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constraints, a reduced capability version of MINDS, SMINDS, was used.
For more information, see reference 13.
This FORTRAN subroutine initlalizes variables such as ambient conditlons,
engine states, engine outputs, actuator outputs, all both
unlagged and lagged to slmulate sensed values, time constants, associated
exponentials, and integration step size.
This FORTRAN subroutine initializes the elements of the H and D
matrices which remain constant at all operatlng conditions. The flag
DFLAG is initialized to O. This flag Is used in EMODEL to indicate
whether or not to recalculate several of the matrix elements. The
flag's value must be changed using MINDS.
This assembly language routine does table look-up and interpolation
on a function of one variable using the slope/intercept method.
This FORTRAN subroutine calculates properties of combustion.
This FORTRAN function evaluates a polynomial passed as an argument to
it.
This assembly language program interpolates between points in a
lookup table. It works with small-model programs, i.e., the code
sections of all modules are combined and allocated within one segment.
The program is described in more detail in reference 14.
This assembly language program calculates reference point schedules
for the engine variables. The first time through, the routine starts
at the label RPFANINT which is slightly earlier in the code than
RPFAND. Thls first part of the code initializes pointers which are
used in successlve calls of RPFAND.
This assembly language program is the continuation of RPFAND. It
calculates more reference point schedules and limits for the scheduled
values. The first time through, the routine starts at the
label RPLIMiNT which is slightly earlier in the code than RPLIMD.
This first part of the code initializes pointers which are used in
successive calls of RPLIMD.
This FORTRAN functlon returns temperature as a function of enthalpy.
12
REFERENCES
I. Merrill, W.C., et al.: AdvancedDetection, Isolation, and Accommodatlon
of Sensor Failures - Engine Demonstration. NASATP-2836, 1988.
2. Merri11, W.C.; DeLaat, O.C.; and Bruton, W.M.: Advanced Detection,
Isolatlon, and Accommodation of Sensor Failures - Real-Time Evaluation.
NASA TP-2740, 1987.
3. DeLaat, J.C.; and Soeder, J.F.: Design of a Microprocessor-Based Control,
Interface and Monitoring (CIM) Unit for Turbine Englne Controls Research.
NASA TM-83433, 1983.
4. Merrill, W.C., et. al.: HYTESS - A Hypothetical Turbofan Engine
Simplified Simulation. NASA TM-83561, 1984.
5. Merrill, W.C.: HYTESS II - A Hypothetical Turbofan Engine Simplified
Simulation With Multivariable Control and Sensor Analytical Redundancy.
NASA TM-87344, 1986.
6. DeLaat, J.C.: and Merrill, N.C.: A Real-Time Implementation of an
Advanced Sensor Failure Detection, Isolation, and Accommodation
Algorithm. AIAA Paper 84-0569, Jan. 1984 (NASA TM-83553).
7. Beattie, E.C., et al.: Sensor Failure Detection For Jet Engines.
(PWA-5891-18, Pratt and Whitney Aircraft; NASA Contract NAS3-23282) NASA
CR-168190, 1983.
8_ iSBC 86/14 and iSBC 86/30 Single Board Computer Hardware Reference
Manual. Order Number: 144044-001, Intel Corp., Santa Clara, CA, 1982.
9. ZX-2OOA Single Board Disk Controller. Publication Number-98-200A, Zendex
Corp., Dublln, CA, 1983.
I0. User Manual for DT1741 SERIES (DTI741, DT1742, DT1744, DT1751, DT1754,
DT1841, DT1842, DT1843. Analog Input, Analog Output and Analog I/O
Systems), Document UM-00048-3 (Ref. DTI-UM-1740-3), Data Translatlon,
Inc., Marlboro, MA.
11. ASM86 Language Reference Manual. Order Number:
Santa Clara, CA, 1982.
121703-002, Intel Corp.,
12. DeLaat, J.C.: A Real-Time FORTRAN Implementation of a Sensor Failure
Detectlon, Isolation and Accommodation Algorithm. Proceedings of the 1984
American Control Conference, Vol. l, IEEE, ]984, pp. 572-5?3.
13. Soeder, J.F.: MINDS - A Microcomputer Interactive Data System for
8086-Based Controllers. NASA TP-2378, 1985.
14. Mackin, M.A.; and Soeder, J.F.: Floating-Point Function Generatlon
Routines for 16-Bit Microcomputers. NASA TM-83783, 1984.
13
TABLE I. - SIMULATOR INPUTS
Input channel Variable Description
number
8 Commanded main combustor fuel flow (WF)
9
10
II
12
13
WFCOM
AJCOM
CIVVCM
RCVVCM
BLCCM
TT2ACT
Commanded exhaust nozzle area (AJ)
Commanded fan inlet variable vane angle (CIVV)
Commanded rear compressor variable vane angle (RCVV)
Commanded compressor bleed (BL) (bleed is used open-loop)
Fan inlet temperature (used only in actuator mode)
TABLE If. - SIMULATOR OUTPUTS
　
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