A formal structure for advanced automatic flight-control systems
[Pages:42]FORMAL $ 1
3
STRUCTURE FOR ADVANCED
AUTOMATIC FLIGHT-CONTROL SYSTEMS(
George Meyer and Lzligi Cicolani Ames Research Center
Moffett Field, Gal$ 94035
FATIONAL 3AERONAUTICS AND SPACE ADMIN.---
1
WASHINGTON, D. C.
3,"%.I@
GAY w)75
I
__1. Report No.
TN D-7940
2. Government Accession No.
7. Author(s)
George Meyer and Luigi Cicblani
9. Performing Organization Name and Address
Ames Research Center Moffett Field, Calif., 94035
12. Sponsoring Agency Name and Address
National Aeronautics and Space Administration Washington, D. C. 20546
15. Supplementary Notes
TECH LIBRARY KAFB, N M
IIlil1111/1l1/1l11l1111111I1l1Il 0333435
5. Report Date
May 1975
6. Performing Organization Code
8. Performing Organization Report No.
A-5710
10. work Unit No.
501-03-11
11. Contract or Grant No.
13. Type o f Report and Period Covered
Technical Note
14. Sponsoring Agency Code
__
16. Abstract
An effort is underway at Ames Research Center to develop techniques for the unified design of multimode, variable authority automatic flight-control systems for powered-lift STOL and VTOL aircraft. This report describes a structure for such systems which has been developed to deal with the strong nonlinearities inherent in this class of aircraft, to admit automatic coupling with advanced air traffic control requiring accurate execution of complex trajectories, and to admit a variety of active control tasks. The specific case being considered is the augmentor wing jet STOL research aircraft.
~
7. Key Words (Suggested by Author(sJ)
Handling qualities Flight controls Autopilot
18. Distribution Statement
- Unclassified unlimited
.- .
19. Security Classif. (of this report)
Unclassified
1 20; Security Classif. (of this page)
Unclassified
~~~
21. No. o f Pages
39
~~~~
*For sale by the National Technical Information Service, Springfield, Virginia 22151
22. Price'
$3.75
TABLE OF CONTENTS
Page
SYMBOLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . v
SUMMARY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1
. INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1
BASIC COMMANDS TO AUTOMATIC FLIGHT-CONTROL SYSTEM . . . . . . . . . . . . 4
TRACKING ACCURACY . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
EQUATIONSOFMOTION . . . . . . . . . . . . . . . . . . . . . . . . . . .
8
. . AUGMENTOR WING JET STOL RESEARCH AIRCRAFT . . . . . . . . . . . . . . 13
. TheTrimmap . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
Perturbation . Controller . . . . . . . . . . . . . . . . . . . . . . 18
Angular Acceleration . Controller . . . . . . . . . . . . . . . . . . 23
Trajectory Command Generator . . . . . . . . . . . . . . . . . . . . 27
. . . . . PROPOSED STRUCTURE FOR ADVANCED AUTOMATIC FLIGHT-CONTROL SYSTEMS
31
CONCLUSIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32
. REFERENCES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
iii I-
SYMBOLS
direction cosine matrix, actual attitude of the aircraft with respect to inertial space
direction cosine matrix, commanded attitude of the aircraft with respect to inertial space
direction cosine matrix, commanded velocity axes with respect to inertial space
wing span
wing chord
drag coefficient
commanded drag coefficient
cold thrust coefficient
lift coefficient
commanded lift coefficient
moment coefficient vector with respect to body axes
commanded moment coefficient with respect to body axes
total force vector coefficient
drag
elementary rotation about axis i through angle $
total aerodynamic and propulsive force in inertial coordinates
right-hand side of system state equation
acceleration of gravity
trimmap
body coordinates of total angular momentum
right-hand side of transition dynamics
feedback gain schedule
L
lift
m
aircraft mass
M a
body coordinates of aerodynamic and propulsive moment
Q
dynamic pressure
inertial coordinates of position vector
RS
R*
inertial coordinates of position vector commanded by air traffic
S
control
R
inertial coordinates of position given by command generator
SC
sw
wing area
t
time variable
6T
thrott1e
'e
cold thrust
'h
hot thrust
U
control vector
U a
body coordinates of unit vector along relative velocity vector
U
inertial coordinates of unit vector along relative velocity vector
S
V
airspeed (true airspeed)
V a
body coordinates of relative velocity vector
van measured body coordinates of relative velocity vector
inertial coordinates of relative velocity vector
vS
inertial coordinates of aircraft velocity vector
*S
v"
inertial coordinates of velocity commanded by air traffic control
S
inertial coordinates of velocity commanded by command generator
vSC
inertial coordinates of aircraft acceleration vector
v
inertial coordinates of acceleration commanded by air traffic control
S
tse
inertial coordinates of acceleration commanded by command generator
%I
inertial coordinates of acceleration input to trimmap
vi
L7
W
S
h
wS
X
6
yV
6ec 6F
6i
6rc 6T
6wc rl
e
V P
w a w n
inertial coordinates of acceleration modifications due to perturbation controller
inertial coordinates of wind inertial coordinates of estimated wind system state angle of attack angle of sideslip glide-slope angle of relative velocity vector elevator command flap angle column matrix with 1 in ith row and 0 in the other two rows rudder command throttle command wheel command variables of unsteady aerodynamics pitch angle nozzle angle density of air side-force angle roll angle yaw angle body coordinates of aircraft angular velocity bandwidth
vi i I
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