Aircraft Dynamics and Control Aircraft motion is more complicated than spacecraft motion due to the dependence of forces and moments on attitude and velocity Typical first investigations of aircraft dynamics and control focuses on the longitudinal and lateral motions of symmetric (left-to-right) aircraft near straight and level flight

Motion Equations for a Rigid Aircraft b : _ v = ¡ ! £ + 1 m f a e r o t h u s ¤ R i g I µ S ( ) w [ ] T N n d x p , U l y c & k ; q A - z 6

Reference Frames for Aircraft D&C l F m , . T y p c s u ° E h b o g d f 3 - x w V v A 2 z » : R = ( ) W 1 k ¹ B ¯ ® ¡ Ã µ Á

Reference Frames for Aircraft D&C (2) l u s t r a i o n ( f m R . S e g ' F h D y c ) w - p b , k d ° N z : 1 x v

Motion Equations for a Rigid Aircraft (2) y p i c a l k n e m t s v r b w ( Ã ) , h µ d o Á g 3 - 2 1 q u E f V ® ¯ R ; ° : 4 5 = + ¡

Straight and Level Flight c o r i x = ! µ [ u w p q y z Á Ã ] F g n d l ° , f m - k ( ) ¤ V ® ± E A R

Linearized Motion L i n e a r z g b o u t h s d l v ° y m w = 1 2 , p 4 ( ) T q c k - : x M [ ¢ µ ] ± E Á Ã A R

Longitudinal Motion L o n g i t u d a l M : E e v r T h s c p , y - x = [ ¢ w q z µ ] ± A 2 6 4 X ¡ Z 1 _ + ( ) b 3 7 5 . m f ; °

Longitudinal Motion (2) : E e v r T h s c p , y - x = [ ¢ w q z µ ] ± B 2 6 4 X Z 1 ¡ _ + 3 7 5 A m f ° b

Longitudinal Motion (3) 4 h r e m ) : E v T s c - y p , x = [ ¢ w q µ ] ± A 2 6 X ¡ Z 1 _ + 3 7 5 B

Longitudinal Motion (4) B u s i n e J t E x a m p l o f L g d M ( 4 h r ) : - v T c y , A = 2 6 ¡ 1 9 5 7 8 3 S b k ¸ § ; z

Longitudinal Motion (5) B u s i n e J t E x a m p l o f L g d M ( 4 h r ) c . C b y = 2 6 : 7 5 ¡ 1 9 3 8 £ k O v I w , A ¤

Longitudinal Motion (6) B u s i n e J t E x a m p l o f L g d M ( 4 h r ) c . Note Final Time S h o r t - p e i d , a v l y m n s u g f c ¯ w ¸ = ¡ 1 : 2 7 6 § 8

Longitudinal Motion (7) B u s i n e J t E x a m p l o f L g d M ( 4 h r ) c . Note Final Time L o n g - p e r i d , l h t y a m s u f c w ¸ = ¡ : 7 4 § 1 2 5 6 . T

Lateral Motion L a t e r l M o i n : A d R u c p s , v y w g x = [ ¢ Á Ã ] T ± h m B f z j ; b - D