WYLE LABORATORIES SCIENTIFIC SERVICES & SYSTEMS GROUP

WYLE LABORATORES - RESEARCH STAFF

TECHNICAL REPORT 66338-01

A DATA BASE AND ANALYSIS PROGRAM

FOR SHUTTLE MAIN ENGINE

DYNAMIC PRESSURE MEASUREMENTS

/ (NASA-CB-1788C8) A DA1A BASE A8D ANAIXSIS

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iPRESSOBE MEASDBEHEM1S Final Beport {Hyle

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WYLE LABORATORES - RESEARCH STAFF

TECHNICAL REPORT 66338-01

A DATA BASE AND ANALYSIS PROGRAM

FOR SHUTTLE MAIN ENGINE

DYNAMIC PRESSURE MEASUREMENTS

BY

THOMAS COFFIN

A final report of

work performed under contract NAS8-34343

for

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

GEORGE C. MARSHALL SPACE FLIGHT CENTER

MARSHALL SPACE FLIGHT CENTER, ALABAMA 35812

JANUARY 1986
FOREWORD

This report describes a dynamic pressure data base and data

base management system developed to characterize the Space

Shuttle Main Engine (SSME) dynamic pressure environment.

The data base represents dynamic pressure measurements

obtained during single engine hot firing tests of the SSME.

Software is provided to permit statistical evaluation of

selected measurements under specified operating conditions.

An interpolation scheme is also included to estimate

spectral trends with SSME power level. This report was

prepared by Wyle Laboratories Scientific Services and

Systems Group for the National Aeronautics and Space

Administration, George C. Marshall Space Flight Center. The

work was performed under NASA contract NAS 8-34343, entitled

"Flow Dynamic Environments in High Performance Rocket

Engines."

The author wishes to acknowledge the contribution to this

study by Dr. G. Meares, Chief Architect of the data base

management software described herein. Messrs. B. Dobbs and

D. Duck contributed long hours over a digitizer pad to

accomplish data base input. The singular value

decomposition software for spectrum interpolation was

developed by Dr. J. Jong. Mr. T. Nesman, MSFC technical

contract monitor, provided continuing support through

informal project reviews and served as a focal point for

definition of SSME data requirements.
baseQman^gement system for measurements obtained from space

-^ 1*15-c* esc ri bfcDi

shuttle main engine (SSME) hot firing fr-gat-s^ff-*- t-h* TT.M iuno»Lk

rpprp TrrTTTTnlnrQ- T^nnt-nrl nr mnl ttir Pint i in in i li I

The data were provided

in terms of engine power level and -r. m, ts. pressure

time histories, and power spectra of the dynamic pressure

measurements at selected times during each test!- Test

measurements and engine locations are defined along with a

discussion of data acquisition and reduction procedures. A

description of the data base management$analysis system is

provided and subroutines developed for obtaining selected

measurement means, variances, ranges and other statistics of

interest are discussed. A summary of pressure spectra

obtained at SSME rated power level is provided for

reference. Application of the singular value decomposition

technique to spectrum interpolation is discussed and

isoplots of interpolated spectra are presented to indicate

measurement trends with engine power level. Program

listings of the data base management and spectrum

interpolation software are given. Appendices are included

to document all data base measurements.

;i

ABSTRACT ;

— —~i

J.

a__ dynamic pressure data
ABSTRACT

This report describes a dynamic pressure data

base/management system for measurements obtained from space

shuttle main engine (SSME) hot firing tests at the National

Space Technology Laboratories and the Santa Susana test

facility operated by Rocketdyne. The data were provided by

NASA/MSFC in terms of engine power level and r.m.s. pressure

time histories, and power spectra of the dynamic pressure

measurements at selected times during each test. Test

measurements and engine locations are defined along with a

discussion of data acquisition and reduction procedures. A

description of the data base management/analysis system is

provided and subroutines developed for obtaining selected

measurement means, variances, ranges and other statistics of

interest are discussed. A summary of pressure spectra

obtained at SSME rated power level is provided for

reference. Application of the singular value decomposition

technique to spectrum interpolation is discussed and

isoplots of interpolated spectra are presented to indicate

measurement trends with engine power level. Program

listings of the data base management and spectrum

interpolation software are given. Appendices are included

to document all data base measurements.
TABLE OF CONTENTS

SECTION TITLE

1.0 INTRODUCTORY SUMMARY 1-1

2.0 THE SSME DYNAMIC PRESSURE DATA BASE 2-1

2. l Background 2-1

2.2 SSME Development and Acceptance Testing 2-5

2.3 Data Base Measurements, Format and Locations 2-6

3.0 THE SSME DYNAMIC PRESSURE DATA BASE

MANAGEMENT AND ANALYSIS SYSTEM 3-1

3.1 Data Entry 3-5

3.2 Data Filing System 3-10

3.3 Directory Files 3-12

3 .4 Subroutines 3-13

3.5 Programs 3-24

4.0 SUMMARY OF THE SSME DYNAMIC PRESSURE

ENVIRONMENT AT RATED POWER LEVEL 4-1

5.0 SPECTRUM NORMALIZATION AND INTERPOLATION 5-1

5.1 Dimensional Analysis 5-1

5.2 Interpolation By Singular Value Decomposition .... 5-6

5.3 An Interpolated Library of Spectra for

Dynamic Pressure Measurements 5-11

5.4 A Computer Routine for Estimating Dynamic

Pressure Environments 5-13

Appendix A FLOW DYNAMIC ENVIRONMENT DATA BASE DEVELOPMENT

FOR THE SSME A-l
UNDER SEPARATE COVER

Appendix B

Appendix C

Appendix D

Appendix E

Appendix F

A Data Base Analysis Program For Shuttle Main

Engine Dynamic Pressure Measurements Data Base

Plots for SSME Tests

901-290 through 901-414 B-l

A Data Base Analysis Program For Shuttle Main

Engine Dynamic Pressure Measurements Data Base

Plots for SSME Tests

902-214 through 902-314 C-l

A Data Base Analysis Program For Shuttle Main

Engine Dynamic Pressure Measurements Data Base

Plots for SSME Tests

750-047 through 750-111 D-l

A Data Base Analysis Program For Shuttle Main

Engine Dynamic Pressure Measurements Data Base

Plots for SSME Tests

750-112 through 750-118 E-l

A Data Base Analysis Program For Shuttle Main

Engine Dynamic Pressure Measurements Data Base

Plots for SSME Tests

750-120 through 750-200 F-l

i i
FIGURES

PAGE

Space Shuttle Main Engine 2-3

Space Shuttle Main Engine Power Head 2-4

Typical SSME Measurement Layout 2-7

Thrust Time History 3-2

Pressure Time History 3-3

Pressure PSD 3-4

Comparison of Digitized Points to 400-Line

Spectra Obtained by Interpolation 3-7

Figure 3-5. Comparison of Digitized Points to 400-Line

Spectra Obtained Using the CV-400 Subroutine 3-9

Figure 3-6. SSME Data Base Management and Analysis

Software Operational Sequence and Capabilities 3-31

Figure 2-1

Figure 2-2

Figure 2-3

Figure 3-1

Figure 3-2

Figure 3-3

Figure 3-4

Figure 4-1.

Figure 4-2.

Figure 4-3.

Figure 4-4.

Figure 4-5.

Figure 4-6.

Figure 4-7.

Figure 4-8.

Figure 4-9.

Figure 4-10.

Figure 4-11,

Figure 4-12,

Figure 4-13,

Figure 4-14,

Figure 4-15,

Figure 4-16,

Figure 4-17,

Figure 4-18,

Figure 4-19,

Figure 4-20,

Figure 4-21,

Spectrum of LPFP in PR at RPL 4-3

Spectrum of LPOP DS PR at RPL 4-3

Spectrum of HPOP BAL CAV PR2 at RPL 4-4

Spectrum of HPOP BAL CAV PR1 at RPL 4-5

Spectrum of HPOP DS PR at RPL 4-6

Spectrum of LOX IN DUCT PR2 at RPL 4-7

Spectrum of HPOP DISC PR at RPL 4-8

Spectrum of MCC HOT GAS in PR at RPL 4-9

Spectrum of PBP DS PR at RPL 4-10

Spectrum of LPFP DS PR at RPL 4-11

Spectrum of FPB Fuel Man PR at RPL 4-12

Spectrum of LPOT TURB DR PR at RPL 4-13

Spectrum of OPB PC PR at RPL 4-14

Spectrum of HEX OUTLET at RPL 4-15

Spectrum of HPFP DS PR at RPL 4-16

Spectrum of HOT GAS MAN PR3 at RPL 4-17

Spectrum of HPFP BAL CAV PR at RPL 4-18

Spectrum of MCC FUEL INJ PR at RPL 4-19

Spectrum of FPB PC at RPL 4-20

Spectrum of MCC FUEL INJ PR DC at RPL 4-21

Spectrum of OPB PL at RPL 4-22

1 1 i
Figure 4-22

Figure 4-23

Figure 4-24

Figure 4-25

Figure 4-26

Figure 5-1.

Figure 5-2.

Spectrum of HPOP IN PR at RPL 4-23

Spectrum of AUX LX 1 PR at RPL 4-24

Spectrum of LX 1 PR at RPL 4-25

Spectrum of MCC in PR at RPL 4-26

Spectrum of OPB PC PR DC at RPL 4-27

Frequency Spectrum of Turbulent Wall Pressure Field 5-2

Power Spectral Density of the High Pressure

Oxidizer Pump Discharge Pressure 5 seconds after SSME Startup 5-3

Figure 5-3. Nondimensionalized Frequency Spectrum for High

Pressure Oxidizer Pump Discharge Pressure 5 Seconds

after SSME Startup 5-3

Figure 5-4. Ensemble Average Spectra As A Function of Engine

Power Level (HPOP DS PR) 5-8

Figure 5-5. Normalized Spectrum Functions (Eigenvectors) 5-9

Figure 5-6. Interpolated Spectral Trend By Singular Value

Decomposition (2.5% PWL Increments) 5-10

Figure 5-7. Spectral Trend of LPFP In PR (60 -100% RPL) 5-14

Spectral Trend of LPOP DS PR (60 - 100% RPL) 5-15

Spectral Trend of HPOP BAL CAV PR2 (60 - 109% RPL) 5-16

Spectral Trend of HPOP BAL CAV PR1 (60 - 109% RPL) 5-17

Spectral Trend of HPOP DS PR (59 - 109% RPL) 5-18

Spectral Trend of LOX IN DUCT PR2 (60 - 100% RPL) 5-19

Spectral Trend of HPOP DISC RP (60 - 100% RPL) 5-20

Spectral Trend of MCC HOT GAS IN PR (59 - 100% RPL) 5-21

Spectral Trend of PBP DS PR (59 - 100% RPL) 5-22

Spectral Trend of LPFP DS PR (60 - 100% RPL) 5-23

Spectral Trend of PBP FUEL SUB PR (60 - 90% RPL) 5-24

Spectral Trend of FPB FUEL MAN PR (60 - 100% RPL) 5-25

Spectral Trend of LPOT TURB DR PR (60 - 100% RPL) 5-26

Spectral Trend of LOX HX OUT PR (60 - 90% RPL) 5-27

Spectral Trend of HPFP BAL CAV PR (65 - 1005 RPL) 5-28

Spectral Trend of MCC Fuel Inj PR (65 - 109% RPL) 5-29

Spectral Trend of FPB PC (65 - 109% RPL) 5-30

Spectral Trend of MCC Fuel Inj PR DC (65 - 109% RPL) 5-31

Spectral Trend of HPOP IN PR 5-32

Spectral Trend OPB PC PR DC (65 - 109% RPL) 5-33

Figure 5-8.

Figure 5-9.

Figure 5-10.

Figure 5-11.

Figure 5-12.

Figure 5-13.

Figure 5-14.

Figure 5-15.

Figure 5-16.

Figure 5-17.

Figure 5-18.

Figure 5-19.

Figure 5-20.

Figure 5-21.

Figure 5-22.

Figure 5-23.

Figure 5-24.

Figure 5-25.

Figure 5-26.

I V
Tables

PAGE

Table 2-1. Glossary of Abbreviations Used In Measurement

Descriptions 2-8

Table 2-2. Dynamic Pressure Measurement Descriptions and

SSME Location (from Beckman Test Log) 2-9

Table 2-3. Data Plot Listing for Test Stand Al 2-11

Table 2-4. Data Plot Listing for Test Stand A2 2-22

Table 2-5. Data Plot Listing for Test Stand A3 2-23

Table 3-1. Data Base Analysis Program Listing 3-32

Table 5-1. A Spectrum Interpolation Program Based On

Singular Value Decomposition 5-34
SECTION I

INTRODUCTORY SUMMARY

The Space Shuttle Main Engines (SSMEs) are designed to

provide maximum performance within stringent constraints on

size, weight, and efficiency. As a result the SSMEs are

required to operate under extreme temperatures, with high

fluid pressures and rotational pump speeds. Since the Space

Shuttle Vehicle (SSV) is man-rated, and a key to the cost

effectiveness of the SSV concept is hardware reusability,

system reliability is of paramount importance.

Even under nominal operating conditions, the rocket engine

systems and components are subject to significant pressure

fluctuations. These pressure fluctuations emanate from

pumps, turbines, valves, and in some instances highly

turbulent propellant line flows at high dynamic pressures.

These dynamic environments have temporal characteristics

such that in some cases they appear as complex periodic

functions and in other instances as wide-band random noise.

Intense pressure oscillations have been a source of high

cycle fatigue damage and SSME component failure.

Measurement and empirical classification of the dynamic

pressure environment is therefore desirable to define

nominal SSME operating characteristics and for the

diagnostic evaluation of system malfunction or failure.

Extensive dynamic pressure measurements have been acquired

at critical engine locations in the course of the SSME

development and certification test program. Under NASA

contract NAS 8-34343 Wyle Laboratories has developed a

computerized data base and analysis program to characterize

the SSME dynamic pressure environment under a wide range of

engine operating conditions. This report summarizes the

results of this investigation. (An interim review of the

1 -1
program is given in Appendix A.) The objective of this

study was threefold:

1. Generate a data base of dynamic pressure spectra

obtained from SSME hot firing tests measurements.

2. Develop data base management software to sort,

recall and perform statistical analysis of selected

measurements, to characterize the dynamic pressure

environment under specified SSME operating conditions.

3. Develop and apply analytical techniques to

normalize the data base and predict spectral trends

with SSME operating condition.

The approach employed to accomplish these objectives is

discussed in the following sections„

The SSME dynamic pressure data base is discussed in Section

II. An overview of the SSME development and acceptance test

program is given. Dynamic pressure measurements acquired

during hot firing tests were reduced by NASA/MSFC. A brief

description of data reduction procedures employed by MSFC is

given and the data format provided Wyle for data base

generation is described. Data base measurements and

associated SSME locations are defined. Tables are included

which summarize the SSME tests/measurements entered into the

dynamic pressure data base.

Section III describes the SSME dynamic pressure data base

management system and associated analysis software. The

original software was developed for implementation on a

Perkin Elmer Interdata 8/32 computer system or similar

equipment. Recently the program has been rewritten for

application on more readily available PC/compatible systems.

Data entry/edit routines are described along with

subroutines for estimating statistical means, variances,

ranges, etc. of selected measurements under user defined

1-2
engine operating conditions. A program listing of the data

base management/analysis software is included.

A number of the dynamic pressure measurements were available

for only a limited range of engine operating power levels.

However, the great majority included operation at SSME rated

power level (RPL) . In addition, an extensive data base of

related vibration measurements at RPL has been developed by

MSFC. Therefore ensemble average spectra were computed for

each available measurement at RPL. These results, and their

method of extraction are presented in Section IV. These

summary spectra should provide a valuable reference of SSME

dynamic pressure environments under nominal engine operating

conditions.

Scaling and interpolation of the dynamic pressure spectra is

discussed in Section V. Early in the program, it was

anticipated that dynamic pressure scaling would be performed

through dimensional analysis based on pertinent

flow/geometric parameters. Several simple models were

investigated to represent phenomena such as turbulent duct

flow and blade wake excitation sources. A detailed review

of data base spectra indicated, however, that the pressure

environment is too complex to be adequately represented by a

superposition of simple sources. Dimensional arguments were

therefore abandoned in favor of a more generalized

interpolation technique based on the Singular Value

Decomposition (SVD) of a spectral matrix representing each

measurement over the range of observed test power levels. A

description of the SVD technique is given in Section 5-2,

along with an example of application to a typical data base

measurement. The SVD technique was applied to each

measurement representing an adequate sample size and

available range of test power levels. In this manner a

library of interpolated spectra was generated representing

each measurement in 2.5% power level increments. These

1-3
isoplots illustrate the spectral trend of each measurement

with varying engine power level. Finally, a software routine

was developed to permit prediction of the pressure spectral

density for a desired measurement at a selected engine power

level.

Plots representing the complete SSME dynamic pressure data

base are included as Appendices to this report under

separate cover.
SECTION II

THE SSME DYNAMIC PRESSURE DATA BASE

2.1 Background

The Space Shuttle Main Engines (SSMEs) are extremely

sophisticated machines, designed to provide maximum

performance within stringent constraints on size, weight,

and efficiency. As a result, the SSMEs are required to

operate under extreme temperatures with high fluid pressures

and rotational pump speeds. Additionally, development work

is presently in progress to uprate SSME performance. Since

the Space Shuttle Vehicle (SSV) is man-rated, and a key to

the cost effectiveness of the SSV concept is hardware

reusability, system reliability is of paramount importance.

The Orbiter vehicle main propulsion system consists of three

SSMEs. The SSMEs are reusable, high-performance, 1iquidpropel 1 ant rocket engines with variable thrust. They are

ignited on the ground at launch and operate in parallel,

with approximately 500 seconds total firing duration. Each

of the rocket engines operates at a mixture ratio (liquid

oxygen/liquid hydrogen) of 6:1 and a chamber pressure of

approximately 3000 psia to produce a sea-level thrust of

375,000 pounds and a vacuum thrust of 470,000 pounds. The

engines are presently throttleable over a thrust range of 60

to 109 percent of the design thrust level. This provides a

higher thrust level during liftoff and the initial ascent

phase, and allows Orbiter acceleration to be limited to 3

g's during the final ascent phase. The engines are gimbaled

(+10.5 degrees for pitch and +8.5 degrees yaw) to provide

pitch, yaw, and roll control during the Orbiter boost phase.

2-1
Significant to meeting performance requirements is the use

of the staged combustion power cycle coupled with high

combustion chamber pressures. In the SSME-staged combustion

cycle, the propellants are partially burned at high pressure

and relatively low temperature in the preburners, then

completely combusted at high temperature and pressure in the

main chamber before expanding through the high-area-ratio

nozzle. Hydrogen fuel is used to cool all combustion

devices in contact with high-temperature combustion

products. An electronic engine controller automatically

performs checkout, start, mainstage, and engine shutdown

functions. Major components of the SSME are illustrated in

Figure 2-1. A more detailed view of the SSME power head is

shown in Figure 2-2. This figure provides an indication of

the complexity of the SSME turbomachinery.

2-2
LOW-PRESSURE

FUEL DUCT

LOW-PRESSURE

FUEL TURBOPUMP

HIGH-PRESSURE

FUEL TURBOPUMP

LOW-PRESSURE

OXIOIZER

TURBOPUMP

MAIN COMBUSTION

CHAMBER

HIGH-PRESSURE

OXIOIZER

TURBOPUMP

NOZZLE

FUEL

PREBURNER

OXIOIZER

PREBURNER

LOW-PRESSURE

OXIOIZER

DUCT

CHAMBER

COOLANT

VALVE

FIGURE 2-1. SPACE SHUTTLE'MAIN ENGINE"

2-3
FIGUR E 2-2.Space Shuttle Main Engine Power Head

2-4
2.2 SSME Development and Acceptance Testing

To validate system performance and ensure equipment

reliability, the SSME and components have been and are

presently undergoing extensive development and qualification

tests. Testing of the engine and components is conducted at

several NASA and contractor locations. Full scale engine

test firings for development and flight acceptance are

performed on two single-engine test stands at the National

Space Technology Laboratories (NSTL), Bay St. Louis,

Mississippi, and at one stand operated by Rockwell

International near Santa Susana, California, with plans to

include a development test stand at MSFC. In addition, main

propulsion testing (MPT) is performed at NSTL on a stand

designed to accommodate the Shuttle main propulsion system

elements—the three-engine cluster, the ET, and the Orbiter

systems.

Testing is being performed on a continuing basis. The

length of a given test is dependent on specific test

objectives and may run from several seconds to over 800

seconds. Tests are generally designed to satisfy multiple

specific objectives, which fall into two broad categories;

acceptance/certification firing of flight hardware and

development testing directed towards design verification,

performance and reliability improvement. Test operations

are controlled by a computer called the Command and Data

Simulator (CADS) which communicates with the engine,

displays vital measurements for on-line observation/control

and initiates pre- and post-test procedures.

Approximately 250 measurements are recorded on a given test

including wide band vibration, dynamic pressure and strain

at critical engine locations. Some of these measurements

2-5
are utilized on-line as emergency cut-off indicators and all

are recorded on magnetic tape for subsequent analysis and

evaluation. Limited SSME measurements are recorded on

magnetic tape during SSV flights for evaluation with orbiter

return. Typical dynamic measurements obtained during SSME

operation are illustrated in Figure 2-3.

2.3 Data Base Measurements. Format and Locations

The dynamic pressure data provided by MSFC was received in

three formats for defining each measurement:

1. Engine Power Level as a function of time.

2. Root-Mean-Square pressure as a function of time

(0.4 second averaging time)

3. Mean-square density spectra (PSD's) defining the

frequency decomposition of each measurement at

selected test conditions.

The spectral data were defined over 1-5 kHz, 1-20 kHz, and

1-40 kHz frequency bands. The great majority of data were

reduced over a 1-20 kHz frequency range. The spectral data

were reduced on a B&K wave analyzer yielding 400 spectral

estimates over the range of analysis. This proved to be a

consideration in the data base entry from continuous analog

plots provided.

The dynamic pressure measurements are defined in terms of a

number of acronyms for efficiency in computerized log and

test description. A glossary of these abbreviations is

given in Table 2-1. Table 2-2 defines the measurements and

engine locations utilized in data base development. The

SSME test measurement locations are illustrated in Figure 2-

3. A summary of test measurements thus far entered into the

data base is given in Tables 2-3, 2-4, and 2-5.

2-6
rua

ENGINE FUEL IN PR. TEW

( OFJF9. OF3F80 )

SSME INSTRUMENTATION

r

ENG He INT PR |»T

«NE«3, |

OXIDIZER

LPOP RAO. AX ACC

(AZZAA. 20A, ZCA. 1AA )

IPOT IN PR 1 TENP

ENGINE OHIO IN PR. TEMP \!f,

( 001F8. 001F88 ) *

(SE 8) V

ENERSENCY V

HPOTP IMT SEAL

PURGE PR ( S£J ]

V/N OX ID BIO VALVE POS

KAIN ISJ SEC OP

( CF8AP/CG1A ) "0V ACTUATOR POS

BAIN INO ttNT PR

CF8AP )

PR I TEKP

( C6IA, IB, 1C. ID, IP

"HUM " Ollllltl »»l» I t 1 II I 1

WOT PRI SL N PR t TEW

(SGI. SG2, SG8)

HPCP IHSL DR PR I TEMP

(S63. SG4. SU)

HPOP PHI SL DR PR i TEW

PC(—1

(F6IC) I I

na tma

MCIM VfltflCAtlM

MMIItlOM I

ItllBt IMIIMUIAIIM

VIEW A-A

viEwB-B

O FLIGHT INSTRUMENTATION (CADS)

O APPENDED DATA WORDS (CADS)

D BECKMAN DATA (BKM)

G BECKMAN NFD DATA

O HIGH FREQUENCY ANALOG DATA

2/15/79

FIGURE 2-3. TYPICAL SSME MEASUREMENT LAYOUT

2-7
TABLE 2-1. GLOSSARY OF ABBREVIATIONS USED

IN MEASUREMENT DESCRIPTION

LPFP Low Pressure Fuel Pump

IN Inlet

PR Pressure

LPOP Low Pressure Oxider Pump

DS Discharge

HPOP High Pressure Oxidizer Pump

BAL Balance

CAV Cavity

LOX Liquid Oxygen

DISC Discharge

MCC Main Combustion Chamber

PBP Preburner Pump (Oxidizer)

SUP Supply

FPB Fuel Preburner

LPOT Low Pressure Oxidizer Turbine

TURB Turbine

DR Drive

HX High Pressure

OPB Oxidizer Preburner

HEX High Pressure Lox

HPFP High Pressure Fuel Pump

MAN Manifold

INJ Injector

PC Chamber Pressure

DC (Direct Current) Indicates that

measurement includes mean pressure

AUX Auxiliary

LX Lox

HI High Pressure

OX Oxidizer

2-8
TABLE 2-2. DYNAMIC PRESSURE MEASUREMENT

DESCRIPTIONS AND SSME LOCATION (FROM BECKMAN TEST LOG)

MEASUREMENT DESCRIPTION

LPFP in PR

LPOP DS PR

HPOP BAL CAV PR1

HPOP DS PR

LOX IN DUCT PR2

HPOP DISC PR

MCC HOT GAS IN PR

PBP DS PR

CHAMBER PR

LPFP DS PR

PBP FUEL SUP PR

FPB FUEL MAN PR

LPOT TURB DR PR

LOX HX OUT PR

OPB PC PR

HEX OUTLET

HPFP DS PR

HOT GAS MAN PR3

HPFP BAL CAV PR

MCC FUEL INJ PR

FPB PC

MCC FUEL INJ PR DC

OPB PC

HPOP IN PR

AUX LX I PR

HI LX I PR

HOT GAS MAN PR2

MCC OX INJ PR

OPB PC PR DC

SSME LOCATION

LPFP UB

BOIB

B02A

B04D1-B2

BOIB

BO4CI

CGIP

BO6A-B2

CG2AP

JF21

CF91

FF1A

AD31

H02AP

OG1B

H02AP

KF4P

CG1B

KF2A

C1P

FG1B-B2

CG10P

OG1D

BOIB

SEQ505

BOIB

CGID

C01H

OG1B

2-9
The management, analysis and interpolation of these data to

characterize the SSME dynamic pressure environment is

described in the following sections.

2-10
TABLE 2-3. DATA PLOT LISTING FOR TEST STAND Al

Channel Descriptor

(Time History or PSD)

MMC HOT GAS IN PR

Maximum

Frequency

(Hz)

40,000

293 HPOP DS PR 20,000

PBP DS PR

OPB PC PR DC

294 HPOP DS PR 20,000

PBP DS PR

I

OPB PL

Time

Slice

(Sec)

25

55

75

195

315

435

500

10

200

400

600

800

10

200

400

600

800

10

200

400

600

800

10

40

100

300

500

645

660

10

40

100

300

500

645

660

10

40

100

300

500

645

660

2-11
DATA PLOT LISTING FOR TEST STAND Al (Continued)

295

297

299

300

Channel Descriptor

(Time History or PSD)

HPOP IN PR

HPOP DS PR

PBP DS PR

HPOP IN PR

OPB PC PR DC

HPOP DS PR

PBP DS PR

OPB PC PR DC

HPOP DS PR

PBP DS PR

HPOP IN PR

AUX LX I PR

OPB PC PR DC

PBP DS PR

HPOP IN PR

OPB PC PR DC

Maximum

Frequency

(Hz)

20,000 10

40

100

300

500

645

660

20

45

100

300

450

500

20

45

100

300

450

500

20

45

100

300

450

500

20

45

100

300

450

500

6

2-12
DATA PLOT LISTING FOR TEST STAND Al (Continued)

Maximum Time

Channel Descriptor Frequency Slice

Test (Time History or PSD) (Hz) (Sec)

301 HPOP DS PR 20,000 100

1

I

PBP DS BR

I

OPB PC PR DC

1

I

303 HPOP DS PR

1

I

PBP DS PR

I

HPOP IN PR

1

OPB PC PR DC

1 I '

304 HPOP DS PR

i

3(

i

I

PBP DS PR

'I

LPFP DS PR

1

FPB FUEL MAN PR

I

HPOP IN PR

1

HI LX I PR

1

5 HPOP DS PR

1

*

T

250

400

100

250

400

100

250

400

5

30

45

5

30

45

5

30

45

5

30

45

5

50

75

5

50

75

5

50

75

5

50

75

5

50

75

5

50

75

5

25

50

75

2-13
DATA PLOT LISTING FOR TEST STAND Al (Continued)

Maximum Time

Channel Descriptor Frequency Slice

Test (Time History or PSD) (Hz) (Sec)

31

i

15 PBP DS PR 20,

FPB FUEL MAN PR

1

HPOP IN PR

1

HI LX I PR

1

306 HPOP DS PR

i

1

000 5

25

50

75

5

25

50

75

5

25

50

75

5

25

50

75

5

6

35

70

MCC HOT GAS IN PR 40,000 5

1 1 2°

1 50

T T 75

PBP DS PR 20,

FPB FUEL MAN PR

1

i

T

HPOP IN PR

1

HI LX I PR

1

1

f T

307 HPOP DS PR

i 1

000 5

35

70

5

20

50

75

5

20

50

75

5

20

50

75

5

20

45

70

2-14
fi

r

i!

DATA PLOT LISTING FOR TEST STAND Al (Continued)

Maximum Time

Channel Descriptor Frequency Slice

Test (Time History or PSD) (Hz) (Sec)

307 MCC HOT GAS IN PR 40,000 5

)

| 20

t 70

PBP DS PR 20,000 5

1

1

T

FPB FUEL MAN PR

i

HPOP IN PR

1

1

f

HI LX I PR

1

f

309 HPOP..DS PR

T

MCC HOT. GAS IN PR

t

PBPDSPR

HPOP IN PR

t

HI LX I PR

' t

310 HPOP DS PR

'

r

MCC HOT GAS IN PR

t

PBPDSPR

20

45

70

5

20

45

70

5

20

45

70

5

20

70

6

30

6

24

6

30

6

24

6

24

6

30

6

30

6

f ! 30

HPOP IN PR 2,000 6

t t 30

HILXIPR 20,

311 HPOP, DS PR

1

f

MCC HOT GAS IN PR

1

PBP ,DS PR

t

000 6

30

6

30

6

30

6

30

2-15
DATA PLOT LISTING FOR TEST STAND Al (Continued)

312

313

314

Channel Descriptor

(Time History or PSD)

HPOP IN PR

t

HI LX I PR

MCC HOT GAS IN PR

T

HPOP IN PR

T

HI LX I PR

MCC HOT GAS IN PR

I

HPOP IN PR

?*

HI LX I PR

T

HPOP DS PR

T

MCC HOT GAS IN PR

Maximum

Frequency

(Hz)

20,000

I

315

316

317

PBP DS PR

T

HPOP IN PR

t

HI LX I PR

f

HPOP DS PR

f

MCC HOT GAS IN PR

I

PBP DS PR

T

HPOP DS PR

I

MCC HOT GAS IN PR

PBP DS PR

f

OPB PC PR DC

f

HPOP DS PR

40,000

t

20,000

40,000

T

20,000

6

30

6

30

6

40

6

40

6

4

30

4

30

3

30

6

30

6

30

6

30

6

30

6

30

6

30

4

30

3D

60

4

30

4

11

4

11

4

11

4

11

4

11

4

11

2-16
DATA PLOT LISTING FOR TEST STAND Al (Continued)

Maximum

Channel Descriptor Frequency

Test (Time History or PSD) (Hz)

317 MCC HOT GAS IN

PBP DS --PR

f

OPB PC PR DC

f

319 HPOP DS PR

•

1

MCC HOT GAS IN

1 •

PBP DS PR

1

MCC IN PR

1

OPB PC PR DC

321 MCC HOT GAS IN

1

FPI PC

1

OPB PC PR DC

1 i

PR 20,000

f

40,000

T

20,000

-

PR

•

• i

40,000

1 20,000

PR

40,000

20,000

i

t

Time

Slice

(Sec)

4

11

4

11

4

•11

4

11

6

30

92

6

30

92

6

30

92

12

60

180

6

30

92

6

30

90

100

270

6

30

90

100

270

6

30

90

100

270

6

30

90

100

270

2-17
DATA PLOT LISTING FOR TEST STAND Al (Continued)

Channel Descriptor

(Time History or PSD)

HPOP DS PR

Maximum

Frequency

(Hz)

20,000

I

MCC HOT GAS IN PR

PBP DS PR

FPBPC

OPB PC PR DC

6

130

170

190

210

230

260

280

6

130

150

170

190

210

230

260

280

6

130

150

170

190

210

230

264

284

6

130

150

170

190

210

230

260

280

6

130

150

170

190

210

230

260

280

2-18
DATA PLOT LISTING FOR TEST STAND Al (Continued)

f

Test

384

385

388

389

390

391

393

394

395

397

398

400

401

402

403

404

405

406

407

1

'

Maximum Time

Channel Descriptor Frequency Slice

(Time History or PSD) (Hz) (Sec)

THR

*

UST i

*

_

ft

1

1

t

HPOP BAL CAV PR2 20,

HPOP BAL CAV PR1

OPB PC PR

HPFP BAL CAV PR

FPB PC

t !

000 20

100

220

20

100

220

20

100

220

20

100

220

20

100

220

THRUST

HPOP BAL CAV PR2 20,000 20

i

'

HPOP BAL CAV PR1

i

45

75

200

400

430

20

45

75

200

400

430

2-19
DATA PLOT LISTING FOR TEST STAND Al (Continued)

Channel Descriptor

(Time History or PSD)

FPBPC

Maximum

Frequency

(Hz)

20,000

OPB PC PR

HPFP BAL CAV PR

408

409

THRUST

?

HPOP BAL CAV PR2 20,000

HPOP BAL CAV PR1

OPB PC PR

HPFP BAL CAV PR

20

45

75

200

400

430

20

45

75

200

400

430

20

45

75

200

400

430

15

240

500

525

705

725

15

240

500

525

705

725

15

240

500

525

705

725

15

240

500

525

705

725

2-20
DATA PLOT LISTING FOR TEST STAND Al (Concluded)

r Test

40

Channel Descriptor

(Time History or PSD)

FPB PC

Maximum

Frequency

(Hz)

20,000

f:

r

410

413

414

Time

Slice

(Sec)

7

240

500

525

705

•725

THRUST

2-21
TABLE 2-4. DATA PLOT LISTING FOR TEST STAND A2

Channel Descriptor

(Time History or PSD)

MMC FUEL INJ PR

Maximum

Frequency

(Hz)

40,000

215

251

252

253

254

255

256

257

258

259

260

261

262

263

264

265

266

267

268

269

270

271

276

277

279

283

284

303

306

307

310

311

313

314

Time

Slice

(Sec)

25

50

70

150

300

450

500

30

50

70

THRUST

2-22
TABLE 2-5. DATA PLOT LISTING FOR TEST STAND A3

Test

047

048

049

050

052

053

066

067

068

069

070

071

072

073

074

075

076

077

078

079

087

088

089

090

U91

092

093

094

095

096

097

098

099

100

Channel Descriptor

(Time History or PSD)

THRUST

Maximum

Frequency

(Hz)

LPFP IN PR

LPOP DS PR

HPOP BAL CAV PR2

HPOP BAL CAV PR1

LPFP IN PR 5,000 10

40

85

95

2-23
DATA PLOT LISTING FOR TEST STAND A3 (Continued)

101

Channel Descriptor

(Time History or PSD)

LPFP IN PR

LPOP DS PR

HPOP BAL CAV PR2

HPOP BAL CAV PR1

THRUST

LPFP IN PR

LPOP DS PR

HPOP BAL CAV PR2

LPFP IN PR

Maximum

Frequency

(Hz)

20,000

5,000

20,000

102

LPOP DS PR

HPOP BAL CAV PR2

THRUST

LPFP IN PR

HPOP BAL CAV PR2

HPOP DS PR

LPFP IN PR 20,000

I

Time

Slice

(Sec)

10

40

85

95

10

40

85

95

10

40

85

95

10

40

85

95

5

30

80

95

5

30

80

95

5

30

80

95

5

30

80

95

15

35

60

80

2-24
DATA PLOT LISTING FOR TEST STAND A3 (Continued)

Channel Descriptor

(Time History or PSD)

LPFPIN PR

HPOP BAL CAV PR2

Maximum

Frequency

(Hz)

20,000

HPOP DS PR

LOX IN DUCT PR2 5,000

20,000

103 THRUST

LPFPIN PR

LPOP DS PR

HPOP BAL CAV PR2

HPOP BAL CAV PR1

HPOP DISC PR

LPFP IN PR 5,000

20,000

I

Time

Slice

(Sec)

100

200

280

15

35

60

80

100

150

200

280

15

35

60

80

100

200

280

15

35

60

200

280

15

35

60

80

100

200

280

5

15

20

26

30

5

15

20

2-25
DATA PLOT LISTING FOR TEST STAND A3 (Continued)

Channel Descriptor

(Time History or PSD)

LPFP IN PR

?

LPOP DS PR

HPOP BAL CAY PR2

HPOP DISC PR

MCC HOT GAS IN PR

104

105

T

MMC LONG ACCEL 1

THRUST

LPFP IN PR

LPOP DS PR

HPOP BAL CAV PR2

HPOP BAL CAV PR1

HPOP DISC PR

MMC HOT GAS IN PR

LPFP IN PR

LPOP DS PR

HPOP BAL CAV PR2

HPOP DISC PR

MMC HOT GAS IN PR

' ?

PBP DS PR

THRUST

LPFP IN PR

Maximum

Frequency

(Hz)

20,000

40,000

20,000

40,000

20,000

26

30

5

15

20

26

30

5

15

20

26

30

5

15

20

26

30

5

15

20

26

30

5

15

20

26

30

5

2-26
r

DATA PLOT LISTING FOR TEST STAND A3 (Continued)

r.

r

106

107

Channel Descriptor

(Time History or PSD)

LPOP DS PR

HPOP BAL CAV PR2

HPOP BAL CAV PR1

HPOP DS PR

* HPOP DISC PR

MMC HOT GAS IN PR

PBP DS PR

LPFP IN PR

LPOP DS PR

HPOP BAL CAV PR2

HPOP BAL CAV PR1

HPOP DS PR

HPOP DISC PR

MMC HOT GAS IN PR

T

PBP DS PR

CHAMBER PR

THRUST

LPFP IN PR

LPOP DS PR

HPOP BAL CAV PR2

HPOP BAL CAV PR1

HPOP DS PR

HPOP DISC PR

MCC HOT GAS IN PR

PBP DS PR

LPFP IN PR

LPOP DS PR

I

HPOP BAL CAV PR2

I

HPOP BAL CAV PR1

HPOP DS PR

I

HPOP DISC PR

T

PBP DS PR

f

THRUST

Maximum

Frequency

(Hz)

20,000

40,000

20,000

5,000

I

20,000

6

11

6

11

6

11

6

11

11

6

11

6

11

6

11

2-27
DATA PLOT LISTING FOR TEST STAND A3 (Continued)

Channel Descriptor

iTime History or PSD)

THRUST

LPFP IN PR

LPOP DS PR

HPOPDS PR

109

110

HPOP DISC PR

t

MCC HOT GAS IN PR

PBP DS PR

t

THRUST

LPFP IN PR

LPOP DS PR

HPOP BAL CAV PR2

HPOP BAL CAV PR1

HPOP DS PR

HPOP DISC PR

MCC HOT GAS IN PR

PBP DS PR

LPFP IN PR

f

LPOP DS PR

T

THRUST

LPFP DS PR

LPOP DS PR

HPOP BAL CAV PR2

HPOP BAL CAV.PR1

CHAMBER PR

PBP FUEL SUP PR

FPB FUEL MAN PR

LPFP DS PR

HPOP BAL CAV PR2

Maximum

Frequency

(Hz)

5,000

T

20,000

40,000

f

20,000

20,000

20,000

6

12

6

12

6

12

6

12

6

12

6

6

12

6

12

6

14

6

14

10

30

150

300

400

10

30

150

2-28
DATA PLOT LISTING FOR TEST STAND A3 (Continued)

I

Channel Descriptor

(Time History or PSD)

HPOP BAL CAV PR2

T

HPOP DS PR

Maximum

Frequency

(Hz)

20,000

I

MCC HOT GAS IN PR

40,000

111 THRUST

LPFP DS PR

LPOP DS PR

HPOP BAL CAV PR2

HPOP BAL CAV PR1

HPOP DS PR

BPB DS PR

CHAMBER PR

PBP FUEL SUP PR

FPB FUEL MAN PR

LOX HX OUT PR

LPFP DS PR

I

20,000

LPOP DS PR

Time

Slice

(Sec)

300

400

10

30

150

300

10

30

150

10

30

150

15

40

50

60

70

80

90

100

120

200

280

15

40

50

60

70

80

90

100

120

200

280

2-29
DATA PLOT LISTING FOR TEST STAND A3 (Continued)

Channel Descriptor

(Time History or PSD)

HPOP BAL CAV PR2

Maximum

Frequency

(Hz)

20,000

HPOP BAL CAV PR1

HPOP DS PR

PBP DS PR

15

40

50

60

70

80

90

100

120

200

280

15

40

50

60

70

80

90

100

120

200

280

15

40

50

60

70

80

90

100

120

200

280

15

40

50

60

70

80

90

100

120

200

280

2-30
DATA PLOT LISTING FOR TEST STAND A3 IContinued)

Channel Descriptor

(Time History or PSD)

PBP FUEL SUP PR

Maximum

Frequency

(Hz)

20,000

LPOT TURB DR PR 5,000

20,000

LOX HX OUT PR 5,000

20,000

Time

Slice

(Sec)

15

40

50

60

70

80

90

100

120

200

280

15

40

80

90

100

120

200

1-5

40

50

60

70

80

90

100

120

200

280

15

40

50

60

70

80

90

100

120

200

280

40

50

60

70

2-31
DATA PLOT LISTING FOR TEST STAND A3 (Continued)

Test

111

Channel Descriptor

(Time History or PSD)

LOX HX OUT PR

Maximum

Frequency

(Hz)

20,000

Time

Slice

(Sec)

80

90

100

120

200

280

2-32
DATA PLOT LISTING FOR TEST STAND A3 (Continued)

Channel Descriptor

(Time History or PSD)

THRUST

LPOP DS PR

HPOP BAL CAV PR2

HPOP BAL CA.V PR1

HPOT TURB DR PR

LPFP DS PR

LPOP DS PR

I

HPOP BAL CAV PR2

I '

MCC HOT GAS IN PR

LPOT TURB DR PR

OPB CPR

113

HEX OUTLET

THRUST

LPOP DS PR

HPOP BAL CAV PR2

HPOP BAL CAV PR1

HPOP DS PR

MCC HOT GAS IN PR

PBP DS PR

LPOP DS PR

HPOP BAL CAV PR2

I

Maximum

Frequency

(Hz)

Time

Slice

(Sec)

20,000

40,000

I

5,000

20,000

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

20,000

5,000

f

30

150

280

150

280

2-33
DATA PLOT LISTING FOR TEST STAND A3 (Continued)

Maximum

Channel Descriptor Frequency

Test (Time History or PSD) (Hz)

113 HPOP BAL CAV PR2 20,000

* I

HPOP DS PR 5,000

*

,

|

20,000

MCC HOT GAS IN PR

1

40,000

PBPDSPR 5.000

|

1

20,000

LPFP DS PR

I

LPOT TURB DR PR 5 , 000

1

1

20,000

!

f

OPB PC PR 5,000

'

1

20,000

t

MCC LONG ACCEL 1 40 , 000

OPB PC PR DC 5,000

I

I

20,000

1

?

Time

Slice

(Sec)

30

150

280

30

150

280

30

150

280

30

150

280

30

150

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

280

30

150

280

30

150

280

114 THRUST

LPOP DS PR

HPOP BAL CAV PR2

2-34
DATA PLOT LISTING FOR TEST STAND A3 (Continued))

Channel Descriptor

(Time History or PSD)

HPOP BAL CAV PR1

HPOP DS PR

MCC HOT GAS IN PR

PBP DS PR

LPOT TURB DR PR

LPOP DS PR

Maximum

Frequency

(Hz)

20,000

HPOP BAL CAV PR2

HPOP DS PR

MCC HOT GAS IN PR

PBP DS PR

LPFP DS PR

LPOT TURB DR PR 5,000

• *

20,000

115

OPB PC PR

I

HPOP DS PR

THRUST

LPOP DS PR

HPOP BAL CAV PR2

HPOP BAL CAV PR1

MCC HOT GAS IN PR

PBP DS PR

HPFP DS PR

LPOP DS PR

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

20,000 30

150

280

2-35
DATA PLOT LISTING FOR TEST STAND A3 (Continued)

Channel Descriptor

(Time History or PSD)

HPOP BAL CAV PR2

MCC HOT GAS IN PR

PBP D.S PR

LPFP DS PR

I

LPOT TURB DR PR

116

OPB PC PR

T

HPFP DS PR

HOT GAS MAN PR3

OPB PC PR DC

THRUST

LPOP DS PR

HPOP BAL CAV PR2

HPOP BAL CAV PR1

HPOP DS PR

MCC HOT GAS IN PR

PBP DS PR

OPB PC PR

HPFP DS PR

HOT GAS MAN PR3

HPFP BAL CAV PR

Maximum

Frequency

(Hz)

5,000

I

20,000

40,000

20,000

5,000

t

20,000

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

30

150

280

30

150

30

150

280

30

150

280

30

150

280

2-36
r

DATA PLOT LISTING FOR TEST STAND A3 (Continued)

Maximum Time

Channel Descriptor Frequency Slice

Test (Time History or PSD) (Hz) (Sec)

i 116 LPOPDSPR 5,000 30

r

\

^

f

|

i

ri.

L

r

I ,

*•-

f.

.

..

r

[

I;

I

f

1.

r • i

i , \

i

j1 150

T

 280

20,000 30

i

1 150

t 280

HPOP BAL CAV PR2 5,000 30

1 150 1

t 280

20,000 30

HPOP DS PR

1

T

MCC HOT GAS IN PR

150

280

30

150 '

280

30

150

280

40,000 30

1 150

t 280

PBPDSPR 5,000 30

1 150

t 280

20,000 30

LPFP DS PR

1

f

150

280

30

150

280

LPOTTURBDRPR 5,000 30

1 150 1

t 280

20,000 30

OPB PC PR

1

T

HPFP DS PR

1

t

* HOT GAS MAN PR3

11

t t

150

280

30

150

280

30

150

280

30

150

280

2-37
DATA PLOT LISTING FOR TEST STAND A3 (Continued)

Test

116

117

Channel Descriptor

(Time History or PSD)

HPFP BAL CAV PR

OPB PC PR DC

I

1

THRUST

LPOP DS PR

HPOP DS PR

MCC HOT GAS IN PR

PBP DS PR

LPFP D$ PR

LPOT TURB DR PR

OPB PC PR

HPFP DS PR

HPFP BAL CAV PR

Maximum

Frequency

(Hz)

20,000

Time

Slice

(Sec)

30

150

280

4

30

150

280

LPOP DS PR 5,000 30

I

1 150

f 297

20,000 30

HPOP DS PR

1

y

MCC HOT GAS IN PR

i

i

150

297

30

150

297

30

150

297

40,000 30

1 150

T 280

PBPDSPR 20,000 30

LPFP D* S PR

1

LPOT TURB DR PR

1

OPB PC PR

I 1

150

297

30

150

297

30

150

297

30

150

297

2-38
DATA PLOT LISTING FOR TEST STAND A3 (Continued)

Maximum Time

Channel Descriptor Frequency Slice

est (Time History or PSD) (Hz) (Sec)

17 HPFP DS PR 20,000 30

1

1

HPFP BAL CAV PR

- I '

OPB PC PR DC

t

,

-

150

297

30

150

297

30

150

297

18 THRUST

LPOP DS PR

HPOP BAL CAV PR1

PBP DS PR

LPOP DS PR 20,000 30

MCC HOT* GAS IN PR

150

280

30

150

280

40,000 30

1 150

T f 280

PBP DS PR 20,000 30

1

HPFP BAL CAV PR

1

t

OPB PC PR DC

t 1 f

150

280

30

150

280

30

150

280

2-39
DATA PLOT LISTING FOR TEST STAND A3 (Continued)

Test

120

-121

Channel Descriptor

(Time History or PSD)

THRUST

HPOP BAL CAV PR2

KPOP BAL CAV PR1

HPOP DS PR

MCC HOT GAS IN PR

PBP DS PR

LPOP DS PR

HPOP DS PR

I

MCC HOT GAS IN PR

PBP DS PR

HPFP BAL CAV PR

OPB PC PR DC

I

THRUST

LPOP DS PR

T

HPOP DS PR

I

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HOT GAS MAN PR2

f

HPFP BAL CAV PR

T

OPB PC PR DC

f

Maximum Time

Frequency Slice

(Hz) (Sec)

20,000 30

100

200

30

100

200

30

100

r 200

40,000 30

1 100

f 200

20,000 30

i

100

200

30

100

200

30

100

200

20,000 8

I

16

8

16

8

16

40,000 8

f 16

20.000 8

1

16

8

16

8

16

2-40
DATA PLOT LISTING FOR TEST STAND A3 (Continued)

Test

123

124

125

Channel Descriptor

(Time History or PSD)

THRUST

MCC FUEL INJ PR

Maximum

Frequency

(Hz)

126

127

128

129

130

THRUST

T

FPBPC

THRUST

FPB PC

OPB PC PR DC

THRUST

FPBPC

t

MCC FUEL INJ PR

f

OPB PC PR DC

f

THRUST

FPB PC

f

MCC FUEL INJ PR

20,000

40,000

20,000

20,000

20,000

40,000

t

20,000

20,000

40,000

f

Time

Slice

(Sec)

6

95

125

155

185

215

245

265

285

6

10

50

95

125

155

185

215

245

265

285

6

11

6

6

11

5

11

6

11

6

11

6

11

6

11

2-41
DATA PLOT LISTING FOR TEST STAND A3 (Continued)

Maximum

Channel Descriptor Frequency

Test (Time History or PSD) (Hz)

130 OPBPCPRDC 20,000

I - I t

131 THRUST

MCCFUELINJPR 20,

r

FPBPC

!

-

300

40,000

OPBPCPR.DC 20,000

{ 1

132 THRUST

MCC FUEL INJ PR

OPB PC PR DC

FPBPC 20,000

MCC FUEL INJ PR

.

40,000

OPBPCPRDC 20,000

i i

133 THRUST

i

FPBPC 20,000

i

Time

Slice

(Sec)

6

11

30

70

100

30

70

100

30

70

100

30

70

100

10

90

150

260

291

10

90

150

260

291

10

90

150

260

291

10

90

150

260

291

6

71

76

150

280

2-42
DATA PLOT LISTING FOR TEST STAND A3 (Continued)

Test

13

134

135

Maximum

Channel Descriptor Frequency

(Time History or PSD) (Hz)

OPBPCPRDC 20,000

THRUST

MCC FUEL INJ PR 20 , 000

40,000

FPBPC 20,000

MCC FUEL INJ PR DC

40,000

OPBPCPRDC 20,000

THRUST

MCC FUEL INJ PR 20 , 000

40,000

\ \

Time

Slice

(Sec)

6

71

76

150

280

4

30

45

150

280

4

30

45

150

200

4

30

55

150

280

4

30

45

150

280

4

30

45

150

280

4

30

45

150

280

6

15

45

75

150

6

15

45

2-43
.DATA PLOT LISTING FOR TEST STAND A3 (Continued)

Maximum

Channel Descriptor Frequency

Test (Time History or PSD) (Hz)

135 MCC FUEL INJ PR 40,000

1

I I

MCC FUEL INJ PR DC 20 , 000

1

40,000

1

OPBPCPRDC 20,000

i

»

136 THRUST

MCC FUEL INJ PR 20,000

i

i

40,000

MCC FUEL INJ PR DC 20 , 000

'

OPB PC PR DC

1

1

f t

138 THRUST

139

140

141

142

143

144

145

146 1

Time

Slice

(Sec)

75

150

6

15

45

.75

150

6

15

45

75

150

6

15

45

75

150

4

25

50

150

280

4

25

50

150

280

4

25

50

150

280

25

50

150

280

2-44
DATA PLOT LISTING FOR TEST STAND A3 (Concluded)

Test

147

148

150

151

152

153

154

155

156

157

158

161

164

165

166

167

168

170

171

172

173

174

175

177

178

179

180

181

182

183

184

185

186

187

188

190

191

192

193

194

195

196

197

198

199

200

Channel Descriptor

(Time History or PSD)

THRUST

Maximum

Frequency

(Hz)

Time

Slice

(Sec)

2-45
Section III

THE SSME DYNAMIC PRESSURE DATA BASE

MANAGEMENT AND ANALYSIS SYSTEM

A primary objective of this study was to develop a data base

and data base management system for SSME dynamic pressure

measurements provided by MSFC. The data was obtained in

the form of time histories (power level and r.m.s. pressure)

and power spectra (PSDs) . The data base management and

analysis system was originally designed for use on an

Interdata 8/32 computer system and other computer systems

utilizing similar file name structures. The data

base/management system has recently been converted for

application on P.O. network systems. The data management

system is designed to store test data in a manner that will

provide rapid and easy access to the data by the display and

analysis programs. The system can accept time history data

and PSD or frequency domain data. Each time history and PSD

is stored in a separate data file. The data base management

system creates and names these files when the data is

entered. The system also makes entries in several directory

files so that the data can be quickly accessed, sorted,

statistically summarized and or plotted as required by the

user.

Figures 3-1 through 3-3 show sample plots of data available

in the data base. Separate volumes of plots of each data

file in the data base have been prepared, and are provided

in appendices to this report.

This section describes the data base management system, the

software that has been developed to enter data into the data

base system, and the software that has been developed to

analyze the data. As this software was developed, general

purpose subroutines were also developed. Subroutines to

3-1
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manipulate and retrieve data from the data base management

system are also described.

3.1 Data Entry

Initially data was provided in the form of PSD and time

history plots. A digitizer pad was used to convert the

plots to digitized data. Computer programs (DIGTIME and

DIGPSD) were written to interface with the digitizer pad and

to enter the data into the data base management system.

Both programs function interactively with the digitizer pad

and its operator. A complete functional description of

these programs is provided in the following section.

Over 300 time histories and 1200 PSDs have been digitized

and entered into the data base management system. These

plots were initially digitized by starting at the point

where the trace intersected the yraxis then moving along the

trace in straight-line segments, digitizing points between

each segment. This resulted in data being taken at random

time intervals for time histories and random frequency

intervals for PSDs. The random time intervals are not

considered to be a problem. For the PSDs, however, analysis

efforts would be facilitated if the data was stored at

uniform frequency intervals. The decision was made to

convert this data to 400-line spectra to match the data

reduction format in use at MSFC. Several methods were

considered for making this conversion. The simplest was to

interpolate between digitized points to obtain the necessary

400 points at specific frequency intervals. As shown in

Figure 3-4, this method resulted in inaccuracies in the

magnitudes of the peaks. Several modifications of this

method were considered, but the method that proved to be the

most accurate utilized the following steps:

1. Eliminate duplicated digitized points. Points

that are within one-fourth of a bandwidth and within 10

3-5
percent in magnitude of each other are considered

duplicates.

2. For each of the 400 bandwidths in which there is

one and only one digitized point, assign that point to

that bandwidth.

3. For each of the 400 bandwidths in which there are

two or more digitized points, assign the lowest

frequency point to the next lower bandwidth if it is

unoccupied. Assign the second from the lowest

frequency point within the bandwidth to that bandwidth,

and if there is a third point, assign it to the next

higher bandwidth if it is unoccupied. If the next

lower bandwidth is occupied, then assign the lowest

frequency point in the bandwidth to that bandwidth, and

assign the highest frequency point in that bandwidth to

the next higher bandwidth if it is unoccupied.

Digitized points that cannot be assigned to a bandwidth

. by this method are not used.

4. Use interpolation to obtain points for bandwidths

that remain unoccupied.

This conversion method was implemented in the subroutine

CV400. Figure 3-5 shows a comparison of digitized PSD data

to the converted 400-line spectra.

More recently, a method of entering data into the data base

via magnetic tape has been developed. Time history and PSD

data is transferred from a Norland analyzer to an HP 1000

computer system at MSFC. The data is then put on magnetic

tape, and the tape is read by the computer system at Wyle.

Software was developed to read these tapes and enter the

data directly into the data base management system. This

method of data transfer has proven to be more accurate and

significantly more efficient than the manual digitizing

3-6
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3-9
3.2 Data Filing System

The data base management system is designed to accommodate two types of datas time

histories and PSD or other frequency domain data. Each time history file consists of

two real numbers in each record. The first value in each record is a time and the

second value is the magnitude of the quantity at that time. The data points are in

chronological order. The file may consist of any number of data points (records), but

most of the analysis program presently has an upper limit of 500 points.

Rapid access to time history data is gained through a file-naming structure that is

programmed into the data base management system. Users of the data base

management system and its associated subroutines need not understand the file naming

structure; however, to illustrate the flexibility of the filing system and to assist those

attempting to expand or modify the system, the naming structure is outlined here;

File Name: TXYYYYYY.ZZZ

where

T - All time history files start with the letter T. PSD files

never start with the letter T.

X - May be any letter or number and designates the type of

filter used in reducing the time history data. A description

of the filter corresponding to each letter/number is contained in a directory file named DFILT.

YYYYYY - The 6-digit test number.

ZZZ - A 3-digit channel number. Channel descriptors corresponding to each channel number is contained in a directory file

named DCHN.

3-10
Each PSD file consists of a single real number in each record. The first N records in

the file contain the magnitude at N evenly spaced frequencies. The last 10 records

contain information as follows:

Record Contents

N+l N - the number of magnitude points.

N+2 Composite on plots. *

N+3 Composite computed from digitized data.

N+4 Composite computed from data after being converted to N discrete

points.*

N+5 Number of digitized points that could not be used in the conversion to

N discrete points.*

N+6 Time slice.

N+7 Maximum frequency.

N+8 Spare.

N+9 Spare.

N+10 Spare.

The number of discrete points, N, may be any value, but most of the analysis programs

currently have an upper limit of 512.

Access to PSD data files is gained through a file-naming structure similar to that used

by the time histories. PSD files are named as follows:

File name: XXYYYYYY.ZZZ

where

XX

YYYYYY

ZZZ

- is a single letter followed by a single number. The letters

A-S and U-Z and numbers 0-9 are used. The letter T is

reserved for time histories. This letter combination designates the maximum frequency and time slice of the PSD

contained in that file. The time slice and maximum

frequency corresponding to each XX is found in a directory

file named DPSD.

- The 6-digit test number.

- A 3-digit channel number. Channel descriptors corresponding to each channel number is contained in a directory file

named DCHN.

* Applies only to data obtained by digitizing plots.

3-11
3-3 Directory Files . .

A total of four directory files are used by the data base management system. Three of

these files—DFILT, DCHN, and DPSD—have already been mentioned in conjunction

with the file-naming structure. A fourth file, named TDIR, contains the engine number,

HPOP number, HPFP number, and the test date associated with each test number.

Since the use of these directory files is programmed into the data base management

system, the user need not be concerned with their use. To develop new programs,

however, it may be necessary to know the format of the files. The format of each

directory file is:

TDIR - The file TDIR contains one record for each test number. Each record

has the following format:

Column Contents

1-6 Test number

8-16 Test date (YR:MO:DY)

18-26 Engine number

28-36 HPFP number

38-46 HPOP number

DCHN - The file DCHN contains a record for each channel descriptor. The

position of the channel descriptor (i.e., record number) is the channel

numbers. NOTE: Record must not be deleted from or inserted into

this file. Each record has the following format:

Column Contents

1-40 Channel descriptor

DFILT - The file DFILT contains a record for each filter description. Each

record has the following format:

Column Contents

1 Unique letter or number for filter description

3-15 Filter description

DPSD - The file PSD contains one record for each PSD in the data base. The

format of each record is as follows:

Column Contents

1-6 Test number

8-10 Slice code (letter number combination used in naming PSD

files)

12-15 Channel number (must include high order zeros)

16-29 Slice time

31-44 Maximum frequency

3-12
3.4

Subroutines that have been developed for use with the SSME data base are stored in

FORTRAN code in a file named MSFCSUBS.FTN. A file named MSFCSUBS.OBS

contains the assembly code for these subroutines, which are ready for use when

establishing a program.

To use these subroutines, simply call them in the program as required. The subroutine

source code need not be included in the program. The following is a description of the

subroutines included in MSFCSUBS.FTN.

Subroutine SCHN

Purpose: Search the channel descriptor file DCHN for a given channel descriptor and return with the corresponding channel number.

Subroutines and functions used: None.

Logical units used: DCHN is opened to LU 14 in SRO mode and closed before

return. Error .messages are returned as LU 11, which must be assigned before the

call.

Usage: Call SCHN (ICH, CH, ISTAT)

ICH - ASCII representation of channel descriptor in 10A4 format. ICH

must be dimensioned in the main program to be 10 words long.

CH - ASCII representation of the channel number in A3 format.

ISTAT - Status on return: 0 = normal return; -1 = unable to find given

channel descriptor—the message "CHANNEL DESCRIPTOR NOT

FOUND" outputted to LU 11.

Errors:

Open Error - An error in opening DCHN results in the message "OPEN

ERROR XXX ON DCHN" being outputted to LU 11 where XXX is the open

error code.

3-13
Code Meaning

0 No error; requested function complete.

1 Illegal function.

2 LU error; illegal LU.

3 Volume error; no such volume.

4 Name error; no such name on given volume.

5 Size error; no room on disc for data or index block.

6 Protect error; mismatch on protection keys.

7 Privilege error; requested privilege may not be granted.

8 Buffer error; no room for FCB or buffer.

9 Assignment error; LU already assigned or off-line.

10 File descriptor syntax error.

12 Attempt to assign a trap generating device.

128-255 I/O error.

An open error results in the program being stopped.

Close Error: An error in closing DCHN results in the message "CLOSE

ERROR XXX ON DCHN" being outputted to LU 11 where XXX is the close

error code.

Code Meaning

0 No error; requested function complete.

2 LU error.

9 Assignment error; LU not assigned.

128-255 I/O error.

A close error results in the program being stopped.

Read Error: A read error results in the message "READ ERROR ON SCHN"

being outputted to LU 11 and the program is stopped.

Subroutine SPSD

Purpose: Search the PSD directory file DPSD of a given test number,

channel number, slice time, and maximum frequency, and return

with the slice code.

Subroutines and functions used: None.

Logical units used: The file DPSD is opened to LU 13 in SRO mode and closed

before return. Error messages as outputted to LU 11, which must be assigned

before the call.

Usage: Call SPSD (TEST, CH, SLICE, FREQM, ISLICE, ISTAT).

3-14
TEST - ASCII representation of the 6-digit test number in A4.A2

format. TEST must be dimensioned at least two words long.

CH - ASCII representation of the channel number in A3 format.

SLICE - Slice time (real variable).

FREQM - Maximum frequency (real variable).

ISLICE - ASCII representation of the slice code on return in A2

format.

ISTAT - Status on return: 0 = normal return; -1 = entry in DPSD

matching request was not found.

Errors:

Open Error - An error in opening DPSD results in the message "OPEN

ERROR XXX ON DPSD" being outputted to LU 11 where XXX is the open

error code.

Code Meaning

0 No error; requested function complete.

1 Illegal function.

2 LU error; illegal LU.

3 Volume error; no such volume.

4 Name error; no such name on given volume.

5 Size error; no room on disc for data or index block.

6 Protect error; mismatch on protection keys.

7 Privilege error; requested privilege may not be granted.

8 Buffer error; no room for FCB or buffer.

9 Assignment error; LU already assigned or off-line.

10 File descriptor syntax error.

12 Attempt to assign a trap generating device.

128-255 I/O error.

An open error results in the program being stopped.

Close Error: An error in closing DPSD results in the message "CLOSE

ERROR XXX ON DPSD" being outputted to LU 11 where XXX is the close

error code.

Code Meaning

0 No error; requested function complete.

2 LU error.

9 Assignment error; LU not assigned.

128-255 I/O error.

3-15
A close error results in the program being stopped.

Read Error: A read error results in the message "READ ERROR ON SPSD"

being outputted to LU 11 and the program is stopped.

Subroutine DSORT

Purpose: Sort vectors X and Y in descending order in X.

Subroutines and Function Used: None.

Logical Units Used: None.

Usage: CALL DSORT (X, Y, LEN)

X - REAL*4 vector.

Y - REAL*4 vector.

LEN - INT*4 length of vectors X and Y.

Errors: None.

Subroutine PEAK

Purpose: Find the peaks in a set of data and return with the X and Y values of

each peak.

Subroutines Used: None.

Logical Units Used: None.

Usage: Call PEAK (X, Y, LEN, XP, YP, LENP).

X - REAL*4 X values in descending order.

Y - REAL*4 Y values.

LEN - INT*4 length of X and Y.

XP - REAL*4 X values of the peaks on return. XP must be

dimensioned in calling program at least LEN/2 words long.

YP - REAL*4 Y values of the peaks on return. YP must be

dimensioned in the calling program at least LEN/2 words

long.

LENP - INT*4 number of peaks found.

3-16
Errors: None.

Subroutine STDIR

Purpose: Search the test number directory TDIR for a given combination of test

number, test date, engine number, HPFP numbr, and HPOP number.

Any parameter(s) may be a "DON'T CARE" by calling the subroutine

with blanks in that field. On return, all fields will be filled if search is

successful. The subroutine may be called repeatedly to find all entries

in TDIR that satisfy the request.

Subroutines and Functions Called: None.

Logical Units Used: The file TDIR is opened to LU 13 the first time the

subroutine is called and is closed when a call results in an unsuccessful search.

Error messages are outputted on LU 11, which must be assigned before the call.

Usage: Call STDIR (TEST, DATE, ENG, HPFP, HPOP, ISTAT).

TEST - ASCII representation of the 6-digit test number in A4.A2

format.

DATE - ASCH representation of the test date (MO:DY:YR).'

ENG - ASCII representation of the engine number in 2A4.A2

format.

HPFP - ASCII representation of the HPFP number in 2A4.A2

format.

HPOP - ASCII representation of the HPOP number in 2A4.A2

format.

ISTAT - Call status:

On first call - ISTAT not equal 0.

Call to continue search - ISTAT equal 0.

On successful return - ISTAT equal 1.

On unsuccessful return - ISTAT equal 0.

On file read error - ISTAT equal 1.

3-17
Page Intentionally Left Blank
Errors:

Open Error - An error in opening TDIR results in the message "OPEN

ERROR NO XXX" being outputted to LU 11 where XXX is the open error

code.

Code Meaning

0 No error; requested function complete.

1 Illegal function.

2 LU error; illegal LU.

3 Volume error; no such volume.

4 Name error; no such name on given volume.

5 Size error; no room on disc for data or index block.

6 Protect error; mismatch on protection keys.

7 Privilege error; requested privilege may not be granted.

8 Buffer error; no room for FCB or buffer.

9 Assignment error; LU already assigned or off-line.

10 File descriptor syntax error.

12 Attempt to assign a trap generating device.

128-255 I/O error.

An open error results in the program being stopped.

Subroutine RDTH

Purpose: Read the time history file specified by test number, filter code, and

channel number, and return with the contents.

Subroutines and Functions Used: None.

Logical Units Used: The specified time history file is opened to LU 12 and closed

before return error messages are outputted to LU 11, which must be assigned

before the call.

Usage: Call RDTH (TEST, CH, IFLT, TIME, MAG, LEN, 1ST AT).

TEST - ASCII representation of the test number in A4.A2 format.

CH - ASCII representation of the channel number in A3 format.

IFLT - ASCII representation of the filter code in Al format.

TIME - REAL*4 time values on return.

MAG - REAL*4 magnitude values on return

LEN - Dimension of vectors TIME and MAG on CALL number of

data points read on return.

3-19
1ST AT - 0 = Normal return

-1 = Number of data points greater the LEN at CALL

1 = Illegal function

2 = LU error; illegal LU

3 = Volume error; no such volume

4 = Name error; no such mane on given volume

5 = Size error; no room on disc for data or index block

6 = Protect error; mismatch on protection keys

7 = Privilege error; requested privilege may not be granted

8 = Buffer error; no room for FCB or buffer

9 = Assignment error; LU already assigned or off-line

11 = File descriptor syntax error

12 = Attempt to assign a trap generating device

128-255 = I/O error

Errors:

Read Error - A read error results in the message "Read Error on File XXX"

being outputted to LU 11 where XXX is the file name being read.

Subroutine ERROR

Purpose: Output an error message on LV11 in the form:

Error message ISTAT = 10

Subroutines and Functions Used: None.

Logical Units Used: The message is outputted to LU 11, which must be assigned

before the call.

Usage: Call ERROR (MESG, ISTAT).

MESG - May be a 1X5 array with ASCII representation of the

message or the message may be placed in the call CALL

ERROR ("MESSAGE GOES HERE: ISTAT) the message

must be 20 characters long including blanks ISTAT - INT*4

variable or constant to be outputted. Example: ISTAT =

10; IF (ISTAT.NE.O) CALL ERROR ("THIS IS A SAMPLE '

ISTAT) will result in the following message being outputted

to LU 11: THIS IS A SAMPLE ISTAT = 10.

3-20
Errors: None.

Subroutine PROMPT

Purpose: Output a message to LU11.

Usage: Call PROMPT(TEXT)

TEST - Message is in the form "EXAMPLE MESSAGE!" the message may be any length but must end with a !. Example:

Call PROMPT ("EXAMPLE MESSAGE!") result in the following being outputted to LU 11: EXAMPLE MESSAGE!.

Errors: None.

Subroutine INTERP

Purpose: Interpolate between data points.

Usage CALL INTERP (X, Y, XX YY, SLOPE, LEN).

X - REAL*4 array containing x data points.

Y - REAL*4 array containing y data points.

XX - REAL*4 scalar the x value for which a y value is to be

computed.

YY - REAL*4 scalar y value found to correspond to given x

value.

SLOPE - REAL*4 scalar slope at XX.

LEN - The length of the vectors X and y.

Errors: None.

Subroutine RDPSD

Purpose: Read the contents of a PSD data file and put frequency values in X

and magnitudes in Y.

Subroutines and Function Called: None.

3-21
Logical Units Used: The PSD data file is opened to LU 12 and closed before the

return usage: Call RDPSD (TEST, CH, ISLICE, X, Y, COMP, LEN, ISTAT)

TEST - Test number in A4-A2 format.

CH - Channel number in A3 format.

ISLICE - Slice code in A2 format.

X - REAL*4 any containing frequency value on return must be

dimensioned at least LEN words long in calling program.

Y - REAL*4 array containing magnitude values on return must

be dimensioned at least LEN+10 words long in calling

program. On return:

Y(LEN+1) = LEN

Y(LEN+2) = composite on plots

Y(LEN+3) = composite computed from digitized data

Y(LEN+4) = composite computed from discrete spectra

data

Y(LEN+5) = number digitized points not assigned during

conversion to discrete spectra

Y(LEN+6) = time slice

Y(LEN+8)-Y(LEN+10) = spare

LEN - Dimension of X at call and number of data points read on

return.

ISTAT - Call status on return

-625 to -755 I/O error at close

-509 Assignment error; LU not assigned at close

-502 LU error at close

-3 LEN check failed

-2 Data exceed dimension of X

-1 Read error

0 Normal return

1 Illegal function

2 LU error; illegal LU

3 Volume error; no such volume

3-22
4 Name error; no such name on given volume

5 Size error; no room on disc for data or index block

6 Protect error; mismatch on protection keys

7 Privilege error; requested privilege may not be granted

8 Buffer error; no room for FCB or buffer

9 Assignment error; LU already assigned or off-line

11 File descriptor syntax error

12 Attempt to assign a trap generating device

128-255 I/O error

Errors: None.

Subroutine SPSD1

Purpose: Search the PSD directory file for a given test number and channel

number, and return with the time slice maximum frequency and slice

code. The subroutine can be called repeatedly to find all entries that

satisfy the request.

Subroutines and Function Called: None.

Logical Unit Used: The DPSD file is opened to LU 13 and remains open until a

search is unsuccessful. Error messages are outputted on LU 11, which must be

assigned before the call.

Subroutine CV400

Purpose: Converts digitized PSD data taken at nonuniform frequency intervals

to 400 data points at constant frequency intervals.

3-23
3.5 Programs

Both data base management and data analysis programs have been written and used

with the SSME data. The data base management program includes programs for

entering new data, for summarizing the contents of the data base, and for removing

erroneous or incorrectly identified data. Data analysis programs include programs for

plotting data and computing statistcal data summaries. The following is a brief

summary of the programs that have been completed to date.

Program name: DIGTIME

Purpose: Used in digitizing time history plots.

Method: The program asks the operator to enter the filter description, test

number, and channel descriptor for the plot to be digitized. It then

checks the TDIR directory file to see if the test number has already

been entered. If the entry is found, the test date, engine number,

HPOP number, and HPFP number is displayed for verification. If no

entry is found, the operator is asked to enter the test date, engine

number, HPOP number, and HPFP number, and this information is

entered into TDIR.

The DCHN directory file is then searched for the channel descriptor

and to obtain the corresponding channel number. If the channel

descriptor is not found, then the program asks if it is a new channel

descriptor. If the operator responds with "yes", then an entry is made

in DCHN assigning to that channel descriptor a channel number. If the

response is "no" then the operator is given the opportunity to reenter

the channel descriptor.

The program then asks the operator to enter the X and Y values at the

origin of the plot to be digitized and the values of one other point on

the x-axis and one on the y-axis. It then instructs the operator to

digitize these points using the digitizer pad. From this information

the program determines the orientation of the plot on the digitizer pad
and the scaling parameter needed to convert the output of the

digitizer pad into engineering units. The operator digitizes the plot in

as many straight-line segments as is necessary to produce an accurate

digital image. When the digitizing is complete, the program creates a

file, using the naming structure described previously, and enters the

data in that file, completing the process of entering a time history

into the data base.

Program name: DIGPSD

Purpose: Used in digitizing PSD plots.

Method: The DIGPSD program starts by asking the operator for. the test number

and channel descriptor—much like DIGTIME—and, if necessary, makes

the same search of entries in the TDIR and DCHN directory files. In

addition, it asks for the time slice and maximum frequency of the PSD

to be digitized. With this information, it searches the DPSD directory

file to find a unique slice code for the plot to be digitized. The slice

code, test number, and channel number are used to name the data file

to be created. The program asks the operator to digitize three points

on the axes of the plot from which it determines the plot orientation

and scaling factors. The program assumes that the magnitude axis is

iggortthm and the frequency axis is linear. After the plot is digitized,

the program converts the data to 400 magnitude points at uniform

frequency intervals. These points are stored in a data file named using

the file naming structure described previously. The program asks the

operator to enter the composite value. It also computes the composite

from the digitized data and the data after being converted to 400

points. All three composite values are entered into the data file, and

the computed values are displayed so the operator can check the

digitization. An entry is then made in the DPSD directory file,

completing the data entry process.

Program name: REMTH

Purpose: Remove time history data from the data base.

3-25
.Method: The program asks for the test number, filter description, and channel

descriptor of the time history to be removed. It then reads the

corresponding time history file and displays the minimum and maximum values of magnitude and time as well as the number of data

points in the file. The operator is then asked, by the program, if this

is the file to be removed. If the operator's response is yes, then the

file is removed; otherwise it remains unchanged.

Program name: REMPSD

Purpose: Remove PSD data from the data base.

Method: The program asks the operator to enter the test number, channel

descriptor, time slice, and maximum frequency of the PSD data to be

removed. It then searches the DPSD directory file for the given

combination of test number, channel descriptor, time slice, and

maximum frequency to obtain the slice code. The data file is then

read. The minimum and maximum magnitudes and composite value is

displayed. The operator is then asked if this is the PSD data to be

removed. A response of yes by the operator results in the data file

being deleted and the corresponding entry in the DPSD directory file

being removed. Any other response results in no action being taken.

Program name: LSTTH

Purpose: List the test number and channel descriptor of all time history data in

the data base.

Method: The program uses a system command to obtain a list of all the time

history file names from which the test numbers and channel numbers

are obtained. The DCHN directory file is read to obtain the channel

descriptor corresponding to each channel number. The test number

and channel descriptor for each data file is then printed.

e

Program name: LSTPSD

Purpose: List the test number, time slice, maximum frequency, and channel

descriptor of each PSD in the data base.

3-26
Method: The DPSD directory file is read to obtain the test number, time slice,

maximum frequency, and channel number of each PSD in the data

base. The DCHN directory file is used to find the channel descriptor

that corresponds to each channel number. The test number, time

slice, maximum frequency, and channel descriptor is then printed.

Program name: PLOTTH

Purpose: Plot time history data.

Method: The program asks for the test number filter description and channel

descriptor. The channel number corresponding to the given channel

descriptor is found by searching the DCHN directory file. The data

file is read and the data is plotted on a Tektronix graphics terminal

from which a hard copy may be produced. The plot includes scaled and

labeled axes and a title. The title consists of the test number, channel

descriptor, and filter description.

Program name: PLOTPSD

Purpose: Plot PSD data.

Method: The program asks the operator to enter the test number, channel

descriptor, time slice, and maximum frequency of the PSD data to be

plotted. The program searches the DCHN directory file to find the

channel number and the DPSD directory file for the slice code. The

corresponding data file is read and the data is plotted on a Tektronix

graphics terminal. The axes are scaled and labeled, and a title

consisting of the test number, channel descriptor, and slice time is

included on the plot.

Program name: STATPSD

Purpose: For a set of PSDs specified by engine number, HPFP number, HPOP

number (any or all may be "don't care"), maximum frequency, channel

descriptor, and thrust range, calculates the following as a function of

frequency.

- Mean

3-27
- Standard deviation

- rms

- Third central moment

- Fourth central moment

- Minimum value

- Maximum value

- Range

Method: The program asks the operator to enter the engine number, HPOP

number, and HPFP number of the data to be considered. Entries that

are left blank are assumed to be "don't care." The program searches

the TDIR directory file to find the test numbers that correspond to the

given combination of engine number, HPOP number, and HPFP number. The DCHN directory file is searched to find the channel number

corresponding to the channel descriptor. The DPSD file is searched to

find slice codes and time slices that correspond to the given channel

number, maximum frequency, and each test number. For each entry

found, the corresponding thrust time history is read to find the thrust

at that time slice. If the thrust is within the specified range, then the

PSD data file is read and included in the statistical calculations. Once

all the PSDs that correspond to the given set of requirements have

been found, the data is outputted to a file in a format to be used by

other programs. This output file also includes information needed to

title and label the axis of plots.

Program name: EXPSD

Purpose: For each PSD as specified by engine number, HPFP number, HPOP

number (any or all may be "don't care"), maximum frequency, and

channel descriptor, finds the magnitude and frequency of the N largest

peaks, where N is specified by the operator. Also, finds the thrust

that corresponds with each PSD considered. The output of this

program can be used to plot the magnitude or frequency of a given

peak as a function of thrust.

3-28
Method: PSD files that satisfy the specification are found by using the method

described for STATPSD. The peaks in each PSD are found by

examining the slope of the PSD as a function of frequency. When the

slope changes from positive to negative, that point is stored as a peak.

When all the peaks in a PSD are found, they are sorted by magnitude,

and the N largest peaks are reported to an output file together with

the thrust corresponding to that PSD. This process is repeated for

each PSD that satifies the given specification.

Program name: PLOT

Purpose: Plot the contents of a file generated by analysis programs such as

STATPSD and EXPSD.

Method: The data file to be plotted is specified by name when the program is

started. From this file, the program reads a description of each

channel of data that the file contains. These descriptions are

displayed and the operator is asked to enter a number corresponding to

the channel to be plotted on the x-axis and for the channel to be

plotted on the y-axis. The operator is asked to specify linear or

logarithmic scaling for each axis. The choice of line plot or dots is

given. If line plot is specified, the option of sorting the data by xvalues is given. The plots are titled and axes are labeled using the

information provided by the data file.

Program name: LOADTHST

Purpose: Enter thrust profile or rms time history data into the data base via 9-

track magnetic tape.

Method: The program reads the test number, engine number, HPOP number,

HPFP number, and test data from the tape. The TDIR file is checked

for the test number. If the test number is not found, the test number,

HPOP number and HPFP number are added to the file. The program

then reads the time history from the tape and looks to see whether the

information is already in the data base. If it is not in the data base,

then the history read from the tape is added to the data base.

3-29
Program name: LOADPSD

Purpose: Enter PSD data into the data base.

Method: The program reads the test number channel descriptor and time slice

from the tape. It then checks the TDIR file to see if that test

number is present. If not found, the program prints an error

message and proceeds to the next data set on the tape. The

program then checks the DPSD file for a data file with the same

test number, channel descriptor, and time slice. If one is

found, the program proceeds to the next data set on the tape;

if no match is found, a slice code is obtained and -the PSD data

is transferred from tape to the data base management system.

A flow diagram of the data base management and analysis software is

illustrated in Figure 3-6.

A computer listing of the programs and subroutines discussed in this

section is provided on the following pages. This code is operational

on PC/compatible systems. The routines are also available on disc for

efficient transfer to MSFC computers.

3-30
Read time

history and

PSD data Into

data bank

Octet* erroneous

data from

data bank

Entar test Information |

on computer prompts

I Enter test Information

I on eomputar prompts

Entar toat

Information

oneomputar

prompts

SSME data baaa

management and

analysis software

library

Raeall and

plot tlma history

and PSD data

Entar data

salactlon

conatralnta

on eomputar

prompts

En

•rn

op<

P«

Perform statlatlcal -

analysis on data

and plot rasulta

tar

glna

•rating

ramatars

Mean

-Standard deviation

-fine

-Third eantral moment

-Fourth eantral momant

-Minimum value

-Maximum value (envelope)

-Range

Calculate

nondlmenalonallzad

data and plot

FIGURE 3-6. SSME DATA BASE MANAGEMENT AND ANALYSIS

SOFTWARE OPERATIONAL SEQUENCE AND CAPABILITIES

3-31
TABLE 3-1

DATA BASE ANALYSIS PROGRAM LISTING

Page 1

O1-23-86

O9:3£:46

D Line* 1 7 Microsoft FORTRAN77 V3.SO OS/84

1 *DEBUG

£ C MflIN PROGRflM TO CflLCULflTE STflTISTICS ON PSD'S

3 C THE PROGRflM SEflRCHES THE DflTfl BflSE FOR fl GIVEN COMBINATION

AC OF ENGINE NO., HPFP NO., HPOP NO. (flNY OR flLL MflY BE "DON'T CflRE")

5 C CHflNNEL DESCRIPTOR AND THRUST RANGE.

6 C

7 C THE MEAN,STANDARD DEVIATION,THIRD CENTRAL MOMENT,FOURTH CENTRAL

8 C MOMENT, RMS, MINIMUM VALUE, MAX IMUN VALUE AND RANGE ORE CflLCULflTED

3 C

10 C OUTPUT DflTfl IS WRITTEN ON LU 7 (ISO CHPlRflCTORS)

11 C THE GIVEN ENGINE NUMBER, HPFP NUMBER flND HPOP NUMBER, TEST NUMBERS

1£ C PSD'S flND QUflNTITY OF PSD FROM EflCH TEST USED flRE OUT PUT ON LU 5

13 C

14 C

15 C

16 CHARflCTER TEST*6, DflTE*8, ENG*1O, HPFP»10, HPOP*10

17 CHflRflCTER TESTX*6, DflTEX*8, ENGX*1O, HPFPX*1O,HPOPX*1O

18 CHflRflCTER ICH*£O,CH*3 ,

19 REflL TIME(SOO),MflG(SOO), X(5OO) , Y(5OO)

SO REflL XXFOUR(SOO)

21 REflL XXTOT(aOO),XXMIN(SOO),XXMflX(SOO),XXSQR(SOO), XXCUB<£OO)

££ OPEN <7,FILE='DflTfl.PRT')

53 OPEN (5, FILE='STflTS. DflT' )

54 C

55 C INITIALIZE VflRIflBLES

£6 C

£7 DO 5 J=1,£OO

1 S3 XXTOT(J)=p.O

1 £9 XXMIN(J)=1.OE3£

1 3O XXMflX(J)=-1.0E3£

1 31 XXCUB(J>=0.0 ,

1 3£ XXFOUR(J)=0.0

1 33 5 XXSOR(J)=O.0

34 ISTAT=Q

35 ISTflTT=O

36 SO FORMflT (ftlO)

37 SS FORMflT (' 'ftlO)

38 3O FORMflT (fl£O)

39 TEST=' '

40 1O DflTE=' »

41 C

4£ C flSK FOR ENGINE NO., HPFP NO. , HPOP NO.

43 C

44 1 WRITE <*,4O)

45 40 FORMflT (' ENTER ENGINE NO.')

46 REflD (*,£O)ENG

47 IF<ENG.EQ.'STOP')STOP

•48 WRITE <*,5O)

49 5O FORMflT (' ENTER HPFP NO. ')

50 REflD <*,SO)HPFP

51 WRITE <*,6O>

5£ 6O FORMflT C ENTER HPOP NO. ' )

53 READ (*,£O)HPOP

54 C

55 C PSK ^OR CHflNNEL DESCRIPTOR AND FI,\D CHANNEL (MO.

56 C 3-32
58

53

WKi I C. <*, •* I ' tN I t.P< UI-IHININtL. UC.5JI-K J. H I

REflD <*,3O)ICH

CflLL SCHN(ICH,CH,ISTflT)

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D Line* 1

60

61

6£

63 C

64 C

65 C

66

67

68

69 21

7O

71 C

7£ C

73 C

74

75

76

77

78 C

79 C

80 C

81

82 64

83 C

84 C

85 C

86

87 65

88 C

89 C

9O C

91

9£ 66

93

94

95

96

97 C

98 C

99 C

10O

101

1O£

103 67

104 68

105 69

1O6

1O7 C

108 C

iog c

1 1 0 70

11 I

iia 71

113

114

115 7.E.

7 Microsoft FORTRON77 V3. £O Oc

I F ( I STftT. EQ. - 1 ) GO TO 1

IF < ISTflT. NE.O) CflLL ERROR C IN ICHN ', ISTflT)

CflLL DPSDTEMP<TESTX,CH, ISTftT)

flSK FOR MflXIMUM FREQUENCY

WRITE <*,*>' ENTER MflX. FREQUENCY."

REflD <*,£1)FREQM

flFREQS=FREQM/4OO.

FORMfiT(G13. 6)

FREQL=FREQM

ftSK FOR THRUST RPNGE

WRITE <*,*>' ENTER LOWER THRUST LIMIT!'

REflD <*,£1)THRL

WRITE <*,*>' ENTER UPPER THRUST LIMIT!'

REflD (*, £1)THRH

WRITE NUMBER OF OUT PUT COLUMNS TO LU 7 (THIS CflSE 9)

WRITE(7,64)

FORMflTC 0009')

WRITE HEflDER

WRITE (7, 65) ICH, THRL, THRH

FORMflTC '010, 5X, 'THRUST RflNGE = ' F5. 1,' - ' F5. 1)

WRITE OUTPUT COLUMN ID'S

WRITE<7, 66)

FORMflTC FREQUENCY HZ'/' MEflN P**£/HZ'

I/' STflNDflRD DWIftTION P**2/HZ' /' THIRD CENTRflL MOMENT P**6/HZ'

4/' FOURTH CENTRflL MOMENT P*#8/HZ'

£/' RMS P**£/HZ'/' MINIMUM VflLUE P**2/HZ'

3/' MflXIMUM VflLUE P**£/HZ' /' RflNGE P**£/HZ' )

WRITE ENGINE NO. , HPFP NO. , HPOP NO. COMBO TO LU 5

WRITE(5, 67)ENG

WRITE (5, 68) HPFP

WRITE (5, 69) HPOP

FORMflTC ENGINE NO. = 'fllO)

FORMflTC HPFP NO. = 'fllO)

FORMflTC HPOP NO. = 'fllO//' TEST NO. QTY. ' )

JK=O

SEflRCH FOR TEST NO. FOR GIVEN COMBO

CONTINUE

T£STX=TEST

DflTEX=DflTE

ENGX=ENG

upopx=HPOP

HPFPX=HPFP
o i Ui. n ^ i c.s ( A, UH I C.A, ciMLJA, nHr PA, rlHUPA, io i H I i

117 IF (ISTATT.LT.Q) GO TO 39O

118 IF (ISTATT. EQ.O) GO TO 3OO

Page 3

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09:3£:46

D Line* 1 7 Microsoft FORTRAN77 V3. 20 02/84

119 NCOUT=0

120 LENT=10O

121 C

122 C READ THRUST DATA

123 C

124 C CALL RDTH(TESTX,'OO1 ','1 ',TIME,MAG,LENT, ISTAT)

125 C IF(ISTAT. EQ.4)GO TO 11OO

126 C IF(ISTAT.NE.O)CALL ERRORCIN RDTH ',ISTAT)

127 C

128 ISTAT1=1

129 C

130 C SEARCH FOR PSD DATA

131 C

132 100 CALL SPSD1(TESTX,CH,SLICE,FREQ,ISLICE,ISTAT1,THRUST)

133 C

134 C IF FILE FOUND GO TO 110

135 C

136 IF<ISTAT1.NE.-1)GO TO 11O

137 C

138 C IF NO MORE FOUND WRITE TEST NO. AND QUANTITY OF PSD'S FOUND

139 C FOR THAT TEST NO... GET NEW TEST NO.

140 C

141 IF<NCOUT.EQ.O)GO TO 70

142 WRITE<»,1O5)TESTX,NCOUT

143 WRITE(5,1O5)TESTX,NCOUT

144 1O5 FORMATC 'A6,2X,I3>

145 GO TO 7O

146 C

147 HO CONTINUE

148 C

149 C IF OUT SIDE THRUST RANGE GET NEW PSD

150 C

151 IF((THRUST.LT.THRL).OR.(THRUST.GT.THRH))GO TO 1OO

152 C

153 C IF PSD DOES NOT COVER FREQUENCY RANGE GET NEW PSD

154 C

155 IF (FREQ. NE. FREQDGO TO 10O

156 NCOUT=NCOUT+1

157 LEN=500

158 C

159 C READ PSD DATA FILE

160 C

161 CALL RDPSD(TESTX,CH,ISLICE,X,Y,COM,LEN,ISTAT)

162 IF (ISTAT. NE. O) CALL ERRORCIN RDPSD ', ISTAT)

163 JK=JK+1

164 DO 2OO J=1,4OO

1 165 FREQZ=(J-1)*AFREQS

1 166 C

1 167 C ACCUMULATE DATA FOR 4OO FREQUENCIES BETWEEN O AND MAX FREQUENCY

1 16S C

1 163 XXTOT(J)=XXTOT(J)+Y(J)

170 XXMIIM(J)=AMIN1 (XXMIN(J), Y(J ) )

1 171 XXMAX(J)=HMAX1(XXMAX(J),V(J) )

1 172 XXSQR(J)=XXSQR(J)+Y<J>** 2

I 173 XXFOUR(J)=XXFOUR(J)+Y(J>** 4

1 174 XXCUB(J)=XXCUB(J)+Y(J)**3
1 /O

176

177 300

I J-iMUC.

GO TO 1OO

CONTINUE

D

1

1

1

1

1

1

1

1

1

1

1

1

1

Line*

178

179

ISO

181

182

183

184

185

186

187

188

189

190

191

192

193

194

195

196

197

198

199

20O

201

2O2

203

2O4

205

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1

C

c

C

3O1

4OO

31O

32O

990

991

110O

1110

Name Type

Microsoft

Page 4

01-23-86

09:32:46

FORTRAN77 V3.20 O2/S4

IF(JK. 6T.O)BO TO 301

WRITE <*,*)' NONE FOUND!'

STOP

CALCULATE AND OUTPUT STATISTICS

DO 4OO J=l,40O

F REQS=(J-1)*AFREQS

XMEAN=XXTOT<J>/JK

XM2=XXSQR(J)/JK

VAR=XM2-XMEAN**2

STD=SQRT<ABS<VAR)>

RMS=SQRT<XM2)

RANGE=XXMAX(J)-XXMIN(J)

XM3=XXCUB(J)/JK

XM4=XXFOUR<J)/JK

XU3=XM3-3.*XMEAN*XM2-2. *XMEAN**3

XU4=XM4-4. *XM3*XMEAN+6. *XM2*XMEAN**2-3. *XMEAN#*4

WRITE(7,310)FREQS,XMEflN,VflR,STD,XU3,RMS,XXMIN(J),XXMftX(J>

1,RANGE

FORMftTC '9G13. 6)

WRITE(5,320)JK

FORMftTC TOTflL ' 13)

STOP

WRITE (#,991)

FORMflT (' FILE REflD ERROR')

STOP

WRITE(*,111O)TESTX

FORMftTC THRUST DftTfi FOR TEST NO. ' ft4, fl2

1' NOT IN DflTfl BflSE')

GO TO 7O

END

Offset P Class

ABS

AFREOS

AMAX1

AMIN1

CH

COM

DATE

DATEX

ENG

ENGX

FREQ

FREQL

FREQM

FREQS

FREQZ

1-fCi-p

HPFPX

REAL

CHAR*3

REAL

CHAR*8

CHAR*8

CHAR* 10

CHAR*1O

REAL

REAL

REAL

REAL

REAL

CHAR-* 10

CHAR* 1C

HPOPX CHAR*10

ISuICE INTEGER*4

13000

12986

13640

12859

13556

12891

13564

13610

13O12

12996

13648

13644

12924

135S4

12956

13574

12966

1 3fo 14

INTRINSIC

INTRINSIC

INTRINSIC
i t> ; H i

ISTAT1

ISTATT

INTEGER*4

INTEGER*4

13602

15824

D Line*

J

JK

LEN

LENT

MAG

NCOUT

RANGE

RMS

SLICE

SDRT

STD

TEST

TESTX

THRH

THRL

THRUST

TIME

VAR

X

XM2

XM3

XM4

XMEAN

XU3

XU4

XXCUB

XXFOUR

XXMAX

XXMIN

XXSQR

XXTOT

Y

1 7

INTEGER*4

INTEGER#4

INTEGER*4

INTEGER*4

REAL

INTEGER*4

REAL

REAL

REAL

REAL

CHftR*6

CHftR*6

REAL

REAL

REAL

REAL

REAL

REAL

REAL

REAL

REAL

REAL

REAL

REAL

REAL

REAL

REAL

REAL

REAL

REAL

REAL

Microsoft

Page 5

01-23-86

O9:32:46

FORTRAN77 V3. 20 02/84

12816

13552

13636

13598

1O816

13594

13672

13668

13606

13664

12853

12989

13020

13O16

13618

16

1366O

2O16

13656

13676

13680

13652

13684

13688

10016

6016

9216

7616

8416

6816

4O16

INTRINSIC

210

211

212

213

214

215

216

217

218

219

2£0

2£l

222

2£3

224

2£5

226

C

C*PROG

C

C

C

i

C

C

C i

C

C

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1

1

1

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—' °*? •*

I—wf j.

OOO

7O:

SCHN

PURPOSE: SEARCH THE DESCRIPTOR FILE FOR A GIVEN DESCRIPTOR

AND RETURN THE CHANNEL NUMBER

SUBROUTINE SCHN(ICH,CH,ISTAT)

ICH - DISCRIPTOR (2O CHARACTERS)

CH - CHANNEL NO. (RETURNED)

ISTAT - RETURN STATUS

O-NORMAL

-1-DISCRIPTOR NOT FOUND

CHARACTER ICHY*4

CHARACTER FD14*4,CH*3, ICH*2O, ICHX*20, DMY*1

DATA FD14/'DCHN'/

OPEN(14,FILE=FD14,IOSTAT=ISTAT)

IF(ISTAT.NE.O)GO TO 2O4O

I =O

I = I •+• 1

READ(14,7O3,END=35OO,ERR=10OO)ICHX

FORMAT(A20)

IF(ICHX.NE.ICH) GO ~O 3OOO
£33

£34

IF < I ERR. ME. O)GO TO £O6O

I = H-1OOO

D Line*

£35

£36

£37

£38

£39

£40

£41

£4£

£43

£44

£45

£46

£47

£48

£49

£50

£51

. £5£

£53

£54

£55

£56

£57

1

3O3O

35 OO

3501

360O

701

1OOO

111O

£O4O

£050

£06O

£070

Microsoft FORTRRN77

Page 6

01-33-36

09:32:46

V3.£0 0£/S4

WRITE(ICHY, 3030) I

FORMflTC14)

GO TO 36OO

WRITE(*,3501)

FORMflTC CHANNEL DESCRIPTOR NOT FOUND')

ISTflT=-l

CLOSE(14,IOSTftT=IERR)

IFdERR. NE. 0)GO TO £O6O

RETURN

REflD <ICHY, 701)DMY, CH

FORMflT(fll, fl3)

WRITE <*, 7ODDMY, CH

RETURN

WRIT£<*, 1110)

FORMflTC REflD ERROR ON SCHN' )

STOP

WRITE(*,£O5O)ISTflT

FORMflTC OPEN ERROR '13'ON DCHN» )

STOP

WRITE<*,£07O>IERR

FORMflTC CLOSE ERROR '13' ON DCHN' )

STOP

END

Name

CH

DMY

FD14

•I

ICH

ICHX

ICHY

IERR

ISTflT

Type

CHflR*3

CHflR*!

CHflR*4

INTEGER*4

CHftR#£O

CHflR*£0

CHflR*4

INTEGER*4

INTEGER*4

Offset P Class

4 *

13904

13S£4

13828

O *

1383£

13862

13858

8 *

£58

£59

£60

£61

£6£

£63

£64

£65

£66

£67~

£58

£69

£7O

£71

£72

£73

£74

£75

£76

C*PROG

C

C

C

C NOT '

C

t

1

I

1

S£O i

11

330 i

840 !

SPSD

PURPOSE: SEflRCH THE PSD

VERIFIED

CHflNNEL NO.,TIME

WITH THE SLICE

ON IBM 12/85

DIRECTORY FOR fl

SLICE,flND MflX

CODE

GIVEN TEST NO.

FREQ.- — RETURN

SUBROUTINE SPSD(TEST,CH,SLICE,FREQM,ISLICE,ISTflT)

ChflRflCTER TEST*6,TEST1*6

CHflRflCTER FD13*4

DflTfl FD13 /'DPSD'/

OPEN(13,FILE=FD13, IOST«T=ISTAT>

IF(ISTflT.NE. 0) GO TO 118O

REflD (13, 830, E,MD=86O, ERR=1OOO) TEST1, ISLICE, CHX, SLICE1,

1FREQ

FORMflT(fl6,IX,fi£,IX,fl3,£(1X,G13.6))

IF(TEST.NE.TEST 1)GO TO 8£O

ONTINUE

IF(CHX.NE.CH)GO TO 8£O

IF (SLICE. NE. SLICED GO TO 8£O
£.11 11- \t- Ktb!. !\lt. I- HtUI'U L3U lU

£78 85O CLOSE(13,IOSTAT=IERR)

£79 IFdERR.NE. O)GO TO 2OOO

£8O

£81

£8£

283

£84

£85

£86

£87

£88

£89

£9O

£91

£9£

860

10OO

1110

1180

1130

£000

£010

Name

CH

CHX

FD13

FREQ

FREQM

IERR

ISLICE

ISTAT

SLICE

SLICE1

TEST

TEST1

Type

7

RETURN

ISTAT=-1

60 TO 85O

WRITE(*,1110)

FORMATC READ ERROR IN SPSD' )

STOP

WRITE <*, 119O)ISTAT

FORMAT (' OPEN ERROR NO.

STOP

WRITEC*,£O1O>IERR

FORMATC CLOSE ERROR NO. '13'ON FILE DPSD' )

STOP

END

Page 7

01-£3-86

09:32:46

Microsoft FORTRAN77 V3. £0 02/84-

13,' ON FILE DSPD')

REAL

REAL

CHAR*4

REAL

REAL

INTEGER*4

INTEGER*4

INTEBER*4

REAL

REAL

CHAR*6

CHAR*6

Offset P Class

4 *

14OO6

13996

14O14

1£ *

14O46

16 *

£O *

8 *

14O1O

O *

14OOO

1

1

£

£

£

£

£

£

£

2

S.

£93

£94

£95

£96

£97

£98

£99

30O

3O1

302

3O3

3O4

3O5

306

3O7

308

3O9

31 0

311

312

313

C*PROS DSORT

C

C PURPOSE: SORT X

C NOT VERIFIED ON IBM

C

SUBROUTINE DSORT(X,Y, LEN)

DIMENSION X(1),Y(1)

LM1=LEN-1

DO 1O 1=1,LM1

LEND=LEN-I

DO 10 J=1,LEND

JP1=J+1

IF(X(J).GT. X(JP1) )GO TO 1C)

XTEMP=X (JP1)

YTEMP=Y<JP1)

X(JP1)=X(J)

Y(JP1)=Y<J)

X(J)=XTEMP

Y(J)=YTEMP

10 ' CONTINUE

END

AND Y IN TO DECENDING ORDER IN X

12/85

iMarne

I

J

: YDS

INTEGER*4

INTEGER*4

Offset P Class

14156

14168
JH1

LEN

LEND

IN I

INTEGER*4

INTEGER*4

8 *

14164

D Lir.e# 1 7

LM1 INTEGER*4 14152

X REAL O *

XTEMP REflL 1418O

Y REflL 4 *

YTEMP REflL 14184

Page 8

01-23-86

09:32:46

Microsoft FORTRflN77 V3.20 02/84.

1 •

1

1

1

1

1

1

314

315

316

317

318

319

320

321

322

323

324

325

326

327

328

329

330

331

332

333

334

335

336

337

338

339

C*PROG

C

C NOT

C

<

C

C

C

C 1

C

C

C 1

C

]

1

1

]

*

1

1

10 (

1

i

PEflK

PURPOSE:

VERIFIED

SEflRCH

ON IBM

PSD DflTfl TO

12/85

FIND PEflKS

SUBROUTINE PEflK (X, Y, LEN, XP, YP, LENP)

X - PSD FREQ POINTS

Y - PSD MflG. POINTS

LEN - NUMBER OF DflTfl POINTS

XP - FREQUENCY OF PEflKS

YP - MflGNITUDE OF PEflKS '

LENP - NUMBER OF PEflKS

DIMENSION X(l), Yd), XP<1), YP(1)

LENM1=LEN-1

LENP=0

DO 10 J=2,LENM1

JP1=J+1

JM1=J-1

IF (.NOT. (Y(J)-Y(JMD.GT. O. O) . flND. (Y < J) -Y < JP1) . LT. O. O) ) GO TO 1O

LENP=LENP+1

XP(LENP)=X(J)

YP(LENP)=Y(J)

CONTINUE

RETURN

END

Name

J

JM1

JP1

LEN

LENM1

LENP

X

XP

Y

YP

Type

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

REflL

REflL

REflL

REflL

Offset P Class

14192

14204

14200

8 *

14188

£0 *

O *

12 *

4 *

16 *

340 C

341 CSPROG STDIR

342 C SUBROUTINE STDIR

343 C

344 C PURPOSE: SEflRCH TriE TEST NUMBER DIRECTORY FILE (TDIRJ FOR ft SPECI

345 C COMBINATION OF TEST NUMBER, ENGINE NUMBER,OXIDIZ£R PUMP NUMBER, FUEI

346 C PUMP NUMBER AND TEST DATE

347 C
349

350 C

L. UtDHtDC.

C CALL STDIR(TEST, DATE, ENG, HPFP, HPOP, ISTAT)

D' Line*

351

352

353

354

355

356

357

358

359

36O

361

362

363

364

365

,366

367

368

369

370

371

372

373

374-

375

376

377

378

379

38O

381

382

383

384

385

386

387

388

389

3 9O

391

392

393

394

395

396

397

398

399

4OO

401

4 O2

4O3

4O4

4O5

406

1

C

C

C

C

C

C

C

C

C

C

C

C

C

1

5

6

1O

11

2O

25

3O

4O

50

6O

7O

SO

3O

1 OO

Page 9

01-23-86

O9:32:46

7 Microsoft FORTRAN77 V3.2O 02/84

TEST - TEST NUMBER TO, BE SEARCHED FOR (6* CHACRACTERS)

DATE - TEST DATE TO BE SEARCHED FOR (MO/DY/YR)

ENG - ENGINE NUMBER TO BE SEARCHED FOR (1O CHARACTERS MAX. LEFT

JUSTIFIED)

HPFP - FUEL PUMP NUMBER TO BE SEARCHED FOR (1O CHARACTERS MAX. LEF

JUSTIFIED)

HPOP - OXIDIZER PUMP NUMBER TO BE SEARCHED FOR (1O CHARACTERS MAX.

LEFT JUSTIFIED)

ISTAT - SEARCH RESULTS

1-SEARCH SUCCESSFUL

O - NONE FOUND

-1 - FILE READ ERROR

SUBROUTINE STDIR(TEST,DATE,ENG,HPFP,HPOP, ISTAT)

CHARACTER TEST*6,DATE#8,ENG*1O,HPFP*1O, HPOP*1O

CHARACTER TEST1*6,DATE1*8,ENG1*1O,HPFP1*1O, HPOP1*1O

CHARACTER TESTO*6,DATEO*8,ENGO*1O,HPFPO#1O, HPOPO*1O, FD*4

DATA TESTO,DATEO,ENGO,HPFPO,HPOPO /5*' ' /

DATA FD/'TDIR' /

IF(ISTAT.NE. 0)GO TO 1

LV=10

OPEN(LV,FILE=FD,IOSTAT=ISTAT)

IF (ISTAT.NE.O) GO TO 999

CONTINUE

TEST1='0'

DATE1 = '0»

ENG1 = 'O'

HPFP1='O'

HPQP1='0»

READ(10, 11,END=200,ERR=3OO)TEST1, DATE1,

1ENG1,HPFP1,HPOP1

FORMAT(A6,1X,AS,2X,3(A1O,2X))

CONTINUE

IF(TEST.NE.TESTO) GO TO 3O

CONTINUE

GO TO 4O

CONTINUE

IF(TEST.NE.TEST1) GO TO 10

CONTINUE

IF(DATE.NE.DATEO) GO TO 5O

GO TO 6O

CONTINUE

IF (DATE. NE. DATED GO TO 1O

CONTINUE

IF(ENG.NE.ENGO) GO TO 7O

GO TO SO

CONTINUE

IF(ENG.NE.ENG1) GO TO 1O

CONTINUE

IF (HPFP.NE.HPFPO) GO TO 9O

GO TO 10O

CONTINUE

IF(nPFP.NE.HPFP1) GO TO 1O

CONTINUE

IF(HPOP.NE.HPOPO) GO TO 110

GO TO 12O
H-IJ I 1 IU L-UIM I IIMUC

408 IF(HPOP. NE.HPOP1)

409 12O ISTAT=1

SO TO 1O

Line* 1

41O

411

412 13O

413

414

415

416

417 2OO

418

419

420 300

421

422 399

423 1OOO

424

425

Name

DATE

DATEO

DATE1

ENS

ENGO

ENB1

FD

HPFP

HPFPO

HPFP1

HPOP

HPOPO

HPOP1

IERR

ISTAT

LV

TEST

TESTO

TEST1

Type

Microsoft FORTRAN77

Page 1O

O1-23-86

09:32:46

V3.20 02/84

TEST=TEST1

DATE=DATE1

ENG=ENG1

HPFP=HPFP1

HPOP=HPOP1

RETURN

CLOSE(10,IOSTAT=IERR)

ISTAT=0

RETURN

ISTAT=-1

RETURN

WRITE (*,10OO) ISTAT

FORMAT (' FILE OPEN ERROR

STOP

END

NO. 14)

CHAR*8

CHAR*8

CHAR#8

CHAR*10

CHflR*lO

CHAR*10

CHftR*4

CHftR*lO

CHAR*1O

CHAR*1O

CHflR*lO

CHflR*10

CHAR*1O

INTESER*4

INTEGER*4

INTEGER*4

CHftR*6

CHflR*6

CHftR*6

Offset P Class

4 *

14214

14266

8 *

14222

14274

14252

12 *

14232

14284

16 *

14242

14294

14328

20 *

14256

O *

142O8

14260

426

427

428

429

430

431

432

433

434

435

436

437

438

439

440

•H-4 t

C

C

C

C

C

C

C

C

C

C

C

C

tw— k

C

C

SEARCH THE TIME HISTORY FILES TO FIND THE MAGNITUDE AT A GIVEN TIME

USAGE: CALL STIMEH(TEST,CH,TIME,MAG,ISTAT)

TEST-TEST NUMBER

CH-CHANNEL NUMBER

TIME-TIME FOR WHICH MAGNITUDE IS TO BE FOUND

MAG-MAGNITUDE AT TIME

ISTAT-CALL STATUS

-3=TIME EXCEEDS MAXIMUM TIME IN DATA FILE. MAXIMUM TIME AND

MAGNITUDE AT MAXIMUM IME ARE RETURNED IN TIME AND MAGNITUDE.

-2=TIME L.ESS THAN 0

-1=NORMAL RETURN

1-225=OPEN ERROR CODES

NOT VERIFIED ON IBM 12/85

SUBROUTINE STIMEH(TEST,CH,TIME,MAG,ISTAT)
M-f-C.

443

444

CHARACTER FD*12,IFLT*1

REAL MAG, MAGO, MAGI

D-Line*

445

446

447

448

443

450

451

452

453

454

455

456

457

458

453

460

461

462

463

464

465

466

467

•468

463

470

471

472

473

474

475

476

477

478

473

Name

1 7 Microsoft FORTRAN77

C **APPEARS TO BE MISSING FILTER DESCR

WRITE(*,*)'ENTER IFLT, 1 CHAR, SUB STIMEH'

READ(*,'(Al)')IFLT

C **ADDED 12/85

C

WRITE(FD,10)IFLT,TEST,CH

10 FORMATOT', Al, A6, ' . ' , A3)

LV=12

IFdSTAT.NE. 0) RETURN

OPEN(LV,FILE=FD,IOSTAT=ISTAT)

IFdSTAT.GT. 0) RETURN

ISTAT=-1

REflD(12, 2O,END=8OO,ERR=85O) XTIMEO,XMflGO

2O FORMftT(2G13.O)

IF(XTIMEO.LT.TIME) GO TO 5O

ISTOT=-2

GO TO 1000

REfiD(12,2O,END=8OO,ERR=85O) XTIMEi,XMftGl

IF(XTIME1.GE.TIME) GO TO 70

XTIMEO=XTIME1

XMftGO=XMfiGl

GO TO 50

MftG=XMflGO+<TIME-XTIMEO)*(XMftGl-XMflGO>/(XTIME1-XTIMEO)

GO TO 1000

MflG=XMftGl

TIME=XTIME1

ISTftT=-3

GO TO 1000

WRITE(*,875)FD

Page 11

01-23-86

09:32:46

V3.20 02/84

50

70

8OO

850

875 FORMftTC REfiD ERROR ON FILE', A12)

CLOSE<12, IOSTflT=IERR)

STOP

1OOO CLOSE(12,IOSTftT=IERR)

RETURN

END

Type

CH

FD

IERR

IFLT

1ST AT

LV

MAGMAGO

MAGI

TEST

TIME

XMAGO

Xi*ASl

XTIMEO

XTIME1

CHAR*3

CHAR*12

INTEGER*4

CHAR*1

INTEGER*4

INTEGER*4

REAL

REAL

REAL

CHAR*6

REAL

REAL

REAL

REAL

REAL

Offset P Class

4 *

14363

14452

14362

16 *

14336

12 *

*****

*****

O *

8 *

144Q4

144£O

1440O

14416

4SO CSPROG RDTH
u ut>Ht3c. : UHI_I_ KU i ri ^

482 C TEST-TEST NUMBER

483 C CH-CHANNEL NUMBER

i , un, ir i_ i I*IHUJ, I_C.IM, i H i

Page 12

01-23-86

09:32:46

D Line* 1 7 Microsoft FORTRAN77 V3.2O O2/84

484 C IFLT - FILTER CODE

485 C TIME - TIME VECTOR

466 C MAG-MAGNITUDE VECTOR

487 C LEN - DIMENSION F TIME AND MAG ON CALL NUMBER OF DATA POINTS ON RETURN

488 C ISTAT-CALL STATUS

489 C O=NORMAL RETURN

490 C -1=NUMBER OF DATA POINTS GREATER THEN LEN

491 C 1-££5=OPEN ERROR CODES

492 SUBROUTINE RDTH(TEST,CH,IFLT,TIME,MAG,LEN,ISTAT)

493 CHARACTER TEST*6,CH*3

494 CHARACTER FD*12

495 REAL MAG(512),TIME(512)

496 WRITE(FD,1O)IFLT,TEST,CH

497 1O FORMAT ('T'A1,A6,'.', A3)

498 LV=12

499 IF(ISTAT. NE. O) RETURN

500 OPEN(LV,FILE=FD,IOSTAT=ISTAT)

501 IFdSTAT. NE. 0) RETURN

502 LENM=LEN

503 LEN=O

504 15 LEN=LEN+1

505 READ(1£,2O,END=1OOO,ERR=850) TIME(LEN),MAG(LEN)

506 20 FORMAT(£613.O)

507 IF (LEN. LT. LElMM)GO TO 15

508 ISTAT=-1

• 509 GO TO 1000

510 850 WRITE(*,875)FD

511 875 FORMAT(' READ ERROR ON FILE',A1£)

512 CLOSE(12,IOSTAT=IERR)

513 STOP

514 1OOO CLOSE(12,IOSTAT=IERR)

515 LEN=LEN-1

516 RETURN

517 END

Name

CH

FD

IERR

IFLT

ISTAT

LEN

LENM

LV

MAG

TEST

TIME

Type

CHAR*3

CHAR*12

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

REAL

CHAR*6

REAL

Offset P Class

4 *

14456

1453O

8 *

£4 *

2O *

14490

14486

16 *

O *

12 *

518 C*PROG ERROR

519 SUBROUTINE ERROR(rtSSG,ISTAT)

520 CHARACTER I*ESG*2O

521 WRITE(*,*)*SUBROUTINE ERROR'

522 WRITE(», DMESG, ISTAT

523 1 FORMAT (' .ERROR ' A2O, ' !STAT=
525

b i UH

END

D Line* 1 7

Name Type

ISTAT INTEGER*^

MESG CHAR»2O

Microsoft

Page 13

01-23-86

09:32:46

FORTRAN77 V3.2O 02/84

Offset P Class

4 *

O *

526 C

527 C*PROG INTERP

528 C

529 C INTERPOLATION ROUTINE

530 C

531 SUBROUTINE INTERP(X,Y,XX,YY,SLOPE,LEN)

DIMENSION X(50O),Y(50O)

IF(XX.GE.X(1)) GO TO 1O

YY=Y(1)

RETURN

XLST=X<1)

YLST=Y(1)

DO 20 J=2,LEN

IF(X(J).GT.XX)GO TO 3O

XLST=X(J)

YLST=Y(J)

YY=Y<LEN)

RETURN

SLOPE=(Y(J)-YLST)/(X(J)-XLST)

YY=YLST+SLOPE*<XX-XLST>

RETURN

END

1

1

1

532

533

534

535

536

537

538

539

540

541

542

543

544

545

546

547

1O

2O

30

Name Type

J INTEGER*4

LEN INTEGER*4

SLOPE REAL

X REAL

XLST REAL

XX REAL

Y REAL

YLST REAL

YY REAL

Offset P Class

14570

20 *

16 *

O *

14562

8 *

4 *

14566

12 *

548 C*PROG RDPSD

549 C PURPOSE: READ THE CONTENTS OF A PSD DATTA FILE AND PUT

550 C FREQ. IN X AND PUT MAG. IN Y AND PUT COMPOSITE

551 C IN COMP

552 C

553 C TEST - TEST NUMBER (1 WORD 6 CHARACTERS)

554 C CH - CHANNEL NO.

555 C ISLICE - SLICE CODE

55S C LEN - DIMENSION OF X AND Y WHEN CALLED - NUMBER OF DATA

557 C POINT ON RETURN

558 C 'IV MUST BE DIMENSIONED ATLEAST LEN=1O IN MAIN PROGRAM ' !

559 C Y(LEN) = LEN

560 C T(LEN+5> = COMPOSITE ON PLOTS
L,

562 C

563 C

i kutilN-i->i; =

YCLEN+4) =

YCLEN+5) =

c. UUIMHU i C.LJ rrxui'i uioiiiic-u UM i >-<

COMPOSITE COMPUTED FROM CONVERTED DATA

NO. OF POINT NOT ASSIGNED DURING CONVERSION

D Line*

564

565

566

567

568

569

57O

571

572

573

574

575

576

577

578

579

58O

581

582

583

584

585

586

587

588

589

59O

591

592

593

594

595

596

1 597

598

599

6OO

6O1

602

1

C

C

C

C

C

C

C

C

C

10

20

3O

40

5O

55

C ??

60

7 Microsoft FORTRAN77

Y(LEN+6) = TIME SLICE

Y<LEN+7) = MAX. FREQUENCY

Y<LEN+8) - Y(LEN-t-lO) = SPARE

ISTAT - CALL STATUS

>0 OPEN ERROR CODES

,-5OO C(-5OO-CLOSE ERROR CODES)

-1 READ ERROR

-2 DATA EXCEEDED DIMENSION

LEN CHECK FOILED

SUBROUTINE RDPSD <TEST,CH, ISLICE,X,Y,COMB,LEN, ISTAT)

CHfiRftCTER CH*3,TEST*6

CHflRPCTER FD12*12

DIMENSION X<5OO),Y(50O)

WRITE(FD12,10)ISLICE,TEST,CH

FORMftT(A£, fl6, ' . ' ft3)

OPEN(12,FILE=FD12, IOSTftT=ISTftT)

WRITE(5,'(fl!2)')FD12

WRITE(*,*)FD12

IF(ISTftT.NE. O)RETURN

LENM=LEN+10

LEN=0

LEN=LEN-+1

READ <12,30,END=50, ERR=4O)Y(LEN)

IF(LEN.LT. LENM)GO TO 20

FORMAT(G13. 6)

ISTAT=-2

GO TO 60

ISTAT=-1

GO TO 60

LEN=LEN-11

COMB=Y(LEN+2)

STEP=Y<LEN+7)/LEN

DO 55 J=1,LEN

X(J)=J*STEP

IF(LEN.NE.IFIX(Y<LEN+1)))ISTAT=-3

CLOSE(12,IOSTAT=IERR)

IF(IERR.NE.0)ISTAT=-IERR-5OO

RETURN

END

Page 14

01-23-86

09:32:46

V3.2O 02/84

Name Type Offset P Class

CH

COMB

FD12

IERR

ISLICE

ISTAT

J

LEN

LENM

STEP

TEST

X

Y

CHAR*3

REAL

CHAR*12

INTEGER*4

INTEBER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

REAL

CHAR*6

REAL

REAL

4

20

14578

14628

a

28

1 462O

24

146O4

1461S

O

12

16

*

*

*

*

*

#

*

*
603 CPROG SPSD1

604 C PURPOSE: SEARCH THE TEMPORARY PSD DIRECTORY FOR A GIVEN TEST NO.

D Linetf

6O5

6O6

6O7

608

609

610

611

612

613

614

615

616

617

613

613

62O

621

622

623

624

625

626

627

628

629

63O

631

632

633

' 634

635

1

C

C

C

820

83O

86O

1OOO

111O

1180

113O

2OOO

2010

Page 15

O 1-23-86

09 : 32 : 46

7 Microsoft FORTRAN77 V3. 20 02/84

AND CHENNEL NO. — RETURN WITH TIME SLICE

MAX FREQ. AND SLICE CODE

SUBROUTINE SPSD1 (TEST, CH, SLICE, FREQM, ISLICE, ISTAT, THRUST)

CHARACTER TEST*6, TEST1*6, ISLICE*2, CHX*3

CHARACTER FD13*8,CH*3

DATA FD13 /'DPSD.TMP'/

IFdSTAT. EQ. O) GOTO 82O

OPEN (13, FILE=FD13, IOSTAT=ISTAT)

IFdSTAT. NE.O) GO TO 118O

READ < 13, 830, END=860, ERR=10OO) TEST1, ISLICE, CHX, SLICE,

1FREQM, THRUST

FORMAT <A6, IX, A2, IX, 03, 3 ( IX, G 13. 6) )

IF ( TEST 1. GT. TEST) GOTO 860

IF<TEST1.NE. TEST) GO TO 82O

IF (CHX. NE. CH)GO TO 82O

RETURN

ISTAT=-1

CLOSE (13, IOSTAT=IERR>

IFdERR. NE. 0)GO TO 2OOO

RETURN

WRITE(*,

FORMATS

STOP

WRITE (*, 119O) ISTAT

FORMAT (' OPEN ERROR NO. '13,' ON FILE DSPD. TMP' )

STOP

WRITE(*,2010) IERR

FORMAT (' CLOSE ERROR NO. '13' ON FILE DPSD.TMP')

STOP

END

READ ERROR IN SPSD1')

Name

CH

CHX

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ISLICE

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TEST

TEST1

THRUST

Type

CHAR*3

CHAR*3

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CHAR*2

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Offset P Class

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CREATE TEMP FILE FOR SELECTED CHANNEL NUMBER

SEARCH DPSD FOR ALL ENTRIES OF MATCHING CHANNEL

WRITE THEM TO DPSD.TMP

SUBROUTINE DPSDTEMP(TEST, CH, ISTAT)

CHARACTER TEST*6,T£ST1*6, ISLICE*2,CHX*3

CHARACTER FD13*4,CH*3

DATA PD13 /' D3SD' /

OPEN (13, FII_E=FD13, IOSTAT=ISTAD
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1FREQM,THRUST

FORMftT(fl6, IX, O2, 1X,«3, 3 (IX, 613.6))

IFCCHX.NE.CH)GO TO 82O

IF (ICHflN. EQ.O) OPEN<6,FILE='DPSD.TMP'>

ICH«N=1

WRITE <#,*)TEST1, CHX, ' ',THRUST

WRITE(6,83O)TEST1,ISLICE,CHX,SLICE,FREQM,THRUST

GOTO 82O

CONTINUE

IF (ICHflN. EQ.O) WRITE<*,*)'NO PSD FILES FOR SELECTED CHftN

CLOSE(13,IOSTftT=IERR>

IF<IERR.NE.O)GO TO £OOO

CLOSE(6,IOSTRT=IERR>

IF (IERR.NE.O) GOTO 2OOO

RETURN

WRITE**,1110)

FORMftTO REftD ERROR IN DPSD')

STOP

WRITE(»,1190)ISTflT

FORMflTC OPEN ERROR NO. '13,' ON FILE DSPD' )

STOP

WRITE(*,£O10)IERR

FORMftTC CLOSE ERROR

STOP

END

Page 16

01-23-86

09:32:46

V3.20 02/84.

NO. '13'ON FILE DPSD OR .TMP')

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STIMEH

Page 17

O1-23-86

O9:3£:46

Microsoft FORTRfiN77 V3. 2O O2/8ASUBROUTINE

Pass One No Errors Detected

674 Source Lines
Section IV

SUMMARY OF THE SSME DYNAMIC PRESSURE

ENVIRONMENT AT RATED POWER LEVEL

The appendices to this report include spectra for all the

SSME tests, dynamic pressure measurements, and operating

power levels provided by MSFC. A number of these

measurements represent SSME operation over a limited power

level range. However, the great majority of measurements

include operation at RPL. In addition, an extensive data

base of related vibration measurements has been developed at

MSFC, representing SSME operation at RPL.

Average spectra were therefore extracted from the data base,

to summarize the dynamic pressure measurements obtained at

RPL. The procedure applied is summarized as follows.

1. Applying the data base sort routine, the spectra

representing engine operation at RPL (99% - 101% RPL) were

identified for each measurement.

2. The spectra were plotted in a waterfall format to

permit a qualitative evaluation of measurement trends and

repeatability.

3. These spectrum families were reviewed in detail and,

based on engineering judgement, clearly deviant spectra were

deleted from subsequent analysis. (It should be noted that

no spectra were deleted from the original data base.)

4. Finally, the edited collection of spectra for each

measurement was ensemble averaged using the statistical

analysis subroutine, to obtain a single spectrum
representing each measurement at RPL. These results are

presented as figures 4-1 through 4-27.

The above described spectra should provide a valuable

reference to summarize the SSME dynamic pressure environment

under nominal operating conditions. In applying these plots

as a "benchmark"/ it should be noted that the spectra

represent measurements with widely varying available sample

size. For example, the auxilliary lox inlet pressure

spectrum, figure 4-23, represents a single observation

(PSD) , whereas the main combustion chamber hot gas inlet

pressure spectrum, figure 4-8, is the average of 44 PSD's

available in the data base at RPL. Therefore, considerably

more variation is to be expected about the former 'average1

spectrum than the latter. An interpolation scheme to

estimate the pressure spectrum over a wide range of engine

power levels is discussed in the next section.

k-2
CS9

-5

Sample Size = 12

0, FREQ HZ

FIGURE k-\. SPECTRUM OF LPFP IN PR AT RPL
Sample Size = 29

-4

FIGURE *t-2. SPECTRUM OF LPOP DS PR AT RPL
-4

Sample Size = 30

FIGURE 4-3. SPECTRUM OF HPOP BAL CAV PR2 AT RPL
FIGURE k-k. SPECTRUM OF HPOP BAL CAV PRl AT RPL
1

-2

e

Sample Size = 43

II I I I T I I I

FRED

FIGURE k-5. SPECTRUM OF HPOP DS PR AT RPL

4-6
CS3

0*»

*J>

-6

Sample Size = 3

I I I I F T T T T

FREQ HZ

FIGURE k-B. SPECTRUM OF LOX IN DUCT PR2 AT RPL
1

-3

FRED HZ

FIGURE A-7. SPECTRUM OF HPOP DISC PR AT RPL
2

-2

Sample Size = 12

FIGURE k-8. SPECTRUM OF MCC HOT GAS IN PR AT RPL
2

-2

FIGURE k-3. SPECTRUM OF PBP DS PR AT RPL

4-10
-1

CS»

Sample Size = 17

FIGURE 4-10. SPECTRUM OF LPFP DS PR AT RPL
1

cxa

-4

FIGURE 4-11. SPECTRUM OF FPB FUEL MAN PR AT RPL

4-12
1

CS3

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0.0

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Sample Size = 17

FIGURE 4-12. SPECTRUM LPOT TURB DR PR AT RPL

4-13
0

CSI

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Sample Size = 17

T I I T I TI T

FRED HZ

FIGURE 4-13. SPECTRUM OF OPB PC PR AT RPL
-2

csa

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Sample Size = 13

I I T 7 I T T T T

FRED H7

FIGURE k-\k. SPECTRUM OF HEX OUTLET AT RPL
1

FIGURE 4-15. SPECTRUM OF HPFP DS PR AT RPL

4-16
-1

FIGURE 4-16. SPECTRUM OF HOT GAS MAN PR3 AT RPL
2

-2

FIGURE 14-17. SPECTRUM OF HPFP BAL CAV PR AT RPL

4-18
FIGURE 4-18. SPECTRUM OF MCC FUEL INJ PR AT RPL

4-19
1

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Sample Size = 10

FRED HZ

FIGURE A-19. SPECTRUM OF FPB PC AT RPL

k-20
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FIGURE 4-20. SPECTRUM OF MCC FUEL INJ PR DC AT RPL

4-21
2

Sample Size = 2

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FRED HZ

FIGURE k-2], SPECTRUM OF OPB PL AT RPL

4-22
3

-2

Sample Size = 13

1 I I I I I I I I I

FRED

FIGURE k-22. SPECTRUM OF HPOP IN PR AT RPL

k-23
-2

Sample Size = 1

CSI

-7 ITITTITIT T

FRED HZ

FIGURE 4-23. SPECTRUM OF AUX LX I PR AT RPL
FIGURE k-2k. SPECTRUM OF LX I PR AT RPL

4-25
041

-5

FIGURE A-25- SPECTRUM OF MCC IN PR AT RPL
1

csa

-2

0, FRE8 HZ

FIGURE 4-26. SPECTRUM OF OPB PC PR DC AT RPL

4-27
SECTION V

SPECTRUM NORMALIZATION AND INTERPOLATION

In the introduction to this report it was noted that the

study was directed to accomplishment of three major

objectives; data base generation, management software

development, and development of techniques to estimate

measurement spectral trends with engine operating

conditions. This section summarizes approaches taken to

accomplish the last objective.

5.1 Dimensional Analysis

At the outset of the study, it was anticipated that dynamic

pressure measurement scaling would be accomplished through

dimensional analysis based on governing fluid-dynamic and

geometric parameters. A literature search was therefore

initiated to define non-dimensional spectral relations for

fluid/structural systems similar to SSME components. Two

such non-dimensional spectral models are as follows:

Flow Induced Turbulence(1) (Duct Flow)

Sp - Qp (s)/P2v

3d

where Sp is the dimensionless pressure spectral density, and

Qp = measured PSD

P = local fluid density

v = mean flow velocity

d = characteristic length

s= dimensionless frequency = fd/v (Strouhal number)

f = frequency

(1) Clinch, J.M. Prediction and Measurement of Vibrations

Induced in Thin Walled Pipes by Internal Turbulent

Waterflow. J. Sound Vib., V. 12, No. 4, 1970.
KT«

OH l<3 IO-O IOOO

StrauMna. fd/Um

FIGUR E 5-1 -Frequency spectrum of turbulent wall pressure field. (O), 267 in/sec; (A) 450 in/sec; (Q) 520

in/sec

5-2
MIM4 hPOP OS PR - S« 5.0

to1

10'

s

10

10

10,000

FIGUR E 5-2. Power spectral density of the high pressure

oxidizer pump discharge pressure 5 seconds after SSME

startup

10" 8-

I MUM HPOP OS ?R S* U)

t o '

10"

LO 10'1

 10"

StrouMi Muffle*

FIGUR E 5-3- Nondimensionalized frequency spectrum for

high pressure oxidizer pump discharge pressure, 5

seconds after SSME startup

5-3
Blade Wake Excitation(2) (Pump Discharge)

g(s, ) - Qp/Pc2D

3

Mt

3

where

= Flow coefficient

M£ = Blade tip mach number

s = Dimensionless frequency, f/n

D = Blade Diameter

n = Shaft speed

Figure 5-1, from reference (1), illustrates the nondimensional wall pressure spectrum measured on a circular

duct with internal water flow over a range of flow

velocities. Collapse of the data is seen to be quite good.

Figure 5-2 is the ordinary PSD of a dynamic pressure

measurement. Dimensional normalization of this spectrum by

the above technique is shown in figure 5-3. The predominant

spectral peaks appear related to turbopump rotational

speeds. A normalization scheme was therefore developed to

represent the spectra as a linear superposition of simple

non-dimensional sources.

As sufficient data base measurements became available a

detailed evaluation of spectral trends with engine power

level was performed. (It should be noted that the nondimensionalizing parameters such as flow velocity and

turbopump blade tip speed vary in proportion to engine power

level). Since well defined spectral trends were not

indicated in general, it became clear that the measured flow

dynamic interactions are too complex to be adequately

represented by a superposition of simple sources.

(2) Maling, G. C. Jr. Dimensional Analysis of Blower Niose.

J. Acoust. Soc. Am., V. 35 No. 10, 1963.

5-1*
Dimensional analysis was therefore abandoned in favor of a

more general two dimensional interpolation procedure.

5-5
5.2 Interpolation Bv Singular Value Decomposition

The method of Singular Value Decomposition is a mathematical

tool for the decomposition of general rectangular matrices.

By this technique, a family of curves, such as the power

spectra of dynamic pressure measured at a number of power

levels can be reduced to a superposition of basic component

patterns (eigenvectors) and associated weighting

coefficients. The predominant normalized component patterns

yield a good approximation of the given spectra. Thus, the

difficult problem of interpolating (two dimensional) over

the observed spectra can be reduced to one dimensional

polynominal interpolation of the derived weighting

coefficients.

It may be instructive to observe that the SVD technique is

mathematically akin to the normal mode method in structural

dynamics. In the latter application, the complex deflection

patterns of a structure are expressed as a superposition of

normal modes, or eigenvectors. The associated weighting

coefficients (eigenvalues) are the system natural

frequencies. (An excellent review of the SVD technique,

upon which this discussion and the resulting software is

based, is given by S. Tominaga in the IEEE Transactions on

Acoustics, Speech and Signal Processing, Vol. ASSP-29, No.

3, June, 1981.) The technique is best illustrated by

example.

Figure 5-4 illustrates the ensemble average spectra of the

high pressure oxidizer pump discharge pressure observed at

11 engine power levels. Based on this set of data we wish

to extract normalized spectrum functions and associated

coefficients to represent the curves over a continuous range

of power levels. Each PSD may be represented as a vector

p, (n x 1) , representing the spectral values at n

5-6
frequencies. The group of spectra may thus be written as a

matrix P, (n x m) , representing the m spectra at n

frequencies. (In the case at hand this is a 400 x 11

matrix.) If the rank of P is m, it may be expressed as the

sum of m matrices of rank one,

p = rl

 nl

 eTl

 +

 • ' •

 + rm "m

 eTm

where n^, e^ are the orthonormal vectors of PPT and PTP,

respectively, and the singular values r^ are the square

roots of the eigenvalues of PPT.

Now, each of the eleven spectra may be uniquely defined as a

linear combination of the fundamental component waves n±, in

the form

Pi

 = cilnl + + cimnm

where c^j = rje^j and BJ is defined to be [e^, ..

The SVD technique provides a method of synthesizing a set of

observed curves. For purposes of prediction it is then only

necessary to interpolate over the coefficients c^j, as a

function of engine power level, for each fundamental

component pattern.

The software was developed for the implementation of the SVD

technique and interpolation scheme. A program listing of

the routines is given in Table 5-1. Figure 5-5 illustrates

the fundamental component patterns associated with the three

largest singular values for the spectra in Figure 5-4.

The above analysis indicates that all component patterns be

utilized to synthesize the family of curves. This provides

a unique representation. In practice, however, convergence

is quite rapid. This is again similar to the normal mode

5-7
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method, wherein the 'deflection of a bean can generally be

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For the example under discussion, the eleven computed

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are: 105.3, 9.8, 6.5, 4.4, 3.9, 3.4, 3.3, 2.9, 2.7, 2.3 and

.00002. The relative contribution of each fundamental

pattern may be shown to be proportional to its associated

singular value. It is therefore clear that a superposition

of the first three fundamental patterns should provide a

good approximation to the given family of spectra. This was

done for the cited example, and an interpolated library of

pressure spectra was computed at 2.5% power levels over the

range of observed test values. These results are shown in

Figure 5-6, and indicate the spectral trend of dynamic

pressure with engine power level.

5.3 An Interpolated Library of Spectra

for Dynamic Pressure Measurements

To indicate the trend in amplitude/frequency of the SSME

dynamic pressure measurements an interpolated library of

spectra was derived, by the method just discussed. The

analysis procedure was performed as follows:

1. The data base spectra for each measurement

location were plotted, and any obvious outliers

discarded from subsequent analysis.

2. The remaining data sets were segregated by power

level. The range and number of power levels available

varied by measurement location, based on the specific

measurements and test conditions provided by MSFC.

5-11
3. The spectra for each measurement/power level were

ensemble averaged to obtain a family of spectra as

shown in the example, Figure 5-4.

4. An SVD analysis was performed on each set of

curves to extract intrinsic component patterns and

associated singular values. The number of derived

patterns/coefficients varied according to the number of

test power levels available for each measurement.

5. Finally, interpolation was applied to the above

derived coefficients, and plots generated representing

spectral variation in 2.5% power level increments over

the available data range.

The results of this exercise are illustrated in the

remaining figures of this report. These figures provide a

qualitative indication of spectrum variation with engine

power level. A Quantitative estimate of spectral amplitudes

and frequencies may be obtained by cross reference to the

average spectra representing operation at RPL, as given in

Section IV of this report.

It will be noted that several of the data base measurements

are not included in the above discussed spectrum library.

This is essentially due to lack of sufficient data; either a

very limited number of spectra and/or a very limited test

power level range. In either case, one is referred to the

average spectra presented in Section IV or the data base

plots provided in the Appendices for spectral definition of

these measurements.

5-12
5.4 A Computer Routine for Estimating

Dynamic Pressure Environments

The interpolated spectrum libraries presented in the

previous discussion provide a valuable indication of

spectral trends with engine power level. However, as noted,

the results are qualitative. A computer routine was

therefore developed to generate an estimated spectrum for a

user defined dynamic pressure measurement and engine power

level.

This program utilizes the eigenvectors and singular values

obtained by the SVD technique as discussed in Section 5-3

for each measurement, and is therefore totally indepedent of

the complete data base. The routine was designed for the

engineer responsible for dynamic evaluations and requires no

knowledge of the linear algebra implied by SVD.

A simple menu driven format is provided, wherein the user is

querried as to what measurement description and power level

a PSD estimate is desired for. (The user is also asked how

many eigenvectors (fundamental SVD patterns) he/she desires

to use in the spectrum estimate. To answer this question

the user has the option to review the singular value

magnitudes associated with each pattern. However, through

development of the SVD analysis and the pressure spectrum

libraries, experience indicates that a "three mode"

approximation should be satisfactory and efficient.) A

program listing of the spectrum estimation routine is given

in Table 5-1. The program is operational on any

PC/compatible computer.

5-13
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a.

10

CM

i

QC

3

CD

z

m ) asd •SO

00

I

5-28
o.

CC

CC

0.

Ul

3

u.

u

a:

h-

<

cc.

to

LU

0.

CM

UJ

a:

( W m ) dSd DO!

I

5-29
o_

an

vO

o

QOQ

QO

<

ce

ic_>

LU

Qn-v

CM

LPV

UJ

( ZH/ ISJ ) dSJ DOT

5-30
'ttt&Mttz

**£ ff- ^r=£_!#*

a.

a:

i

LTV

o

o

ae

a.

O

z

LU

ee.

a.

1/5

I

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( ZH/ ISJ ) dSi 501

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t£.

Q.

Q.

O

O.

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<

cc.

Q.

to

LT\

CM

I

LA

( ZH/ ISJ ) dSJ D01

5-32
^ .3=

)ilj|S5iN I

I- 4: > i -T ->-£ $ -> £ i

U

3

.lit-fiSV^

X 7

•^

f^«4>5*4M

^fl!

-O11

«

 ^ 1 < ^^:^ 5

ft

if

I

=:_I •;

i?

in

I

3

1

Vi

i

}-

I3

i

I

4

ir

ii

in

o

o

cc.

Q.

O

a_

a.

o

a.

CO

so

CM

urv

C3

( W ISd ) ISJ 501

I

5-33
TABLE 5-1. A SPECTRUM INTERPOLATION PROGRAM Page 1

01-£8-86

BASED ON SINGULAR VALUE DECOMPOSITION 09:36:45

1 7 Microsoft FORTRAN77 V3. £O O£/84

C PROGRAM SVDNASA

£ C THIS PROGRAM GENERATE THE PSD OF SSME PRESSURE MEASUREMENTS

3 C FROM 31 DIFFERENT LOCATIONS. THE ORIGINAL PSD HAVE BEEN

4 C TRANSFORMED TO A FEW BASIC WAVEFORMS BY USING SINGULAR

5 C VALUE DECOMPOSITION METHOD. THESE BflSIC WAVE FORMS WERE

6 C USED IN THIS PROGRAM TO ESTIMATE THE PSD AT ANY POWER LEVEL

7 C WITHIN CERTAIN RANGE.

8 REAl_*4 XXI (10O) , XX£(10O) , WK1 (1OO), WK£(10O)

3 DIMENSION ID(34),NN(34)

10 REAL*4 CCU6, 16) ,DD<1S, 16), U(4OO, 1£> , VV(4OO, 1£> , PSD (400)

11 CHARACTER*3 FNAME(34)

1£ CHARACTER*10 F1,F£,F3

13 CHARACTER*!1 F11,F1£,F13

14 CHARACTER*16 F4, F5

15 WRITE(*,666)

16 666 FORMAT(' THIS PROGRAM GENERATES THE PSD OF PRESSURE MEASURE',

17 1 'MENT AT ANY POWER LEVEL',/,' ( WITHIN CERTAIN RANGE ) BY ' ,

IS 1 'USING SINGULAR VALUE DECOMPOSITION METHOD')

19 WRITE(*,'(A)')' OUTPUT PSD HAS 40O LINE SPECTRA'

£0 OPENd, FILE=' SVDNASA. DAT' , STATUS=' OLD'.)

£1 DO 1£ 1=1,34

££ READC1, 6O1)FNAME(I), ID(I),NN(I)

£3 1£ CONTINUE

£4 6O1 FORMAT(A3, IX, II, IX, I£)

£5 CLOSE(1)

£6 M=4OO

£7 123 CALL CHANNEL

£8 WRITE(*,'(A)')' ENTER CHANNEL #'

£3 READ(*, *)NCH

30 IFdD(NCH). EQ. 9) WRITEC*, ' (A) ' ) ' NO DATA "

31 IF(ID(NCH).EQ. 9)GOTO 1£3

3£ CCCCCCCCCCCCCCCCCCCCCCCCCCC ID=£ CCCCCCCCCCCCCCCCCCCCCCCCCCCCCC

33 IFdD(NCH) .EQ.£)THEN

34 WRITE(*,'(A)')' ENTER 1 FOR MAX FREQ = 20OOG HZ '

35 IF(NCH.NE.7)WRITE(*,'(A)')' £ FOR MAX FREQ = 40000 HZ '

36 IF(NCH.EQ.7)WRITE(*,'(A)')' £ FOR MAX FREQ = 5OOO HZ'

37 READ(#,*)IF12

36 IF(IF1£.EQ.1)THEN

33 WRITE(Fl1,6O£)FNAME(NCH)

40 WRITE(Fl£,6O3)FNAME(NCH)

41 WRITE(F13,6O4)FNAME(NCH)

4£ ELSE

43 WRITE(F11,605)FNAME(NCH)

44 WRITE(Fl£,6O6)FNAME(NCH)

45 WRITE(F13,6O7)FNAME(NCH)

46 ENDIF

47 OPENd,FILE=F11,STATUS='OLD',ACCESS=' DIRECT' , RECL=4*M)

48 OPEN(£,FILE=F1£,STATUS='OLD')

49 OPEN(3, FILE=F13,STATUS='OLD' )

50 WRITE(*,'(A)')F11,Fl£,F13

51 Ei\iDI~

52 CCCCCCCCCCCCCCCCCCCCCCCCCCC ID=O,1 CCCCCCCCCCCCCCCCCCCCCCCCCCCCC

53 IF(ID(NCH).LE.I)THEN

54 [.- (NCH. NE. 31. AND. .NCH. NE. 30. AND. NCH. iME. 3) THEN

55 WRITE(*,'(A)')' MAX FREQ. CF OUTPUT PSD = 20OOO. HZ'

dfe SLo^

57 *iRI "£(*,' (A)')' r-lAX r'R = Q. OF OUTPUT PSD = 40OOO. HZ'

53 £\DIF

55 WRITE (." 1, 60S) FNAME (NCh)

5-34
D Line* 1

SO

61

6£

63

64

65

66 6O£

67 603

68 6O4

69 605

70 6O6

71 607

7£ 60S

73 6O9

74- 610

75

76

77

78

79

1 SO

1 81 £2

8£

1 83

1 84 1

85

86

87 3£1

88

89

9O

Page •=:

Oi-£8-8&

O9 : 36 : 45

7 Microsoft FORTRAN77 V3. £O O£/84

WRITE (F£, 609) FNAME(NCH)

URITE(F3, 610)FNAME(NCH)

OPEN( 1, F1LE=F1, STATUS=' OLD' , ACCESS=' DIRECT' , RECL=4*M>

IF ( ID (NCH) . EQ. 1 ) OPEN (£, FILE=F£, STATUS=' OLD' )

OPEN (3, FILE=F3, STflTUS=' OLD' )

ENDIF

FORMAT < ' PSD' , A3, ' A. EVT' )

FORMAT ( ' PSD' , 03, ' A. EVL' >

FORMAT ( ' PSD' , A3, ' A. PRO' )

FORMAT ( ' PSD' , A3, ' B. EVT' )

FORMAT ( ' PSD' , A3, ' B. EVL' )

FORMAT ( ' PSD' , A3, ' B. PRO' )

FORMAT (' PSD' , A3, '. EVT' )

FORMfiT ( ' PSD' , A3, ' . EVL' >

FORMAT (' PSD' , P>3, '. PRO' )

M=4OO

N=NN<iMCH)

REflD(3, *) (XXI (I), I=£, N-t-1)

CLOSE <3)

DO ££ J=1,N

REflDd, REC=J) (U(I,J), 1 = 1, M)

CONTINUE

DO 1 J=1,N

IF < ID (NCH) . NE. 0)REfiD(£, *) (CC(I,J), 1 = 1, N)

CONTINUE

CLOSE ( 1 )

IF (ID (NCH) . NE. 0) CLOSE (£)

NOUT=1

WRITE(*, ' (ft)')' ENTER FILE NOME OF OUTPUT PSD'

REflD(#, ' (fl) ' )F5.

OPEN (5, FILE=F5, STftTUS=' NEW )

91 CCCCCCCCCCCCCCCCCCCCCCCC ID=0 CCCCCCCCCCCCCCCCCCCCCCCCCCC

9£

93 6£1

94

95

96

97

98

99

I 1 00

1 1O1

1 1O£

1 103

1 04

105 691

106

1 07

1O8

109

IF (ID (NCH). EQ. 0)THEN

FORMflTC PSD ONLY fiVftlLflBLE ftT POWER LEVEL: ' , 10 (F7. £, ' '/. '))

WRITE(», 6£1) (XXI (I) , I=£,N+1)

WRITE (*,' (ft) ')' ENTER DESIRED POWER (IN •/.) '

REflD(*, *)PWL

ftMIN=£OO

MIN=£

DO 691 I=£, N+l

TE=ftBS(PWL-XXl (I)) i

IF(TE. LE.ftMIN)THEN '

flMIN=TE

n i N= i - i

ENDIF

CONTINUE

WRITE(5,*) (U(I, MIN) , 1 = 1, M)

CLOSE (5)

GOTO 1986

ENDIF

1 1 0 CCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCCC

i ll

•) -1 TMl

4. J. L_

1 1 3 6 1 1

t 14

115

US

117

113

IF (ID (NCH) . EQ. DThEN

WRITE (*, 61 1 ) XXI (£) , XXI <N+1 )

FORMAT (' AVPIt_ftBL£ POWER LEVEL = ',FiO. 4, ' 7- TO ', F10. <+„'"/')

WRITE (*, ' (A) ' ) ' ENTER DESIRED POWER LEVEL (•/•) '

REflD(*, *) XX£(1 )

ELSE

WRITE (*, ' (A; ')* ENTER INPUT POWER LEVEL :-ILNftM'

READ(*, ' (A) ' )F4
Mage 3

01-28-86

09 : 36 : 45

i 7 Microsoft FORTRON77 V3. 2O O2/84

119 OPEN (4, FILE=F4,STftTUS=' OLD' )

120 REflD<4, *) <XX2(I) , I=1,NOUT>

121 CLOSE<4)

122 ENDIF

123 IFLftR=2

124 WRITE(*, 61£)N

125 REflD(*, *)MMM

126 612 FQRMftTC ENTER # OF BASIC WAVEFORMS TO BE USED (LE. ' , 13, ' ) ' )

127 IFL=1

128 XXI (1)=XX1 <2)-<XXl (3)-XXl (2) ) .

129 XXI <IM+2)=XX 1 (N-t-l) + <XX l <N+1>-XX 1 (N) >

130 DO 11 1=1, M

1 131 DO 11 J=1,MMM

2 132 VVCI, J)=U(I, J)

2 133 11 CONTINUE

134 DO 66 I=1,MMM

1 135 DO 65 J=1,N

2 136 65 WK1 (J+1)=CC(I, J)

1 137 WK1 <1)=WK1 <2) + <WKl (2)-WKl <3)>

1 138 WK1 <N-*-2)=WKl <N-f-l) + (WKl (N+D-WK1 (N) )

1 139 IFdFLftR. EQ. 1 ) THEN

1 14O CflLL LflR<XXl, WK1, N+2, NOUT, XX2, WK2)

1 141 ELSE

1 142 CftLL LINE (XXI, WK1, N+2, NOUT, XX2, WK2)

1 143 ENDIF

1 144 DO 64 J=1,NOUT

2 145 64 DO (I, J)=WK£(J)

1 146 66 CONTINUE

1 47 C********************************

148 DO 1O2 II=1,NOUT

1 149 DO 101 1 = 1, M

2 ISO PSD(I)=O.

2 151 DO 101 K=1,MMM

3 152 PSD(I)=PSD<I>-*-W<I, K)*DD<K, II)

3 153 101 CONTINUE

1 154 IFdFL. EQ. 1 ) THEN

1 155 DO 1O4 LL=1, M

2 156 1O4 PSD(LL)=10. **(PSD<LL) )

1 157 ENDIF

1 158 WRITEC5, 1O3) < PSD < I ) , 1=1, M)

1 159 1O2 CONTINUE

160 1O3 FORMfiTdX, 5E15. 7)

161 CLOSE(5)

162 1986 WRITE (*,' (ft)')' ENTER 1 FOR SELECTING ANOTHER POWER LEVEL'

163 WRITE <*,' (ft)')' 2 FOR SELECTING ANOTHER CHANNEL'

164 WRITE (*,' (ft)')' ' ELSE FOR STOP PROGROtf'

165 REflD(*, *) IFCG

166 IF ( IFCG. EQ. 2) GOTO 123

167 IFCIFCG.EQ. 1 ) GOTO 3£1

168 STOP

169 END

Name Tyoe Offset P Class

, INTRINSIC

•3"" IN .'£311-

CC REPi- 4:074-

DD "*ZflL- 42896

FI C|-AR*IO 44ii61
D Line* 1

Page 4

01-58-86

09:36:45

Microsoft FORTRAN77 V3. £O O2/84

Fll

F12

F13

F2

F3

F4

F5

FNAME

I

ID

IF12

IFCG

IFL

IFLAR

II

J

K

!_!_

M

MIN

MMM

N

NCH

NN

NOUT

PSD

PWL

TE

U .

vv

WK1

WK2

X XI

XX£

CHAR* 11

ChAR*ll

CHAR*ll

CHAR*1Q

ChAR*lO

CHAR*16

CHAR*16

CHAR*3

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTE6ER*4

INTEG£R*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEG£R*4

REAL

REAL

REAL

REAL

REAL

REAL

REAL

REAu

REAL

44S28

44239

4425O

44271

44281

44636

4449O

43922

44196

1602

44224

4478O

44716

44652

4474O

44474

44752

4476O

44216

4457O

44656

44466

4422O

1738

44486

40274

44562

4457S

1874

21O74

802

1202

2

402

1

1

2

£

2

J.

1

•1

1

2

c.

3j^-

•5

170

171

172

173

174

175

176

177

178

179

130

181

182

183

184

185

186

107

188

SUBROUTINE LAR ( XXI , YY1, IMIN, NOUT, XX2, YY£)

YY1 (1), XX2<1)

7

REAL*4 XXI

DO 3 1=1, NIN

CC(I)=1. OO

DO 4 J=l, NIN

IF (J.ED. I) GOTO 4

CC(I)=CC(I)*(X,X1 (I) -XXI (J) )

CONTINUE

CC(I)=YY1 <I)/CC<I)

CONTINUE

DO 5 I=1,NQUT

A=XX2(I)

DO 6 J=1,NIN

FF(J)=1. OO

DO 7 K=1,!NIN

IF(K. EQ. J)GOTO 7

FF(J)=FF(J) *(A-XX1 (IO)

CONT I NUE

FF(J ) -FF(J) *CC(J)

YY2 ( 1 ) , CC(5O), FF(5O)

YYii ( 1 > =U. i )

DC S '_=! , N
D Line*

£ 133

£ 194

1 135

136

137

Name

Microsoft

Page 5

o1-28-8&

03:36:45

FDRTRflN77 V3.2O 0£/84

YY£(I)=YY2(I)+FF(L)

8 CONTINUE

5 CONTINUE

RETURN

END

Type Offset P Class

A

.CC

FF

I

J

K

L

NIN

NOUT

XXI

XX£

YY1

YY£

REftL

REflL

REftL

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

REftL

REftL

REftL

REftL

45£04

44784

44384

45184

45132

45£1£

45££0

a

1£

O

16

4

£0

*

*

*

*

*

*

1

£

2

£

£

£

1

198

139

£00

£O1

£0£

£03

£O4

£O5

£O6

£07

£O8

£O3

1

33

Name Type

SUBROUTINE LINE(XX1,YY1,NIN,NOUT,XX£, YY2)

REflL*4 XXI(1),YY1(1),XX£(1),YY£<1>

DO 33 1=1,NOUT

DO 1 J=1,NIN-1

IF(XX2(I).GE.XXI(J).flND.XX2(I).LE.XXI<J+1))THEN

YY2(I)=SSS(XX1 (J), XXI (J+-1), YY1 (J) , YY1 < J+l) , XX2(I)>

GOTO 99

END IF

CONTINUE

CONTINUE

RETURN

END

Offset P Class -

I

J

NIN

NOUT

XXI

XX£

YY1

YY2

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

REftL

REftL

REftL

REftL

45££S

45£36

a

1£

O

16

4

£0

*

*

*

*

*•

*

£10

£11

£1£

£13

Name

XI

X£

XX

Yl

Type

REftL

REAu

REftL

REflL

FUNCTION SSS(X1,X£,Yl,Y£, XX)

SSS=Yl-»-<XX-Xl)*(Y£-Yl) / <X£-X1>

RETURN

END

Offset P Class

0

4

16

a
D Line** 1

Y2 REAL

Page 6

01-28-86

09:36:45

Microsoft FORTRAN77 V3. 2O O2/84

12 *

Name

214

215

216

217

213

219

220

221

222

223

224

225

226

227

228

229

230

231

232

233

234

235

236

237

238 666

239

240 667

241

242

Type

THRUST(NO DATA)

IN PR

PR

HPOP BAL CAV PR2

HPOP BAL CAV PR1

HPOP DS PR

LOX IN DUCT PR2

SUBROUTINE CHANNEL

WRITE<*,' (A)' ) ' 1.

1 23. FPB PC'

WRITE<»,'(A)')' 2. LPFP

1 24. MCC FUEL INJ PR DC'

WRITE(*,'(A)')' 3. LPOP DS

1 25. OPB PL*'

WRITE(#, ' (A)' )' 4.

1 26. HPOP IN PR'

WRITE<#, ' (A)' )' 5.

1 27. AUX LX I PR*'

WRITE<»,'(A)')' 6.

1 28. HI LX I PR*'

WRITE(*,' (A)' ) ' 7.

1 29. HOT GAS MAN PR2*'

WRITE(*,' (A)' )' 8. HPOP DISC

1 30. MCC LONG ACCEL

WRITE<»,' (A)' ) ' 9.

1 31. MCC IN PR*'

WRITE<*,' (A)' )' 1O.

1 34. OPB PC PR DC'

WRITE<», ' (A)' )' It.

WRITE<*, 666)

WRITE(», 667)

FORMATS NOTE: CHANNEL DESCRIPTOR ENDED WITH "*" MEANS',

1 ' SVD DATA IS NOT AVAILABLE')

FORMAT<' PSD ONLY AVAILABLE AT SOME FIXED POWER LEVEL')

RETURN

END

Offset P Class

PR

1*'

MCC HOT BAS

PBP DS PR

CHAMBER PR*

IN PR

12. LPFP DS PR

13. PBP FUEL SUP PR

14. FPB FUEL MAN PR

15. LPOT TURB DR PR

16. LOX HX OUT PR

17. OPB PC PRR*

18. HEX OUTLET*

19. HPFP DS PR*

20. HOT GAS MAN PR3*

21. HPFP BAL CAV PR

22. MCC FUEL INJ PR

Name Type

CHANNE

LAR

LINE

MAIN

SSS REAL

Size Class

SUBROUTINE

SUBROUTINE

SUBROUTINE

PROGRAM

FUNCTION

Pass One No trrors Detected

242 Source Lines
D

1

1

2

1

1

2'.

1

1

1

1

If

1

1

1

1

Line*

1

2

3

4

5

6

7

8

g

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

26

27

28

29

3O

31

32

33

34

35

36

37

38

39

4O

41

42

43

44

45

46

47

48

49

5O

51

52

53

54

55

56

57

58

59

1

C

C

C

C

C

C

C

1

78

79

502

5O1

5O4

5O3

777

333

Page 1

01-29-86

1A:06:14

7 . Microsoft FORTRAN77 V3.2O OS/SETHIS PROGRAM USES SINGULATR VALUE DECOMPOSITION METHOD TO .

GENERATE THE BASIC WAVEFORMS AND ITS SINGULAR VALUES IN ORDER

TO ESTABISH THE WHOLE FAMILY OF PSD FROM THE GIVEN MEASURED

PSD AT SOME CERTAIN PARAMETER < e.g. POWER LEVEL )

DIMENSION UK(12),WKC12)

REAL#4 CC <11, 11),DD <11, 11)

REAL*4 A(M,N),U <M,N),V <M,N),SIGMA <M), WORK(M)

INPUT ft OF DATA IN PSD MUST EQUAL M

INPUT ft OF PSD COULD BE SMALL THEN N

REAL*4 A(400, 11),U(4OO, 11),V(4OO, 11), SIGMA(400),WORK(400)

CHARACTER*16 F1,F2,F3

ENTER # OF DATA IN PSD ( MUST EQUAL 4OO) '

(A)

)

)F2

' (A)' ) '

(A)')F3

ENTER ft OF PSD (LE. 11)'

ENTER INPUT FILNAM'

ENTER OUTPUT BASIC WAVEFORM FILNAM'

ENTER OUTPUT SVD COEFFICIENT FILNAM'

ENTER 1 FOR SORTING SV

ENTER 1 FOR LOG Y'

WRITE(*,'(A)')'

READ(», #)M

WRITE(*,'(A)')'

READ(*,*)N

WRITE(»,' (A)')»

READ(»,

WRITE(»,'(A)

READ(», ' (A) '

WRITE(»,

READ(», '

WRITE(»,'(A)')'

READ(*,*)IFST

WRITE(»,'(A)')'

READ (*,*) LOGY

OPEN(1,FILE=F1,STATUS='OLD' )

OPEN(2,FILE«F2,STATUS='NEW')

OPEN(3,FILE=F3,STATUS=' NEW' )

DO 1 1 = 1,N

READU,*) (A(J, I), J=1,M)

IF(LOGY.NE.1)GOTO 73

DO 78 1 = 1, N

DO 78 J=1,M

A(J, I)=ALOG1O(A(J, I) )

CONTINUE,

NM=M

CALL SVD(NM, M,N,A,SIGMA,.TRUE.,U,.TRUE. ,V, IERR,WORK)

WRITE(*,'(A)')' VECTOR NORM OF U ARE:'

DO 5O1 J=1,N

P=0.

DO 5O2 1 = 1, M

P=P+U(I, J)**£

WRITE(*,*) P

CONTINUE

WRITE(*,'(A)')'

DO 503 J=1,N

P=O.

DO 504 1=1,N

p=p+V(I,J)**2

WRITE(*,*)P

CONTINUE

WRITE(*,'(A)')'

IFdFST.EQ. DTHEN

DO 777 1 = 1, N

WK(I)=SIGMA(I)

CALL SORT(WK, UK, N)

ELSE

DO 333 1 = 1, N

UK (I) = I

VECTOR NORM FOR V ARE:'

SINGULAR VALUES ARE:'
D

1

2

1

2

1

2

2

1

2

1

1

1

Linett

6O

61

62

63

64

65

66

6^

68

69

7O

71

72

73

74

75

76

77

78

79

8O

81

82

83

84

1

C

2

3

666

201

2O2

4

7

ENDIF

WRITE <*, ' (A)' )' SORTINB ORDER OF

WRITE<*,*) (SISMAdJKd) >, 1 = 1, N)

IFdERR.NE.O)WRITE<*,2> IERR

FORMAT <'• TROUBLE. IERR=' , 14)

DO 3 I = 1,.N

DO 3 J=1,N

CCd,J)=Vd, J)#SIBMA<J>

DO 666 1=1, N

DO 666 J=1,N

DD(I, J>=CC(J, I)

DO 201 1=1, N

DO 201 J=1,M

A<J, I)=U<J, IJKd) >

CONTINUE

DO S02 1 = 1, N

DO 202 J=1,N

CCd, J)=DD(IJKd), J)

DO 4 J=1,N

WRITEC2,*) (fid, J), 1 = 1, M)

WRITEC3,*) <CCd, J) , 1 = 1, N)

CONTINUE

WRITE <3, *) (SISMfidJKd)), 1 = 1, N)

STOP

END

Microsoft

Page 2

01-29-86

14:O6:14

FORTRAN77 V3.20 O2/84

SINBULER VALUES:'

Name Type Offset P Class

A

ALOG10

CC

DD

Fl

F2

F3

I

IERR

IFST

UK

J

LOBY

M

N

NM

P

SIBMA

U

V

WK

WORK

REAL

REAL

REAL

CHAR*16

CHAR*16

CHAR* 16

INTESER*4

INTEBER*4

INTE6ER*4

INTEGER*4

INTEGER*4

INTESER*4

INTESER*4

INTEGER*4

INTEGER*4

REAL

REAL

REAL

REAL

REAL

REAL

39466

38498

38982

57074

57090

57106

57130

57158

57122

2

57138

57126

57066

5707O

57154

57166

36898

1698

19298

50

98

INTRINSIC

85

86

87

88

39

9O

91

SUBROUTINE SORT (X, UK, N)

DIMENSION X(1),IJK(1 )

AivtIN=X (1)

DO 1 1 = 1,N

IF( X (I) . i_T. AivlIN) AMIN= X (I)

CONTINUE

AMIN=AMIN-1OO.
D Line*

92

33

94

95

96

97

98

Name

flMIN

I

UK

MflX

N

X

Type

Page 3

Oi-29-86

14:O6:14

Microsoft FORTRflN77 V3. 20 02/84

DO £ 1=1,N

CflLL FINDMflX<X,N, MflX)

IJK<I)=MflX

X(MflX)=flMIN

CONTINUE

RETURN

END

REflL

INTEGER#4

INTEGER*4

INTEGER*4

INTEGER*4

REflL

Offset P Class

57254

57258

4 *

57270

8 *

O *

99

100

1O1

102

103

104

105

106

107

108

1O9

HO

111

Name

PMflX

I

MftX

N

X

Type

SUBROUTINE FINDMOX <X, N, MPX)

REflL*4 X ( 1 )

PMflX=X (1)

MftX=l

DO 1 1=2, N

I F ( X ( I ) . GT. flMflX ) THEN

MflX = I

ENDIF

CONTINUE

RETURN

END

REflL

INTEGER*4

INTEGER*4

INTEGER*4

REflL

Offset P Class

57274

57278

8 *

4 »

O *

112 SUBROUTINE SVD (NM, M, N, fl, W, MflTU, U, MflTV, V, IERR, RV1)

113 REflL*4 fl<NM,N),W<N),U(NM,N),V(NM,N),RV1(N)

114 LOGICflL MflTU,MflTV

115 IERR=0

116 DO 1OO 1 = 1,M

1 117 DO 100 J=1,N

2 118 U<I,J)=fl(I,J)

2 119 10O CONTINUE

120 G=O.

121 SCflLE=O.

122 flNORM=O.

123 DO 30O 1 = 1, N

1 124 L=I+1

1 1£5 RV1(I)=SCflLE*B

i ias G=O.

1 127 S=O

1 128 SCflLZ=O.

1 129 Ir (I. GT. POGOTO £1O
Page 4

01-23-86

14:06:14

D Line* 1 7 Microsoft FORTRRN77 V3. EO 02/84

1 130 DO 12O K=I,M

2 131 12O SCfll_E=SCflLE+fiBS(U<K, I))

1 132 IF(SCflLE.EQ. O. 0)GOTO 210

1 133 DO 130 K=I,M

2 134 U(K, I)=U(K, I)/SCfiLE

2 135 S=S-HJ<K, !)**£

2 136 130 CONTINUE

1 137 F=U(I, I)

1 138 G=-SIGN<SQRT<S),F)

1 139 H=F*G-S

1 14O U(I, I)'=F-G

1 141 IFd.EQ. N> GOTO 13O

1 142 DO 150 J=L,N

2 143 S=0.

2 144 DO 14O K=I,M

3 145 14O S=S-HJ<K, I)*U(K, J)

2 146 F=S/H

2 147 DO ISO K=I,M

3 148 U(K, J)=U(K, J)+F*U<K, I)

3 143 ISO CONTINUE

1 150 19O DO 20O K=I,M

2 151 200 U(K, I)=SCflLE*U<K, I)

1 152 210 Wd)=SC«LE*G

1 153 6=0.

1 154 S=0.

1 155 SCftl_E=0.

1 156 IFd.GT.M. OR. l.EQ. N)SOTO 290

1 157 DO 220 K=L,N

2 158 220 SCflLE=SCflLE+flBS(U(I,K))

1 153 IF(SCALE.EQ.O.O)GOTO 23O

1 16O DO 23O K=L,N

2 161 U(I,K)=U<I,K)/SCflLE

2 162 S=S-MJ<I,K>**2

2 163 23O CONTINUE

1 164 F=U(I^L)

1 165 G=-SIGN<SQRT(S),F)

1 166 H=F*G-S

1 ' 167 U<I,L)=F-6

1 168 DO 24O K=L,N

2 163 24O RV1<K)=U(I,K)/H

1 170 IFd.EQ. M) GOTO 270

1 171 DO 26O J=L,M

2 172 S=0.

2 173 DO 250 K=L,N

3 174 250 S=S-HJ<J, K)*Ud, K)

2 175 DO 26O K=L,N

3 176 U<J,K>=U<J,K)+S*RV1 (K)

3 177 260 CONTINUE

1 178 27O DO 28O K=L,N

2 173 280 Ud,K)=SCfll_E*Ud, K)

1 ISO 230 ftNORM=ftMflXl (flNORM, flBS (W (I) >+ftBS<RVl d) > >

1 181 3OO CONTINUE

182 IF(. NOT. MOTV)GOTO 41O

183 DO 40O 11 = 1,N

1 184 I=N+1-II

1 135 IFd.EQ. IM) GOTO 33O

1 186 IF(G. EQ. 0.0)GOTO 36O

1 187 DO 320 J=L,N

£ 188 32O V(J, I) = (Ud, J> /'J(I, L.) )/G
D I

1

2

2

"3

2

3

3

1

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191

192

193

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195

196

197

198

199

200

201

202

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2O4

£05

2O6

£07

208

209

210

211

212

£13

214

215

216

217

218

219

220

221

222

223

224

225

226

227

228

229

230

231

£32

233

234

235

£36

237

238

239

24O

£41

£4£

£43

£44

£43

£46

£47

1

340

35O

360

380

39O

4OO

41O

42O

430

44O

450

46O

47O

475

48O

49O

5OO

51O

"

52O

53O

54O

Page 5

O1-29-86

14:06:14

Microsoft FORTRPN77 V3.2O 02/84

DO 35O J=L,N

S=0.

DO 34O K=l_, N

S=S+U(I,K>*V<K, J)

DO 35O K=L, N

V(K, J)=V(K, J)+S*V<K, I)

CONTINUE

DO 380 J=L,N

V<I, J)=O.

V(J, I)=0.

CONTINUE

V(I,I)-1.

G=RV1(I)

L=I

CONTINUE

IF (.NOT. MflTU)GOTO 51O

MN=N

IF(M.LT.N)MN=M

DO 5OO II=1,MN

L=I + 1

G=W <I)

IF(I.EQ.N)GOTO 43O

DO 42O J=L,N

U(I, J)=O.

IF<G.EQ.O. )GOTO 475

IFd.EQ. MN)GOTO 46O

DO 450 J=L,N

5=0.

DO 44O K=L,M

S=S+U(K,I)*U(K,J)

F=(S/U(I, I))/G

DO 450 K=I,M

U<K, J)=U<K, J)+F*U<K, I)

CONTINUE

DO 470 J=I,M

U(J, I)=U(J, D/G

GOTO 490

DO 48O J=I,M"

U(J,I)=0.

U<I, I)=U(I, D-H.

CONTINUE

DO 700 KK=1,N

K1=N-KK

X=K1+1

ITS=0

DO 53O LL=1,K

L1=K-LL

L=Ll-t-l

IF(fiBS<RVl(L)>+PNORM.EQ.ftNORM)GOTO 565

IF(flBS(W(Ll) J-f-ANORM. EQ. flNORM)GOTO 54O

CONTINUE

C=0

5=1.

DO 560 I=L,K

F=5*RV1(I)

RV1(I)=C*RV1(I)

:F(ftBS(F)+flNORPl.EQ.ftNORM)GOTO 565

G=U<I)
j Page G

j . 01-29-86

• 14:06:14

; D Line* 1 7 Microsoft FORTRRN77 V3. 2O 02/84

! 2 248 H=SQRT<F*F+B*G>

• 2 249 W<I)=H

2 25O C=G/H

! 2 251 S=-F/H

2 252 IF (.NOT. MflTU)GOTO 56O

; 2 253 DO 550 J=1,M

; 3 254 Y=U<J,Ll>

; 3 255 Z=U(J,I)

] 3 256 U(J,L1)=Y*C+Z*S

! 3 257 U<J,I)=-Y#S+Z*C

» 3 258 550 CONTINUE

| 2 259 560 CONTINUE

J 1 260 565 Z=W(K)

i 1 261 IF(L.EQ.K)GOTQ 65O

1 262 IF(ITS.EQ.3O)GOTO 1OOO

' 1 263 ITS=ITS+1

1 264 X=W(L)

• 1 265 Y=W(K1).

! 1 266 G=RVKK1>

} 1 267 H=RV1(K)

j 1 268 F=«Y-Z)*<Y+Z) + <G-H>*<B+H> )/(2.*H*Y)

: 1 269 G=SQRT<F*F+1. )

I 1 270 F=((X-Z)*(X+Z)+H*(Y/(F+SIGN<B,F))-H))/X

; 1 271 C=l.

1 1 272 S=l.

1 273 DO 600 I1=L,Kl

i 2 274 1=11+1

j £ 275 G=RV1(I)

} 2 276 Y=W<I)

2 277 H=S*G

2 278 G=C*G

i 2 279 Z=SQRT<F*F+H*H>

2 28O RV1(I1)=Z

2 281 C=F/Z

; 2 282 S=H/Z

2 283 F=X»C+G*S

2 284 G=-X*S+G*C

2 285 - H=Y*S

; 2 286 Y=Y*C

2 287 IF<.NOT. MflTV)GOTO 575

2 288 DO 570 J=1,N

; 3 289 X=V(J, ID

3 290 Z=V<J, I)

3 291 V(J,I1)=X*C+Z*S

3 292 V(J, I)=-X*S+Z*C

: 3 293 570 CONTINUE

i 2 294 575 Z=SQRT<F*F+H*H)

2 295 W(I1)=Z

2 296 IF(Z.EQ. 0. 0)GOTO 58O

2 297 C=F/Z

2 298 S=H/Z

2 299 580 F=C*G+S*Y

2 3OO X=-S*G-»-C*Y

2 3O1 IF (.NOT. MflTU)GOTO 60O

2 3O2 DO 59O J=l,M

3 3O3 Y=U(J,II)

3 3O4 Z=U(J,I)

3 3O5 LKJ, I1)=Y*C + Z*B

3 3O6 U(J,I)=-Y*S+Z*C
D:

3

2

•4

^

1

1

1

1

1

1'

L.

£'•

1'

Line*

3O7

308

3O9

31O

311

312

313

314

315

316

317

318

319

32O

321

322

1

590

600

650

690

700

10OO

1 OO 1

Page 7

01-29-86

14:06:14

Microsoft FORTRflN77 V3.£0 0£/S4

Name

ft

fiBS

ftMftXl

ftNORM

C'

F

:

GH

i:

ii

IERR

II

ITS

T

*J

KKl

KK

!__

LI

LL

M

MftTU

MftTV

MN

N

NM

RV1

S

SCftLE

SIGN

SORT

U

V

w

X

Y

z

Type

REftL

REAL

REftL

REflL

REftL

REflL

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTE6ER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

INTEGER*4

LOBICflL*4

LOGICOL*4

INTEGER*4

INTEGER*4

INTEGER*4

REftL

REftL

REftL

REftL

REflL

REfti_

REftu

REftu

REfti_

CONTINUE

CONTINUE

RV1(L)=O.

RV1(K)=F

W(K)=X

GOTO 520

IFCZ.GE. 0.0) GOTO 7OO

W(K)=-Z

IF (.NOT. MflTV)GOTO 70O

DO 690 J=1,N

V<J,K)=-V<J,K>

CONTINUE

GOTO 1001

IERR=K

RETURN

END

Offset P Class

12 *

5731O

57478

57338

5730£

57342

57286 .

575O2

36 *

5739O

57462

57294

57326

57458

5745O

57318

57474

57466

4 *

£O *

£8 *

57418

8 *

O *

4O *

57322

57306

INTRINSIC

INTRINSIC

INTRINSIC

INTRINSIC

24 *

32 *

16 *

57498

57490
APPENDIX A

FLOW DYNAMIC ENVIRONMENT

DATA BASE DEVELOPMENT FOR THE SSME

C. V. Sundaram

wyle Laboratories, Huntsville

Abstract

This paper describes the studies being carried

out on the fluid flow-induced vibration of the Space

Shuttle main engine (SSME) components. This study is

being carried out with a view to correlating the frequency characteristics of the pressure fluctuations in

a rocket engine to its operating conditions and geometry. An overview of the data base development for

SSME test firing results and the interactive computer

software used to access, retrieve, and plot or print

the results selectively for given thrust levels,

engine numbers, etc., is presented. The various statistical methods available in the computer code for

data analysis are discussed. Plots of test data,

nondimensionalized using parameters such as fluid flow

velocities, densities, and pressures, are presented.

Comparative studies of these results with results

available in the literature are made. Correlations

between the resonant peaks observed at higher frequencies in power spectral density plots with pump geometry and operating conditions are discussed. Finally,

an overview of the status of the investigation is presented and future directions are discussed.

Introduction

The development efforts expended on the main

engine of the Space Shuttle has resulted in the evolution of highly complex machinery which is capable of

generating high thrust levels. Even from the earliest

days of spacecraft engine development, achieving the

highest possible specific thrust, based on engine

weight or overall size, has been identified as one of

the prime goals. The earlier spacecraft, however,

were equipped with power sources which were designed

for just one mission. The advent of the concept of

reusable space vehicles added a new dimension to the

A-l
engine design/ that they not only satisfy the requirements on thrust but also that they be capable of

carrying out multimissions into outer space with,

ideally/ the least amount of maintenance and component

replacements between missions. This has imposed a

greater emphasis on preventing failures and prolonging

the fatigue life expectancy of the SSME during operation. Furthermore, specific knowledge relating to the

frequency characteristics of the pressure fluctuations in rocket engine systems is not well understood.

It is important to understand the functional relationships between pressure fluctuations in these systems

in terms of the geometrical and performance characteristics because of their effect on hardware

lifetime.

The SSME has been subjected to extensive hot

firing and flow tests. During these tests, system

failures and malfunctions have occurred from time to

time. These failures range from wear on component

bearings and flow-induced failures to explosions due

to intense pressure fluctuations and accompanying

dynamic stresses in the pumps, valves, and/or propellant lines. The large volume of data on pressure

fluctuations, strain, and acceleration obtained from

these tests provide a good basis for studies on the

flow-induced vibrations taking place in the SSME.

The sheer volume of test data available makes it

absolutely essential that a computerized data base

management system be employed to perform any meaningful analysis. wyle Laboratories is engaged in the

development of such a data base management software.

This paper provides an overview of the work being performed on the software development and discusses the

method of approach suggested for analyzing the data.

SSME Data Base Management

The SSME data base management and analysis system

developed at wyle Laboratories has been designed for

use on an Interdata 8/32 computer system and other

computer systems utilizing similar file name

structures.

A-2
Data Piling System

The data base management system is designed to

accommodate two types of data: time histories and

power spectral density or other frequency domain data.

The time history (rms pressure or thrust) data files

consist of a pair of values in each record, the first

value being the number of seconds into the test and

the second being the magnitude. The file may consist

of any number of data points (records), but most of

the routines presently have an upper limit of 500

points.

Each PSD file consists of a single real number in

each record. These are the spectral magnitudes.

Since the PSD test data is recorded using constant

bandwidth filters, the frequencies corresponding to

each PSD value is automatically calculated by the program when the frequency range is entered. A considerable saving in computer disc storage space has been

realized by this method because of the large amount of

PSD data involved.

Data entry into files can be performed through a

digitizing tablet. When the volume of data is large/

however, use of a digitizing tablet can be very time

consuming. Hence the data in this case is directly

read from a digital tape using the dedicated magnetic

tape drive units. File names are automatically

assigned by the software based on test numbers/ engine

numbers, channel descriptors, etc., to uniquely identify each data set. Figure 1 provides an insight into

the operational sequences and capabilities of the SSME

data base management and analysis software.

Figure 2 shows a- plot of power versus time/ and

figure 3 shows the rms pressure variations with time

for the low pressure fuel pump. These plots were

generated using the data retrieval system described

above. Figures 4 shows a PSD plot generated from the

digitized data for the high pressure oxidizer pump.

The input to the computer to generate these plots are

the file names for the time history plots and the test

A-3
number/ time slice/ and maximum frequency for the PSD

plots.

Statistical parameters/ such as mean/ standard

deviation/ cms values/ third and fourth central

moments/ and minimum and roaxlTnv" values and range/ cart

be calculated and plotted with ease for any number of

data sets selected based on engine/ HPFP, and HFOP

numbers; thrust level; and channel descriptors. The

abscissa and the ordinate can have any combination of

linear and logarithmic scales/ and any statistical

parameter can be plotted against any other or a frequency scale. The uniqueness of the set of PSDs

selected for statistical analysis can be controlled by

specifying or leaving out/ in any combination/ the

engine/ HPOP/ and HPFP numbers.

A detailed description of all the capabilities of

the data base management and analysis software is presented in reference 1.

General Character of Turbomachinery Noise

Background

The jet noise theory gained importance with

increasing use of jet engines in aircraft. It is well

known that the acoustic power generated by a jet

exhaust is strongly dependent^ on the exit velocity

(Lighthill's 8th power law ). However/ during

approach configuration of the aircraft/ when the jet

noise level is generally low/ the engine compressor

noise was observed to be a major noise source. The

study of compressor noise/ especially the multistage

axial flow types/ has acquired great importance during

the last 25 years.

Noise Sources in Axial Flow Compressors

In general/ the noise spectra of different types

of compressors exhibit similar gross characteristics.

In this paper/ we limit our attention to axial flow

compressors because it is believed that their noise

characteristics should be more relevant to the noise

A-
generation mechanism of the axial flow pumps on the

SSME.

The general form of an acoustic spectrum of an

axial flow compressor would indicate broadband noise

extending over a wide range of frequencies. Superimposed on this are a number of discrete peaks which

represent the blade passage frequencies and their

harmonics*

The broadband noise component has been attributed

to various mechanisms. At least three that merit consideration are

1. The random force fluctuations due to a moving

flow on the surface. These fluctuations can be interpreted to act as acoustic sources located within the

turbulent boundary layer.

2. The shedding of vortices from the trailing edges

of a body immersed in a moving fluid. This vortex

shedding imparts to the body fluctuating lift forces

that are periodic at low Reynolds number flows and

become random as the Reynolds number increases. (It

is believed that the periodic component of the shedding does not disappear completely.) This random excitation force of vortex shedding is also considered to

be instrumental in the broadband characteristic of the

acoustic spectrum.

3. A turbulent flow at the inlet to the compressor

sets up fluctuating forces due to flow incidence on

the surface. The perturbation velocity component in a

turbulent flow is random in nature/ and hence the

acoustic energy due to the fluctuating forces can be

expected to have a broadband nature.

Another significant broadband component in the

case of the SSME would be the structurally transmitted

secondary vibrations due to the close proximity of the

components, all having highly turbulent flow taking

place within them. A challenging task in the analysis

of SSME component vibration is the development of a

prediction scheme that will provide quantitative

A-5
estimates of the acoustic energy due to flow-induced

and structurally transmitted vibrations in a frequency

spectrum at various locations on the SSME.

The pure tones, which are a result of the spinning modes of the pressure field, exhibit decaying

trends downstream of the rotor when the impeller tip

Mach number is below critical, as in the case of a

subsonic rotor. For a rotor-stator combination, however, a number of spinning modes are generated, many

of which spin at Mach numbers above the critical tip

Mach numbers, and these modes exhibit strong propagation characteristics.

SSME Flow-Induced Vibration Characteristics

In this section, preliminary studies conducted on

pressure spectra obtained from SSME firing tests are

discussed. Fluid flow variables, which may be of

lesser importance in conventional axial flow compressors, but which may be of greater significance in the

SSME flow environment, are highlighted.

The initial efforts in the data analysis have

been directed toward obtaining nondimensional PSD as a

function of Strouhal number. The power spectral densities, which have dimensions of mean square pressure

per hertz, were normalized as follows:

D (1)

where S is nondimensional PSD, Q_(f) is the measured

PSD, pf

p is the local fluid density, V is the mean

velocity, and D is a characteristic length. Strouhal

number is defined as

St » fD/V (2)

*

where f is the frequency.

Figures 5 and 6 show nondimensionalized PSD plotted as a function of Strouhal number for the high

pressure oxidizer pump discharge pressure. Similar

analyses have been carried out to estimate the

A-6
pressure fluctuations due to turbulent flow of water

at the wall of a duct. Figure 7, reproduced from

reference 5, shows the pressure fluctuation dependence

on Strouhal number. Figures 5, 6, and 7 indicate

similar trends in the variation of nondimensionalized

PSD for increasing Strouhal number. The scaling

applied to the SSME data is based on the assumption

that the pressure fluctuations are flow induced. This

assumption is somewhat oversimplified as it does not

address the various other noise-generating mechanisms

present during turbomachinery operation.

6

Dimensional analysis studies of blower noise

provide a functional relationship,

B - F(D,N,Q,f,p,;t, C) (3)

where E is the acoustic power/hertz; D, the blower

diameter; N, the rpm; Q, the flow rate; f, the frequency; p, the fluid density; \L, the viscosity; and C,

the acoustic speed. A similar analysis on the SSME

turbopump would require accounting for the acoustic

propagation characteristic of the structure.

Another important factor that should be considered is the fluid properties. The fluid flow

conditions in the SSME undergo extreme variations in

temperature and pressure. The mechanism of propagation of disturbances in fluids at extremely low temperatures and very high pressures requires further

studies for proper mathematical modeling. Since the

fluid flow conditions experience wide variations in

the SSME, it is reasonable to expect variations in

local propagation velocities and hence local Mach

numbers.

The studies on the flow dynamic environment of

the SSME being carried out at Wyle Laboratories are

directed toward applying the existing theories on

noise generation mechanism in turbomachinery after

modifications to reflect the flow environment present

in the SSME. An approach that would involve developing an empirical formulation rather than a very rigorous and purely analytical solutions seems to indicate

A-7
pranise. The basic idea involves modeling the noise

generation mechanism due to turbulent flow and the

pressure pulses generated by the spinning modes of the

pressure field due to rotor-stator interactions separately and combining the two components to obtain the

total frequency spectrum. That an empirical approach,

though somewhat complicated, is not totally Impossible

has been amply demonstrated through similar studies

performed by Van Niekerk and others.

Acknowledgements

The author wishes to acknowledge the help provided by Mr. T. Coffin in directing the research

efforts, Or. G» T. Meares, the chief architect of the

data base software development. This project was

sponsored by the NASA, Marshall Space Flight Center

under contract No. NAS8-34343.

References

1. Meares, 6., T. Coffin, and J. Reinhardt. Flow

Dynamic Environments in High Performance Rocket

Engines." Wyle Laboratories Research Staff Technical

Memorandum TM 84-01, Jan. 1984.

2. Lighthill, M. J. On Sound Generated Aerodynamically, II, Turbulence as a Source of Sound. Proc. Roy.

Soc., A222, 1954, pp. 1-32.

3. Sharland, I. J. Sources of Noise in Axial Flow

Fans. J. Sound Vib., V. 1, No. 3, July 1964.

4. Tyler, J. M., and T. G. Sofrin. Axial Flow Compressor Noise Studies. Soc. Auto. Engr., Aeronautical

meeting, preprint 345D, 1961.

5. Clinch, J. M. Prediction and Measurement of the

Vibrations Induced in Thin-Walled Pipes by the Passage

of Internal Turbulent Water Flow. J. Sound Vib.,

V. 12, NO. 4, 1970, pp. 429-451.

A-8
6. Maling, 6. C. Jr. Dimensional Analysis of Blower

Noise. J. Acoust. Soc. Am., V. 33, No. 10, Oct.

1963, pp. 1556-1564.

7. Van Niekerk, C. G. Noise Generation in Axial

Plow Pans. J. Sound Vib., V. 3, No. 1, Jan. 1966.

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langim

looaratlng

IparanMtara

-j-Maan

-Standard deviation

-rma

—Third uanbal nratnant

-fourtfi'cantral momant

-Mlninumi valuo

-Maximum valuo (•nvatopa)

Caleulato

nondlnwnalonaib

data and plot

Figure 1. SSME data base management and analysis

software operational sequence and capabilities

A-9
I

M

^

•

a*

1

a

*

730121 THRUST

IM 309

TIM (not

Figure 2. SSME power level variations as a function

of time

Figure 3. rras pressure time history at the inlet of

the low pressure fuel pump

.A-10
W1304 HPOP OS PR - S* 9.0

10,000 10,000

Figure 4. Power spectral density of the high pressure

oxidizer pump discharge pressure 5 seconds after SSME

startup

10

,-T

fl-".

to

MUM HPOP OS ?B S* 5J

10

-I

10 10" 101

10*

Figure 5. Nondimensionalized frequency spectrum for

high pressure oxidizer pump discharge pressure, 5

seconds after SSME startup

A-11
10

ur

I if

10

10

901301 UPOP D9 n .3* 4000)

10 10 10" 10* 10*

Figure 6. Nondimensionalized frequency spectrum for

high pressure oxidizer pump discharge pressure 400

seconds after SSME startup

CH

AO o

Extrantous

low fraqwncy

KO IOO 1000

Strauhdncx* >

Figure 7. Frequency spectrum of turbulent wall pressure field. (O), 267 in/sec; (A) 450 in/sec; (a) 520

in/sec3

A-12