × f = i j k x y z f x f y f z = yf z − zf y ( ) i + zf x − xf z ( ) j + xf y − yf x ( ) k m = yf z − zf y ( ) zf x − xf z ( ) xf y − yf x ( ) # $ % % % % & ' ( ( ( ( =  rf ... Dihedral effect" •  Vertical t...

Ngày tải lên: 04/07/2014, 19:22

... Cruising Flight Performance
 Robert Stengel, Aircraft Flight Dynamics, MAE 331, 20 12! Copyright 20 12 by Robert Stengel. All rights reserved. For educational use only.! http://www.princeton.edu/ ~stengel/ MAE331.html! http://www.princeton.edu/ ~stengel/ FlightDynamics.html! •  ... = C T 1 2 ρ V 3 S ≈ independent of airspeed Thrust = T = C T 1 2 ρ V 2 S ≈ independent...

Ngày tải lên: 04/07/2014, 19:24