Individual variants
Variant 1
The equation of motions for the Ling-Temco-Vought A-7A Corsair II aircraft is given in state space form. The state space vector composes the following variables:
x=[u w q θ]T
;
Variant 2
The equation of motions for the Corsair II aircraft is given in state space form. The state space vector composes the following variables:
x=[u w q θ]T
;
Variant 3
The longitudinal data for the Douglas A-4D Skyhawk flying at Mach 1.0 at 15,000 ft are given as follows:
Speed of sound at 15,000 ft 1058 ft/s.
Xw=-0.0251
1/s; 
1/ft;
Xu=-0.1343 1/s; Mw=-0.1072;
Zw=-1.892 1/s; Mu=0.00263 1/fts;
Zu=-0.0487 1/s; Mq=-2.455 1/s;
ft/rad/s2; 
ft/rad/s2;
1/s2;
The derivatives are not quoted are assumed to be insignificant and are given a zeros value.
The state space vector composes the following variables: x=[u w q θ]T Using state space approach it is necessary to obtain the state space matrices for the Skyhawk and perform the above given task;
Variant 4
The equation of motions for the Lockheed F-104 Straightfighter aircraft is given in state space form. The state space vector composes the following variables:
x=[u w q θ]T
;
Variant 5
The equation of motions for the McDonnell F-4C Phantom aircraft is given in state space form. The state space vector composes the following variables: x=[u w q θ]T
;
Variant 6
The equation of motions for the X-15 aircraft is given in state space form. The flight condition assumed corresponds with Mach 2.0 at an altitude of 60,000 ft. The state space vector composes the following variables:
x=[u w q θ]T
;
Variant 7
The longitudinal data for the Republic F- 105 Thunderchief flying at 35,000 ft are given as follows:
Xw=0.0714; Xu=-0.0599; Xq=0; Zq=0;
Zw=-4.1188; Zu=-0.1427; Mw=-0.8021; Mu=0;
; Mq=-4.1303; 
; 
; 
;
The derivatives are not quoted are assumed to be insignificant and are given a zeros value.
The state space vector composes the following variables: x=[u w q θ]T
Using state space approach it is necessary to obtain the state space matrices for the Republic F- 105 Thunderchief and perform the above given task;
Variant 8
The longitudinal data for the canard configured FBW combat aircraft flying at sea level altitude are given as follows:
Xw=0.260; Xu=0.050; Xq=0; Zq=-1.200;
Zw=-2.800; 
; Zu=-1.200; Mw=0.282;
Mu=0.003; 
; Mq=-0.500;
;
; 
;
The derivatives are not quoted are assumed to be insignificant and are given a zeros value. The state space vector composes the following variables: x=[u w q θ]T
Using state space approach it is necessary to obtain the state space matrices for the canard configured FBW combat aircraft and perform the above given task;
Variant 9
The equation of motions for the McDonnell Douglas F-4C Phantom aircraft is given in state space form. The flight condition assumed corresponds with Mach 1.0 at a sea level altitude. The state space vector composes the following variables:
x=[u w q θ]T
;
