Aircraft Flight Dynamics Robert F Stengel Lecture2 PointMass Dynamics and Aerodynamic Thrust Forces

... 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

... 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& quot; •  Flight ceiling defined by available climb rate" –  Absolute: 0 ft/min" – ...

Ngày tải lên: 04/07/2014, 19:25

... ∂  ψ ∂ψ " # $ $ $ $ $ $ $ % & ' ' ' ' ' ' ' •  Four (6 x 6) blocks distinguish longitudinal and lateral-directional effects " F = F Lon F Lat−Dir Lon F Lon Lat−Dir F Lat−Dir " # $ $ % & ' ' Effects of longitudinal ... Spring" Spring Force vs. Displacement" Spring" Damper" Displacement"...

Ngày tải lên: 04/07/2014, 19:25

... = ∂ 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

... 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 ... Equations?" F LD = F DR F RS DR F DR RS F RS ! " # # $ % & & = F DR small small F...

Ngày tải lên: 04/07/2014, 19:26

... } Δu(s) 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 ... = h 11 h 12 h 21 h 22 ! " # # $ % & & adj s − f 11 ( ) − f 12 − f 21 s − f 22 ! " # # $ % & & det s − f 11 ( ) − f 12 − f 21 s − f 22 ( ) ( ) * *...

Ngày tải lên: 04/07/2014, 19:27

... vehicles. !  Understanding of aircraft equations of motion, configuration aerodynamics, and methods for analysis of linear and nonlinear systems. !  Appreciation of the historical context within which past aircraft ... only.! http://www.princeton.edu/ ~stengel/ MAE331.html! !  Dynamics & Control of Atmospheric Flight !  Configuration Aerodynamics !  Aircraft Performance...

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& quot; Grumman F8 F! Grumman F4 F! GB R1! C T o ,C T V ,C T δ T ,C L δ T World ... compressibility effects on drag! •  Dramatic change in stability, control, and flying qualities! •  North American FJ-1 and FJ-4 Fury! •  Republ...

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