Aircraft Stability & Control
Transcript of Aircraft Stability & Control
Aircraft Stability & Control 11/8/05
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MECH 594
Aircraft Performance: Stability and Control
MECH 594
If we wish to trim the aircraft at a
higher or lower trim speed we have to
alter the equilibrium angle of attack, !e.
The most practical manner is through
elevator deflection. But how does !e
affect CMcg
?
Static Longitudinal Control
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The tail lift coefficient is a function of
both !t and "
e
!CL
t
!"= rate of change of C
Lt
with respect
to "t at constant #
e
!CL
t
!#e
= rate of change of CL
t
with respect
to #e at constant "
CL
t
=!C
Lt
!"t
"t+!C
Lt
!#e
#e= a
t"
t+!C
Lt
!#e
#e
So we have for the pitching moment about
the center of gravity:
CMcg
= CM
acwb
+CL
wb
hcg$ h
acwb
( )$ %Ha
t"
t+!C
Lt
!#e
#e
&
'(
)
*+
new tail zerolift line
ti!
Elevator Deflection to Trim
MECH 594
Taking the partial derivative of CMcg
wrt to !e gives
"C
Mcg
"!e
= #$H
"CL
t
"!e
where $H=
lt
c
St
S= tail volume ratio
but we see by the figure that "C
Lt
"!e
is constant and since $H
depends on
the aircraft type then, the increment in CMcg
due only to a given elevator
deflection !e is
%CMcg
= #$H
"CL
t
"!e
!e
Elevator Deflection to Trim
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MECH 594
CMcg
= CM 0
+
!CMcg
!""
a+ #C
Mcg
= CM 0
+
!CMcg
!""
a$ %
H
!CL
t
!&e
&e
Elevator Deflection to Trim
MECH 594
What elevator deflection will give the aircraft a new equilibrium angle of attack !n?
At a new trim CMcg
= 0 at !a=!
n where "
e= "
trim so we can write
CMcg
= CM 0
+
#CMcg
#!!
a$ %
H
#CL
t
#"e
"e and 0 = C
M 0+
#CMcg
#!!
n$ %
H
#CL
t
#"e
"trim
So "trim
=
CM 0
+#C
Mcg
#!!
n
%H
#CL
t
#"e
This equation gives the elevator deflection necessary to trim the aircraft at a given
angle of attack !n. %
H is a known value from the aircraft design, and
CM 0
, #CMcg
/ #! , and #CL
t
/ #"e are known values derived from wind-tunnel or
free-flight data.
Elevator Deflection to Trim
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Free elevator deflection generally reduces the static longitudinal stability.
Stick-free Longitudinal Static Stability
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Takeoff Static Stability
The CG affects our longitudinal controlrequirements at takeoff.
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Directional and Lateral Stability and Control
Directional stability and control refersto airplane behavior in yaw
Movement of longitudinal axis whenit’s rotated about its vertical axis.Rotation caused by yawing moments.
In pure yawing case, there is nopitching or rolling.
Dynamic directional stability iscoupled with dynamic roll stability.
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Directional and Lateral Stability and Control
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Static Directional Stability
Sideslip angle β is angle between relative wind and airplane’s longitudinal axis. When relative wind to right, the sideslip is positive.
Airplane has positive static directionalstability if trimmed for non-sideslipflight and reacts to perturbation byturning into the new relative wind andtends to reduce sideslip angle to zero.
Has negative static directional stability if it tends to increase sideslip angle.
Has neutral static directional stability if it doesn’t react to sideslip.
Figure (a) is negative, figure (b) is positive
MECH 594
The Yawing Moment Equation
Yawing moment about aircraft CG
NCG
= CN (CG )
q!Sb
CN (CG )
=N
CG
q!Sb
where
NCG
= yawing moment about
CG (ft-lb)
CN (CG )
= coefficient of yawing
moment about CG
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Graphic Representation of Static Directional Stability
Positive static directional stability has slope which is exactly opposite for static pitch stability.
• For positive slope, plane experiencing right (+) sideslip develops nose-right yaw coefficient and yaws into new relative wind
• Trim point is where there is no yawing moment. As with pitch stability, degree of slope is indication of degree of stability. Steeper slope means increased stability.
MECH 594
Graphic Representation of Static Directional Stability
As with pitch, it is not unusual for airplane to be stable at smallsideslip angles and unstable at high sideslip angles.
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Contribution of Aircraft Components to Yaw Stability
Wing contribution to positive static directional stability is small, but increases with amount ofsweepback.
In the figure, the right wing produces more drag, so plane turns toward RW. The right wing produces more lift,and this is a roll factor.
MECH 594
Contribution of Aircraft Components to Yaw Stability
CP near quarter length of fuselage (subsonic),which is ahead of CG ∴ the fuselage is destabilizing.
Effect of engine nacelles is comparableto impact discussed for pitch stability.
• For propeller or engine inlet ahead of CG, effect is destabilizing.
• For propeller or engine inlet behind CG, effect is stabilizing.
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Contribution of Aircraft Components to Yaw Stability
• Vertical Tail (ie vertical stabilizer). As name implies, strongly stabilizing.
• Dorsal tail better, because it does not increase parasite drag as much.
MECH 594
Contribution of Aircraft Components to Yaw Stability
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Rudder Fixed versus Rudder Free Stability
• Fixing rudder in neutral position prevents rudder float and increases vertical tail area. This increases directional static stability.
• For aircraft with conventional, reversible controls, there is increased directional stability results if the pilot keeps both feet on pedals and holds the rudder in a neutral position.
MECH 594
Effect of High Angle of Attack
• If vertical tail engulfed in stalled air from wings at high angles of attack, it will not be effective in developing sideward forces.
• Static directional stability will deteriorate.
• Stalled air will have a strong, negative effect on ability to recover from spins and unusual attitudes
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Directional Control
Five conditions of flight can be critical todirectional control exerted by rudder:
1. Spin Recovery 2. Adverse yaw 3. Slipstream rotation · Rotates about fuselage as shown · If strikes left side of stabilizer, will cause nose-left yawing moment · Yawing moment must be overcome with rudder force to maintain directional control 4. Crosswind takeoff and landing 5. Asymmetrical thrust · Left engine assumed to have lost thrust, resulting in nose-left yawing moment · Opposite yawing moment must be developed by rudder / vertical stabilizer
MECH 594
Lateral Stability and Control
Lateral stability refers to behavior of airplane inroll
• Movement of lateral axis when rotated about longitudinal axis. Results when rolling moment (L´) acts on aircraft.
• Caused by either pilot activating ailerons or sideslip angle
From stability standpoint, more interested insideslip angle impact
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Static Lateral Stability
Picture shows airplane sideslipping to right
• Rolling moment developed Since yawing to right, left wing moves faster than right wing, left wing develops more lift, plane rolls to right
• For static lateral stability need wings leveling rolling moment
Three possible tendencies:
(a) Left-wing-down rolling moment (positive lateral static stability) (b) No rolling moment developed (neutral lateral static stability) (c) Unstable airplane (negative lateral static stability)
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The Rolling Moment Equation
Rolling moment about aircraft CG
L'
CG= C
L' (CG )qSb where
L 'CG
= rolling moment about CG
CL '(CG )
= coefficient rolling moment about CG
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Graphic Representation of Static Lateral Stability
• Same slope as for static longitudinal stability
• Trim point is where there is no rolling moment. Occurs at zero sideslip angle
• Assume plane trimmed and has right (+) sideslip Negative rolling moment coefficient (-CL) developed Right wing raised Degree of slope indication of degree of stability
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Contributions of Aircraft Components to Roll Stability
Wing Dihedral:
Makes angle of γ with horizontal Sideslip gives velocity of Vy Roll gives velocity of Vz
Vz
Vy
Vx
γ
Vn
Vy
Vz
Wing line
Vn= V
zcos! + V
ysin!
For ! small,
Vn= V
z+ V
y!
! "# due to dihedral $
Vy%
V=
V&%
V= &%
Dihedral increases α by βγ on right wing and decreases it by same amount on left, tending to bring wings level
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Contributions of Aircraft Components to Roll Stability
• Vertical wing position gives pendulum effect.
• High wing position places airplane CG below wing CP. Results in positive effective dihedral.
• Low mounted wing with airplane. CG above wing CP is unstable and has negative effective dihedral.
• Low-wing airplanes/larger dihedral. Wing sweepback stabilizing, because right wing has more drag but also more lift.
CG
CG
Vβ
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Contributions of Aircraft Components to Roll Stability
Vertical tail:
Side forces stabilizing since tail is above CG
Complete aircraft:
Total airplane must have positive lateral stability
Some components may have negative stability. Okay as long as this is overcome by other components
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Lateral Control
• Accomplished by providing differential lift on wings with ailerons or spoilers.
• Delta wing aircraft often combine ailerons and elevators into single control unit called elevon or ailevator. • Both left and right surfaces act together when elevator action is needed. Left and right surfaces act in opposition when roll motion is required.
• A combination of pitch and roll response is also possible. High roll rates desirable.
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Dynamic Directional and Lateral Coupled Effects
• From before, static stability depends on aircraft’s reaction to imposed sideslip angle.
• Both yawing and rolling produce sideslip. Conversely, sideslip produces yawing and rolling moments.
• Two moments interact and result in coupled effects that determine dynamic stability in yaw and roll.
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Roll Due to Yawing
Rolling moments usually produced by use of ailerons.However, as stated previously, yawing can produce roll.
Example: pilot applies right rudder and
• The aircraft yaws to right• The left wing moves faster than right wing• The left wing develops more lift, and aircraft rolls to the right
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Roll Induced SpinCharacteristics
Roll Due to Yawing
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Adverse Yaw
• Airplane normally yaws in same direction as it is rolled.
• Possible for airplane to yaw in opposite direction to roll can lead to loss of control, and is called adverse yaw.
• Effective wind on up-going right wing is resultant of freestream and downward winds. Lift vector tilted backward.
• Lift vector on down-going wing tilted forward.
• Lift vector on up-going wing and lift vector on down-going wing both oppose yaw in direction of turn.
Try to turn to right∴ adverse yaw
MECH 594
(a) Spiral divergence
➣ Static directional stability great in comparison to static lateral stability. ➣ Wing lowered, but dihedral effect is weak, and wing will not raise to level position.
(b) Directional divergence
➣ Results from negative directional stability➣ Airplane disturbed in either roll or yaw and develops yawing moment that makes it yaw even further
(c) Dutch roll
➣ Sideslips to right, yaws to right➣ Right wing develops more lift , plane rolls to left➣ If not controlled, right wing causes sideslip to left
Types of Motion Resulting from Coupled Effects
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Roll Coupling
Types of Motion Resulting from Coupled Effects
MECH 594 Notes
Questions?
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MECH 594 Notes
See you next time.