SynchroLite ~
Trim, Stability & Control - TrimThe algorithms on this page have not yet been completed nor checked.
Overview:
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Trim Analysis:
For general information and specific use symbols, see:-
OTHER: Aerodynamic - Trim
Main Rotors:
Forces and Moments from Main Rotor (Port):
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XP = |
(Ha1s=0M - TP ) * cos(Yα) |
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YP = |
TP * sin(Yα) - Ha1s=0M * cos(Yα M) |
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ZP = |
- TP * cos(Yα M) |
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RP = |
(dR / db1sM)* b1sM + QP * sin(a1sM ) |
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MP = |
(dM / da1sM)* a1sM - QP * sin(b1sM ) + QP * sin(Yα) |
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NP = |
QP * cos(a1sM ) * cos(b1sM ) * cos(Yα) |
Forces and Moments from Main Rotor (Starboard):
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XS = |
(Ha1s=0M - TS ) * cos(Yα) |
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YS = |
TS * sin(Yα) - Ha1s=0M * cos(Yα M) |
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ZS = |
- TS * cos(Yα) |
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RS = |
(dR / db1sM)* b1sM + QS * sin(a1sM ) |
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MS = |
(dM / da1sM)* a1sM - QS * sin(b1sM ) - QS * sin(Yα) |
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NS = |
-QS * cos(a1sM ) * cos(b1sM ) * cos(Yα) |
Horizontal Stabilizer:
Forces on Horizontal Stabilizer:
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XH = |
LH * sin[Θ - (εMH + εFH + γc)] - DH * cos[Θ - (εMH + εFH + γc)] |
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YH = |
-LH * cos[Θ - (εMH + εFH + γc)] - DH * sin[Θ - (εMH + εFH + γc)] |
Vertical Stabilizer:
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Physical Parameters: |
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Root chord |
crV |
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Tip chord |
ctV |
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Average chord |
CavgV |
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Taper ratio |
λ V |
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Half chord sweep ratio |
Λ c/2V |
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Fuselage depth |
r1 |
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Horizontal distance from main rotor |
x |
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Vertical distance from main rotor |
z |
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Rudder angle |
δ |
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Thickness ratio |
t/cV |
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Flap/chord ratio |
cf/c |
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Aerodynamic Characteristics: |
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Slope of Lift Chord |
aV |
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Dynamic Pressure Ratio |
qV /q |
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Rotor Downwash Ratio |
vV /v1 |
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Fuselage Downwash Ratio |
Dε F /dα |
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Span Efficiency Factor |
δ iV |
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Zero Lift Drag Coefficient |
CD0V |
Forces on Vertical Stabilizer:
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XV = |
-DV * cos[β + ηPV + ηSV + ηFV] - LV * sin[β + ηPV + ηSV + ηFV] |
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YV = |
LV * cos[β + ηPV + ηSV + ηFV] - DV * sin[β + ηPV + ηSV + ηFV] |
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ZV = |
XV * sin[Θ - (εPV + εSV + εFV + γc)] |
Fuselage:
Forces and Moments at the Fuselage:
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XF = |
-D F * cos[Θ - γc - εMF] + L F * sin[Θ - γc - εMF] |
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YF = |
S.F. F * cos(β) - D F * sin(β) |
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ZF = |
-L F * cos[Θ - γc - εMF] + L F * sin[Θ - γc - εMF ] |
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MF = |
q * (M/q)F |
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NF = |
q * (N/q)F |
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RF = |
q * (R/q)F |
Vectored Efflux (exhaust & cooling):
No effect during autorotation.Forces on End of Boom:
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XE = |
Ω * k * direction |
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YE = |
Ω * k * direction |
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ZE = |
Ω * k * direction |
Working Papers:
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DESIGN: |
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MAKE: |
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BUY: |
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Items:
DESIGN:
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Name |
Item |
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Main Rotors |
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Horizontal Stabilizer |
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Vertical Stabilizer |
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Fuselage |
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Efflux |
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Longitudinal Solution |
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Lateral Solution |
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Last Revised; June 20, 2001