Гоман, Храмцовский, Шапиро (2001) - Разработка моделей...
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М.Г.Гоман, А.В.Храмцовский, М.Шапиро «Разработка моделей аэродинамики и моделирование динамики самолета на больших углах атаки», доклад на международной конференции «Тренажерные технологии и обучение», прошедей в ЦАГИ, г.Жуковский, 24-25 мая 2001 г. M.Goman, A.Khramtsovsky and M.Shapiro "Aerodynamics Modeling and Dynamics Simulation at High Angles of Attack", presentation at the International conference on Simulation Technology & Training held at TsAGI, Zhukovsky (Russia), on 24 May 2001.TRANSCRIPT
24 May, 2001 Simulation Technology & Training 1
Aerodynamics Modeling and Dynamics Simulation at High Angles of Attack
M.Goman, A.Khramtsovsky and M.ShapiroCentral Aerohydrodynamic Institute (TsAGI), Zhukovsky, Russia
24 May, 2001 Simulation Technology & Training 2
Contents:
• Introduction• Closed-loop research & development cycle• General structure of the mathematical model• Aerodynamics modeling• Nonlinear dynamics analysis• Control laws design• Simulation & pilot training• Conclusion
24 May, 2001 Simulation Technology & Training 3
TsAGI Research/Training Simulators
24 May, 2001 Simulation Technology & Training 4
Research & Development Cycle
FlightTests
Simulation&
Stability&
DynamicsAnalysis
ControlLaws
Design
AerodynamicsModelling Pilot Training
24 May, 2001 Simulation Technology & Training 5
General Structure of Aircraft Mathematical Model
Equationsof motion
Undercarriagemodel
Aerodynamicforces and moments
model
Aerodynamiccharacteristics
database
Atmosphericturbulence
model
Engine model
Altitude-velocityengine characteristics
Cockpit
Control systemand actuator
models
Flight testssafety equipment
24 May, 2001 Simulation Technology & Training 6
Wide-Range Aerodynamics Model
AerodynamicsModel:
o
o
o
Static tests
Forced oscillation
tests
testsRotary balance
Flight testsFree spin tests(Vertical wind tunnel M=1:16)
Large-scalecontrolled models(flight tests M 1:4)
24 May, 2001 Simulation Technology & Training 7
Anti-Spin Parachute Model
a
a
b
b
XZ
Y
V
p
p
p
p
r
p
F
lp
V
V
V
p
p
p
p
p
p
p
= V0 + +
+
+
+
+
rp
pp
pp
p
p
p
p p
pl
l
dd t = -
[ ]
(r )
)F
F
= CD S S( 2
2
M = r
w
r
24 May, 2001 Simulation Technology & Training 8
Qualitative Analysis of Nonlinear Aircraft Dynamics
24 May, 2001 Simulation Technology & Training 9
Deep Stall and Unrecoverable Flat Spin Regimes
Pitc
h m
omen
t coe
ffici
ent
Pitc
h m
omen
t coe
ffici
ent
Full pitch-up control Full pitch-up control
Full pitch-down control
Full pitch-down control
Deep stalllock-inNormal flight regimes
(stable with FCS)
Deep stall regimes Unrecoverable flat spin regimes
Flat spin lock-in
CC
mm
Angle of Attack Angle of Attack
IIIxyz- sin2a2
inertia moment
Angle of Attack
Cn asym
Potential function analogy
Normal flight regimes
Critical regimes
Rocking control
p r
Yaw
mom
ent
Aerodynamicyaw asymmetry
24 May, 2001 Simulation Technology & Training 10
Aerodynamic Yaw Asymmetry (X-31)
Data range
-.10 -.05 0 .05 .1020
30
40
50
60
70
80
Ang
le o
f atta
ck (d
eg)
C n0
.06 .08
Flight Tests
24 May, 2001 Simulation Technology & Training 11
Flat Spin Due To Aerodynamic Asymmetry
24 May, 2001 Simulation Technology & Training 12
Pitch Rocking Control for Spin Recovery
Tim
e of
reco
very
(sec
)
0
10
20
30
40
50
0 0.05 0.10 0.15
with rocking
withoutrocking
Yaw asymmetry Cn0
Potential function analogy
Normal flight regimes
Critical regimes
Rocking control
24 May, 2001 Simulation Technology & Training 13
Spin Prevention & Recovery Control System
ConventionalControl Laws
Spin Prevention& RecoveryAlgorithms
Spin Entry& RecoveryIdentification
a,b,V,p,q,r
d
24 May, 2001 Simulation Technology & Training 14
Deep Stall Departure and Recovery
24 May, 2001 Simulation Technology & Training 15
Flat Spin Departure and Recovery
24 May, 2001 Simulation Technology & Training 16
Cobra Maneuver Simulation
24 May, 2001 Simulation Technology & Training 17
Unsteady Nonlinear Aerodynamic Modeling
24 May, 2001 Simulation Technology & Training 18
High Incidence Flight Simulation of a General Aviation Aircraft
24 May, 2001 Simulation Technology & Training 19
Canard Flow Separation & Pitch Self-Sustained Oscillations
Low angle of attack
High angle of attack
Attached flow
Canard separated
aq
q
X
X
e
thr
18
64
16
-3
3
0
(deg/s)
(deg)
24 May, 2001 Simulation Technology & Training 20
Concluding Remarks:
• Piloted simulation of an aircraft dynamics at high angles of attack is extremely important element of the aircraft development and sertification processes
• Piloted simulation helps in assessment of aerodynamic model, accompanying flight tests, and training of rank-and-file pilots
24 May, 2001 Simulation Technology & Training 21
Desktop Training Simulator
24 May, 2001 Simulation Technology & Training 22
Research & Training Flight Simulator
24 May, 2001 Simulation Technology & Training 23
Medium-Size Training Simulator