Aircraft Flight Dynamics Robert F Stengel Lecture8 Aircraft Equations of Motion 1

... 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 ... of inertia, I xz " North American XB-70! Nominal Configuration Tips folded, 50% fuel, W = 38,524 lb x cm @0. 218 c I xx = 1. 8 10 6 slug-ft 2 I yy = 19 .9 10 6...

Ngày tải lên: 04/07/2014, 19:25

... sin γ ! " # # # $ % & & & Relationship of Inertial Axes to Velocity Axes" Aircraft Equations of Motion - 2
 Robert Stengel, Aircraft Flight Dynamics, MAE 3 31, 2 012 " •  Rotating frames of reference" •  Combined equations ... ) •  Rate of change of Translational Velocity " •  Rate of change of Angular Velocity " Mirro...

Ngày tải lên: 04/07/2014, 19:25

... a 23 a 31 ( ) a 11 a 33 − a 13 a 31 ( ) − a 11 a 23 − a 13 a 21 ( ) a 21 a 32 − a 22 a 31 ( ) − a 11 a 32 − a 12 a 31 ( ) a 11 a 22 − a 12 a 21 ( ) ! " # # # # $ % & & & & a 11 a 22 a 33 + ... 0,t f ! " $ % !  Analytical evaluation of partial derivatives" ∂ f 1 ∂ x 1 = 0; ∂ f 1 ∂ x 2 = 1 ∂ f 2 ∂ x 1 = 10 − 30x...

Ngày tải lên: 04/07/2014, 19:25

... ratio" Root Locus Analysis of Parameter Variations
 Robert Stengel, Aircraft Flight Dynamics MAE 3 31, 2 012 " •  Effects of system parameter variations on modes of motion& quot; •  Root locus ... − λ 1 ( ) s − λ 1 * ( ) = s − µ 1 + j ν 1 ( ) $ % & ' s − µ 1 − j ν 1 ( ) $ % & ' = s 2 − µ 1 − j ν 1 ( ) + µ 1 + j ν 1 ( ) $ % &...

Ngày tải lên: 04/07/2014, 19:27

... Normal load factor" –  Pitch-command/attitude-hold" –  Flight path angle" USAF F- 15 IFCS! Princeton Variable-Response Research Aircraft! USAF AFTI /F- 16 ! United Flight 232, DC -10 
 Sioux ... selected angles of attack" •  Effectiveness of low mounting is unaffected by wing wake at high angle of attack" •  Effectiveness of high-mounted elevator...

Ngày tải lên: 04/07/2014, 19:28

... Velocity" Normal " Velocity" Phases of Flight& quot; Flight of a Paper Airplane Flight of a Paper Airplane
 Example 1. 3 -1, Flight Dynamics& quot; •  Red: Equilibrium flight path" •  ... Aerodynamics of Airplane Configurations !  Cruising Flight Performance !  Gliding, Climbing, and Turning Performance !  Nonlinear, 6-DOF Equations of Motion !...

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

... H. Bryan (18 64 -19 28)! –  Longitudinal equations of motion (with W.E. Williams, 19 03)! –  Full equations of motion and linearized equations (19 11) ! Comfort and Elegance by the End of the Decade! •  ... Panther and F9 F-6 Cougar! Toward Supersonic Flight and Stealth Fighter Jets of the 19 50s! •  Emphasis on supersonic speed! Republic F- 10 5! Lockheed F- 1...

Ngày tải lên: 04/07/2014, 19:21

... Dihedral effect" •  Vertical tail effect" Rolling Moment due to Sideslip Angle! •  Crossflow effects depend on vertical location of the wing" Example of Configuration and Flap Effects! NACA ... 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 = 0 −z y...

Ngày tải lên: 04/07/2014, 19:22

... Cruising Flight Performance
 Robert Stengel, Aircraft Flight Dynamics, MAE 3 31, 2 012 ! Copyright 2 012 by Robert Stengel. All rights reserved. For educational use only.! http://www.princeton.edu/ ~stengel/ MAE3 31. html! http://www.princeton.edu/ ~stengel/ FlightDynamics.html! •  ... Flight  Reading Flight Dynamics, 13 0 -14 1, 14 7 -15 5 Virtual Textbook, Parts 6,7...

Ngày tải lên: 04/07/2014, 19:24