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The following transformation matrix is presented without proof.lnterested readers
may refer elsewhere.4
               e~ + e? - e?/ - e~     2(ele2 + eOe3)        2(ele3 - eOe2)
   T12 =     2(ele2 - eOe3)     e~ - e~-+elj - e~     2(e2e3+eOel)       (4.191)
                 2(eOe2 + ele3)        2(e2e3 - eoei)     e~ ~ e~ - e~ + e~
With l/r, O, and 4 as Euler angles, the transformation matrix T12 is also given by
Eq. (4.2h22t,Equating the corresponding elements of the two matrices, it can be
shown tha
Let
so that
     11   0  4   V'. 0 . 4
eo = cos ~/ coS 2 cOs ~ + sin r/2 sm 2 sm 2                     (4.192)
    }s/pcos0 . ~  . /r . 0  4
ei - cos -      s - sm -T .                                          (4.193)
                  2    2 -sm 2 sm 2 coS 2
     v, . 0  4    4r  0 . 4
e2 = ,os 2 sm 2'cos ~ +s,. Y/ ,os 2 sin 2                (4.194)
e3 = _cos/p si. jj] si.~ +sin yr cos ; ,os ~
   222
          Cll C12 C13
    C~= C21 C22 C23
           C31 C32 C33
            Cll C21
  T12=C7f= C12 C": g3;:]
            C13 C23
(4.195)
(4.196)
(4.197)
Then equating the relations (4.22) and (4.197) and using Eqs, (4.192-4.195), the
following relations between the elements of the direction cosine matrix, Euler
angles, and the four quaternion parameters can be obtained. For detailed mathe-
matical derivations, the interested reader may refer elsewhere.4
- cos O cos lr = e~ +ef - e~ - e~
C21  - COS t) sin V  : 2(e1e2 + eOe3)
C31 - -sin 0 -. 2(ele3 - eOe2)
C12 - siri0 siriq COS l/f - sin  Vr cos gb = 2(ele2 - eOe3)
C22 = siri0 siri~ siriltJ +cos p cos ~ : e~ - e/- + at~ - e~
(4.198)
(4.199)
(4.200)
(4.201)
(4.202)
a
  .
j
7
~
.
d.
   I
..
~.
."
  '. .
(.
e2 = ,os B sm ~-)
e3 =.os C sm /j~
:
PERFORMANCE, STABILJTY, DYNAMICS, AND CONTROL
C32  - cos 0 suJ- 4 = 2(e2e3 + eoei)
C13  = sin 0 cos ~ cos p + sin Vr sin ~ : 2(eOe2 + ele3)
C23 = siri0 cos 4 sin ~ - cos yr sin 0 - 2(e2e3 - eoei)
C33 = co\s O cos @ = elji - ef - eg- + e~
(4.203)
(4.204)
(4.205)
(4.206)
The rate equations for the four quaternion parameters are given by the following
relations. For detailed mathematical derivation, the interested reader may refer
elsewhere.4
eo = -2! (ei P + e2q + e3r)
ei = ~ (eoP + e2r - e3q)
e2 = lz (eoq + e3 p - eir)
e3 = ;: (eor + eiq - e2p)
(4.207)
(4.208)
(4.209)
(4.210)
where
eo = -:}: (ei p + e2q + e3r) + A6eo
ei = ;: (eoP + e2r - e3q) + A6et
e2 = ;: (eoq + e3 p - eir) + 1ee2
e3 = ~ (eor + eiq - e2P) + Aee3
e = 1- (eg + el + eg + e~)
(4.211)
(4.212)
(4.213)
(4.214)
(4.215)
Here, A is a free parameter. Usually, A is set equal to a small multiple of the
integration time step.3
     A forward integration of Eqs. (4.211-4.214) generates the time history of four
parameters eo, ei, e2, and e3. Then, the Euler angles can be obtained as follows.
From Eq. (4.200), we have
sin O -. -2(ele3 - eOe2)                                      (4.216)
o = sin-l[-2(ele3 - eOe2)J
(4.217)
EQUATIONS OF MOTION AND ESTIMATION OF STABILITY DERIVATIVES 347
　
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