MORTON’S METHOD

MORTON’S METHOD

This method is illustrated in the specific context of the missile ex­ample. The same result as in the previous subsection is obtained. The idea is to rewrite equations (2.11) of the linearized missile model as:

with:

Подпись:QS

Mass * V QSd

h

Подпись: (4.3)QS

Mass * д

MORTON’S METHOD

Ma = (1 + ^)М° Ms = (1 + S2)Ms Za = (1+*з)Я“ Zs = (1 + ВД0

As in the previous subsection, the tail deflection input S is renamed as u. Let then:

 

(4.4)

 

Equation (4.2) is rewritten as:

a

q

и

 

(4.5)

 

with:

 

Г CxZl 1 CxZg C2Ml 0 C2M$ . C3Z° 0 c3z

 

(4.6)

 

Po

 

and:

 

Pi

P2

Рз

 

MORTON’S METHOD

T

= uxv{ T

= ulv2 T

= u2v T

– U2v2

 

Pa

 

t

ui

T

Щ

T

Ъ

T

u2

 

(4.7)

 

MORTON’S METHOD

The above equations can thus be rewritten as:

= (Po + BAC) with Д = diag(6i, S2, S3, $4) and:

Let the augmented plant with additional fictitious inputs w and outputs z:

Подпись: ' a " ' a ’ Q ' Po В Я V . c 0 . и . z . . w .

MORTON’S METHOD

(4.10)

When applying the fictitious feedback w = Az, the initial plant of equation (4.8) is recovered. The LFT model is given in Figure 4.2 (with x = [a, g]).

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