Aircraft Flight Dynamics Robert F Stengel Lecture12 LateralDirectional Dynamics

... 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 # $ % % % % % & ' ( ( ( ( ( Stability ... top! Dutch Roll, front! Why Modify the Equations?" F LD = F DR F RS DR F DR RS F RS ! " # # $ %...

Ngày tải lên: 04/07/2014, 19:26

... Frame" C X C Y C Z ⎡ ⎣ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ B = axial force coefficient side force coefficient normal force coefficient ⎡ ⎣ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ C D C Y C L ⎡ ⎣ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ = drag coefficient side force coefficient lift coefficient ⎡ ⎣ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ •  ... = v x v y v z ⎡ ⎣ ⎢ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ ⎥ F I = f x f y f z ⎡ ⎣ ⎢ ⎢ ⎢ ⎢ ⎤ ⎦ ⎥ ⎥ ⎥ ⎥ I = F gravity + F aerodynamics + F thrust ⎡...

Ngày tải lên: 04/07/2014, 19:20

... = ∂ f 1 ∂ V ∂ f 1 ∂γ ∂ f 1 ∂ q ∂ f 1 ∂α ∂ f 2 ∂ V ∂ f 2 ∂γ ∂ f 2 ∂ q ∂ f 2 ∂α ∂ f 3 ∂ V ∂ f 3 ∂γ ∂ f 3 ∂ q ∂ f 3 ∂α ∂ f 4 ∂ V ∂ f 4 ∂γ ∂ f 4 ∂ q ∂ f 4 ∂α $ % & & & & & & & & & & & ' ( ) ) ) ) ) ) ) ) ) ) ) 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 ∂...

Ngày tải lên: 04/07/2014, 19:26

... G f Δu Δ  x s = F f s Δx f + F s Δx s + G s Δu •  Algebraic solution for Δx fast " 0 ≈ F f Δx f + F s f Δx s + G f Δu F f Δx f = F s f Δx s − G f Δu Δx f = F f −1 F s f Δx s + G f Δu ( ) •  ... Δx fast in differential equation for Δx slow " Δ  x s = F f s F f −1 F s f Δx s + G f Δu ( ) # $ % & + F s Δx s + G s Δu = F s − F...

Ngày tải lên: 04/07/2014, 19:29

... 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" •  ... Flight Dynamics Book and Computer Code" •  All programs are accessible from the Flight Dynamics web page" –  http://www.princeton.edu/ ~stengel/ FlightDynamics...

Ngày tải lên: 04/07/2014, 19:19

... effects" •  Short-Takeoff-and-Landing (STOL) aircraft augment takeoff/landing lift in many ways, e.g.," –  Full-span flaps" –  Deflected thrust" Grumman F8 F! Grumman F4 F! GB R1! C T o ,C T V ,C T δ T ,C L δ T World ... to 1990
 Robert Stengel, Aircraft Flight Dynamics, MAE 331, 2012" Copyright 2012 by Robert Stengel. All rights reserved. For educationa...

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 ... = Surface ∫ L B M B N B " # $...

Ngày tải lên: 04/07/2014, 19:22

... Cruising Flight Performance
 Robert Stengel, Aircraft Flight Dynamics, MAE 331, 2012! Copyright 2012 by Robert Stengel. All rights reserved. For educational use only.! http://www.princeton.edu/ ~stengel/ MAE331.html! http://www.princeton.edu/ ~stengel/ FlightDynamics.html! •  ... tubes on Fouga Magister" Cessna 172 pitot tube" X-15 Q Ball" Flight Testing Ins...

Ngày tải lên: 04/07/2014, 19:24

... Glide" Climbing Flight Gliding, Climbing, and Turning Flight Performance
 Robert Stengel, Aircraft Flight Dynamics, MAE 331, 2012 ! Copyright 2012 by Robert Stengel. All rights reserved. For educational ... Flight Envelope Flight Envelope Determined by Available Thrust" •  Flight ceiling defined by available climb rate" –  Absolute: 0 ft/min" –  Ser...

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 ... sequences of 3 rotations can be chosen; however, once sequence is chosen, it must be retained " Effects of Rotation on Vector Transformation from Inertial to Body Frame of R...

Ngày tải lên: 04/07/2014, 19:25