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PSL
CLLOOP
CALIB
ACTSIM
= O, (default) program runs in initialization loop
= 1, program runs in real-time run loop
= O, (default) scaling of inputs and outputs corresponds to that
of Hybrid simulation
= l, scaling of inputs and outputs corresponds to Propulsion
Systems Laboratory hardware
= O, (default) program runs in open-loop mode, command signals
are taken from memory (the values can be changed using MINDS)
= I, program runs in closed-loop mode, analog command signals
are read in through A/D converters
= O, (default) each routine in run loop is executed fully
= 1, only the A/D converter and D/A converter routines are
executed in the run loop, ACTUAT and EVOLVE are not. Thus the
effect of scale factors for both input and output can be
checked directly using MINDS
= O, (default) scheduled AJ (nozzle area) is proportional to the
steady-state scheduled value calculated in RPLIMD
= l, scheduled AJ is calculated as a function of TT2 read in by
the simulation at each control interval. This should only be
used in the actuator simulation mode.
TABLE VIII. - ERROR MESSAGES
Message Description
8086 F-100 SIMULATION
UPDATE FAILURE OCCURRED
DIVIDE INTERRUPT OCCURRED
FLOATING POINT EXCEPTION OCCURRED
SYSTEM BUS TIMEOUT{_I
IP AT XXXX SEGMENT AT XXXX
Sign on message
Update failure message
Divide interrupt message
Floating point exception message
Bus timeout message
17
F100 ENGINE SIMULATOR
iTr2
l RESEARCH
ACTUATOR
SYSTEM
1
F100
ENGINE
SYSTEM
r"-- w
PATCH
PANEL
1
I
SENSORS /I
" I
*" I
ACTUATOR
SYSTEM
F100 ENGINE
L._
PLA
i
I I SENSOR I
£1M FAILURE
UNIT = SIMULATOR
' l _ ACTUATOR FEEDBACK
I AMBLEhiT CONDITIONS
FI00
ENGINE
SYSTEM
I
II
I
1,1 1,
PATCH
1
FT2
I
m
I
_ 'e_NSORS J / ' - I
PANEL
i
___1
PLA
Flgure 1. - Test setup In PSL.
ORIG/NAL PAGE IS
OF POOR QUALITY
18
ORIGINAL PAGE IS
OF POOR QUALITY
HIGH-PRESSURE TURBINE "-_
\
MAIN COMBUSTOR -_ \ F LOW-PRESSURE TURBINE
\ \ I
', \ ! AUGMENTOR NOZZLE
\ \ / ___.
INLET FAN COMPRESSOR \ ,\ / _ ......
-5_'-- I "\------'--_ _'_'-_
' _,_RE_- "- _,._:_USTOR i
L INLET SOil FUEL FLOW (WF) /
GUIDE VARIABLE L. EXHAUST NOZZLE
VANES VANES t_- COMPRESSOR AREA (AJ)
(CIW) (RCW) BLEED (BL)
Rgure 2. - F100 engine Inp_JtS.
HIGH-PRESSURE TURBINE -'_
\ r- LOW-PRESSURE TURBINE
\ I
MAIN COMBUSTOR -_, \ I
\ \ \ I AUGMENTOR NOZZLE
INLET FAN CC_PRESSORX, _\ 2 __
t _ t \ L. PT4 \ \
L PT2 _- N1 LTT25"\-- N2 \ "_" PT6
TT2
FTIT
Figure 3. - F100 sense points.
19
24
21
18
15
9
22.9K/L 2 22._/Z3
21.4KI.85 21.4KI2.1
19.2KI1.2 19.8KI1.8
2ZgK/Z 5
,19.8K12.5
M
uTI
u"
s
DAC #1
FLOPPY
DISKS
32
DIFFERENTIAL
INPUTS
8 ANOLOG
OUTPUTS
8ANOLOG
OUTPUTS
DAC#2
2O
FigureS.- Engineslmul=_orhardware.
INITIALIZATION
PHASE
RUN - TIME
PHASE
r-- INITIALIZATION
I, OF VARIABLES
P- SET TIMER INTERRUPT
,'_ ,,
' ,-- INLET I
', _ r- MATRIX
• r .' , CALCULATION
/
I
w
i
i
MINDS
0 7 20
SET INTEGRATION CYCLE
, TIMER INTERRUPT
, ._READ IN
.-" CONTROL SIGNALS
"'" SEND OUT SENSOR
m B °
.' READINGS
', MINDS",
ACTUATOR SYSTEM '
CALCULA- EVOLUTION
TK_NS
bTIMER INTERRUPT
5O
0 1 5 9 10
bTIMER INTERRUPT
I
I
!
I!
12 24
Figure 6. - Software timing diagrams.
I
I
100
II
t (msec)
I
I
I
I
I
t (msec)
INITFIAOLRIZEINTEESRRRUEPGTISSTER I
Is_oPI"_ERRUPITVEOTORS
I SET UP INTERVAL TIMER IVlC)OES I
I SETUP82SgAINTERRUPTCONTROLLERJ
t
t
1
I _,RXSIIT
I
l
ILOADSTARTADDRESSOFS_N-C_ MESSAGEI
Figure 7. - Flow chart foxexecutive routine0 EXEC.
21
l
I
I
I
I
I
I
I
I
I
I
!
22
INITIALIZE VARIABLES AND FLAGS I
INITIALIZE TIME CONSTANT FOR LAGS I
INITIALIZE AMBIENT CONDITIONS I
INITIALIZE PLA J
　
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