chapter 2uavbook.byu.edu/lib/exe/fetch.php?media=lecture:chap2.pdf · • con: mathematical...
TRANSCRIPT
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 1
Chapter 2
Coordinate Frames
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 2
Reference Frames • In guidance and control of aircraft, reference frames
used a lot • Describe relative position and orientation of objects
– Aircraft relative to direction of wind – Camera relative to aircraft – Aircraft relative to inertial frame
• Some things most easily calculated or described in certain reference frames – Newton’s law – Aircraft attitude – Aerodynamic forces/torques – Accelerometers, rate gyros – GPS – Mission requirements
Must know how to transform between different reference frames
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 3
Rotation of Reference Frame
p = p0x
i0 + p0y
j0 + p0z
k0
p = p1x
i1 + p1y
j1 + p1z
k1
p1x
i1 + p1y
j1 + p1z
k1 = p0x
i0 + p0y
j0 + p0z
k0
p1 4=
0
@p1x
p1y
p1z
1
A =
0
@i1 · i0 i1 · j0 i1 · k0
j1 · i0 j1 · j0 j1 · k0
k1 · i0 k1 · j0 k1 · k0
1
A
0
@p0x
p0y
p0z
1
A
p1 = R10p
0 R10
4=
0
@cos ✓ sin ✓ 0
�sin ✓ cos ✓ 0
0 0 1
1
Awhere
(rotation about k axis)
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 4
Rotation of Reference Frame Right-handed rotation about j axis:
R10
4=
0
@cos ✓ 0 �sin ✓0 1 0
sin ✓ 0 cos ✓
1
A
Right-handed rotation about i axis:
R10
4=
0
@1 0 00 cos ✓ sin ✓0 �sin ✓ cos ✓
1
A
Orthonormal matrix properties:
P.1. (Rba)
�1 = (Rba)
> = Rab
P.2. RcbRb
a = Rca
P.3. det�Rb
a
�= 1
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 5
Rotation of a Vector
R10 can be interpreted
as left-handed rotation of
vector by angle ✓.
Let and q4= |q|, then
p =
0
@p cos(✓ + �)p sin(✓ + �)
0
1
A
=
0
@p cos ✓ cos�� p sin ✓ sin�p sin ✓ cos�+ p cos ✓ sin�
0
1
A
=
0
@cos ✓ �sin ✓ 0
sin ✓ cos ✓ 0
0 0 1
1
A
0
@p cos�p sin�
0
1
A
where p4= |p|.
Define
q =
0
@p cos�p sin�
0
1
A
then
p = (R10)
>q =) q = R10p
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 6
Inertial Frame and Vehicle Frame
• Vehicle frame has same ori-
entation as inertial frame
• Vehicle frame is fixed at cm
of aircraft
• Inertial and vehicle frames
are referred to as NED frames
• N �! x, E �! y, D �! z
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 7
Euler Angles
• Need way to describe attitude of aircraft • Common approach: Euler angles
• Pro: Intuitive • Con: Mathematical singularity
– Quaternions are alternative for overcoming singularity
: heading (yaw)
✓: elevation (pitch)
�: bank (roll)
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 8
Vehicle-1 Frame
Rv1v ( ) =
0
@cos sin 0
� sin cos 0
0 0 1
1
A
gives
pv1= Rv1
v ( )pv
where is the heading.
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 9
Vehicle-2 Frame
Rv2v1(✓) =
0
@cos ✓ 0 � sin ✓0 1 0
sin ✓ 0 cos ✓
1
A
gives
pv2= Rv2
v1(✓)pv1
where ✓ is the pitch angle.
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 10
Body Frame
Rbv2(�) =
0
@1 0 0
0 cos� sin�0 � sin� cos�
1
A
gives
pb= Rb
v2(�)pv2
where � is the roll (bank) angle.
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 11
Inertial Frame to Body Frame Transformation
Define
Rbv(�, ✓, ) = Rb
v2(�)Rv2v1(✓)Rv1
v ( )
=
0
@1 0 0
0 cos� sin�0 � sin� cos�
1
A
0
@cos ✓ 0 � sin ✓0 1 0
sin ✓ 0 cos ✓
1
A
0
@cos sin 0
� sin cos 0
0 0 1
1
A
=
0
@c✓c c✓s �s✓
s�s✓c � c�s s�s✓s + c�c s�c✓c�s✓c + s�s c�s✓s � s�c c�c✓
1
A
to give
pb= Rb
v(✓)pv
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 12
Stability Frame
Stability frame helps us rigorously define angle of attack and is useful for analyzing stability of aircraft
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 13
Wind Frame
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 14
Wind Frame (continued)
• Wind frame helps us rigorously define side-slip angle
• Side-slip angle is nominally zero for tailed aircraft
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 15
ground track
Airspeed, Wind Speed, Ground Speed
a/c wrt to inertial frame expressed in body frame
wind wrt to inertial frame expressed in body frame
a/c wrt to surrounding air expressed in body frame
Va = Vg �Vw
Vbg =
0
@uvw
1
A
Vbw =
0
@uw
vwww
1
A = Rbv(�, ✓, )
0
@wn
we
wd
1
A
Vwa =
0
@Va
00
1
A
Vba =
0
@ur
vrwr
1
A =
0
@u� uw
v � vww � ww
1
A
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 16
Airspeed, Angle of Attack, Sideslip Angle
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 17
Flight path projected onto ground
horizontal component of groundspeed vector
Course and Flight Path Angles
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 18
ground track
north Wind Triangle
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 19
Vg
VwVa
�a
�
↵✓
ib
Wind Triangle
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 20
When wind speed and sideslip are zero…
If both the windspeed and the sideslip angles are zero, i.e.,
Vw = 0
� = 0
then we have the following simplifications
Va = Vg Airspeed equals groundspeed
u = ur Velocity equals velocity relative to the air mass
v = vr
w = wr
= � Heading equals course
� = �a Flight path angle equals air-mass-referenced flight path angle
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 21
Differentiation of a Vector �b/i
p = px
ib + py
jb + pz
kb
d
dti
p = px
ib + py
jb + pz
kb + px
d
dti
ib + py
d
dti
jb + pz
d
dti
kb
d
dtb
p = px
ib + py
jb + pz
kb
ib = !b/i
⇥ ib
jb = !b/i
⇥ jb
kb = !b/i
⇥ kb
px
ib + py
jb + pz
kb = px
(!b/i
⇥ ib) + py
(!b/i
⇥ jb) + pz
(!b/i
⇥ kb)
= !b/i
⇥ p
d
dti
p =d
dtb
p+ !b/i
⇥ p
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 22
2
1
3
4
5
6 7
8
10
9
11
14
13
16
15
12
Project Aircraft
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 23
wing_l
fuse_l3
fuse_l2
fuse_l1
tailwing_l
tail_h
fuse_h
Project Aircraft
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Beard & McLain, “Small Unmanned Aircraft,” Princeton University Press, 2012, Chapter 2: Slide 24
fuse_l1 fuse_l2
fuse_l3
tailwing_l
wing_l
wing_w
tailwing_w
fuse_w
Project Aircraft