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TABLE OF CONTENTS

PART 2

APPENDICES

APPENDIX A:

APPENDIX B:

APPENDIX C:

APPENDIX D:

APPENDIX E:

DAST ARW-2 AERODYNAMIC, INERTIA AND THRUST DATA

DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION

STUDY

DAST ARW-2 FINAL FLUTTER SUPPRESSION SYSTEM

PERFORMANCEDATA

DAST ARW-2 SENSITIVITY ANALYSIS DATA

DAST ARW-2 AUTOMATIC CONTROL SYSTEM (ACS) AND

AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS) ROOT LOCl

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55

101

136

176
LIST OF FIGURES

FIGURE

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LONGITUDINAL STABILITY DERIVATIVES AND TRIM COEFFICIENTS

LATERAL-DIRECTIONAL STABILITY DERIVATIVES

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK,

LAUNCH CONDITION

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACKp

LAUNCH CONDITION

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK,

MLA TEST CONDITION

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK,

MLA TEST CONDITION

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK,

MLA DESIGN CONDITION

PITCHING MOMENTCOEFFICIENT VERSUS ANGLE OF ATTACK,

MLA DESIGN CONDITION

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK,

GLA TEST CONDITION

PITCHING MOMENTCOEFFICIENT VERSUS ANGLE OF ATTACK,

GLA TEST CONDITION

LIFT COEFFICIENT VERSUS ANGLE OF ATTACKp

GLA DESIGN CONDITION

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK,

GLA DESIGN CONDITION

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK,

HIGH ALTITUDE CONDITION

PITCHING MOMENTCOEFFICIENT VERSUS ANGLE OF ATTACK,

HIGH ALTITUDE CONDITION

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK,

CRUISE CONDITION

PITCHING MOMENTCOEFFICIENT VERSUS ANGLE OF ATTACK,

CRUISE CONDITION

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK,

MAXIMUM DYNAMIC PRESSURE CONDITION

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FIGURE

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LIST OF FIGURES (CONTINUED)

PITCHING MOMENT COEFFICIEICT VERSUS ANGLE OF AI-FACK,

MAXIMUM DYNAMIC PRESSURE CONDITION

MOMENT OF INERTIA

DRAG COEFFICIENT VERSUS ANGLE OF AI-FACK AT

MACH: 0.60, WITH SPEEDBRAKES

DRAG COEFFICIENT VERSUS ANGLE OF ATTACK AT

MACH: 0.70, WITH SPEEDBRAKES

DRAG COEFFICIENT VERSUS ANGLE OF AI-I'ACKAT

MACH: 0.80, WITH SPEEDBRAKES

DRAG COEFFICIENT VERSUS ANGLE OF ATTACK AT

MACH: 0.90, WITH SPEEDBRAKES

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK AT

MACH: 0.60, WITH SPEEDBRAKES

LIFT COEFFICIENT VERSUS ANGLE OF AI-I'ACKAT

MACH: 0.70, WITH SPEEDBRAKES

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK AT

MACH: 0.80, WITH SPEEDBRAKES

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK AT

MACH: 0.90, WITH SPEEDBRAKES

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK

AT MACH: 0.60, WITH SPEEDBRAKES

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF AI-I'ACK

AT MACH: 0.70, WITH SPEEDBRAKES

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF AI-rACK

AT MACH: 0.80, WITH SPEEDBRAKES

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK

AT MACH: 0.90, WITH SPEEDBRAKES

THRUST DATA FOR 80 PERCENT ENGINE RPM

THRUST DATA FOR 85 PERCENT ENGINE RPM

THRUST DATA FOR 90 PERCENT ENGINE RPM

THRUST DATA FOR 95 PERCENT ENGINE RPM

THRUST DATA FOR 100 PERCENT ENGINE RPM

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FIGURE

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LIST OF FIGURES (C(]NTINUED)

DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION STUDY

SYMMETRIC ELASTIC MODE

MACH: 0.80, ALTITUDE:

SYMMEIIRIC ELASTIC MODE

MACH: 0.83, ALTITUDE:

SYMMETRIC ELASTIC MODE

MACH: 0.86, ALTITUDE:

SYMMETRIC ELASTIC MODE

MACH: 0.83, ALTITUDE:

SYMMETRI C ELASTIC MODE

MACH: 0.86, ALTITUDE:

SYMMETRIC ELASTIC MODE

MACH: 0.91, ALTIIIJDE:

DAMPING AND FREQUENCY,

2,000 FEET, UNSCALED EOM

DAMPING AND FREQUENCY,

3,000 FEET, UNSCALED EOM

DAMPING AND FREQUENCY,

4,500 FEET, UNSCALED EOM

DAMPING AND FREQUENCY,

12,000 FEET, UNSCALED EOM

DAMPING AND FREQUENCY,

15,000 FEET, UNSCALED EOM

DAMPING AND FREQUENCY,

8,000 FEET, UNSCALED EOM

ANTISYMMETRIC ELASTIC MODE DAMPING AND FREQUENCY

WITH PARAIVETER SCHEDULING, MACH: 0.86,

ALTITUDE: 4,250 FEET, UNSCALED EOM

ANTISYMMETRIC ELASTIC MODE DAMPING AND FREQUENCY

WITH PARAMETER SCHEDULING, MACH: 0.83,

ALTITUDE: 12,000 FEET, UNSCALED EOM

ANTISYMMETRIC ELASTIC MODE DAMPING AND FREQUENCY

WITH PARAMETER SCHEDULING, MACH: 0.86,

ALTITUDE: 15,000 FEET, UNSCALED EOM

ANTISYMMETRI C ELASTIC MODE DAMPING AND FREQUENCY

WITH PAPjMVETER SCHEDULING, MACH: 0.91,

ALTITUDE: 8,000 FEET,

SYMMETRIC FLLFFTER MODE 0.80

SYMMETRIC FLUTTER MODE 0.83

SYMMETRIC FLUT'IIERMODE 0.86

SYMMETRIC FLLFFTER MODE 0.91

ANTISYMMETRIC FLUTTER MODE DAMPING, MACH:

ANI ISYMMETIRIC FLUTTER MODE DAMPING, MACH:

UNSCALED EOM

DAMPING, MACH:

DAMPING, MACH:

DAMPING, MACH:

DAMPING, MACH:

0.80

0.83

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FIGURE

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LIST OF FIGURES (CONTINUED)

ANTISYMMETRIC FLUTTER MODE DAMPING, MACH:

ANTISYMMETRIC FLUTTER MODE DAMPING, MACH:

SYMMETRIC FLUTTER MODE DAMPING, ALTITUDE:

0.86

0.91

15,000 FEET

ANTISYMMETRIC FLUTTER MODE DAMPING, ALTITUDE: 15,000 FEET

SYMMETRIC FLUTTER MODE DAMPING, ALTITUDE: 12,000 FEET

ANTISYMMETRIC FLUTTER MODE DAMPING, ALTITUDE= 12,000 FEET

PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, NOMINAL SYSTEM,

MACH: 0.80, ALTITUDE= 2,000 FEET 124

PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, NOMINAL SYSTEM,

MACH: 0.83, ALTITUDE: 3,000 FEET 125

PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, NOMINAL SYSTEM,

MACH: 0.83, ALTITUDE: 12,OO0 FEET 126

PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, NOMINAL SYSTEM,

MACH: 0.86, ALTITUDE: 4,250 FEET 127

PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, NOMINAL SYSTEM,

MACH: 0.86, ALTITUDE: 15,000 FEET 128

PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, NOMINAL SYSTEM,

MACH: 0.91, ALTITUDE: 8,000 FEET 129

PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS, NOMINAL SYSTEM,

MACH: 0.80, ALTITUDE: 2,000 FEET 130

PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS, NOMINAL SYSTEM,

MACH: 0.83, ALTITUDE: 3,000 FEET 131

PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS, NOMINAL SYSTEM,

MACH: 0.83, ALTITUDE: 12,000 FEET 132

PBASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS, NOMINAL SYSTEM,

MACH: 0.86, ALTITUDE: 4,250 FEET 133

PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS, NOMINAL SYSTEM,

MACH: 0.86, ALTITUDE: 15,000 FEET 134

PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS, NOMINAL SYSTEM,

MACH: 0.91, ALTITUDE: 8,000 FEET 135

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FIGURE

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LIST OF FIGURES (CONTINUED)

SYMMETRIC SENSOR LOCATION SENSITIVITY 138

ANTISYMMETRIC SENSOR LOCATION SENSITIVITY .141

NOTCH FILTER TRANSFER FUNCTION FOR SENSITIVITY STUDIES 144

SYMMETRIC NOTCH FILTER SENSITIVITY TO NOTCH FREQUENCY,

85 RAD. NOTCH 145

SYMMETRIC NOTCH FILTER SENSITIVITY TO NOTCH FREQUENCY,

170 RAD. NOTCH 146

SYMMETRIC NOTCH FILTER SENSITIVITY TO NOTCH MAGNITUDE,

85 RAD. NOTCH 147

SYMMETRIC NOTCH FILTER SENSITIVITY TO NOTCH MAGNITUDE,

170 RAD. NOTCH 148

AN'I'ISYMIVETRIC NOTCH FILTER SENSITIVITY TO NOTCH FREQUENCY,

110 RAD. NOTCH 149

ANTISYMMETRIC NOTCH FILTER SENSITIVITY TO NOTCH FREQUENCY,

230 RAD. NOTCH 150

ANTISYMMETRIC NOTCH FILTER SENSITIVITY TO NOTCH MAGNITUDE,

110 RAD. NOTCH 151

ANTISYMMETRIC NOTCH FILTER SENSITIVITY TO NOTCH MAGNITUDE,

230 RAD. NOTCH 152

PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, NOMINAL SYSTEM 153

PHASE-GAIN ROOT.LOCUS OF SYMMETRIC FSS WITH AR-25

SERMOVALVE 154

ROOT LOCUS OF SYMMETRIC AND ANTISYMMETRIC FSS WITH

SERIES 30 SERVOVALVE 155

PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS, NOMINAL SYSTEM 156

PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS WITH AR-25

SERVOVALVE 157

PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, EFFECTS OF

UNCOMPENSATING ACTUATOR 158

PHASE-GAIN ROOT LOCUS OF ANT ISYMMETRIC FSS, EFFECTS OF

UNCOMPENSATINGACTUATOR 159
FIGURE

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LIST OF FIGURES (CONTINUED)

SYMMETRIC FSS SENSITIVITY TO SURFACE-ACTUATOR MODE

CHANGES

PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, EFFECTS OF A 20%

SURFACE-ACTUATOR MODE FREQUENCY INCREASE

PHASE'GAIN ROOT LOCUS OF SYMMETRIC FSS, EFFECTS OF A 20%

SURFACE-ACTUATOR MODE FREQUENCY DECREASE

SYMMETRIC FSS SENSITIVITY TO PRESSURE FEEDBACK GAIN

REDUCTION

PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, EFFECTS OF A 30%

PRESSURE FEEDBACK MODE FREQUENCY REDUCTION

ANTISYMMETRIC FSS SENSITIVITY TO PRESSURE FEEDBACK GAIN

REDUCTI ON

PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS WITH A 30

PERCENT PRESSURE FEEDBACK GAIN REDUCTION

HINGE MOMENT SENSITIVITY, OUTBOARD SERVOACTUATOR

GAIN AND PHASE RESPONSE @ 23.8 HZ

EFFECT OF HINGE MOMENT ON OUTBOARD SERVOACTUATOR

AMPLITUDE FREQUENCY RESPONSE

EFFECT OF HINGE MOMENT ON OUTBOARD SERVOACTUATOR

PHASE FREQUENCY RESPONSE

EFFECT OF MAXIMUM AIDING HINGE MOMENT ON OUTBOARD

SERVOACTUATOR

EFFECT OF HINGE MOMENT ON SYMMETRIC FSS

PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, MAXIMUM

HINGE MOMENT AIDING (230 IN-LBS)

EFFECT OF HINGE MOMENT ON ANTISYMMETRIC FSS,

UNCOMPENSATED ACTUATOR

PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS,

MAXIMUM HINGE MOMENT AIDING (230 IN-LBS)

EFFECT OF ACS ON FUSELAGE MODE SYMMETRIC AIRPLANE

ROOT LOCI FIGURE IDENTIFICATION

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FIGURE

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L IST OF F IGURES (CONTI NUED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC

AIRPLANE FOR FOI:_/ARDC.G. MLA TEST CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH

PCS CLOSED FOR FOI:_/ARDC.G. MLA TEST CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

AND GLA CLOSED FOR FORWARD C.G. MLA TEST CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS

CLOSED FOR FORWARD C.G. MLA TEST CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED

FOR FORWARD C.G. MLA TEST CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA

CLOSED FOR FORWARD C.G. MLA TEST CONDITION

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS

CLOSED FOR FORWARD C.G. MLA TEST CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC

AIRPLANE FOR AFT C.G. MLA TEST CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

CLOSED FOR AFT C.G. MLA TEST CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

AND GLA CLOSED FOR AFT C.G. MLA TEST CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS

CLOSED FOR AFT C.G. MLA TEST CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED

FOR AFT C.G. MLA TEST CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA

CLOSED FOR AFT C.G. MLA TEST CONDITION

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH

RSS, PCS AND GLA STABILIZER LOOPS CLOSED FOR AFT C.G.

MLA TEST CONDITION

DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI

WITH RSS, PCS AND GLA AILERON LOOPS CLOSED FOR AFT

C.G. MLA TEST CONDITION

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FIGURE

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LIST OF FIGURES (CONTINUED)

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS

CLOSED FOR AFT C.G. MLA TEST CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC

AIRPLANE FOR FORWARD C.G. GLA TEST CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

CLOSED FOR FORWARD C.G. GLA TEST CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

AND GLA CLOSED FOR FORWARD C.G. GLA TEST CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS

CLOSED FOR FORWARD C.G. GLA TEST CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED

FOR FORWARD C.G. GLA TEST CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA

CLOSED FOR FORWARD C.G. GLA "rEST CONDITION

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH

RSS, PCS AND GLA STABILIZER LOOPS CLOSED FOR FORWARD

C.G. GLA TEST CONDITION

DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI

WITH RSS, PCS AND GLA AILERON LOOPS CLOSED FOR

FORWARD C.G. GLA TEST CONDITION

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS

CLOSED FOR FORWARD C.G. GLA TEST CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC

AIRPLANE FOR AFT C.G. GLA TEST CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

CLOSED FOR AFT C.G. GLA TEST CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

AND GLA CLOSED FOR AFT C.G. GLA TEST CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS

CLOSED FOR AFT C.G. GLA TEST CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED

FOR AFT C.G. GLA TEST CONDITION

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FIGURE

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LIST OF FIGURES (CONTINUED)-

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA

CLOSED FOR AFT C.G. GLA TEST CONDITION

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH

RSS, PCS AND GLA STABILIZER LOOPS CLOSED FOR AFT C.G.

GLA TEST CONDITION

DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI

WITH RSS, PCS AND GLA AILERON LOOPS CLOSED FOR AFT

C.G. GLA TEST CONDITION

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS

CLOSED FOR AFT C.G. GLA TEST CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC

AIRPLANE FOR FORWARD C.G. LAUNCH CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

CLOSED FOR FORWARD C.G. LAUNCH CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

AND GLA CLOSED FOR FORWARD C.G. LAUNCH CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS

CLOSED FOR FORWARD C.G. LAUNCH CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED

FOR FORWARD C.G. LAUNCH CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA

CLOSED FOR FORWARD C.G. LAUNCH CONDITION

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS

CLOSED FOR FORWARD C.G. LAUNCH CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC

AIRPLANE FOR AFT C.G. LAUNCH CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

CLOSED FOR AFT C.G. LAUNCH CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

AND GLA CLOSED FOR AFT C.G. LAUNCH CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS

CLOSED FOR AFT C.G. LAUNCH CONDITION

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272

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FIGURE

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166

LIST ON FIGURES (CONTINUED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED

FOR AFT C.G. LAUNCH CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA

CLOSED FOR AFT C.G. LAUNCH CONDITION

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH

RSS, PCS AND GLA STABILIZER LOOPS CLOSED FOR AFT C.G.

LAUNCH CONDITION

DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI

WITH RSS, PCS AND GLA AILERON LOOPS CLOSED FOR AFT

C.G. LAUNCH CONDITION

DAST ARW-2 I_3S SYSTEM GAIN/PHASE ROOT LOCI WITH RSS

CLOSED FOR AFT C.G. LAUNCH CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC

AIRPLANE FOR FORWARD C.G. HIGH ALTITUDE CONDITION

DAST ARW'2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

CLOSED FOR FORWARD C.G. HIGH ALTITUDE CONDITION

DASTARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

AND GLA CLOSED FOR FORWARD C.G. HIGH ALTITUDE

CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS

CLOSED FOR FORWARD C.G. HIGH ALTITUDE CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED

FOR FORWARD C.G. HIGH ALTITUDE CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA

CLOSED FOR FORWARD C.G. HIGH ALTITUDE CONDITION

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS

CLOSED FOR FORWARD C.G. HIGH ALTITUDE CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC

AIRPLANE FOR AFT C.G. HIGH ALTITUDE CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

CLOSED FOR AFT C.G. HIGH ALTITUDE CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

AND GLA CLOSED FOR AFT C.G. HIGH ALTITUDE CONDITION

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II
FIGURE

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178

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181

LIST OF FIGURES (CONTINUED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS

CLOSED FOR AFT C.G. HIGH ALTITUDE CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED

FOR AFT C.G. HIGH ALTITUDE CONDITION

DAST ARW-2 PCS GAIN/PHASE RooT LOCI WITH RSS AND GLA

CLOSED FOR AFT C.G. HIGH ALTITUDE CONDITION

DAST

RSS,

HIGH

ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH

PCS AND GLA STABILIZER LOOPS CLOSED FOR AFT C.G.

ALTITUDE CONDITION

DAST

WITH

C.G.

ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI

RSS, PCS AND GLA AILERON LOOPS CLOSED FOR AFT

HIGH ALTITUDE CONDITION

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCl WITH RSS

CLOSED FOR AFT C.G. HIGH ALTITUDE CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC

AIRPLAI_Z FOR FORWARD C.G. CRUISE CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

CLOSED FOR FORWARD C.G. CRUISE CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

AND GLA CLOSED FOR FORWARD C.G. CRUISE CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS

CLOSED FOR FORWARD C.G. CRUISE CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED

FOR FORWARD C.G. CRUISE CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA

CLOSED FOR FORWARD C.G. CRUISE CONDITION

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS

CLOSED FOR FORWARD C.G. CRUISE CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC

AIRPLANZ FOR AFT C.G. CRUISE CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

CLOSED FOR AFT C.G. CRUISE CONDITION

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320

322

324

326

328

330

332

334

336

12
FIGURE

182

183

184

185

186

187

188

189

190

191

192

193

194

LIST OF FIGURES (CONTINUED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

AND GLA CLOSED FOR AFT C.G. CRUISE CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS

CLOSED FOR AFT C.G. CRUISE CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED

FOR AF-F C.G. CRUISE CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA

CLOSED FOR AFT C.G. CRUISE CONDITION

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH

RSS, PCS AND GLA STABILIZER LOOPS CLOSED FOR AFT C.G.

CRUISE CONDITION

DAST

W ITH

C.G.

ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI

RSS, PCS AND GLA AILERON LOOPS CLOSED FOR AFT

CRUISE CONDITION

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS

CLOSED FOR AFT C.G. CRUISE CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC

AIRPLANE FOR FORWARD C.G. MAXIMUM DYNAMIC PRESSURE

CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

CLOSED FOR FORWARD C.G. MAXIMUM DYNAMIC PRESSURE

CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

AND GLA CLOSED FOR FORWARD C.G. MAXIMUM DYNAMIC

PRESSURE CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS

CLOSED FOR FORWARD C.G. MAXIMUM DYNAMIC PRESSURE

CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED

FORFORWARD C.G. MAXIMUM DYNAMIC PRESSURE CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA

CLOSED FOR FORWARD C.G. MAXIMUM DYNAMIC PRESSURE

CONDITION

338

340

342

344

346

349

352

354

356

358

360

362

364

13
FIGURE

195

196

197

198

199

200

201

202

203

204

LIST OF FIGURES (CONCLUDED)

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS

CLOSED FOR FORWARD C.G. MAXIMUM DYNAMIC PRESSURE

CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC

AIRPLAI_E FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE

CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

CLOSED FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS

AND GLA CLOSED FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE

CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS

CLOSED FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED

FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA

CLOSED FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH

RSS, PCS AND GLA STABILIZER LOOPS CLOSED FOR AFT C.G.

MAXIMUM DYNAMIC PRESSURE CONDITION

DAST

W ITH

C.G.

ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI

RSS, PCS AND GLA AILERON LOOPS CLOSED FOR AFT

MAXIMUM DYNAMIC PRESSURE CONDITION

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS

CLOSED FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION

366

368

370

372

374

376

378

38O

383

386

14
INTRODUCTION

This volume contains the appendices for Boeing document D500-I0897-I,

"Design Verification and Fabrication of Active Control Systems for the

DAST ARW-2 High Aspect Ratio Wing", the final report summarizing the work

accomplished under Contract NASI-16010.

Appendix A contains data defining the aerodynamics and inertias used in

the airplane and control systems linear analyses and nonlinear simulation.

A study is presented in Appendix B that compares servoactuator bench test

results to analysis and investigates various factors that affect actuator

performance and stability. Appendix C contains data which summarizes the

airplane stability and performance with the final flutter suppression

system. The data contained in Appendix D shows stability and performance

sensitivity to variation in the dynamics and location of the control system

components. Appendix E contains data that shows the relative gain and

phase stability margins of each individual ACS and AFCS feedback loop and

the compatibility of the combined loops.

15
(This page intentionally left blank)

16
APPENDIX A

DAST ARW-2 AERODYNAMIC, INERTIA AND THRUST DATA

This appendix containsthe aerodynamic and inertia data used in airplane and

control systems linear analyses and non-linear simulation. It also contains

speed brake and thrust data used in the determination of speed brake requirements.

List of data included:

• Longitudinal derivatives

25 percent MAC C.G.

8 flight conditions

• Lateral-directional derivatives

25 percent MAC C.G.

8 flight conditions

• Non-linear CL and CM versus alpha

8 flight conditions

• Moments of inertia

3 weight-C.G, combinations, body axis

• Plots of CD versus alpha with speed brakes

• Plots of thrust versus altitude for constant Mach numbers and percent

RPM

PRECEDING PAGE BLANK NOT FILM_

pR]_C_DI_G PAGE BLANK NOT FILMED
APPENDIX A

18

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19
APPENDIX A

• MACH: 0.40

e ALTITUDE: 15,000 FEET

• STABILIZER: 0.0

;, ,; , . l ..... , ,1..;-_ .L .: .:-',:: .... _'" _ .... : : _ " : _ _4_'_---_'_

- i t ; .... : t: ; ]"

T:: : :.......... :.-t---:-:-:-] ........: -I .... _--,_:"-:: 't-:-::-:--:t.:..-1:--,:./-:: - t ..... :...... , -

r-"T _'::-__ ! t ' _ I ; t ! r' ' i ....

• l I • ] : :t : I..:/" I : I. i ' r :li i ' : :

"''I".........: 'r "::,:: ' :........' :l "':'"I:": :: ; ,_F:: : ..... 17_I:........ : " :" "-:i '' : _: "

, , . _ : : , .... • .: ; ' • . . ,, : :

- : :: :T-T:/ ::::::-:: r::: ....

........... r- / ..... i ...... :::

__:....... :._LI_ET.._:._:.G..6 _ : _ _. .......................... __

COEFFICIENT: " I . : :/-_ : . : . ;

• ::-i:! .....F-::::: .... :.:-"9:: .......:....".... r :_ ....i ...... :

:;::;: ::4i::::::::::::::::::::: ........ :::::::

-: : .:_._.,::____0_.._ : : :...... _ : ,,-:.......

................. :......; ....:-..:......._:_.: ........... :_......:-:--

...... :-_- i-: '---0_2-- ', ; - ; : , ;--_ _ ' --_---

; I : ::' : :.: .-:. I : " : . :

.......... J i-_:_:-_--: ....,--:.!:--:-:--::--:=:::.::-:-..:-:--÷:--.:-:-_.--:-_..

, !/: : .:-:: , I. _ : .: • : , r-

...........f "':....! "::m" ":....I....... :": .............. r" : "':.......:"':" , :...._-

.:.-l.::.---..--..i .... P:::-:.I:-:l::-i}-_:l=-::.{--:.::--::-.4-+--i--: :-::-::-:

: ! q : : : -' .': 1 .,. .I::: '. " ' i " _. ; i " ,

• , I .... t ........ _ ;

FIGURE 3

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK, LAUNCH CONDITION

2O

_G_NAL PAGE 15

_OR QUAL[_
APPENDIX A

ORIGINAL PAGE IS

POOR QUALITY

• MACH: 0.40

• ALTITUDE: 15,000 FEET

• STABILIZER: 0.0

t + : : L

: _ i ., ! :+"

+

• : + _ + !

............ i-o

! • +,

}

..... :........ +....... :_. +I . :

-8 :.6 -+ .-2 ........ i+::+.i+__4+

} "

FIGURE 4

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK, LAUNCH CONDITION

21
APPENDIX A

• MACH: 0.42

• ALTITUDE: 10,000 FEET

• STABILIZER: 0.0

t

I _::__ _ i___ ::_I_" i__ _-!

" -if:I-.L__ i ii-iI :i-I - -h:.i.__-_ _ 4"----i......

.......' : -_ ;-_, ._' I ! .I _ I: I : ! ' '

...._..... ..... :---;=--r--'. :--;--".-: T

I .....

•"__:I _I ....:_:I..... :_I::i_ :Y:_::b._I._:_ .

- -_ " -=_ " -_-_t--t--_

--!'--_m_-_-_d_N_-_"'-'--i LIF_:___ _I_____::: .... _.... .'--i, ................. , :

........ ;.....".....I -----:_-- I _-:--:.... - -

_ " _ . : ' --_; : .i: :1! : i, :_ I ' i ; :

i _ _ ;..: ..I....:--I-.$_ ........... _ ......; ......... : "....

i: _ . ._ " ...... , "

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; : i "UF : : i:: " _ , _ •

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......'.... _ _:-_": "-:-'_........ _ !-i: "_-::' ,

-8. -6._.-4/.,'-Z-. : ...... :2. i..g ...... 6 .... 8 .:i.10. 12

..... i.....', =/'_ _ANC___O£_ATI,_.X,_.I_EGI_EES1____._

.....___/_ _,_-,, .. :. ....,.... . .....

: J i :..I. :.... . ._ . ..:.._......_....._.

....... _" .... I " -t::"! "_,_............ "" t ". .... _""I ' ": .... ' _ '

• _I . ! V _ ; ." :. : : i .....

• :::::' ': _ I ," I : ! i

__ i, :: " ; I:i _ " i ' '

• _ L._! ....... I.... ::..__:... :. ,: ......... _......... ,i ..:..:_; .......

'i ...... : _ i" : " I : I ' ] _ : i " ' "

......... _-----G .... L_O.6! : : !

FIGURE 5

LIFT COEFFICIENT VERSUSANGLE OF ATTACK, MLA TEST CONDITION

22/

/

!
APPENDIX A

• MACH: 0°42

• ALTITUDE: 10,000 FEET

• STABILIZER: 0.0

I[. ,

' _ ' _ i i ._0.08-

.i ........{._.:_.M:...

-- E • ; " -f- ........ :..........

_ii i!.... i.... i i _ i _ i __

...!-.-'-;--;MOMEtCT--->_I.:._t4- - , ........

.----4]_-:--.L-_ -._----L _ " ---._.4'.... :----

...... ;........ :]............... ,....... /i .....

-=-o .-, -= . i:i_'_ = ,2-

i

• • ." i . _ _ • i , i _ '

" ! :. 0.02' : i !---_.'! i ,--_ ' "

......] .....i.-:] .... i...... [...... _.,ii i ....

FIGURE 6

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK, MLA TEST CONDITION

23
APPENDIX A

• MACH: 0.35

• ALTITUDE: SEA LEVEL

• STABILIZER: 0.0

" :.... ;-i .........:t-''•F_p ...... -! ........ {.... T.... :.:-T!t ....... 7-: .......... :-::

t : . ; " /: '; i J , : _ - ; :

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i i !. i i_::_ , ;!;ii : I- _; I _:-i_, i" 7.:!

....f i-_;i •:::77t!!7:77-7!7-7 :...:77:!_]--77-:t::: :77-F-::7t771!7:i---7-:i-

" r: _',w# i I,_ ........... < : '

f ............ I . t .....

FIGURE 7

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK, MLA DESIGN CONDITION

24
APPENDIX A

ORIGINAL P[_ JS

OF POOR QUALrrY

• MACH: 0.35

• ALTITUDE: SEA LEVEL

• STABILIZER: 0.0

: \; : _ ° i .... . : _ l : t i ' ! I

i. :! \i _:_:F': _ !-i _ i ! \ i ! :,

____.z._NTZ_____ - :......... ____.,-..___: ; _ .,'........ : ._.......

--.I:COEFFICIENT-_-:................... _..... :--4............... _-.._........... J..

!

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___.._____ .___..____., : ?...! .T_/---- _-

................ l " [ .......................

-8...-6 ..-;4.:::-2:.-..._ .i:...21..i:.-i!::!.:.._...:.:8_._. ]0. 12,

" ' i

FIGURE 8

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK, MLA DESIGN CONDITION

25
APPENDIX A

i MACH: 0,70

e ALTITUDE: 15,000 FEET

• STABILIZER: 0.0

L

• , t: _ I I I

i

, . ; . i t . > , t: +. : : ; " + !

; " : .... ;" . I , ...... t t ; ....

_i_:._.jL!FT_L --L--dM-_.+.........4--

i COEFFI]CIENT ! "___L::_; ' _ _

•_ _..::.i/....i":.t _ _ i : ! .

"_ " + ", .... T < _ ..... i •

_-B :-_6 _. ......... 2. _ 4...... 6.... B...... io 12

:.... ._ii: ,..... !............ _ : :-..j-.:-.:• ........ ._-:!.... :--,-. ̧•. ̧i  ̧•

.....___7_ _e:.e_ .... : i•::. ."-i:• _ :' , : "_i...... ! I ._ ; 1 ; : ; !

-I" _t ......!....:'+T-:-......._.............. _-_:_t .........!::.-:,: ......:

] t: , ! .... ' :. : : "

..... : { : ........_:::_:-7,;;7:7::j:_:::7!-:: ....:--,.7: ............ :!::-::iFIGURE 9

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK, GLA TEST CONDITION

26
APPENDIX A

ORIGIN;_L __c

OF POOR QUALITY

• MACH: 0.70

• ALTITUDE: 15,000 FEET

• STABILIZER: 0.0

- I ...... c;....... _r._ ;. , _., --:'-,-

.... z....... [PI;TCHtNG i--:.

.... _ ! MO_M]ZNT

.COEFFI_IEN! i

.o ...................... ,.........

i....._2.....

I _ I : |

-:................. - -0-,04-

............ i ....................

.!

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:_ _ t-_ i _ ! _I ̧  ̧ i

"'7"1:'T:I" _ T....... Z .... ?.... I" - '/" :........

° i t _. ;i ; i :: ]

,__: .......... ; -: .... : .... ; ........ ..... _...... ; ..

, .

............. f ' _.

} :

....T ............................

! ; : ; , ! i i

• i " I + " -....

_-8...-.'6..:_,iI .:i.;2,.i!...(J.L_i:i._i. ;i..,41 ,!.::gi..;_..8.::;::. 7jLO::,12_.

_._ _,, N.GLE_Q . t_C____E_S_L4_;,_: i i

. !..: _.i ...... : _.i.-.i.#:_i :. I :.:i..:I T . .J:. I ; -

FIGURE 10

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK, GLA TEST CONDITION

27
APPENDIX A

I MACH: 0.60

• ALTITUDE: 7,000 FEET

• STABILIZER: 0.0

......... i

< i'_ .... i---_

-:. . ! ! : i , ! . _ -

_.L i:I : i i_ i-'-i -,_ i. _I i•

T-- o

.... i I --_-_,_: i.--iI ! !-:? !._ ! L____L......

, ; _ .... ! ] ' ! i I : _ i _

-r

'........." ;i. ......'

T....:+: ..... _..!' '_!-il:!/IZT: i:::1:i'!_ " -I

#

.z .............COEFFIClIENT i

......... ,......... :_ . ,.....................

:__"1=-=r-!-7-T:":!..... i::]57.7;;. Z_.

............. __!/_i [___A,_,E _.,._.<_(._s_____

i .........

................... --- .'-_,:.2-

i / .......,

, . ,

_..,I i " " : :

i " '. ; i

! ....

i " i . IUI_

..t 1_..!.......... _ . _

7 ; 7 i i i' : i

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.... ! '"; .I '-_

: i ; i

;! i ' i I ......

i

I

. ] I

l

( : i

, i

FIGURE 11

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK, GLA DESIGN CONDITION

28
APPENDIX A

OF' POOR QUALITy

• MACH: 0.60

• ALTITUDE: 7,000 FEET

• STABILIZER: 0.0

' ' , ........... _ ...... i .... i 1 ....... i

: ; i i _ . i ,i .: t ! _ ,i: i _ ! :: F!I i

_ "i_d " " i ..... _k:_ ...._ .... _.... _.... i

i

\

-i ...... hITCIilNG;;i' :.............

........ MOMENTr................... L..................... \

i ..... ::.ii:].... ;' \

........................................... i........ T.......... i ......... {............... 2

..i!-::]'"_ ...... !--:-.i......... _ .....

L,,.

................... ---- .......0-.-02-- .... _ " ' -- _

[

" " ;.......!.......................:..I .. : ......

i

_-.L ] ' " ............

I

........ I ..........

....... i__ ,__ A_T___.._._(_1±._________......

FIGURE 12

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK, GLA DESIGN CONDITION

29
APPENDIX A

• MACH: 0o70

• ALTITUDE: 50,000 FEET

e STABILIZER: 0.0

........... _ " " _ ...... T " "T ...... _ 71 -'-$ "

_--T----T-.---_-_ . T-_._-IT'_ _ k_._._.... .,._-.

--_-_. _ _o_q--__--_ _--,

,.:_.........._. LI.E'3"...... ; • :

..:_...i __.

COEFFICIENT ___ ;;..: _ _,

!, _; _ i i-I-.- : I _, I _ _

4 ---+/-_----_'I _ i . i ,,-_ ..... --:---

. ._ ....... _ ...... _ ...... .'.......... i....... _. .

A_AIIIACJL_I !DeGI_ES)_ .....

.... T--T_O:; : _ : . : : :. .. : • ,,

i_ni_ .; : i : ! :

• :. ........... : .............. ! ............... L_" ...... !_.__. ! .:L.;. .........

FIGURE 13

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK, HIGH ALTITUDE CONDITION

30
APPENDIX A

............. MOME_

-ICOEFF_-IOIE

FIGURE 14

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK, HIGH ALTITUDE CONDITION

31
APPENDIX A

• MACH: 0.80

• ALTITUDE: 46,800 FEET

• STABILIZER: 0.0

i i.L - ".........

" i

FIGURE 15'

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK, CRUISE CONDITION

32
APPENDIX A

• MACH: 0°80

• ALTITUDE: 46,800 FEET

• STABILIZER: 0.0

..... i

OF' POOR QUAL/Ty

I : I 1

K I .... :" -'T-

!

FIGURE 16

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK, CRUISE CONDITION

33
APPENDIX A

• MACH: 0.86

• ALTITUDE: 15,000 FEET

,I STABILIZER: 0.0

!

FIGURE 17

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK, MAXIMUM DYNAMIC PRESSURE CONDITION

34
APPENDIXA

• MACH: 0.86

o ALTITUDE: 15,000 FEET

• STABILIZER: 0.0

! . i : !: _ i .:-/ X.F" i::::i!._i!_i : i :_ !

, --!......_..!-..÷--:-.--i.-+ _l-._L_i:. - !---i-:--:_.---÷-_ ...... _------ -:-.-

........... _-_........ ,.... -7...... :-._...... ,_........ i-.\!. -i........ !-...... -_-- ',_ ! _,.._ i,,t_,,_:-i-:!" ' .f . i t..':i _ _ : ;

._ ..........._#__,_----r_.; t-_--_..-_--_--: ...,.....

.._....... _............. ............... ..................... ._...._., ............ ,......... _.

, : , _ _ " t _I : : _: " _-:": t :1i_i' i..: ;

....... " " "...... : " , t" :...."r ....... : " "

.......... r.................. io- ..... .............

PITCHING:,:; ........ T" 'I"...." '; ............ ] I --

'. t. I .... _ ! ,

...._...... COEFF-IIOIENel.... i.... :--i:T!....... ::-:l"-:;-::i ...... !, *....... '

......._- T "" -'--_---_06;-:: _ ;" I " 'I ...... < ! .....: ! " : -

......... I.:_....__...z ....... _....7-;TT;;I7 i

I !

i ; 2 i

.................. : ....... _l: "_" i_'-:...." ......

! i!

............: '. ":" "'T';......

..... ' } : i " '

-_-04-' _-_ _ ......,.............

i

{ I i

I ! : i

, I .... ' .... / , " . " .....

.:Z..::..,.7¢..._.. :'_i...L._i_.._i ID 12..

ANGItF!CiF A_TTACK_(D.F_: -, . , _ES]____._.

-::"-I.... : I: ..... I::""I........ !II.......

ORIGINAL _''....""

OF POOR QUALITY

FIGURE 18

PITCHING MOMENTCOEFFICIENT VERSUS ANGLE OF ATTACK,

MAXIMUM DYNAMIC PRESSURE CONDITION

35
APPENDIX A

GROSS

WEIGHT

(LBS)

C.G.

(%MAC)

*MOMENT OF INERTIA (SLUG-FT 2)

IXX Iyy IZZ IXZ

2500 19.93 163.5 2802.0 2286.3 20.25

2350 27.40 163.3 2173.8 2236.4 22.54

2200 32.75 163.1 2146.4 2210.5 24.16

*BODY AXIS

FIGURE 19

MOMENTS OF INERTIA

36
APPENDIX A

ORIGIN,'%L F_,_.,_ {3

OF POOR Q_ALITY

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DRAG

COEFFICIENT

0.10

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I

1 2 3 4 5 6 7 8

ANGLE OF ATTACK (DEGREES)

FIGURE 20

DRAG COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0.60, WITH SPEEDBRAKES

37
APPENDIX A

ORJG£NAE PAGE IS

DR I_)OR QUALITY

DRAG

•COEFFICIENT

0.10

ANGLE OF ATTACK (DEGREES)

FIGURE 21

DRAG COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0.70, WITH SPEEDBRAKES

38
APPENDIX A

ORIGINAL PAGE IS

OF POOR QUALITY

0.22

0.20

0.18

0.16

0.14

0.04

............ :.-: -: :: _.-

5 6 7 8

ANGLE OF ATTACK (DEGREES)

FIGURE 22

DRAG COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0.80, WITH SPEEDBRAKES

39
APPENDIX A

0.22

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0.18

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DRAG "

COEFFICIENT _. 0.I0 " : ...........

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FIGURE 23

DRAG COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0,90, WITH SPEEDBRAKES

4O
ORIGI'NAL PAGE IS

OF POOR QUALITY.

APPENDIX A

ORIGINAL PAGE I_

OF POOR QUALITY

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=============== ========== ::_:-========

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ANGLE OF ATTACK (DEGREES)

FIGURE 24

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0°60, WITH SPEEDBRAKES

41
APPENDIX A

ORIGINAL PAGE IS

OF..POOR QUALITY

0,8 ........................................

0.4 ........

I 2 3 4 5 6 7

ANGLE OF ATTACK (DEGREES)

FIGURE 25

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0.70, WITH SPEEDBRAKES

42
APPENDIX A

ORIG!NAL PAGE IS

OF POOR QUALm.

LIFT

COEFFICIENT

ANGLE OF ATTACK (DEGREES)

FIGURE 26

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0.80, WITH SPEEDBRAKES

43
APPEND I X A

" " - : ........ T": ...............

FIGURE 27

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0.90, WITH SPEEDBRAKES

44
APPENDIX A

ORIGINAL PAGE IS

OF POOR QUALITY

:: : _:--- SPEEDBRAKES

0.3

:- .._- oo

20 °

400

500

I:=,: .........

- .... ::':-i 600

PITCHING

MOMENT 0

FIGURE 28

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH:

WITH SPEEDBRAKES

0.60,

45
APPENDIX A

o!dGLNAL PAGE IS

l )OR QUA.U'r 

o.3!

0.2

0.1

PITCHING

MOMENT 0

COEFFICIENT

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--!T SPEEDBPJ%KES

" Lz

_ o°

................................

_.. ..... -= ::ii::=-:;-_i:z:._:__:e=e:_=_NOT CORRECTED FOR FLEXIBILITY

FIGURE 29

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH:

WITH SPEEDBRAKES

0.70,

46
APPENDIX A

• . _. ,_ ,.J

!'_OOg :::j ITYI

PITCHING

MOMENT

COEFFICIENT

0.3 :-:-::. SPEEDBI_KES ::-':._:-::--:-:_-:..-__--;:_:--_::.-:-_:_.---:..:-_---_--._:.:.z.::::-: ._ ........

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FIGURE 30

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0.80,

WITH SPEEDBRAKES

47
APPENDIX A

"'"'""-"_AL PAGE IS

OF POOR QUALITy

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FIGURE 31

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH:

WITH SPEEDBRAKES

0.90,

48
APPENDIX A

OE I?OOR QUAJAT:_

THRUST

(LBS.)

800

700

400

300

200'

0 o 10 20 30 40 50

ALTITUDE (I000 FEET}

FIGURE 32

THRUST DATA FOR 80 PERCENT ENGINE RPM

49
APPENDIX A

THRUST

(LBS.)

_-MACH i 0.0 ....

:-_.!__'_-_-_.:=_:-_ii:.!___ _.__ MACH: O. 8 _..

...... --=._T:=-_:----_ ..... =F:'=-=:-:_ MACH: 1.O ....

900 ..: : _/_-:_-_.=!.-=-_<-:__-_\<_>__:_Fi___--_-%:<._

600 _-::- _:_-]_=:"{:==-

.:. ..... -=_-_.-7_-:_-_---_T..:i: ",:__-..- : ..

3OO

o Io 20 30 40 bo

ALTITUDE (lOOO FEE-r)

FIGURE 33

THRUST DATA FOR 85 PERCENT ENGINE RPM

5O
APPENDIX A

ORIGINAL PAGE IS

OF POOR QUALITY

MACH: 1.0

THRUST

(LBS.)

400 -

3O0

10 20 30 40 50

ALTITUDE (1000 FEET)

FIGURE 34

THRUST DATA FOR 90 PERCENT ENGINE RPM

51
oRIGINAL pAGE IS.

OF pOOR QU_

APPENDIX A

1000

900

IMACH: 0.'0.....

CH: 0.4 --

........ 0.8---

MACH: 1.0....

800iii .......

THRUST

(LBS.)

700

600

5OO

400 .....

300

200

100

___

• =; i:.;_ ::!'_:;G_T:L-:_:_:_'.-i_!-::--_'.;:_- _-:_:: ! . _- ; .

10 20 30 40 50

ALTITUDE (fOOD FEET)

FIGURE 35

THRUST DATA FOR 95 PERCENT ENGINE RPM

52
'.ORIGINAl; p_:GE I_

OF pOOR QUALITY

APPENDIX A

160

1200

THRUST

(LBS.) 80( ::_-_.:-::::::-:..

600

200

..7: "1 :-" : : - d:'--':.:": .:£::_:::.:-:::i::::._: "- -..- : .::..:- :.

iO 20 30 40 50

ALTITUDE (fOOD FEET)

FIGURE 36

THRUST DATA FOR 100 PERCENT ENGINE RPM

53
(This page intentionally left blank)

54
APPENDIX B

DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION STUDY

This appendix contains a study (see Figure 37) initiated when data obtained

during bench testing of the servoactuator of DAST ARW-I did not compare

favorably with the model used for analysis.

The testing was conducted to determine if the DAST ARW-2 outboard aileron

servovalves should be moved outboard closer to the actuators. Line lengths,

load variations and position feedback gain variations were investigated.

__EDiN6 PAGE BLANK NOT FILMED

PP_CED/_G PAGE E_A,_ ,"_.OT F_

55
APPENDIX B

COORDINATION SHEET

TO Gary Hodges NO. 3-75610-79-015

DATE 31 October 1979

MODEL DAST ARW-2

GROUP INDEX Flight Controls Analysis

SUBJECT DAST ARW-2 Outboard Aileron Servovalve Relocation Study

1.0 INTRODUCTION AND SUMMARY

The DAST ARW-I outboard aileron servoactuators installed in the test vehicle

have about 84 inches of 3/16-inch outside diameter steel tubing between the

servovalves mounted in the center wing section and the actuators mounted out

in the wing at the inboard edges of the ailerons. Ground testing on the test

vehicle shows higher frequency servoactuator modes, at about I12, 155 and

380 hertz, which cause servoactuator instability at the desired feedback

gains. In addition, a lower frequency dominant mode with peak at 50-60

hertz has been shown by analysis to couple adversely with wing structural

elastic modes with the flutter suppression systems engaged. The higher frequency

modes required addition of notch filters to reduce actuator gain at the mode

frequencies. The lower frequency dominant mode will also require additional

compensation to provide satisfactory performance from the flutter suppression

system on the test vehicle.

As part of the subject study, testing was accomplished on a breadboard of the

DAST ARW-I outboard aileron servoactuator to establish the effects of line

length between Lhe servovaive and actuator and load inertia variations on

the servoactuator dynamic performance. The testing was conducted to determine

if the DAST ARW-2 outboard aileron servovalves should be moved outboard closer

to,the actuators and, if so, how much to alleviate the difficulties encountered

with the DAST ARW-I servoactuator:

The test results show that tileservoactuator bandpass does not improve

significantly as the length of the lines between the servoactuator and servovalve is shortened. In general, damping of the dominant, low frequency hydraulic

fluid-actuator coupled mode increases as line length is shortened and as control

surface inertia Is decreased. But, the frequency of this mode, with position

and pressure feedback gains constant, does not vary significantly with line

length or load inertia variations.

The dominant mode, which appears to be a coupled hydraulic fluid-actuator mode,

does not vary significantly in frequency or damping with changes in position

feedback loop gain. The general trend is to decrease frequency and damping

as position feedback gain increases. Pressure feedback increases the damping

on this mode, but decreases damping on higher frequency fluid modes.

The two higher frequency fluid modes increase in frequency as the servovalve

is moved closer to the actuator. With fuIl length (84-inch) lines, the modes

are at 160 and 380 hertz, but with lines reduced by half, the lower frequency

mode is at 230 hertz and the other above 500 hertz.

FIGURE 37

DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION STUDY

56
APPENDIX B

C/S 3-75610-7g-015

Page 2

The test results show that improved performance can be attained with shorter

lines and reduced control surface inertia. The DAST ARW-2 outboard aileron

servovalve should be moved farther outboard in the wing and the control surface

inertia should be reduced. While this should improve the servoactuator

performance, additional electronic compensation may be required to provide

satisfactory performance from the flutter suppression system.

2.0 TEST RESULTS

The tests were conducted on a breadboard of the DAST ARW-I outboard aileron

servoactuator set up in the Hydraulics Laboratory. Position and load pressure

feedback loops were closed on an EAI TR-48 analog co_uter. A 741 operational

amplifier with current feedback was used to drive the electrohydraulic

servovalve. Hydraulic power"was provided by a portable hydraulic power unit

capable of about 5 gallons per minute. The test set up with long lines

between the servovalve and actuator was identical to the servoactuator functional

test set up in August 1978.

The simulated load inertia used in the functional test was cut in half with

a long bolt added so testing could be accomplished with full or half inertia,

or with no inertia by removing the inertia from the actuator shaft. The lines

between the servovaive and actuator used for the functional test were used for

the full length lines tests. Another pair of lines were made up for the shorter

lines tests.

Three groups of tests were accomplished. The first serieswere frequency

response tests with variations in line length and simulated control surface

inertia. The second series of tests were all with full line length to determine

more exactly the nature of the dynamic response. In the third set, dynamic

responses were obtained with full and lO-inch lines with position feedback

gain variations.

Each time a change in the lines was made, the lines were bled and the actuator

oscillated 4 or 5 degrees amplitude at I0 hz for about 5 minutes to preclude

air being trapped in the lines and actuator.

2.1 Line Length and Load Inertia Variations

The servoactuator was first set up with the full length lines (84 inches)

and frequency responses obtained for actuator shaft displacement due to displacement command for full (0.004 in-lb-sec2), half and no load inertia. Then, the

line length was shortened to three-quarter (63 inches), half (42 inches), onequarter (21 inches) and the shortest practical lines (I0 inches), consecutively,

and the same frequency responses obtained. The resulting plots are shown on

Figures l through 15. These frequency responses were all run with the nominal

position and pressure feedback loop gains, 329.6 rad/sec and 0.5678 rad/sec,

respectively. Different notch filters were required as the lines were shortened,

because the higher frequency fluid modes increased in frequency.

The notch filters implemented in the servoactuator feedforward path for each

of the line lengths are tabulated below.

FIGURE 37 (CONTINUED)

DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION STUDY

57
APPENDIX B

C/S 3-75610-79-015

Page 3

LINE LENGTH NOTCH FILTER(S)

Full 380 Hz

Three-Quarter 160, 380

Half ]60, 240

One-Quarter 160, 240

]O-inch 160, 430

The frequency responses all show a first order ro]]-off followed by a dominant

mode peak in the 50-60 hertz range. Table I shows a summary of the frequency

responses. In general, for a given line length, reducing the load inertia

increased damping of the dominant mode (reduced peak magnitude), but changing

line length did not affect this mode significantly in either damping or

frequency. The dominant mode appears to be the coupled hydraulic fluidactuator mode. With full load inertia, the actuator-surface mode is at ]]O-l]5

hertz.

With full length lines, higher frequency fluid modes are evident at 160 and

380 hertz (a notch filter was required at 380 hertz to reach the nominal

feedback gains). With the lines reduced to 63 inches, these modes are at

about 185 and 460 hertz. At half line length, the lower frequency mode has

moved up to 230 hertz and the other is.above 500 hertz. Thus, the two higher

frequency fluid modes increase in frequency as the lines are shortened. The

230 hertz mode evident in the frequency responses with ]O-inch lines is the

servovalve. The servovalve mode is notapparent in the other frequency responses.

The dominant mode appears to change in damping and Frequency with time. Figure

16 shows the frequency response of actuator position obtained in the functional

tests in September 1978, with full length lines, full inertia and the same

position and pressure feedback gains and notch filter as the response shown

on Figure I. The functional test frequency response shows the dominant mode

peak at 72 hertz with amplitude about 2.27 degrees for the one degree amplitude

command. Figure I shows the peak at 60 hertz with amplitude of about

2.03 degrees. The frequency response obtained during the functional test

was run for 0.1 to I00 hertz frequency rangep so the higher frequency modes

cannot be compared. The 380 hertz mode was present and a notch filter at 380

hertz was required to attain the desired feedback gains. The difference in

this mode would tend to suggest air was entrapped in the lines during the

current test, but efforts were made to eliminate trapped air before any data

was taken.

2.2 Dominant Mode Tests

After completion of the line length variation tests, the servoactuator breadboard was reassembled with the full length lines. Figures 17, 18 and ]9 show

frequency responses obtained at this time for full, half and no load inertia,

respectively. A comparison of these plots with responses obtained initially,

FIGURE 37 (CONTINUED)

DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION STUDY

58
APPENDIX B

C/S 3-75610-79-015

Page 4

Figures I, 2 and 3, show the dominant mode to be lighter damped and at

lower frequency. This response is more like that obtained on the servoactuators installed in the DAST ARW-I vehicle. Throughout the remainder

of the testing on the breadboard setup, the response changed some from day

to day, but essentially was the same.

A frequency response with the load inertia removed and low position feedback

gain (90.91 rad/sec) only was run to compare with a response obtained during

the DAST ARW-I functional tests. The two responses are plotted on Figure

20. The dominant mode frequency is at I00 hertz for both responses. The

lower frequency differences in the responses are probably due to actuator

friction, with the friction less now than a year ago. However, the measured

phase angles agree very well throughout the frequency range tested.

The hydraulic fluid mode at 160 hertz also changed some in nature. A notch

filter had to be added when the breadboard was revised to return to full

length lines. This notch was not required during the functional tests or

when the breadboard was first assembled for the current tests.

A frequency response of the valve drive amplifier output voltage, shown on

Figure 21, was run for a one degree actuator command, to determine if

amplifier saturation was occurring. Near the dominant mode peak frequency,

around 60 hertz, the voltage peaks at about 2.70 volts, with the maximum

peak at 500 hertz of about 15.2 volts. Thus, the dominant mode is not being

caused by nonlinear effects due to valve drive amplifier saturation.

Figure 22 shows the servoactuator frequency response obtained with the

hydraulic supply pressure increased to 2000 psi. The dominant mode peak occurs

at 62 hertz, slightly higher than obtained with 1500 psi supply pressure shown

on Fi.gure17. Supply pressure does not affect the servoactuator dynamic

response significantly.

2.3 Position Feedback Gain Variations

The final set of data run on the DAST ARW-I outboard aileron servoactdator

breadboard consisted of frequency responses for actuator displacement and

load pressure for four low position loop gains and no pressure feedback or

notch filters. Figures 23 through 26 show the actuator responses for the

full length lines, and Figures 27 through 30 show the corresponding load

pressure frequency responses. The actuator responses for lO-inch lines are

shown on Figures 31 through 34 and Figures 35 through 38 show load pressure

responses. The responses were obtained to determine if the dominant mode

was affected by position feedback for the full length and lO-inch lines.

The four gains run were Ig.18, 38.36, 76.72 and I15.08 rad/sec. The first

two were obtained using a 2 degree command because the response was so small

at the higher frequency fluid mode frequencies.

FIGURE 37 (CONTINUED)

DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION STUDY

59
APPENDIX B

ClS 3-75610-79-015

Page 5

The dominant mode frequency, with full length lines, show only a weak dependence on position feedback gain. The peak frequency varies from about

85 hertz at 19.18 rad/sec down to about 80 hertz at II5.08 rad/sec. The

higher frequency fluid modes are more apparent in the load pressure frequency

responses.

The responses with lO-inch lines show little effect on the dominant mode

frequency by the position loop gain. The peak occurs at about 85 hertz,

except for the highest gain, I15.08 rad/sec, when it drops to about 82 hertz.

With lO-inch lines, positon feedback gain could be raised to higher loop

gain without driving the dominant mode unstable than with full length lines.

In general, results of these tests show little dependence of the dominant

mode on position feedback gain, in either frequency or damping, Mode damping

is hard to assess because as position loop gain is increased the first order

actuator mode moves farther out on the real axis, resulting in increased

response at the dominant mode frequency.

3.0 CONCLUSIONS AND RECO_ENDATIONS

The test results discussed in Section 2, above, show that the dominant mode

in the DAST ARW-I outboard aileron response limits, the dynamic performance

capability of the servoactuator. Because the DAST ARW-2 outboard aileron

servoactuator is similar in structure and actuator size, it will also have

a dominant fluid-actuator mode of similar frequency and damping which

will limit its capability.

This mode is not a strong function of line length (between the servovaIve

and actuator) or position feedback gain. The nature of the response does

vary some with time, probably due to actuator and servovalve wear-in. The

higher frequency modes increase in frequency as the line length is shortened,

with the higher frequency mode above 500 hertz for 42-inch and shorter lines.

The dominant mode damping increased with a decrease in the simulated control

surface inertia, butthe inertia had no effect on the higher frequency fluid

modes.

While the test results are not totally conclusive, the general trend shows

that better dynamic performance can be attained with shorter lines between

the servovalve and actuator and with lower control surface inertia. Therefore, it is recommended that the DAST ARW-2 outboard aileron servovalve be moved

outboard in the wing from that shown on the design drawings to no more than

40-45 inches from the actuator between the wing spars. Also, the inertia

of the outboard aileron should be reduced to the lowest value consistent

with maintaining structural strength.

FIGURE 37 (CONTINUED)

DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION STUDY

60
APPENDIX B

C/S 3-75610-79-015

Page 6

A more accurate mathematical representation of the outboard aileron servoactuator should be developed to permit analytical exploration for additional

electrical compensation to improve the actuator response. The data generated

in this series of tests should aid in the mathematical formulation.

Other tests could be run on the breadboard test setup, such as other compensation

and line diameter variations. Changing line diameter would require a change

in the feedback potentiometermounting to provide clearance for larger tube

fittings at the actuator ports.

F. Sevart

CC: J. Arnold

FIGURE 37 (CONTINUED)

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APPENDIX C

DAST ARW-2 FINAL FLUTTER SUPPRESSION SYSTEM PERFORMANCEDATA

This appendix contains data which summarizes the airplane stability and

performance withthe final flutter suppression system.

Figures 38 through 47 show the symmetric and antisymmetric mode damping

ratios and frequencies for the critical flight Conditions determined from

analysis. This data yerifies that the FSS meets the requirements to provide

flutter mode stability and not reduce mode damping ratio below 0.01 or

degrade damping of modes with damping ratios below 0.01.

Figures 48 through 59 show the improvement in flutter mode damping with the

FSS operating. Damping ratio data is presented as a function of altitude

and Mach number.

Figures 60 through 71 present root loci showing structural mode stability

for flight conditions within the specified flight envelope. Figures 66,

67, 69 and 71 show the requirement for FSS antisymmetric filter gain scheduling and with gain scheduling, the FSS meets the specifications contained

in the final report.

101
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APPENDIX D

DAST ARW-2 SENSITIVITY ANALYSIS DATA

This appendix contains data which summarizes the sensitivity of structural

mode stability to variations in dynamics and locations of control system

components. For the most part the sensitivity analysis was not repeated

for the final FSS filters, however sensitivity to changes shown in this

data and the root loci analysis performed using the latest filters indicate

that results of this study are valid.

Figures 72 and 73 compare structural mode damping ratios for various accelerometer wing locations. The optimal sensor locations were selected by

zero root locus as presented in the final report for sensors moved along

front and rear spars. Thesensor locations were varied inboard and outboard of the optimal up to two inches. The symmetric gain margin was not

reduced below plus or minus 6 dB but the phase margin was reduced to 20

degrees when the sensors were separated by six inches. The antisymmetric

gain and phase margins were reduced significantly when the sensors were

separated by four inches.

The recommended installation of the symmetric accelerometers was plus or

minus one inch of the wing station 82 on front spar and 84 on rear spar.

The recommended installation of the antisymmetric accelerometers was plus

or minus 0.5 inch of wing station 92 on both front and rear spars. The

vertical accelerometer recommended location was at body station 265 plus

or minus 2.5 inches.

Notch filters are used both in the FSS filter and servoactuator compensation. Sensitivity to notch filter parameter changes was analyzed. Figure

74 shows the transfer functions of the notch filters used in the symmetric

and antisymmetric compensation. The final filters did not include the 170

and 230 radian notch filters, however the sensitivity analysis is presented

here for future reference.

The summary of the notch filter sensitivity analysis is shown on Figures

74 through 82. The capacitors and resistors of the notch filters have very

close tolerances and small sensitivity to temperature changes, therefore

the parameter changes from nominal is expected to be small over the flight

envelope. The damping ratio and frequency of the notch filters were varied

plus and minus five percent and the damping ratio of the actual modes changed

less than eight percent.

Several servovalves were evaluated in an effort to extend the servoactuator

bandwidth. A Moog Series 31 servovalve was initially selected for the

actuator model and later bench tested. The Series 31 servovalve has a wide

bandwidth and improved FSS performance but was expensive and required complicated closed loop circuitry. A Hydraulic Research Model AR-25 servovalve

was selected because it was a direct replacement for the Series 30 used for

the ARW-I servoactuator but had a wider bandwidth. The structural mode

136
APPENDIXD

stability results of the three servovalves are shownon Figures 83 through

88. Figure 85 showsthat a plus 6 dB gain margin cannot be achieved with

the Series 30 servovalves. Although the AR-25 servovalve did not increase

the servoactuator bandwidth, the increased servovalve bandwidth provided

increased performance and 6 dB of gain margin was achieved.

Figures 88 and 89 whencomparedwith Figures 83 and 86 respectively verify

that the compensating actuator filter which cancels the surface-actuator

modeis required. Figures 90 through 92 summarizethe sensitivity analysis

performed by varying the frequency of the surface-actuator modewith respect

to the compensating filter frequency.

The results of this sensitivity study indicated that when the compensating

filter was removedthe symmetric airplane modeswere destabilized and were

difficult to stabilize and the antisymmetric filter modelead phase margin

was decreased to 40 degrees. The FSSwas relatively insensitive to a plus

or minus 20 percent frequency change in the surface-actuator mode.

Servoactuator pressure feedback gain was reduced to determine the effect on

airplane stability. Figures 93 through 96 summarizethis analysis. A reduction of 30 percent in pressure feedback gain did not reduce symmetric

stability below specifications and the antisymmetric lag phase margin was

reduced only to 40 degrees.

A hinge momentsensitivity analysis was performed to determine stability

effects. Figure 97 shows the servoactuator gain and phase response to a

hinge momentchangeat the filter frequency. The maximumaiding (surface

trailing edge up) to the maximumresisting (trailing edge down) hinge moment

causes approximately 45 degrees of phase lag and 4 dB loss in gain. Figures

98 through 104 summarizethe hinge momentsensitivity analysis. Changesin

hinge momentmay require servoactuator gain scheduling. This should be

evaluated further by ground and flight testing.

Other sensitivity studies showedthat the airplane is relatively insensitive

to small changes in stability derivatives and the active control systems

tend to increase frequency and dampingof the fuselage modeas shownon

Figure 105.

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APPENDIX E

ACS/AFCS SYSTEMS ROOT LOCl

Gain and phase stability margins of each individual ACS and AFCS feedback

loop, except the flutter system, are shown on the figures of this section.

The stability margins of each loop were determined with each combination

of systems that may be closed during some phase of flight testing. The

margins were determined at various flight conditions spanning the total

flight range. The root loci plots are identified in Figure 106 and shown

on Figures 107 through 204. The stability margins were evaluated using

QSE equations of motion. Each system loop was evaluated by +4.5 dB gain

and +30 degrees phase margin criteria. Refer to Figure 106 as a guide to

read-gain and phase information.

176
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APPENDIX E

• MLA TEST

• RSS

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20_ MAC

I I I

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FIGURE 107

DAST AKW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

...... FORWARDC.GoMLA TEST CONDITION _
APPENDIX E

• MLA TEST

• RSS

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.: 205 MAC

i I

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DAST ARW-2 RSS SYSTEM C_AIN/PHASE ROOT LOCl WITH BASIC AIRPLANE FOR

FORWARD C,G. MLA TEST CONDITION

179

DO 6000 2145 REV 9182
APPENDIX E

• MLA TEST

• RSS WITH PCS CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20_ MAC

N@, .5GRIN0

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FIGURE 108

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

..... FORWARDC,G. MLA TEST CONDITION
APPENDIX E

• MLATEST

• RSS WITH PCS CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20% MAC

CJ:IN I ' _X_.X, _ I

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DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

.... FORWARDC.G. MLA TESTCONDITION

181
APPENDIX E

• MLA TEST

• RSS WITH PCS AND GLA CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT= 2500 LBSo

• C.G.: 20% MAC

I I

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(RAD/SEC)

]82

FIGURE 109

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

....... FORWARDC°G. MLATEST CONDITION
APPENDIX E

e. MLA TEST

• RSS WITH PCS AND GLA CLOSED

• MACH= 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2500 LBS.

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DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

FORWARD C.G. NLATEST CONDITION

183
APPENDIX E

• MLA TEST

• RSS WITH BCS CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

I I I

NO. GRIN .5950

2 I.O00

3 1.680

/

I

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/

/

-20. O0 -16.00 -t 2. O0 -8. O0 -q. O0 O. O0

(RAD/SEC)

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.=;

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184

FIGURE 110

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

FORWARD C,G. MLATEST CONDITION
APPENDIX E

• MLA TEST

• RSS WITH BCS CLOSED

• MACH= 0.42

• ALTITUDE= 10,000 FT'.

• GROSS WEIGHT= 2500 LBS.

• C.G.= 20% MAC

I

NO. GRIN

I .5950

2 I.O00

3 t.680

\

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+

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0 _4

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FIGURE 110 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAI N/PHASE ROOT LOOI WITH BCS CLOSED FOR

.... FORWARDC.G. MLA TESTCONDITION

185

DO 6000 2145 REV 9/82
APPENDIX E

• MLA lEST

• PCS WITH RSS CLOSED

• MACH: 0,42

• ALTITUDE: 10,000 FT,

• GROSS WEIGHT: 2500 LBS,

• C,G,: 205 MAC

NO.

1

2

3

OlIN

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).. 000

1.680

t I I I

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186

FIGURE 111

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

' FORWARDC.G. MLA TEST CONDITION •
APPENDIXE

• MLA TEST

• PCS WITH RSS CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FTo

• GROSS WEIGHT: 2500 LBS.

• C.G.= 20_ MAC

NO. GRIN

1 .5950

2 t. 000

3 t.680

I I t _k '1

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,.,.;

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o CR/I,D/SEC)

FIGURE 111 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

• ' FORWARDC.G, MLA TEST CONDITION _ "

187
APPENDIX E

• MLA TEST

• PCS WITH RSS AND GLA CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20_ MAC

NO. GRIN

1 .5950

2 1.000

3 1.680

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c_ (RAD/SEC)

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188

FIGURE 112

DASTARW-2 PCS GAIN/PHASE ROOT LOOI WITH RSS AND GLA CLOSED FOR

.... FORWARDC.G. MLATEST CONDITION
APPENDIX E

• MLA TEST

• PCS wI'rH RSS AND GLA CLOSED

• MACH: 0.42

• ALTITUDE= 10,000 FT.

• GROSS WEIGHT: 2500 LBSo

• C.G.: 20_ MAC

I I I

NO, GRIN

1 . $9S0

2 t. 000

3 I. 680

i

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I

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3

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(RAD/SEC)

FIGURE 112 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

.... FORWARD'C.Go MLA TEST CONDITION "

189
APPENDIXE

• MLA .rEST

• BCS WITH RSS CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20% MAC

NO. GRIN

! .5950

2 t. 000

t. 680

\,

\

\

\

g i i i _

c_

I

• \\\ l J

e-_ •

3

(RAD/SEC)

190

FIGURE 113

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

.... FORWARDC,G. MLA TEST CONDITION
APPENDIXE

• MLA TEST

• BCS WITH RSS CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

NO. GRIN l

1 .5950

E 2 t.O00

3 t.680

,=

I I

\

- .(SO

>t.._

t I

- 1.20 -0.8O -0.40 O. O0

(RAD/SEC)

FIGURE 113 (CONCLUDED)

DAS'r ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

• FORWARDC.G. MLA TEST CONDITION

Igl
APPENDIX E

• MLA TEST

• RSS

• MACH: 0.42

• ALTITUDE= 10,000 FT.

• GROSS WEIGHT= 2200 LBS.

• C.G.: 33_ MAC

NO. GRIN t I I I / I

.59S0 / II

Z [.000 / I

3 I. 680 / /

O

0

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n,'

3

(RAD/SEC)

192

FIGURE 114

DAS"FARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

....... AFT C,G. MLA TEST CONDITION
APPENDIX E

• MLA TEST

• RSS

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33% MAC

I _ I I

N]O. •GRIN $950

L .000 t. 680

1

-t .60 -I ._0 -0.80 -0. LIO O.OO 0.40

o (RAD/SEC)

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FIGURE 114 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

........ AFTC.G. MLA TESTCONDITION

193
APPEND I X E

• MLA TEST

• RSS WITH PCS CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33_ MAC

2 t.O00

3 1.600

I I I

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t

F

l

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I

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o

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q.ob

o'.(PAD/SEC)

FIGURE 115

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

..... AFT C.G, MLA TEST CONDITION

194
APPENDIX E

• MLA TEST

• RSS WITH PCS CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33_ MAC

,- \

N10" i. ooo _ _ /

I

I I I I

-1.60 -1.20 -0.80 -0. qO O. O0 O. qO

(RAD/SEC)

C3

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3

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FIGURE 115 (CONCLUDED)

DAST ARW-2 RSS SYSTEH GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

.... AFT C.G.HLA TEST CONDITION

195
APPENDIX E

• MLA TEST

• RSS WITH PCS AND GLA CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33_ MAC

I I I I

NO. GAIN / lI

I .sgso /

2 l. DO0 /,

" I

I

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C.)

LU

cO

3

.--}

oJ

q.ob

(RAD/SEC)

196

FIGURE 116

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

....... AF-rC.G. MLA TEST CONDITION
APPENDI X E

• MLA TEST

• RSS WITH PCS AND GLA CLOSED

• MACH= 0.42

• ALTITUDE= 10,000 FT.

• GROSS WEIGHT= 2200 LBS.

• C.G;: 33_ MAC

J 2 i:000, /

I I

T

I

I

I

i J I I o

- 1.60 - 1.20 -0.80 -0.140 O. O0 O. 40

o (RAD/SEC)

o4

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ao

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FIGURE 116 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

....... AFT C.G. MLA TEST CONDITION

]97
APPENDIXE

• MLA TEST

• RSS WITH BCS CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33_ MAC

t

-20. O0

I I I I I

i.ooo t. 680

1

/

/

. /

/ /

• ( /

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I

- 16. O0 - 12. O0 -8. O0 -q, O0 O. O0

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(RAD/SEC)

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£:) (./) IiTM

rt,-

.,-,,j

c;

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FIGURE 117

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

AFT C.G. MLATEST CONDITION

198
APPENDIX E

t

-|.60

• MLA TEST

• RSS WITH BCS CLOSED

• MACH: 0.42

• ALTITUDE: I0,000 FT.

• GROSS WEIGHT: 2200 LBS.

i C.G,: 33% MAC

I I I

NO. • GRIN 59S0

! .000 1,6eo

-I. 20 -0.80 -0.qO O.O0 O.qo

t_

o

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(_

c_

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(_(RAD/SEC)

c_

c_

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o.ob

c.)

r-.,

OC

3

..--_

FIGURE 117 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

AFT C.G. MLA TEST CONDITION

199
APPENDIXE

• MLA TEST

• PCS WITH RSS CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G;: 33% MAC

NS.

!

2

3

I I I t

GRIN

•5950

I.O00

1.680

I I I

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El

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I

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¢:D

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o (RAD/SEC)

200

FIGURE 118

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

.... AFT C.G. MLA TEST CONDITION _
APPENDIX E

• MLA TEST

• PCS WITH RSS CLOSED

• MACH: 0.42

• ALTITUDE: 10,,000 FT.

• GROSSWEIGHT: 2200 LBS.

• C.G,: 335_ MAC

I

i

J

I I I,

GRIN

.S950

1.680

I I 4'

-1.60 -i.20 _ -0.80 -O.qO 0.00 o.qo

(RAD/SEC)

oJ

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n,-

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o.sb

FIGURE 118 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

' " AFT C.G. MLA TEST CONDITION ....

201
APPENDIX E

• MLA TEST

• PCS WITH RSS AND GLA CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33_ MAC

GRIN

.5950

t.O00

1.680

t I I t

o

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(_ (RAD/SEC)

t

FIGURE 119

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

AFT C.G. MLA TEST CONDITION

202
APPENDIXE

• MLA TEST

• PCS WITH RSS AND GLA CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33% MAC

I I I

NO. GRIN

I .5950

Z 1.000

3 i.680

i

t

I

I

4

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z6o -z2o -o.8o -o.,m o.oo o qo

(RAD/SEC)

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=;

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c;

o,eb

FIGURE 119 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

AFT C.G. MLA TEST CONDITION

203
APPENDIX E

• MLA TEST

• GLA AILERON WITH RSS, PCS AND

GLA STAB IL IZER CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33% MAC

I I I I

I D J I

O.O0 -16.00 -12.00 -8.00 -tt. O0 0.00

(_(RAD/SEC)

(_

C:)

4

(Z)

L_

3

°"'J

C)

(_

C_

oo

_.0b

204

FIGURE 120

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

' ' •STABILIZER LOOPS CLOSEDFOR AFT C,G. MLA TEST CONDITION
-125.00 -100.00 -75.00

APPENDIX E

• MLATEST

• GLA AILERON WITH RSS, PCS AND

GLA STABILIZER CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2200 LB$.

• C.G.: 33% I_C

I I

-50. O0 -25. O0

(RAD/SEC)

u_

pFIGURE 120 (CONTINUED)

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

STABILIZER LOOPS CLOSED FOR AFT C.G. MLA TEST CONDITION

205
APPENDIXE

• MLA TEST

• GLA AILERON WITH RSS, PCS AND

GLA STABI L IZER CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2200 LBS°

• C.G.: 33% MAC

I I

O. O0 O. 40

0 (RAD/SEC)

0

(M

(:D

(3

ILl

U1

3

c_

(:3

C_

tD

'c;

o

(M

(3

Ic;

o_sb

206

FIGURE 120 (CONCLUDED)

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

STABILIZER LOOPS CLOSED FOR AFT CoG. MLA TEST CONDITION
APPENDIX E

• MLA TEST

• GLA STABILIZER WITH RSSp PCS

AND GLA AILERON CLOSED

• MACH: 0.42

• ALTITUDE- lOpO00 FT.

• GROSS WEIGHT= 2200 LBS.

• C.G.. 33_ MAC

t I I f " ',

/

/

/

-20.00 -16.00 -12.00 -B. O0 -u,. O0 0.00

(_(RAD/SEC)

"5

0

C)

.,,G

FIGURE 121

DAST"ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS,, PCS AND GLA

A I LERON LOOPS CLOSED FOR AFT C.G. "MLA TEST CONDIT ION•

207
APPENDIX E

• MLA TEST

• GLA STABILIZER WITH RSS, PCS

AND GLA AILERON CLOSED

m MACH: 0.42

• ALTITIlDE: I0,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33% MAC

I I I I I

t \

r_

• °

_8

A

c.)

uJ

c_

ti" 3

cr (RAD/SEC)

FIGURE 121 (CONTINUED)

DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

• AILERON LOOPS CLOSED FOR AFT C.G. MLA TEST CONDITION

2O8
APPENDIX E

• MLA TEST

• GLA STABILIZER WITH RSS, PCS AND

GLA AILERON CLOSED

• MACH- 0.42

• ALTITUDE: I0,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33% MAC

I I I

I

I I _ I

-_.6o -1.20 -o.Bo -0.40 o.oo 0.40

(_(PAD/SEC )

_4

,-d

o

(._

o

oo

:.o

o

(,o

c)

(._

c)

018b

uJ

OC

3

FIGURE 121 (CONCLUDED}

DAS'r ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

AILERON LOOPS CLOSED FOR AFT C.G. MLA TEST CONDITION

209
APPENDIX E

• MLA TEST

• BCS WITH RSS CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 335 MAC

3

l

i

I

I I I I

G_IIN

• 59S0

I. 000

1.680

\

\

\

\

\

\

\\

_\ \.,

\. /

-16.00

• I

i I

-12.00 -8.00 -I_.O0 0.00

c_(RAD/SEC)

c_

o

C3

C_

e,;

c_

C3

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A

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3

..-.,_

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FIGURE 122

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

AFT CoG. MLATEST CONDITION

210
APPENDIX E

• MLA TEST

• BCS WITH RSS CLOSED

• MACH: 0.42

• ALTITUDE: 10,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33% MAC

+

I

I I

- L. 60 - 1.20 -0.80 -0. q,o O. O0 O. qO

cr(RAD/SEC)

FIGURE 122 (CONCLUDED)

DAST ARW-2 BCS SYSTEN GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

.... AFT C.G, NLA TEST CONDITION .....

211
APPENDIX E

• GLA TEST

• RSS

• HACH: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G,: 20_ MAC

I I I

d

°

....

20.00 tO.DO 12.00 8 O0 q.O0 0.00 _ UU

(RAD/SEC)

¢.)

uJ

(v3

(::3 •

3

o--._

FIGURE 123

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

...... FORWARDC.G. GLATEST CONDITION

212
APPENDIX E

• GLA .3lEST

• RSS

• MACH= 0.70

• ALTITUDE: _ 15,000 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.= 20% MAC

I I

I

I I I _ I

1. G(J [, 20 O. 80 D. 40 O. O0 O. qO

o" (RAD/SEC)

0

UD

C)

_J

C_

CO

0

w

(:3 --_

1' r_ •

3

°--,j

0

0

0

FIGURE 123 (CONCLUDED)

DAS'i"ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

...... FORWARDC.G.GLATESTCONDITION '

213
APPENDIX E

• GLA TEST

• RSS Wll_! PCS CLOSED

• MACH: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

N_j"

I I I

I

I

i I

gO. O0 tG. O0 12. O0 6. O0 q. O0 O. O0

o (I_a.D/SEC)

FIGURE 124

DAS'FARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

..... FORWARDC.G. GLATEST CONDITION

214
APPENDIX E

• GLA TEST

• RSS WITH PCS CLOSED

• MACH: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G,: 20_ MAC

"i

f

I

I I I

I

l o I I I

t.6o z .zo o.so o.qo o.oo o.qo

o (RAD/SEC)

C_

f.o

6

',_H

°

LU

S

FIGURE 124 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

..... FORWARDC.G. GLA TEST CONDITION

215
APPENDIX E

• GLA TEST

• RSS WITH PCS AND GLA CLOSED

• MACH: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

I I I I

1 °

0

20.00 16.00 12.00 e. O0 4.0D 0.00 4.0b

(RAD/SEC)

FIGURE 125

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOOI WITH PCS AND GLA CLOSED FOR

........ FORWARDC.G. GLA TEST CONDITION

216
APPENDIX E

• GLA TEST

• RSS WITH PCS AND GLA CLOSED

• NIACH: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20'_ MAC

I I I

I

, , I ,

t.6o -1.2o o,eo o.4o o.oo o.qo

o (RAD/SEC)

_D

C'o

r,;

CI

¢o

A

(.t")

:=" r'_

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n,"

3

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04

,.,H

0

0

oisb

FIGURE 125 (CONCLUDED)

DAST ARW-2 RSS SYSTEN GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

..... FORWARDC. G. GLA TEST CONDI TI ON

217
APPENDIX E

• GLA TEST

• RSS WITH BCS CLOSED

• MACH: 0.7U

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

I I I

0

C;,

20. O0 16. O0 -12. O0 6. O0 4. O0 O. O0

o (RAD/SEC)

218

FIGURE 126

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

.... FORWARDC.G. GLA TEST CONDITION
APPENDIXE

• GLA TEST

• RSS WITH BCS CLOSED

• MACH: 0.7U

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

I

NO. GRIN

isN

Z

I I

T

I i_ _ _ -

I I ; I I

1.60 1.20 0.80 O.qO 0.00 o.qo

o (RAD/SEC)

IJD

0

OJ

0

CO

0

(D

lID

c;

0

o.8b

A

(.)

u.I

r_

3

FIGURE 126 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

..... FORWARDC,G. GLA TEST CONDITION

219
APPENDIX E

• GLA lEST

• PCS WITH RSS CLOSED

• MAC'H: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20% MAC

I N(_.

l

T

E

h

J

I

+

I I I t

GRIN

.59S0

l.O00

1.680

I I I

c_

/ °C3

/

/

, *,

j- - Z3"

/ ./

/ f i

s

0

÷_

, .ob

CO

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r_"

v

3

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-20. O0 -_e.oo -_2.oo -a.oo -q.oo o.oo

o (I:_ISEC)

FIGURE 127

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

' ' ' FORWARDC.G. GLA lEST CX)NDITION ' "

220
APPENDIX E

• GLA TEST

• PCS WITH RSS CLOSED

• MACH: O.7U

• ALTITUDE, 15,000 FT.

• GROSSWEIGHT: 2500 LBS.

• C.G.: 20_ MAC

NO. GRIN

.5950 .000

F

!

F

)

t

Q

-1,60

I I I

I

- I. 20 -0.80 -0. LIO O. O0 O. qO

o (RAD/SEC)

,==

u_

v

...=_

(:3

c3

(,13

(:3

c3

L'u

o.Bb

FIGURE 127 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

FORWARDC.G. GLA TEST CONDITION

221
APPENDIXE

• GLA TEST

• PCS WITH RSS AND GLA CLOSED

• MACH: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

P

NO. GRIN

l .5950

2 l. O00

3 I. 680

f

i

J

I

I I I

-20. O0 - 16. O0 -12. O0 -8. O0

C,

,-h

C_

- e_i_- a- -_

-4. oo o. oo 4_ob

(RAD/SEC)

FIGURE 128

DAST'ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

' FORWARDC.G. GLATEST CONDITION

222
APPENDIX E

• GLA "lEST

• PCS WITH RSS AND GLA CLOSED

• MACH: 0.70

• ALTITUDE= 15,000 F'l'.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

1

+

3 t. 680

I I I

I I I

I

I

to

,0

o

co

0

03

v

3

• •

"c;

oJ

¢;

Od

¢;

-_.6o -_.2o -o.ao -o._o o.oo o.qo 0.sb

0"(RAD/SEC)

FIGURE 128 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

• • FORWARD C.G. GLATEST CONDITION " • '

223
APPEND IX E

• GLA TEST

• GLA AILERON WITH RSS, PCS AND

GLA STABILIZERCLOSED

• MACH: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

I I I

-20. O0 - 16. O0 - 12. O0 -8. O0 -q,. O0 O. O0

O"(RAO/SEC)

0

0

0

,o,;

(:::)

0

0

LI,J

oo o0

c_

3

.,,.,_

0

0

0,i

_.ob

224

FIGURE 129

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

STABILIZER LOOPS CLOSED FOR FORWARDC.G. GLA TEST CONDITION
APPENDIX E

• GLA TEST

• GLA AILERON WITH RSS, PCS AND

GLA STABI L I ZER CLOSED

• MACH: 0.70

• ALTITUDE= 15,000 FT.

• GROSSWEIGHT: 2500 LBS.

• C.G.:. 20% MAC

NO. _9_N \ I

3 t.680 \ I o

1\ _ I Io

I \ \ ,

I

-_2s.oo -_oo.oo -_s.oo -_o.oo -_s.oo "o'.oo '. o

c_(RAD/SEC)

3

:;3

F I GURE 129 (C1:)NTI NUED)

DAS'I" ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

.. STABILIZER LOOPS CLOSED FOR FORWARDCoGo GLA TEST CONDITION

225

........................... ........
APPEND IX E

• GLA TEST

• GLA AILERON WITH RSS, PCS AND

GLA STABI L IZER CLOSED

• MACH: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20% MAC

I I I

0

0

co

3

0

l

.60 -1.20 -0.80 0 0 0 0 0 8b

o' (RAD/SEC)

226

FIGURE 129 (CONCLUDED)

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

• STABILIZER LOOPS CLOSED FOR FORWARDC.G. GLA TEST CONDITION
APPENDIXE

• GLATEST

• GLA STABILIZER WITH RSS, PCS

AND GL.A AILERON CLOSED•

• MACH: 0.70

• ALTITUDE= 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ P,ff_C

C3

('U

C3

C3

C3

.=;

A

r..3

r'_

• c:_

c3

i I i I

-20.00 -16.00 -12.00 -B.O0 -_.00 0.00 _0_

(RAD/SEC)

FIGURE 130

DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

AILERON LOOPS CLOSED FOR FORWARDC.G. GLA TEST CONDITION

227
APPENDIX E

• GLA TEST

• GLA STABILIZER WITH RSSp PCS

AND GLA AILERON CLOSED

• MACH: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT.- 2500 LBS.

• C.G..- 20_ MAC _

I I I I !

NO. GRIN I

3 t:seo I

I co

-tO0.O0 I .50, O0 0

o u'}

Io3

°...._

C)

- 125. O0 -75. O0 -25. O0

(RAD/SEC)

FIGURE 130 (CONTINUED)

DAbT ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

'' AILERON LOOPS CLOSED FORFORWARD C.Go GLA TEST CONDITION

228
I

GRIN

.5950

APPEND I X E

• GLA TEST

• GLA STABILIZER WITH RSS, PCS AND

GLA AILERON CLOSED "

• MACH: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G;: 20_ MAC

I I I c,i

C3

C3

('_

0

_33

LI.I

U3

--...

v

3

C3

=;

J

-1.60 -2.2o -0.80 -0. _0 o. oo o. qo o. 8b

_r (RAD/SEC)

FIGURE 1)0 (CONCLUDED)

DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

• AILERON LOOPS CLOSED FORFORWARD C.G. GLA "lEST CONDITION

229
APPENDIX E

• GLA TEST

• BCS WITH RSS CLOSED

• MAC'H: 0.70

• ALTITUDE: 1.5•000 FT,

• GROSS WEIGHT: 2.500 LBS,

• C.G.: 20_ MAC

• 5950

2"_\ t.l. 000 680

\,

'\

\

I

!

\\,

l I I I

,\

\\

\,

\

\

\,,

'\

<

I I I

-20. O0 - 16. O0 - 12. O0 -8. O0 -LI. O0 O. O0

(RAD/SEC)

C_

(:3

C_

(::3

3

.-,,_

C_

C3

C3

0

_:ob

FIGURE 131

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

.... FORWARDC,Go GLA TEST CONDITION ....

230
APPENDIX E

• GLA TEST

• BCS WITH RSS CLOSED

• MAC'H: 0.70

• ALTITUDE= 15,000 FT.

• GROSS WEIGHT= 2500 LBSo

• C.G,: .20_ MAC

t'"7-_ 11-°°°'_9s°='"'._,o* / '

j_ \

\

'.N

-I. 60 -I. 20 -0.80 -0, _0

/

O. O0

/

//

/

/ C_)

LU

I oO

rr

3

o-==j

(:3

oo

o (RAD/SEC)

C3

(:3

C_

I o. o

FIGURE 131 (CONCLUDED)

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

• FORWARD C.G. GLA TEST CONDITION •

231
APPENDIX E

• GLA TEST

• RSS

• MACI-I: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT= 2200LBSo

• . C.G,= 33% MAC

-20. O0 -I 6. O0

I I !

cr (RAD/SEC)

FIGURE 132

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

....... AFT" C.G, GLA TEST CONDITION

232
APPENDIX E

• GLATEST

• RSS

• MACH: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C,G.: 33_ MAC

I I

FIGURE 132 (CONCLUOED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

AFT C.G. GLA TEST CONDITION

233
APPENDIX E

• GLA TEST

• RSS WITH PCS CLOSED

• I_,CH: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,= 33% MAC

I I I I

NO. GRIN

.5950 1.000

3 I. 680

I

t I

-4. O0 O. O0

/

0

o

C_

(RAD/SEC)

I,I

0_.

3

°--,,,j

FIGURE 133

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOOI WITH PCS CLOSED FOR

...... AFF C.G. GLA TEST CONDITION

234
APPENDIX E

• GLA TEST

• RSS WITH PCS CLOSED

• MACH: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 _LBS,

• C.G,; 33_ MAC

NO,

1

GAIN

.5950

t.O00

t .680

I I I I I

I

I I I I I

C;I

¢0

C_

(:3

0

¢,O

"(5

(:3

(M

(3

ic:;

08b

L_

03

n"

3

-l. 60 -1.20 -0.80 -0. qo O. O0 O. qo

(RAD/SEC)

FIGURE 133 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

....... AFT C.G, GLA TEST CONDITION

235
APPENDIX E

• GLA TEST

• RSS WITH PCS AND GLA CLOSED

• MACH: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33% MAC

I I I I ! / _

NO. GRIN / [

1 .sgso ' / ]

3 t. 680

/ , /i

I o

t _2

E

3

-20.00 -t6.oo -z2.oo -e.oo -q.oo o.oo q:ob

cr (RAD/SEC)

FIGURE 134

DASTARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

....... AFTC.G.GLATEST CONDITION ' ' _

236
APPENDIX E

• GLA TEST

• RSS WITH PCS AND GLA CLOSED

• MACH: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBSo

• C.G.: 33% MAC

NO. GR N

.$9 o 3 1:8 8

I I I

I

l i j I i

• 60 -l. 20 -0.80 -0. u,o O. O0

(RAD/SEC)

0.40

0_

o

c,J

o

LU

c_ 03

. • r_

r_

o

o

_o

"c;

o

o,sb

FIGURE 134 (CONCLUDED)

DASTARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

....... AFT C.G.GLA TEST CONDITION '

237
APPENDIX E

• GLA TEST

• RSS WITH BCS CLOSED

• MACH: 0.70

• ALTITUDE: 15•000 FT.

• GROSS WEIGHT: 2200 •LBS.

• C.G,: 33_ MAC

I I I

/

/

/

!

/

/

/

FIGURE 135

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

.... AFT C.G, GLATESTCONDITION

238
APPENDIX E

• GLA TEST

• RSS WITH BCS CLOSED

• MACH: 0.70

• ALTITUDE: 15,000 FT.

• GROSSWEIGHT= 2200 LBS.

• C.G,: 33_ MAC

NO.

I

C)

(D

0

ED

(;0

A

L4J

TM

r_

r_

v

3

o

(23

0

_D

0

(_

I o

-l. 60 -t. 20 -0.80 -0. qo O. O0 O. qo O.

(RAD/SEC)

FIGURE 135 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

....... AFT C.G. GLATEST CONDITION " ' •

239
APPENDIX E

• GLA TEST

• PCS WITH RSS CLOSED

• MACH: 0.70

• ALTITUDE= 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33_ MAC

I ! 1 I

(:3

0

¢;

LIJ

-20. O0

I

I I I I

- 16. O0 - t 2. O0 -8. O0 -U,. O0 O. O0

(RAD/SEC)

FIGURE 136

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

.... AFT C.G. GLATEST CONDITION

240
APPENDIX E

• GLA TEST

• PCS WITH RSS CLOSED

• MACH: 0.70 '

• ALTITUDE: 15,000 FT.

• GROSSWEIGHT: 2200LBS.

• C.G;: 33% MAC

I I I

| I

'o-i

0

_o

0

o,,I

GO

. °

A

LI.I

o,--,_

. °

C_

0

I

0 I

-i. 60 -t.2o -0.80 -0.40 0.00 0.40 o: 8b

(RAD/SEC)

FIGURE 136 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOOI WITH RSS CLOSED FOR

.... AFT C,G. GLA TEST CONDITION '

241
APPENDIX E

• GLA TEST

• PCS WITH RSS AND GLA CLOSED

• MACH: 0.70

• ALTITUDE: 1.5,000 FT.

• GROSS WEIGHT: 2200 •LBSo

• C.G.: 33_ MAC

I I I I

15950

0

0

c_J

..j.1 °_3

-20.00 -16.00 -12.00 -8.00 -tLO0 0.00

(RAD/SEC)

E3

(:3

C:)

u,.ob

FIGURE 137

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

. . •AFT C.G_ GLA TEST CONDITION '

242
APF_NDIX E

• GLA TEST

• PCS WITH RSS AND GLA CLOSED

• MACH= 0.70

• ALTITUDE: 15,000 FT.

• GROSSWEIGHT: 2200LBS.

• C.G.: 33% MAC

.

I I I

I

, 4 I I 0

-1.60 -_. 20 -0. BO -o.'m o.oo o. 4o

ar (RAD/SEC)

o.;

C)

10

"e3

UJ

¢.,'3

=" n,"

3

'..3

o.sb

FIGURE 137 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

AF'r CoG. GLA TEST CONDITION

243
APPEND IX E

• GLA TEST

• GLA AILERON WITH RSS, PCS AND

GLA STAB I L I ZER CLOSED

• MACH: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS,

• C.G,: 33% MAC

I I I Y / I/

,/

//',

/

/

/

._.._

t.O00 1.680

_-_ ...__....._ _tJ"

-i I I

/ / /

) /

, /

/

[

I

0

.

0

-20. O0 -16. O0 -I 2, O0 -8. O0 -4. O0 O, O0

(RAD/SEC)

T_

i

¢;

c_

o

0

0

_.ob

A

FIGURE 138

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

STABILIZER LOOPS CLOSED FOR AFT C.G. GLA TEST CONDITION

244
APPENDIX E

• GLA TEST

• GLA AILERON WITH RSS, PCS AND

GLA STABI L I ZER CLOSED

• MACH: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33_ MAC

iN@. GRIN

isgso

L,

\ °

\

4-

\

I I I I

-125.00

D_RIGINAL PAGE rg

_'00R QUALITY

oo

.If)

CD

O

c;

c-j

.4

I °

t_

in 3

T_

d

F . -OJ

-I00.00 -TS.O0 -S0.O0 -2S.O0 O.00 2s.bo

cI(RAD/SEC)

FIGURE 138 (CONTINUED)

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

STABILIZER LOOPS CLOSEDFOR AFT C.G. GLA TEST CONDITION

245
APPENDIX E

• GLA TEST

• GLA AILERON WITH RSS, PCS AND

GLA STABILIZER CLOSED

• MACH= 0.70

• ALTITUDE= 15,000 FT.

• GROSS WEIGHT= 2200 LBS.

• C.G.= )3% MAC

GRIN

NO. .5950

2 I. 000

3 I. 680

pI

I

4-

f

J

+

÷

+

I

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t

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- .60

I I I

-I. 20

I I I

-0.80 -0.40 0.00 0. q0

c_

oD

A

C.D

LU

o0

0C

3

,-=)

c3

c_

c_

t_

c_

o

c5

(RAD/SEC)

o

c,J

o.ob

246

FIGURE 138 (CONCLUDED)

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

STAB I L IZER LOOPS CLOSED FOR AFT C. Go GLA TEST CONDI T I ON
APPENDIX E

• GLA TEST

• GLA STABILIZER WITH RSS, PCS

AND GLA AILERON CLOSED

• MACH; 0.70

• ALTITUDE: 15,000 FT.

• GROSSWEIGHT: 2200 LBS.

• C.G, = 33_ MAC

ORIGINAL PAGE IS

DE POOR QUALITY

t \

, I

-20. O0 - 16. O0 - 12. O0 -8. O0 -q. O0 O. O0

c_(RAD/SEC)

FIGURE 139

DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

AILERON LOOPS CLOSED FOR AFT C.G. GLA TEST CONDITION

247
N?. GRIN

595 i.o(_

3 !. 680

t

l

iX

APPENDIX E

• GLA TEST

• GLA STABILIZER WITH RSS, PCS

AND GLA AILERON CLOSED

• MACI_: 0.70

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• O.G,: 33% MAC

I I I I

0

,.i- ed

t

t

"\,,

i ",s

l

J

_\ i \'

// _L../ ,

-125.00 -100.00 -75.00

c_

6

C_

LLJ

E3

i'D

( > i,,'_ 1

-- 7-- '

-50. O0 -25. O0

(RAD/SEC)

6

8

o. oo 2s. bo

r_

3

FIGURE 139 (CONTINUED)

DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOOI WITH RSS, PCS AND GLA

AILERON LOOPS CLOSED FOR AFT CoGo GLA TESTCONDtTION

248
APPENDIX E

• GLA TEST

• GLA STABILIZER WITH RSS, PCS AND

GLA AILERON CLOSED

• MACH- 0.70

• ALTITUDE: 15,000 FT,

• GROSS WEIGHT" 2200 LBS.

• C.G,: 33_ MAC

t

÷

Z

±

+

i

I

t

I

@,e

- .60

GRIN

,5950

l.OOO

1.880

I I I I I

I

I t I I

-1.2o -0.80 -0.40 o.oo o.4o

(_(RAD/SEC)

c_

T_

I

]

Iv

°

0

l.u

3

,-..,}

(5

c_

c_

O. llb

FIGURE 139 (CONCLUDED)

DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

' AILERON LOOPS CLOSED FOR AFT C.G. GLA TESTCONDITION

249
APPENDIX E

• GLA TEST

• BCS WITH RSS CLOSED

• MACH: 0.70 •

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200LBS.

• C.G,: 33% MAC

I I I

• I

-20. O0

C3

C_

C)

LI.I

oo -..

• r7

n,"

3"

,6

t_

// I /// J

' I/" /U

I I I I '4

- 16. O0 - 12. O0 -8. O0 -q. O0 O. O0 q. O0

(RAD/SEC)

250

FIGURE 140

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

.... AFT CoG. GLATEST CONDITION .....
APPENDIX E

• GLA TEST

• BCS WITH RSS CLOSED

• MACH: 0.70

• ALTITUDE: 1..5,000 FT.

• GROSSWEIGHT: 2200 LBS.

• C.G.: 33_ MAC

ORIGINAL PAGE IS'

DE POOR QUALITY

I I

I

C)

"4

C3

C'd

FIGURE 140 (CONCLUDED)

DASTARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

' AFT C.G, GLATEST CONDITION .....

251
APPENDIX E

• LAUNCH

• RSS

• MACH= 0.40

• ALTITUDE= 15,000 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20_ MAC

r i i I i / i (5

NO, GRIN / o') 1 .sso / '

I

I o

L:

8 ""

t °

.:_ ._

E

3

8

I I ,,"_'_ I

-20.00 -16.00 -12.00 -8.00 -4.00 oloo _:ob

(_(RAD/SEC)

FIGURE 141

DAS'r ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

....... FORWARDC.G. LAUNCH CONDITION

252
APPENDIX E

• LAUNCH

• RSS

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20% MAC

'cJ

I I

CO

•Do -1.2o -o.Bo -o.4o o.oo o.4o

o (RAD/SEC)

C.)

LLJ

CO CO

::2

n,"

3

o-,.,.j

CO

C_

'...:

CO

_D

c:;

CO

0,,I

c_

CO

Od

FIGURE 141 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

........ FORWARDC.G. LAUNCH CONDITION

253
APPENDIX E

• LAUNCH

• RSS WITH PCS CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

i

I I I I I

J

/ C_

C_

A

u.I

3

0

0

ED

-2o.oo -iB.oo -12.oo -B.O0 -4.00 0.00 4_ob

(RAD/SEC)

FIGURE 142

DAS_ ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

.... FORWARDC.G. LAUNCH CONDITION

254
APPENDIX E

• LAUNCH

• RSS WI151PCS CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

! .59

0

C_

0

• °

tm

c_

c_

0 0 0

.6o -_.2o -o.8o -o._o o.oo 0._o o,sb

(RAD/SEC)

A

LU

_3

3

.---j

FIGURE 142 (CONCLUDED)

DASTARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

FORWARDC.G. LAUNCHCONDITION

255
APPENDIXE

• LAUNCH

• RSS Wl'n-I PCS AND GLA CLOSED

• MACH: 0.40 •

• ALTITUDE: 15,000 Fl',

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20_ MAC

/"Jl'"

. // I

! L, L_

/ '/iI

I/['

\(!

I°

-20. O0 -16.00 -12.00 -8. O0 -_. O0 0.00 4.oh

c_(RAD/SEC}

(,.)

ILl

0'3

o C;_

rtr

S

FIGURE 14)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

...... FORWARDC,G. LAUNCH CONDITION'

256
APPENDIX E

• LAUNCH

• RSS WITH PCS AND GLA CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

I

NO. GAIN I \ I

I I

•6o -t. 20 -o. eo -o. qo o. oo o. qo

(RAD/SEC)

C_

(,D

'oJ

Od

'oJ

GO

C)

C_

(D

(.O

6

Co

"c;

C_

Od

c;

o.Bb

CD

uJ

v)

C_

<

D:

3

"I

FIGURE 143 (CONCLUDED)

DASTARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

........ FORWARDC.Go LAUNCH CONDITION

257
APPENDIxE

• LAUNCH

• RSS WITH BCS CLOSED

• MACH= 0.40

• ALTITUDE= 15,000 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20_ MAC

I I I I

-_o.oo -_s.oo -_2.oo -8.oo -qoo o.oo

o" (RAD/SEC)

¢D

0

_6

C:;,

"n;

(:Z)

4.oh

FIGURE 144

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

FORWARDC.G. LAUNCHCONDITION

258
APPENDIX E

• LAUNCH

• RSS WITH BCS CLOSED

• MACH: 0.40

• ALTITUDE= 15,000 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20% MAC

-!

NO. GRIN I

I I

I I

8o -_.2o -o.Bo -0.40 o.oo o.qo

(RAD/SEC)

4

(.0

0

OO

C.)

LIJ

L,9

_23

3

c_

c_

C_

C_

od

oI; 

FIGURE 144 (CONCLUDED)

DASTARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

..... FORWARDC.G. LAUNCHCONDITION

259
APPENDIX E

.

-20. O0

• LAUNCH

• PCS WITH RSS CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

t I I I I

I

- - -,_]k. ,_,,k.-_

C_

4

0

C_

A

CO

LLI

i °

v

3

I I I I "_

-16.00 -12.00 -8.00 -It. O0 0.00 Ll_ob

0_(RAD/SEC)

FIGURE 145

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

FORWARDC.G, LAUNCH CONDITION ....

260
APPENDIX E

• LAUNCH

• PCS WITH RSS CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT, 2500 LBS.

• C.G.: 20_ MAC

I I I

_A

I I I I I

'o-;

CI

CO

",.,,i

(_,

'...:

0

uJ

o ,,,0

',2 _

3

°'-'2

0

-1.60 -I. 20 -0. BO -0.40 O. O0 O.40 O.

o (RAD/SEC)

FIGURE 145 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

' ' ' FORWARDC.G. LAUNCH CONDITION ....

261
APPENDIX E

• LAUNCH

• PCS WITH RSS AND GLA CLOSED

• MACH: 0.40

• ALTIT1JDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

I I I I I

o

c_

(_

I I I

-20. O0 -16. O0 -12. O0 -B. OO -4. O0 O. 00

(_(RAD/SEC)

4.ob

262

FIGURE 146

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

' FORWARDC.G.LAUNCHCONDITION "
APPENDIX E

• LAUNCH

• PCS WITH RSS AND GLA CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20_ MAC

I I I

I I I I I

-_.60 -1.20 -o.so -0.40 0.00 0.40

o (RAD/SEC)

"eJ

0

L_

3

oJ

FIGURE 146 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

FORWARDC.G. LAUNCHCONDITION

263
APPENDIX E

• LAUNCH

• BCS WITH RSS CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

I I I I

\

\

FIGURE 147

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

' FORWARDC.G. LAUNCHCONDITION ....

264
APPENDIX E

• LAUNCH

• BCS WITH RSS CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20% MAC

AIN

I I

I I

I

-I.60 -I.20 -0.80 -0.40 O.O0 O.LIO

c_(RAD/SEC)

o=

C3

,-G

c_

0o

. °

('-3

o

c;

o

"c;

,c_

#-,,,

ILl

_o ,_

-- OC

3

FIGURE 147 (CONCLUDED)

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

• ' FORWARD C.G. LAUNCH CONDITION "

265
APPEND IX E

• LAUNCH

• RSS

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: •33% MAC

GRN

NO.I .59_;0

2 I. 000

3 l. 680

I I I

20. O0 - i 6. O0 -12. O0 8. O0

(_ (RAD/SEC)

266

FIGURE 148

DAST ARW-2 RSS SYSTEM GAI N/PHASE ROOT LOCI WI TH BASIC A I RPLANE FOR

........ AFT C.G, l_.AI,_ru TION._,._,, 'CONDI
APPEND IX E

• LAUNCH

• RSS

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33% MAC

t

l l.OO0

3 |.680

I I

I

t •

WI

-1.60 -1,2.0 O.qO

I

-0.80 O. u,O O. O0

(RAD/SEC)

r,-;

0

o,;

CD

gO

LU

LO

-- n,,"

3

(:3

tO

0

0.Bb

FIGURE 148 (CONCLUDED)

DAb_ ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

....... AFT C.Go LAUNCH CONDITION

267
APPENDIX E

• LAUNCH

• RSS WITH PCS CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33% MAC

o (RAD/SEC)

FIGURE 149

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

........ AFT C.G. LAUNCH CONDITION ' "

268
APPENDIX E

• LAUNCH

RSS WITH PCS CLOSED

• •

• MACH. 0.40

• ALTITUDE: 15w000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33_ MAC

=. o.,_j \ ' _ '

i .S9SO X /

2 i,ooo X " t

t

t

<D2>

I I I I

-_.eo -_.2o -o.8o .o.4o o.oo o.qo

o"(RAD/SEC)

o-;

E3

¢0

O4

,...,

(.3

LU

Lr)

. °

n.-

3

¢D

(:3

C,J

¢3

("U

o.Bb

FIGURE 149 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

....... AFT CoG. LAUNCH CONDITION

269
APPENDIX E

• LAUNCH

• RSS WITH PCS AND GLA CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS_WEIGHT: 2200 LBS.

• C.G.= 33% MAC

I I I I

FIGURE 150

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

....... AFT C.G. LAUNCH CONDITION

270
APPENDIX E

• LAUNCH

• RSS WITH PCS AND GLA CLOSED

• MACH: 0.40

• ALTITUDE= 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33% MAC

I

I

3 | .680_

I I I 1

I

I

, I I I

• 60 -I. 20 -0.80 -O.u,o O. O0

(RAD/SEC)

¢:3

to

C)

CU

C)

QD

"3

O

c_

C)

to

c;

C)

°

C)

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I

o.qo O._:b

(..)

uJ

CO

¢=:

n3

FIGURE 150 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

..... AFT C.G. LAUNCH CONDITION

271
APPEND I X E

• LAUNCH

• RSS WITH BCS CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G;: 33_ MAC

I I I I / I

P__d:IN

LI. .ooo 680

I

+

I

_ /

, /

, / /

i i /

t .

-20. O0 - ! 6. O0 - 12. O0 -8. O0 -LI. O0

ar (RAD/SEC)

/

/

/

/

/

//

,/

/

°/'

/

/

o

C_

o

CD

C_

A

LIJ

._ r_

-- ==E

n-

_=_

3

0

CD

c;

/

CO

Q

oc)

0.00 4.ob

FIGURE 151

DAS'r' ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

..... A'FTC.G. LAUNCH CONDITION

272
APPENDIXE

GRIN

NO. ,5950

1o000 I. 680

• LAUNCH

• RSS WITH BCS CLOSED

• MACH: 0.40

• ALTITUDE= 15,000 FT.

• GROSS WEIGHT: 2200 LBS,

• C.G,: 33% MAC

N-

! I

-! . 60 -I. 20 -0.80

I I

I

I

j

: L I

-o.qo o.0o o._o

(RAD/SEC)

o-;

¢,,o

c_

("d

",..,;

ILl

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O:;

v

3

o

c_

Eo

c:;

c_

(%1

c;

o.eb

FIGURE 151 (CONCLUDED)

DAS'T ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

........ AFTC.G. LAUNCH CONDITION

273
APPENDIXE

• LAUNCH

• PCS WITH RSS CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33% MAC

NO.

1

2

3

t

-20. O0

GRIN

.5950

1.0_

I I I I

oJ

r_

f_j

¢.)

LU

(,/3

3

.-..)

-16oo -_zoo -Boo qoo ooo ,_.ob

(RAD/SEC)

FIGURE 152

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

AFT C.G. LAUNCH CONDITION ....

274
APPEND I X E

• LAUNCH

• PCS WITH RSS CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33% MAC

I I I

tL

l

J

÷

I I

-I .BO -I .20 -0.80

l

i I

-0. rio O. O0

(RAD/SEC)

¢,.;

0

r,;

0

,

(,o

"c:;

• °

C'g

I

C_

u.J

:=. {_

:3

(:3

FIGURE 152 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

AFT C.G. LAUNCH CONDITION

275
APPENDIX E

• LAUNCH

• PCS WITH RSS AND GLA CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSSWEIGHT: 2200 LBS.

• C.G,: 33% MAC

I_. GRIN

S 1.680

I I I' I

I I

cJ

£M

(RAD/SEC)

FIGURE 153

DAS'r ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

.... AFT C.G. LAUNCH CONDITION ' '

276
APPENDIX E

• LAUNCH

• PCS WITH RSS AND GLA CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33% MAC

I N_.

3

i.ooo

I I I

1.68o

I

i

I I

-1.60 -1.20 -O,BO

I

i I t

-0.40 0. O0

0 (RAD/SEC)

0.40

o-;

C)

C:)

A

C/3

r_

3

°---.)

C_

• °

t3

'=5

+=5

o.sb

FIGURE 153 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

.... AFT C.G. LAUNCH CONDITION

277
APPENDIX E

• LAUNCH

• GLA AILERON WITH RSS, PCS AND

GLA STABILIZER CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33% MAC

I I I I

,"- o o n I

-20 OO -16. O0 -12.00 -8.00 -it. O0 0.00

o (RAD/SEC)

C3

(:3

C_

C3

A

(.3

I,,

C3

_= <

3

"-"3

C3

C3

I

278

FIGURE 154

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

' STABILIZER LOOPS CLOSED FOR AFT C,G. LAUNCH CONDITION
-125.00 -I00.00 -75.00

APPENDIX E

• LAUNCH

• GLA AILERON WITH RSS, PCS AND

GLA STABILIZER CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33% MAC

I I I

I

-50. O0 -25. O0

(RAD/SEC)

¢/1

E_

C_

,ul

C3

l:3

C3

.(:3

c._

LJJ

E3

(:3

,u;

oa

c:)

o.oo 2s.bo

v

FIGURE 154 (CONTINUED)

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

STABILIZER LOOPS CLOSED FOR AFT C,G. LAUNCH CONDITION

279
t

APPEND IX E

• LAUNCH

• GLA AILERON WITH RSS, PCS AND

GLA STABILIZER CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33% MAC

I I I

/

I I I I

o6D -1.20 -0.80 O. 40

I

-0.40 O. O0

o C D/S ;C)

('M

. °

3

°,,,_

. °

. °

J

o.sb

280

FIGURE 154 (CONCLUDED)

DASTARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCIWlll-I RSS, PCS AND GLA

STABILIZER LOOPS CLOSED FOR• AFT C;G. LAUNCH CONDITION
APPENDIX E

• LAUNCH

• GLA STABILIZER WITH RSS, PCS

AND GLA AILERON CLOSED

• MACH; 0.40

• ALTITUDE; 15,000 FT.

• GROSSWEIGHT: 2200 LBSo

• C.G.: 33% MAC

I I I ._...-- 11

, I

-20. O0 - 16. O0 - 12. O0 -8. O0 -1⁄4. O0 0. O0

(_D/SEC)

C_

,rd

A

O _

3

0

"rd

_.ob

FIGURE 155

DAST ARW-2 GLA STAB IL IZER LOOP GA IN/PHASE ROOT LOC I W ITH RSS, PCS AND GLA

AILERON LOOPS CLOSED FOR AFT C.G. LAUNCH CONDITION

281
APPENDIXE

-125.00 -100.00 --/5.00

• LAUNCH

• GLA STABILIZER WITH RSS, PCS

AND GLA AILERON CLOSED

• MACH: 0.40

• ALTITUDE= 15,000 FT.

• GROSS WEIGHT= 2200 LBS.

• C.G,: 33% MAC

I I I I r-,-

c_

LI3

o

o

-¢3

8

-so. oo -zs. oo o. oo zS.bo

(RAD/SEC)

A

(_

LLI

c_ o')

rv"

3

*'--'3

_3

(_

1.13

FIGURE 155 (CONTINUED)

. . . , . . .

DA_T ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WIT1-! RSS, PCS AND GLA

AILERON LOOPS CLOSED FOR AF'r C.G; LAUNCH CONDITION

282
-I

APPENDI X E

• LAUNCH

• GLA STABILIZER WITH RSS, PCS AND

GLA AILERON CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSSWEIGHT: 2200 LBS.

• C.G.: 33% MAC

I I I

I

I

rJo

Od

aD

:3:

°,,_j

C)

rE)

¢%t

. °

O0

I I I I I_

60 -_.ao -O.BO -O._O o.oo 0._0 o.eb

(7 (RAD/SEC)

FIGURE 155 (CONCLUDED)

DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

AILERON LOOPS CLOSED FOR AFT C.G. LAUNCH CONDITION

283

DO 6000 2145 REV 9182
APPENDIX E

• LAUNCH

• BCS WITH RSS CLOSED

• MACH: 0.40

• ALTITUDE= 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33_ MAC

I I I I

FIGURE 156

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

..... AFT C.G. LAUNCH CONDITION ....

284
APPENDIX E

• LAUNCH

• BCS WITH RSS CLOSED

• MACH: 0.40

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.= 33% MAC

| NO.

i

I

f

4-

i

+

•$95o

[..oQo

\

\

\

i

/

/

/

/

/

/

/

/

/

/

,/ /

/

/

/

/

// •

/'

/

/'

/

l

/

/

/

/

/

{.(}

",-G

C_

, °

0

L_

3

_---a.e,p

0 i , I t o."

-1.6o -l._o -o.eo -o._o o.oo o._o o.eb

o (RAD/SEC)

FIGURE 156 (CONCLUDED)

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

.... AFT C.G. LAUNCH CONDITION

285
APPEND IX E

• HIGH ALTITUDE

• RSS

• MACH: 0.70

• ALTITUDE: 50,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

I I I

NO. GRIN

,5950 1.000

3 t,680

-20. O0 - 16. O0 - 12. O0 -8. O0 -4. O0

o (RAD/SEC)

I

0.00

0

C_

_.ob

FIGURE 157

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

FORWARD C,G. HIGH ALTITUDE CONDITION

286
APPENDIX E

• HIGH ALTITUDE

• RSS

• MACH: 0.70

• ALTITUDE= 50,000 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20_ MAC

,o. ._,_

1,68o I, ooo /

I

-o. 8o -o. _o o. oo o. 4o

a (RAD/SEC)

c_

143

C:)

Cu

,-,l

QO

l: I r-_

I ....

I .'-'l

t , o

I

c:i

¢D

"¢g

C3

I I¢:;

o.sb

FIGURE 157 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

..... FORWARDC,G. HIGH ALTITUDE CONDITION

287
APPENDIX E

• HIGH ALTITUDE

• RSS WITH PCS CLOSED

• MACH: 0.70

• ALTITUDE= 50,000 FI".

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20_ MAC

No. ._

i I.. 000 t.680

I I I

+

/

/

/

/

.

/°

I

r,-,

c3

-20. O0 - 16. O0 - 12. O0 -8. O0 -4. O0 O. O0

(RAD/SEC)

(:3

C3

O

C3

_.ob

288

FIGURE 158

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

..... FORWARDC.G, HIGH ALTITUDE CONDITION
APPENDIX E

• HIGH ALTITUDE

• RSS WITH PCS CLOSED

• MACH= 0.70

• ALTITUDE= 50,000 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.= 20_ MAC

' NO. GRIN I I _ I

l ,$9S0

2 I. 000 i/ /

+

- I. 60 - 1.20 -0.80 -0. llO O, O0

cr (RAD/SEC)

O. qO

0-;

¢.o

Oa

',-,;

L)

ILl

°

3

c_

, °

_o

c;

('%1

c;

0,.I

o.sb

FIGURE 158 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

..... FORWARDC.G; HIGH ALTITUDE CONDITION

289
APPENDIX E

• HIGH ALTITUDE

• RSS WITH PCS AND GLA CLOSED

• MACH: 0.70

• ALTITUDE: 50,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20% MAC

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FIGURE 159

DA_T ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCl WITH PCS AND GLA CLOSED FOR

...... FORWARDC.G. _HIGH ALTITUDE CONDITION

290
APPENDIX E

• HIGH ALTITUDE

• RSS WITH PCS AND GLA CLOSED

• MACH: 0.70

• ALTITUDE= 50,000 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20_ MAC

I NO" I

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DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

...... FORWARDC.G. HIGH ALTITUDE CONDITION

291
APPENDIX E

• HIGH ALTITUDE

• RSS WITH BCS CLOSED

• MACH: 0.70

• ALTITUDE: 50,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

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GRIN

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DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

FORWARDC.G, HIGH ALTITUDE CONDITION
APPENDIX E

• HIGH ALTITUDE

• RSS WITH BCS CLOSED

• MACH: 0.70

• ALTITUDE= 50,000 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20_ MAC

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DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

.... FORWARD C. G, H I GH ALT ITUDE COND I T I ON

293
APPENDIX E

• HIGH ALTITUDE

• PCS WITH RSS CLOSED

• MACH: 0.70

• ALTITUDE: 50,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

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FIGURE 161

DAST ARW-2 PCS GAIN/PHASE ROOT LOCl WITH RSS CLOSED FOR

FORWARD C.G. HIGH ALTITUDECONDITION
APPENDIX E

• HIGH ALTITUDE

• PCS WITH RSS CLOSED

• MACH: 0.70

• ALTITUDE: 50,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

NO. GAIN

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DASTARW-2 PCS GAIN/PHASE ROOT LOOI WITH RSS CLOSED FOR

FORWARDC.G. HIGH ALTITUDECONDIT10N

295
APPENDIX E

• HIGH ALTITUDE

• PCS WITH RSS AND GLA CLOSED

• MACH: 0.70

• ALTITUDE: 50p000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

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DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

' FORWARD C;G. HIGH ALTITUDE CONDITION
APPENDIX E

• HIGH ALTITUDE

• PCS WITH RSS AND GLA CLOSED

• MACH: 0.70

• ALTITUDE = 50,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

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DAS'T ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

FORWARD C.G. HIGH ALTITUDE CONDITION

297
APPENDIXE

• HIGH ALTITUDE

• BCS WITH RSS CLOSED

• MACH: 0.70

• ALTITUDE: 50,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

NO. I I

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DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOOI WITH RSS CLOSED FOR

FORWARDC.G, HIGH ALTITUDE CONDITION
APPENDIX E

• HIGH ALTITUDE

• BCS WITH RSS CLOSED

• MACH: 0.70

• ALTITUDE: 50,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.- 20_ MAC

NO. GRIN

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DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

FORWARDC.G.: HIGH ALTITUDE CONDITION

299
APPENDIX E

• HIGH ALTITUDE

• RSS

• MACH: 0.70

• ALTITUDE: 50,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33% MAC

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(RAD/SEC)

FIGURE 164

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOOI WITH BASIC AIRPLANE FOR

...... AFr C.G, HIGH ALTITUDE CONDITION

300
APPENDIX E

• HIGH ALTITUDE

• RSS

• MACH: 0.70

• ALTITUDE: 50,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33% MAC

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DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

....... AFT C.G. HIGH ALTITUDE CONDITION

301
APPENDIX E

• HIGH ALTITUDE

• RSS WITH PCS CLOSED

• MACH: 0.70

• ALTlll.IDE: 50,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33% MAC

(RAD/SEC)

FIGURE 165

DAST'ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

...... AFT C.G. HIGH ALTITUDE CONDITION

302
APPENDIX E

• HIGH ALTITUDE

• RSS WITH PCS CLOSED

• MACH: 0.70

• ALTITUDE: 50,000 FT.

• GROSS WEIGHT: 2200 LBSo

• C.G,: 33% MAC

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(RAD/SEC)

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FIGURE 165 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

..... AFT C.G. HIGH ALTITUDE CONDITION

303
APPENDIX E

• HIGH ALTITUDE

• RSS WITH PCS AND GLA CLOSED

• MACH- 0.70

• ALTITUDE: 50,000 FT.

• GROSS WEIGHT" 2200 LBS.

• C.G,: 33% MAC

c_(RAD/SEC)

FIGURE 166

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

....... AFT C.G, HIGH ALTITUDE CONDITION

304
APPENDIX E

.e HIGH ALTITUDE

• RSS WITH PCS AND GLA CLOSED

• MACH: 0.70

• ALTITUDE= 50,000 FT.

• GROSS WEIGHT= 2200 LBS.

• C.G;: 335 MAC

I I

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(RAD/SEC)

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DAS't"ARW-2 RSS SYSTEN GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

....... AFT C,Go HIGH ALTITUDE CONDITION

3O5
APPENDIXE

• HIGHALTITlJDE

• RSS WITH BCS CLOSED

• MACH: 0.70

• ALTITUDE: 50,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G;: 33_ MAC

I I I

-20. O0 -16.00 -12.00 -8.00 -=4.00

( RAD/SEC}

O. O0

FIGURE 167

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

...... AFT C.Go HIGH ALTITUDE CONDITION

306
APPENDIX E

• HIGH ALTITUDE

• RSS WITH BCS CLOSED

• MACH: 0.70

• ALTITUDE: 50,000 FT.

• GROSSWEIGHT: 2200 LBS.

• C.G,: 33% MAC

I !

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FIGURE 167 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

...... AFT C,G. HIGH ALTITUDE CONDITION ' '

307
APPENDIX E

• HIGH ALTITUDE

• PCS WITH RSS CLOSED

• MACH: 0.70

• ALTITUDE: 50,000 FT.

• GROSSWEIGHT: 2200 LBS.

• C.G.: 33% MAC

I I I I

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FIGURE 168

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

' ' AFT C.G. HIGH ALTITUDE CONDITION

308
APPENDIX E

• HIGH ALTITUDE

• PCS WITH RSS CLOSED

• I_CH: 0.70

• ALTITUDE: 50,000 FT.

• GROSSWEIGHT: 2200 LBS.

• C.G,: 33% MAC

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FIGURE 168 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

• • . AFTC.G. HIGH ALTITUDE CONDITION " "

309
APPENDIX E

• HIGH ALTITUDE

• PCS WITH RSS AND GLA CLOSED

• MACH: 0.70

• ALTITUDE: 50,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,= 335 MAC

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FIGURE 169

DA_ ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

.... AFT C.G. HIGHALTITUDE CONDITION

3]0
APPENDIX E

• HIGH ALTITUDE

• PCS WITH RSS AND GLA CLOSED

• MACI..I: 0,70

• ALTITUDE: 50,000 FT.

• GROSSWEIGHT: 2200 LBS.

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FIGURE 169 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

.... AFT C.G_. HIGH ALTITUDECONDtTION

311
312

APPENDIX E

• HIGH ALTITUDE

• GLA AILERON WITH RSS, PCS AND

GLA STABILIZERCLOSED

• MACH: 0.70

• ALTITUDE: 50,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33% MAC

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FIGURE 170

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

STAB I L IZER LOOPS CLOSED FOR AFT C.G. H I GH ALT ITUDE CONDI T I ON
APPENDIXE

• HIGHALTITUDE

• GLA AILERON WITH RSS, PCS AND

GLA STABILIZERCLOSED

• MACH: 0.70

• ALTITUDE: 50,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33% MAC

I I

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FIGURE 170 (CONTINUED)

DAS'T ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

STAB I L IZER LOOPS CLOSED FOR AI=T C.G. H I GH ALT I TUDE CONDI T I ON

313
APPENDIX E

• HIGH ALTITUDE

• GLA AILERON WITH RSS, PCS AND

GLA STABILIZER CLOSED

• I_CH: 0.70

• ALTITUDE= 50,000 FT.

• GROSS WEIGHT= 2200 LBS.

• C.G,: 33_ MAC

I I I

+

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1 o.;

to

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FIGURE 170 (CONCLUDED)

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

STABILIZER LOOPS CLOSED FOR AFT CoGoHIGH ALTITUDECONDITION

314
APPENDIX E

• HIGH ALTITUDE

• GLA STABILIZER WITH RSS, PCS

AND GLA AILERON CLOSED

• HACH: 0.70

• ALTITUDE: 50p000 FT.

• GROSS WEIGHT: 2200 LBS.

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0

0

FIGURE 171

DAS'I"ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

' AILERONLOOPS CLOSED FOR AFT C.G. HIGH ALTITUDE CONDITION

3]5
APPENDIX E

• HIGH ALTITUDE

• GLA STABILIZER WITH RSS, PCS

AND GLA AILERONCLOSED

• MACH: 0.70

• ALTITUDE= 50,000 FT.

• GROSS WEIGHT= 2200 LBS.

• C.G,: 33_ MAC

I I I I

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FIGURE 171 (CONTINUED)

DA_ ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

AILERON LOOPS CLOSED FOR AFT C.G. HIGH ALTIT1JDE CONDITION

316
APPENDIXE

• HIGHALTITUDE

• GLA STABILIZER WITH RSS, PCS AND

GLA AILERON CLOSED

• I_CH: 0.70

• ALTITUDE= 50,000 FT.

• GROSS WEIGHT= 2200 LBS.

• C.G;: 33% MAC

t •

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FIGURE 171 (CONCLUDED)

DAb_ ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

AILERONLOOPS CLOSED FOR AFT C.G. HIGH ALTITUDE CONDITION

317
APPENDIX E

• HIGH ALTITUDE

• BCS WITH RSS CLOSED

• MACH: 0.70

• ALTITUDE= 50,000 FT.

• GROSSWEIGHT: 2200 LBS.

• C.G,: 33% MAC

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FIGURE 172

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

' AFT C.G. HIGH ALTITUDE CONDITION ' "

318
APPENDIX E

• HIGH ALTITUDE

• BCS WITH RSS CLOSED

• MACH: 0.70

• ALTITUDE: .50,000 FT.

• GROSSWEIGHT: 2200 LBS.

• C.G,: 335 MAC

I

I

I

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FIGURE 172 (CONCLUDED)

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

.... AFT CoG. HIGH ALTITUDE CONDITION •

319
APPENDIX E

• CRUISE

• RSS

• 1.0g FLIGHT

• MACH: 0,80

• ALTITUDE= 46,800 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20_ MAC

t,,o., .s_ t ' '

1.000

3 t. 680

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FIGURE 173

DASTARW-2 RSS SYSTEM GAIN/PHASE ROOT LOOI WITH BASIC AIRPLANE FOR

..... FORWARDC.G. CRUISE CONDITION

320
NO.

!

3

i

APPENDIX E

• CRUISE

• RSS

• 1.0g FLIGHT

• MACH: 0,80

• ALTITUDE: 46,800 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

GR N'_,. I . I

f

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FIGURE 173 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

....... FORWARDC.G. CRUISE CONDITION

321
APPENDIX E

• CRUISE

• RSS WITH PCS CLOSED

• 1.0g FLIGHT

• MACH: 0.80

• ALTITUDE: 46,800 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

!

!

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-20.00

l, ooo

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FIGURE 174

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

.... FORWARDC.G. CRUISECONDITION
APPENDIXE

• CRUISE

• RSSWITH PCS CLOSED

• l oOg FLIGHT

• MACH: 0.80

• ALTITUDE: 46,800 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

I I I

2 l.O00

3 1.680

I

r

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c_ (RAD/SEC)

UP

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Od

I

o. qo 0.'_

FIGURE 174 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

..... FORWARDC. G. CRUISE CONDI T I ON • •

323
APPENDIXE

• CRUISE

• RSS WITH PCS AND GLA CLOSED

• 1.0g FLIGHT

• MACH: 0.80

• ALTITUDE: 46,800 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

I I I

I

FIGURE 175

DA_T ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

........ FORWARDC.G. CRUISE CONDITION

324
t

2 t .000

3 !. 680

APPENDI X E

• CRUISE

• RSS WITH PCS AND GLA CLOSED

• 1,0g FLIGHT

• MACH- 0,80

• ALTITUDE= 46,800 FT.

• GROSS WEIGHT." 2500 LBS.

• C.G.= 20_ MAC

I I I

i , I I I

-z.so -_.2o -o.eo -o.qo o.oo 0.40

(RAD/SEC)

o;

C3

¢0

C_

OJ

C_

QO

A

r_

LU

o'3

TM

C3

'¢C

n,"

3

.-,,_

0

(-_

C3

C_J

o.sb

FIGURE 175 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

.... FORWARDC.G. CRUISE CONDITION

325
APPENDIX E

• CRUISE

• RSS WITH BCS CLOSED

• 1.0g FLIGHT

• MACH: 0,80

• ALTITUDE, 46,800 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G." 20_ MAC

NO. GAIN .$950

2 t.O00

3 L.880

I I I

3

.-,,_

-20.00 -16.00 -t2.OO -8.00 -q.O0 0.00 4.ob

(_ (I_D/SEC)

FIGURE 176

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

.... FORWARDC.G. CRUISE CONDITION

326
APPENDIX E

• CRUISE

• RSS WITH BCS CLOSED

• 1,0g FLIGHT

• MACH: 0.80

• ALTITUDE= 46,800 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20_ MAC

_,I I _ I

NO OR ," \

2 I.OOO \

: I

-1.6o -1.2o -o.eo -o,4o o.oo 0.40

(RAD/SEC)

C_

(.D

c_

c,J

0

U'3

3

0

c_

¢D

Od

FIGURE 176 (CONCLUDED)

DAST ARW-2 RSS SYS'TEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

..... FORWARDCoG. CRUISECONDITION

327
t

E

P

I

-20.O0

APPENDIX E

• CRUISE

• PCS WITH RSS CLOSED

• 1.0g FLIGHT

• MACH: 0.80

• ALTITUDE: 46,800 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

I I I I

I I I

0

0

Od

0

0

A

r_"

v

3

°..--_

j J° -(3

0

C_

0

0

0

-16.00 -12.00 -8.00 -ll.O0 0.00 4.

o (RAD/SEC)

FIGURE 177

DAST ARW-2 PCS GAIN/PHASE ROOT LOOI WITH RSS CLOSED FOR

FORWARDC.G. CRUISE CONDITION

328
APPENDIX E

• CRUISE

• PCS WITH RSS CLOSED

• 1oOg FLIGHT

• MACH= 0,80

• ALTITUDE- 46,800 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G,: 20_ MAC

I I I

4-

J

I

I I I I

-1.60 -1.20 -0.80 -0._0 O. O0 O. qo

C:,

O

GO

. °

LI.I

::a, C3

3

°.-...)

C,

C_

qD

C_J

"c;

0

0,.I

o.sb

o (RAD/SEC)

FIGURE 177 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOOI WITH RSS CLOSED FOR

' " FORWARDC.Go CRUISE CONDITION

329
APPENDIXE

• CRUISE

• PCS WITH RSS AND GLA CLOSED

• 1.0g FLIGHT

• MACH: 0.80

• ALTITUDE: 46,800 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

I I I I

i

i

I

eE_.- e,le- I

I I I I

C_

C_

£3

C_

0

0

-20.00 -16.00 -12.00 -8.00 -ll.O0 0.00 .ob

0 (RAD/SEC)

FIGURE 178

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

FORWARDC.G.CRUISECONDITION

330
lo

APPENDIX E

• CRUISE

• I:_S WITH RSS AND GLA CLOSED

• 1,0g FLIGHT

• MACH= 0.80

• ALTITUDE= 46,800 FT.

• GROSS WEIGHT= •2500 LBS.

• C.G.= 20_ MAC

I I I

I

I I I I

O

(_

00

(i)

.,,--)

0

0

c_

C)

C)

- I. 60 - 1.20 -0.80 -0. q,o 0. O0 O. qO o.8b

(RAD/SEC)

FIGURE 178 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOOI WITH RSS AND GLA CLOSED FOR

FORWARDC.G.CRUISECONDITION

331
APPENDIX E

• CRUISE

• BCS WITH RSS CLOSED

• 1.0g FLIGHT

• MACH: 0,80

• ALTITUDE= 46,800 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20_ MAC

I I' I I

t I

-2o.oo -_6.oo -12.oo -e.oo -q.oo o.oo

o (RAD/SEC)

C_

C3

Cd

FIGURE 179

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

' FORWARDC.G. CRUISECONDITION '

332
APPENDIX E

• CRUISE

• BCS WITH RSS CLOSED

• 1.0g FLIGHT

• MACH: 0,80

• ALTITUDE= 46,800 FT.

• GROSS WEIGHT= 2.500 LBS.

• C.G.: 20% MAC

I I I

(:3

c_

I (:3

('%1

I ,,c_

-o._o o.oo o.40 o.8b

(_ (RAD/SEC)

FIGURE 179 (CONCLUDED)

DAS'T ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

FORWARDC.G. CRUISECONDITION "

333
APPENDIX E

• CRUISE

• RSS

• 1.2g FLIGHT

• MACH: 0.80

• ALTITUDE: 46,800 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33_ MAC

I I I

Glen

2 t.O00

3 t. 680

t

-20.00 -16.00 -12.00

/

/

!

/

/

/

/

/

/

/

1

I//

/'I

/ J

I //

-8. O0 -q. O0

(RAD/SEC)

,/

/

/

/

A

LLI

3

c_

c_

-=;

C_

c_

C_

0

o.oo q.eb

FIGURE 180

DAS'T ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

........ AFT C.Go CRUISECONDITION

334
NO. / GRIN I

i I / .5950

I:%

J

i

r

- . 60

APF_ENDIX E

• CRUISE

• RSS

• 1.2g FLIGHT

• MACH: 0,80

• ALTITUDE; 46,800 FT.

• GROSSWEIGHT: 2200 LBS.

• C.G,: 33% MAC

I

-t .20

I

I

Ji

I I

-0.80 0 40 0 O0 0 40

tO

r3

CO

CO

CO

0,_

a (RAD/SEC)

C3

3

FIGURE 180 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

....... AFT C.G. CRUISECONDITION

335
APPENDIX E

• CRUISE

• RSS WITH PCS CLOSED

• 1,2g FLIGHT

• MACH: 0,80

• ALTITUDE= 46,800 FT.

• GROSS WEIGHT= 2200 LBS.

• C.G.: 33_ MAC

No.

+

!

I

GRIN

.5950

1.000

1.600

I I

/

/

/

i I

-20. O0 - 16. O0 - 12. O0 -8. O0 -q. O0 O. O0

(RAD/SEC)

C3

'0

C_

I

C3,

¢.>

LIJ

O0

r", •

<E

n."

_o

=;

q.ob

FIGURE 181

DAS'I"ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

.... AFTC.G. CRUISE CONDITION

336
APPENDIX E

• CRUISE

• RSS WITH PCS CLOSED

• 1.2g _FLIGHT

• NIACH: 0,80

• ALTITUDE: 46,800 FT.

• GROSSWEIGHT= 2200 LBSo

• C.G,-. 33_ I_C

NO GR N I '-, I (", I

," .$9 0 \ \

2 t. ooo x

I I

=$(

.60 -1.20 -0.80 -0.40 0.00

o (RAD/SEC)

GO

Ck]

C)

CO

• °

A

O

LU

c_ L/')

r..; r-_

n.-

t_

GO

.

c)

(%1

"¢5

Cd

i ¢5

o.4o o.sb

FIGURE 181 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

........ AFT C.G. CRUISE CONDITION ' •

337
APPENDIXE

• CRUISE

• RSS WITH PCS AND GLA CLOSED

• 1,2g FLIGHT

• MACH: 0,80

• ALTITUDE* 46,800 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33% MAC

t

-20. O0

GRIN

NO. .5950

2 bOO0

3 1.680

ii j/j !i

/ / ,, -o3

__m I

-16.00 " -12,00 -8.00 -U,.O0 0,00

C)

c)

c)

O

4.ob

(RAD/SEC)

FIGURE 182

DAS'T ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

........ AFT C.G. CRUISE CONDITION

338
• MACH:

• ALTITt

• GROSS

• C.G..

•SgSOX

2 l .ooo "x

APPENDIX E

ORUISE

RSS WITH PCS AND GLA CLOSED

1,2g FLIGHT

0,80

ALTITUDE: 46,800 FT.

GROSSWEIGHT= 2200 LBS.

33_ MAC

-1

I I I I

60 -1.2o -o.Bo -0.40 o.oo o.qo

(_ (RAD/SEC)

_D

C)

('d

CD

CO

. °

"c;

Od

o,Bb

A

r.)

LLI

03

oc

v

3

c:)

FIGURE 182 (CONCLUDED)

DAST ARW-2 RSS SYSTl_M GAIN/PHASE ROOT LO01 WITH PCS AND GLA CLOSED FOR

..... AFT C.G. (_RUISE CONDITION

339
APPENDIX E

• CRUISE

• RSS WITH BCS CLOSED

• 1.2g FLIGHT

• MACH: 0,80

• ALTITUDE: 46,800 FT.

• GROSSWEIGHT: 2200 LBS.

• C.G,: 33% MAC

I I I

FIGURE 183

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

........ AFT C.G, CRUISE CONDITION " ' "

34O
N'_30._ GRIN

.59S0

1.000

t.680

i

J

b

!

t

J

I

ii

I

,4-

i

r

-1.60 -1.20 -0.80

APPENDIX E

• CRUISE

• RSS WITH BCS CLOSED

• 1.2g FLIGHT

• MACH: 0;80

• ALTITUDE: 46,800 FT.

• GROSSWEIGHT: 2200LBS.

• C.G,: 33_ MAC

_D

C3

(RAD/SEC)

o

z=.

f--

C_)

Lu

• C3

3

...--:,

FIGURE 183 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

....... AFTC.G. CRUISE CONDITION

341
,

tAPPENDI X E

• CRUI SE

• PCS WITH RSS CLOSED

• 1.2g FLIGHT

• MACH: 0,80

• ALTITUDE:- 46,800 FT.

• GROSS WEIGHT: 2200LBS.

• C.G.: 33_ MAC

i. z& I

,

I I I I

cJ

o')

C;,

-4

A

/ t,,

-....

3

C3

(:_

Q

-G

JO. O0 - 16. O0 - 12. O0 -B. O0 -q. O0 O. O0 it. O0

(RAD/SEC)

FIGURE 184

DAST ARW-2 PCS GAIN/PHASE ROOT LOOI WITH RSS CLOSED FOR

' ' AFTC.Go CRUISE CONDITION "

342
APPENDIX E

• CRUISE

• PCS WITH RSS CLOSED

• 1.2g FLIGHT

• MACH: 0;80

• ALTITUDE: 46,800 FT.

• GROSS WEIGHT: 2200 LBSo

• C.G;= 33_ MAC

I i o_...,.

1

!

I

I

-0.80 -0. LlO O. O0

(RAD/SEC)

0;

C:,

0

QD

A

I.iJ

u3

n.,

3

CD

CD

0

t_

c;

¢'d

J f_

0.40 o.sb

FIGURE 184 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

" ' ' AFTC.G.CRUISE CONDITION ""

343
f

f

i

l

r

APPENDIX E

• CRUISE

• PCS WITH RSS AND GLA CLOSED

• 1.2g FLIGHT •

• MACH= 0.80

• ALTITUDE= 46,800 FT.

• GROSSWE IGHT: •2200 •LBS0

• C.G.= 33_ MAC

(lr.)

C_

0

/ .// _0

/

j,/

/' I

1

/ I /

I t

-20.00 -16.00 -12.00 -8.00 -Lto O0 0.00

(RAD/SEC)

LU

n,"

3

c;

0

o

0

0

_.ob

FIGURE 185

DAS'I" ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

.... AFT C°Go CRUISE CONDITION _ '

344
APPENDIX E

• CRUISE

• PCS WITH RSS AND GLA CLOSED

• 1.2gFLIGHT

• HACH: 0,80

• ALTITUDE; 46,800 FT.

• GROSSWE IGHT: •2200 LBS.

• C.G,: 33% MAC

J

I

I

4

+

t

f

t

-1.60 -1.20 -0.80

" _i_, i

-0. qO O. O0

(RAD/SEC)

0

TM

v

3

o_

O

j

o._o o.Bb

FIGURE 185 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

.... AFT C.G. CRUISE CONDITION ' '

345
APPENDIXE

• CRUISE

• GLA AILERON WITH RSS, PCS AND

GLA STABILIZERCLOSED

• 1.2gFLIGHT

• MACH= 0.80

• ALTITUDE: 48,800 FT.

• GROSS WEIGHT: 2200LBS.

• C.G.: 33_ MAC

I I I I

J

-20.00 -_e.O0 -_2.00 -e.oo -_.00 0.00

(RAD/SEC)

C3

(:3

O_

0

C)

0

.=_

0

L._

3

.--,_

C_

0

FIGURE 186

DA_T ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

STABILIZER LOOPS CLOSED FOR AFT C,G. CRUISE CONDITION

346
APPENDIX E

• CRUISE

• GLA AILERON WITH RSS, PCS AND

GLA STABILIZERCLOSED

• t.2gFLIGHT

• MACH: 0,80

• ALTITUDE= 46,800 FT.

• GROSS WEIGHT= 2200LBS.

• C.G.: 33_ MAC

I I

tn

i_-

c_

c_

,_1")

OJ

0

-C:)

A

(.)

u.I

n,,

3

C_

C3

-c;

u')

C_

C_

"¢j

I

I o

-so.oo -zs.oo o.oo zs.bo

_(RAD/SEC)

FIGURE 186 (CONTINUED)

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

STABILIZER LOOPS CLOSED FOR AFT C;Go CRUISE CONDITION

347
APPENDIX E

• CRUISE

• GLA AILERON WITH RSS, PCS AND

GLA STABILIZER CLOSED

• MACH: 0.80

• ALTITUDE: 46,800 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33% MAC

I I I

/

O

r_

. 0

. °

i

:_._o o:oo o:4o o.8_

(RAD/SEC)

348

FIGURE 186 (CONCLUDED)

DA_T ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

STABILIZER LOOPS CLOSED FOR AFT C,G. CRUISE CONDITION
APPENDIXE

CRUISE

GLA STABILIZER WITH RSS, PCS

AND GLA AILERONCLOSED

-e 1,2gFLIGHT

• MACH: 0,80

• ALTIT1JDE: 46,800 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33_ MAC

C_

Od

C_

C)

P,J

C_

C_

o_

I I I ._..--='

C_

O

"c4

4.ob

t

I

I

I

I

, I

-20.00 -le.oo -12.oo -e.oo -q.oo o.oo

(RAD/SEC)

LU

'=E

n"

v

3

o--,_

FIGURE 187

DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

AILERON LOOPS CLOSED FOR AFT C.G; CRUISE CONDITION '

349
APPENDIX E

• CRUISE

• GLA STABILIZER WITH RSS, PCS

AND GLA AILERON CLOSED

• 1,2gFLIGHT

• MACH: 0;80

• ALTITUDE: 46,800 FT.

• GROSS WEIGHT: 2200LBS.

• C.G.: 33% MAC

I I I

I

-',_5. O0 -tO0.O0 -75. O0 -50. O0 -25. O0 O. O0

(RAD/SEC)

u;

,,.=

.u";

t_

,%-('kl

0

0

ILl

03

• r",

n,"

3

0

-4

.p=

0

• °

t_

i'M

zs.bo

FIGURE 187 (CONTINUED)

DAsT ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOOI WITH RSS, PCS AND GLA

' AILERON LOOPS CLOSED FOR AFT C.G. CRUISE CONDITION

35O
APPEND IX E

• CRUI SE

• OLA STABILIZER WITH RSS, PCS AND

OLA AILERON CLOSED

• MACH: 0.80

• ALTITUDE: 46,800 FT.

• OROSSWEIOHT: 2200 LBS.

• C.G.: 33% MAC

I I I I I

----.._..__....,..,f I

I I l I

• 60 - I. 20 -0. BO -0. LiD 0.00 0. _0

(_ (RAD/SEC)

C_

od

_D

A

0

C_

..: _c

r,.,

0

. °

_uO

c;

3

o.sb

FIGURE 187 (CONCLUDED)

DA_T ARW-20LA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

AILERON LOOPS CLOSED FOR AFT C.O. CRUISE CONDITION •

351
APPENDIX E

• CRUISE

• BCS WITH RSS CLOSED

• • 1.2g FLIGHT

• MACH: 0,80

• ALTITUDE: 46,800 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33_ MAC

\

; /oz_ ,

0

cd

(%1

0

A

3

0

0

0

0

"rd

-20. O0 - 16. O0 - _2. oo -8. oo -_. oo o. oo _.

o" (RAD/SEC)

FIGURE 188

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

.... AFTC.G. CRUISE CONDITION ....

352
APPENDIX E

• CRUISE

• BCS WITH RSS CLOSED

• 1.2g FLIGHT

• I_CH: 0,80

• ALTITUDE: 46p800 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33_ MAC

- .60

r'-

I I I

-- --QI_I

- l. 20 -0.80 -0. u,o O. O0 O. 40

O" (RAD/SEC)

Q

c;

oLBb

FIGURE 188 (CONCLUDED)

DAST ARW-2 BCS SYSTEM GAI N/PHASE ROOT LOCI WI TH RSS CLOSED FOR

AFT CoG. CRUISE CONDITION

353
APPENDIX E

• MAXIMUM 0 (Vd)

• RSS

• MACH= 0.86

• ALTITUDE= 15,000 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20_ NAC

I I I

A

LU

C3

¢=:

,'I"

3

..,-_

-20.00 -t6.00 -t2.00 -8.00 -_,00

C_ (RAO/SEC)

FIGURE 189

DAS'I"ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

FORWARDC.G. MAXIMUMDYNAMIC PRESSURE CONDITION

354
APPEND IX E

• MAXIMUM Q (Vd)

• RSS

• MACH: 0.86

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

I !

-0, qO O. O0

(RAD/SEC)

FIGURE 189 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAI N/PHASE ROOT LOOI WI TH BASI C A I RPLANE FOR

FORWARDC.G. MAXIMUMDYNAMIC PRESSURE CONDITION

355
APPENDIX E

• MAXIMUM _) (Vd)

• RSS WITH PCS CLOSED

• MACH: 0.86

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20_ MAC

I I I

I

-20, O0 -16,00 -12.00 -8.00 -q.O0 0.00

C_ (RAD/SEC)

0

0

0

¢G

_.ob

A

L_

or}

(::3

3

356

FIGURE 190

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LO01 WITH PCS CLOSED FOR

.... FORWARDC.G. MAXIMUM DYNAMICPRESSURECONDITION ''
BOEJ/IM'O

• MAXIMUM Q (Vd)

• RSS WITH PCS CLOSED

• MACH: 0.80

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

I I I

I I

I

i I i

0

l£I

o

0

uJ

n,-

3

C:)

c_

0

0

l::)

0

0

- .60 -t. 20 -0, 80 -0. tlO O.O0 O.qo O.

(RAD/SEC)

FIGURE 190 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

FORWARDC.G. MAXIMUM DYNAMIC PRESSURE CONDITION

357
APPENDIX E

• MAXIMUM Q (V d)

• RSS WITH PCS AND GLA CLOSED

• MACH: 0°86

• ALTITUDE: 15,000 FTo

• GROSS WEIGHT: 2500 LBS°

• C.G.: 20_ MAC

I I I

I

t I

-20,00 -16,00 -12,00 -8.00 -u_0 O0 0,00

cr (RAD/SEC)

0

_.ob

358

FIGURE 191

DAST'ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH POS AND GLA CLOSED FOR

FORWARD C.G° MAXIMUM DYNAMIC PRESSURE CONDITION
APPENDIX E

• MAXIMUM Q (Vd)

• RSS WITH PCS AND GLA CLOSED

• MACH: 0.80

• ALTITUDE: 15,,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20% MAC

I I I

I

o a I o

- 1.60 - ! . 20 -0.80 -0. _0 O.O0

(RAD/SEC)

0

0

0

0

0

0

0..0 0.eb

A

0

LU

C= C/3

3

FIGURE 191 (CONCLUDED]

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

FORWARDC.G. MAXIMUM DYNAMIC PRESSURE CONDITION

359
APPENDIX E

• MAXIMUM Q (V d)

• RSS WITH BCS CLOSED

• MACH: 0.8b

• ALTITUDE= 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

/=/

/i

-20. O0 -16.00 -t2.00 -8.00 --q,.O0 0.00

OJ

(RAD/SEC)

0

0

aO

A

c.)

LU

• r_

3

0

0

0

t-J

• •

0

0

0

0

,_;ob

FIGURE 192

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

FORWARDC.G. MAXIMUM DYNAMIC PRESSURE CONDITION

360
APPENDIX E

• MAXIMUM Q (V d)

• R_S WITH BCS CLOSED

• MACH= 0.86

• ALT I TUDE, 15 _,OOO FT.

• GROSS WEIGHT= 2500 LBS.

• C.G.= 20_ MAC

NO.

2

i 3

GRIN

•59S0

t.O00

1.680

I

I

-1.60 -1.20

C_

(,D

c_

t",J

c)

OD

T=

o

T.-:

I o

I .I-o o

-o. 8o -o. 4o o. oo o. 4o o. 8b

c_ (RAD/SEC)

LI.I

(:3

¢=C

n,"

3

,-.,._

FIGURE 192 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

FORWARDC.G. MAXIMUM DYNAMIC PRESSURECONDITION

361

DO 6000 2145 REV 9182
APPENDIX E

• MAXIMUM Q (Vd)

• PcS W lll-IRSS CLOSED

• MACH: 0.86

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

N_"

I I I I

(_

I

o I

-20.00 -16.oo -12.0o -8.00 -4.00 o.oo _.ob

F I GURE 193

DAST AI_W-2 PCS GAIN/PHASE ROOT LOOI WITH RSS CLOSED FOR

• 'FORWARD C.G; MAXIMUM DYNAMIC PRESSURE CONDITION '

362
APPENDIX E

• MAXIMUM Q (v d)

• PCS WITH RSS CLOSED

• MACH: 0.86

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

-I. 6O

I I I

I

o4

LO

C_

('%1

(D

OlD

A

Lul

(./3

TM

m,.

£:D

(D

(m

I"kl

c;

-1.20 -0. BO -O. qO 0.00 0. qo O_Bb

o (RAD/SEC)

FIGURE 193 (CONCLUDED)

DAST ARW-..2 PCS GAIN/PHASE ROOT LOOI WITH RSS CLOSED FOR

' 'FORWARD C.G. MAXIMUM DYNAMIC PRESSURE CONDITION

363
APPEND IX E

• MAXIMUM Q (V d)

• F_;S WITH RSS AND GLA CLOSED

• MACH: 0.86

• ALTll'UDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20_ MAC

I t I t

F

LU

I / o

l i I I _;

-2o.oo -_6.oo -I_.oo -B.O0 -4.00 0.00 4.oh

o (RAD/SEC)

364

FIGURE 194

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

FORWARDC.G. MAXIMUM DYNAMIC PRESSURE CONDITION
APPENDIX E

• MAXIMUM Q (V d)

• PCS WITH RSS AND GLA CLOSED

• MACH= 0.86

• ALTITUDE; 15p000 FT.

• GROSSWEIGHT: 2500 LBS.

• C.G.= 20_ MAC

l

P

I I I

o-;

I

<-,;

C_

co

• •

C.)

LI.I

_J3

g:3

3

.,.-,_

"c:;

c_

_d

-t. 6o -1.2o -o. BO -0.40 O.O0 O.qO O.Bb

(RAD/SEC)

FIGURE 194 (CONCLUDED)

DAS_ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

.... FORWARDC.G. MAXIMUM DYNAMICPRESSURE CONDITION •

365
APPENDIX E

• MAXIMUM 0 (Vd)

• BCS WITH RSS CLOSED

• MACH: 0.86

• ALTITUDE: 15,000 F"T.

• GROSS WEIGHT= 2500 LBS.

• C.G.: 20_ MAC

.o.\.___ ' ' ' '

8

\

l

I I I I

I:

0

o

c_

CZ)

i

j c_

/ x

I c_ ' Ii I

I

-zo.oo -t6.oo -t2.oo -8.oo -q.oo o.oo 4ob

o (RAD/SEC)

A

u.I

S

°...,}

FIGURE 195

DAS'I"ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

• FORWARDC.G. MAXIMUM DYNAMIC PRESSURE CONDITION

366
APPENDIX E

• MAXIMUM Q (V d)

• BCS WITH RSS CLOSED

• MACH: 0.86

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2500 LBS.

• C.G.: 20% MAC

I:

ii

-1.20 -0.80

C)

oD

C_

(O

c_

=;

\ ' o

-l. 60 -0. LLO O. O0 O. 40 O. 8b

c_ (RAD/SEC)

FIGURE 195 (CONCLUDED)

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

.... FORWARDC.G. MAXIMUM DYNAMICPRESSURECOND1TION

367
APPENDIX E

• MAXIMUM Q (V d)

• RSS

• MACH: 0.86

• ALTITUDE= 15,000 FT.

• GROSS WEIGHT= 2200 LBS.

• C.G.: 33% MAC

I I I t

(RAD/SEC)

FIGURE 196

DA_ ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

AFT C.G. MAXIMUM DYNAMICPRESSURECONDITION

368
APPENDIX E

• MAXIMUM Q (Vd)

• RSS

• MAC'H: 0.86

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33_ MAC

I I I I

3- 1.68o

I

f

L.'.

I

-1.60 -1.20

¢3

_4

=o

---,-_....

f I

t I

O. O0 O. qO

C3

o,;

C3

(0

LU

C/'J

. °

n,.

• °

to

"(5

(:3

'c;

-o.eo -o._o o.eb

c_ (RAD/SEC)

F I GURE 196 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR

' AFT C,G. MAXIMUM DYNAMICPRESSURECONDITION

369
APPENDIX E

• MAXIMUM Q (V d)

• RSS WITH PCS CLOSED

• MACH: 0.86

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33_ MAC

I I !

NO. GAIN

l -4.5dB

2 0 dB (NOMINAL)

3 +4.5dB '/)

/;/

//

, /'i/'

2

I

I

J l

-20.00 -16.00 -12.00 -8.00 -q. O0 0.00

/

I

I

I

A

r,_)

LI.I

'L/')

C3

n,"

v

3

0--,_

C;,

<5

o

0

c_

C:)

Q

(7 (RAD/SEC)

FIGURE 197

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR

'" AFTC.G.MAXIMUM DYNAMIC PRESSURECONDITION "

370
APPENDI X E

• MAXIMUM Q (V d)

• RSS WITH PCS CLOSED

• MACH: 0.86

• ALTITUDE: 15,000 FT.

• GROSSWEIGHT: 2200 LBS.

• C.G.: 33% MAC

ft

l

1

Tf

[

t

i

t

I

t

GRN s_

1.000

1.680

I !

- I. 60 - I. 20 -0.80

, I ,

-0. u,O O. O0 O. qo

_ (RAD/SEC)

C)

(D

LIJ

U'3

°

3

C'D

¢:3

¢D

to

¢:)

"6

C_J

+6

o.Bb

FIGURE 197 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAINPHASE ROOT LOCI WITH PCS CLOSED FOR

AFT C.G.I_%XIMUM DYNAMIC PRESSURE CONDITION

371
APPENDIX E

e MAXIMUM Q (V d)

• RSS WITH PCS AND GLA CLOSED

• MACH" 0.86

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 •LBS.

• C.G,: 33% MAC

I t I t

-20.00 -16.00 -12.00 -8.00 4.00 0.00

(_ (RAD/SEC)

Q

,-G

O

oJ

41ob

FIGURE 198

DAb_ ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

AFTC.G. MAXIMUMDYNAMIC PRESSURE CONDITION

372
APPENDIX E

• MAXIMUM Q (V d)

• RSS wl'n-I PCS AND GLA CLOSED

• MACH: 0.86

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33% MAC

l

-1,60

I I I

(D

¢,i

A

rj

ILl

(,'3

.E3

3

C_

"c;

C)

t_

• °

I I I I I

-_.2o -o.ao -o.qo o.oo o.qo o.ab

(RAD/SEC)

FIGURE 198 (CONCLUDED)

DA:_T ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR

.... AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION

373
APPENDIXE

• MAXIMUM Q (V d)

• RSS WITH BCS CLOSED

• MACH: 0.86

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33_ MAC

l

./

_J

-20.00 -16.00

/

/

/

/

/'

I

-12.00

I !

/

/

/

/

/

/

/

/

/

J /

/

1'

/

(/o

/I °

-8. O0

/

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/

/

/

/

/

/

/

/

/

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o

I ,o.

-q,. O0 O. O0 u,. O_D

C)

/

C_

0

'=:;

a (RAD/SEC)

A

LJ.J

C/'}

C3

3

.°,--j

F I GURE 199

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

• ' AFT C.G. MAXIMUM DYNAMIC PRESSURECONDITION

374
APPENDIX E

• MAXIMUM Q (V d)

• RSS WITH BCS CLOSED

• MACH: 0.86

• ALTITUDE; 15,000 FT.

• GROSSWEIGHT: 2200 LBS.

• C.G.,: 33_ MAC

i

1

I I I !

÷

-1.60 -1.20

(3

&O

C3

c_d

"oJ

I

C3

A

C.)

C_

¢=;

n."

tl_ _._

3

m

I

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-0.80 -0. u,o O. O0 O. qO

or (_D/SEC)

0

°

t_

°

o

C)

o,sb

FIGURE 199 (CONCLUDED)

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR

' AFTC,G,MAXIMUM DYNAMIC PRESSURECONDITION

375
APPENDIXE

• MAXIMUM Q (V d)

• PCS WITH RSS CLOSED

• MACH: 0.86

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT= 2200 LBS.

• C.G,= 33_ MAC

I

NO. GAIN

1 -4.5dB

2 0 dB (NOMINAL)

3 +4.5dB

I I I

I I I

/

-_o.oo -_6.oo -_z.oo -B.oo_ -4.oo o.oo

(RAD/SEC)

C)

4.oh

A

LU

C_

r'_

v

3

FIGURE 200

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

' ' AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION ' '

376
APPENDIX E

• MAXIMUM q (V d)

• PCS WITH RSS CLOSED

• MACH: 0.86

• ALTITUDE; 15,000 FT.

• GROSS WEIGHT: 2200LBS.

• C.G,= 33_ MAC

NO. GAIN .5950

2 I.OgO

3 1.680

1 ! I

I

I

C

ir

-1.50 - t.20 -0.BO -0.40 O. O0

(RAD/SEC)

co

(Jo

c_

£M

0.40 o.Bb

A

c.)

L_

r'h

°,_

FIGURE 200 (CONCLUDED)

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

• ' ' AFT C.G, MAXIMUM DYNAMIC PRESSURE CONDITION

377
APPENDIX E

• MAXIMUM O (Vd)

• PCS WITH RSS AND GLA CLOSED

• MACH: 0.86

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33% MAC

t

i. .000680

I I I I

C_

C)

I I I I

-20. O0 - ! 6. O0 - I Z. O0 -8. O0 -q. O0 O. O0

(RAD/SEC)

¢3

¢3

¢3

FIGURE 201

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

' AFT C,G. MAXIMUM DYNAMIC PRESSURE CONDITION • _

378
APPENDIX E

• MAXIMUM Q (V d)

• PCS WITH RSS AND GLA CLOSED

• MACH: 0.86

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33_ MAC

NO. GRIN

! .5950

2 i.O00

3 l. 680

l

F

t t t I I

- 1.60 -1.20 -0o 80 -0. qO O. O0 O. qO

o" (RAD/SEC)

C_

cd

LI.I

r't

3

c_:l.

¢.o

t_d

FIGURE 201 (CONCLUDED)

DASTARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR

AFT C.G. MAXIMUM DYNAMIC PRESSURECONDITION

379
NO. GRIN

! ,5950

2 1.000

3 1.680

0

APPEND I X E

MAXIMUM Q (Vd)

GLA AILERON WITH RSS, PCS AND

GLA STABILIZER CLOSED

MACH: 0.86

ALTITUDE: 15,000 FT.

GROSS WEIGHT: 2200 LBS.

C.G.: 33_ MAC

J

/

/

/

/

/

/

/

/

,/

/

/

/

!

/

/

/

/

÷

i

i

i

-20. O0

/

/

/

/

/

/

/

/

/

/

J

.z_._l

/

/

/

/

/

/

/

/

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- 12. O0 -8.00 -q. O0 O. O0

o (RAD/SEC)

4-L"J

r

l

",-G

(S)

-Z6.O0 q.o_

r-_

3

.--.,j

380

FIGURE 202

DAS'r ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

STABILIZER LOOPS CLOSED FOR AFTC,G, MAXIMUM DYNAMIC PRESSURE CONDITION
APPENDIX E

MAXIMUM Q (V d)

GLA AILERON WITH RSS, PCS AND

GLA STABILIZER CLOSED

MACH: 0,86

ALTITUDE: 15p000 FT,

GROSS WEIGHT: 2200 LBS,

C.G.: 335 MAC

i I I

NO. GRIN • ,5950

I.O00 1.680

i \

-125.00 -lO0.O0

I I

t _

/

i

/

/

/

i

!

i

/

/

/

'i /

/, /

,/

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/

i/

I

r

i

-7s. oo

(D

/,

/ ,

i

i

d

(/)

.' [

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/

c)

0

o

cS

_ C21 i u; ,Od

-so. oo -2s. oo o. oo 2s.bo

cr (RAD/SEC)

FIGURE 202 (CONTINUED)

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSSp PCS AND GLA

STABILIZER LOOPS CLOSED FOR AFTC.G,MAXIMUM DYNAMIC PRESSURE CONDITION

381
APPENDIXE

• MAXIMUM Q (V d)

• GLA AILERON WITH RSS, PCS AND

GLA STABILIZER CLOSED

• MACH: 0.86

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33_ MAC

"?" ._4_

2 t.O00

3 1.680

I ! I

J

t

i/

-1.60

I I

-I. 20 -0. BO

/ i

'"I

-0. qO O, On

(_ (RADISEC)

\

N. LIFI

i c_)

0

3

I -,

J i:

-1.. -

0

382

FIGURE 202 (CONCLUDED)

DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

STABILIZER LOOPS CLOSED FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION
APPENDIX E

• MAXIMUM Q (V d)

• GLA STABILIZER WITH RSS, PCS

AND GLA AILERON CLOSED

• MACH: 0.86

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G,: 33% MAC

I

3 t;ss0

-- t __

-4-

-2O O0 -t6.00

/

/

f

Y

/

\,

\ \

"-"\ ,\

• ._. 2---i

i

- 12. O0 -8.00

.I"

/t

./

7

/J"

/

/(

/

/'

/

f

/

/

c_

.f./_

i

@

1

i 4

-q. O0 O. O0

(RAD/SEC)

A

! c.) ILl

i <:J L/')

I (:_ °'J

:b

I

I0

CO

(0

0

oJ

.lob

FIGURE 203

DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

AILERONLOOPS CLOSED FOR AFT C.G. MAXIMUMDYNAMIC PRESSURE CONDITION

383
APPENDIX E

• MAXI_JM Q (Vd)

• GLA STABILIZER WITH RSS, PCS

AND GLA AILERON CLOSED

• MACH: 0.86

• ALTITUDE: 15,000 FT.

• GROSSWEIGHT: 2200 LBS.

• C.G.: 33% MAC

+

N_

i

+

L

i

+

J

\

AN

l.O00

l.B80

I I I

\

\

\

'\

\,

\

x ',

i

-125.00 -I00.00

I . I t , - -- -_

T _

I _.

t o

(:3

°

tr

c-j

o

c:)

-zs oo -so.oo -zs.oo o.oo 25.bo

(_ (RAD/SEC)

(3

LU

(I)

r'_

(z:

rr

3

FIGURE 203 (CONTINUED)

DAS'TARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

AILERON LOOPS CLOSED FOR AFT C.G. MAXIMUMDYNAMIC PRESSURE CONDITION

384
'I NO.pl

3

4-

+

i

r

-1,60

APPENDIX E

• .MAXIMUM Q (V d)

• GLA STABILIZER WITH RSS, PCS

AND GLA AILERON CLOSED

• MACH= 0.86

• ALTITUDE- 15,000 FT.

• GROSS HEIGHT: 2200 LBS.

• C.G.: 33% MAC

i i i

GAIN

.$950

L.O00

t.680

J

I

I

0, 00

0

c_

o

!

1 "o

LLI

C_

,. °

3

o

i

c)

c_

'c5

-l. 20 -0.80 -0, qo O.qO O.8b

cr (RAD/SEC)

FIGURE 203 (CONCLUDED)

DAS'I'ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA

AILERON LOOPS CLOSED FOR AFT C,G. MAXIMUM DYNAMIC PRESSURE CONDITION

385
APPENDIX E

• MAXIMUM Q (V d)

• BCS WII_I RSS CLOSED

• MACH: 0.86

• ALTITUDE: 15,000 FT.

• GROSS WEIGHT: 2200 LBS.

• C.G.: 33% MAC

+\

\

\

I

I I I

'\

\

'\

\

\

"\\, '\

I I

I

I )_1 ----

-20. O0 -16. O0 -12. O0 -B. O0 -4. O0 O. O0

(RADtSEC)

0

.¢;

C3

A

I,I

03

ti"r_

• 3

°_

C3

o_

"4

FIGURE 204

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION

386
APPENDIX E.

• MAXIMUM Q (V d)

• BCS WITH RSS CLOSED

• MACH: 0.86

• ALTITUDE= 15,000 FT.

• GROSS WEIGHT= 2200 LBS.

• C.G,: ))_ MAC

0.40

r_

LIJ

oo

r_

3

0=

¢5

o (RAD/SEC)

c_

, °

¢3

c_J

o.sb

FIGURE 204 (CONCLUDED)

DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR

AFT C.G. MAX1MUM DYNAMIC PRESSURE CONDI T I ON

387
Standard BibliographicPage

1. Report No. 2. Government Accession No. 3. Recipient's Catalog No.

NASA CR-177959, Part 2

4. Title and Subtitle

DESIGN VERIFICATION AND FABRICATION OF ACTIVE CONTROL

SYSTEMS FOR THE DAST ARW-2 HIGH ASPECT RATIO WING,

PART 2 - APPENDICES

7. Author(s)

C. R. McGehee

9. Per_rming Organization Name and Address

Boeing Military Airplane Company

P.O. Box 7730

Wichita, Kansas 67277-7730

12. Sponsoring Agency Name and Addr_s

National Aeronautics and Space Administration

Washington, DC 20546

i

5. Report Date

January 1986

6. Performing Organization Code

8. Performing Organization Report No.

0500-10897- l

I0. Work Unit No.

11. Contract or Grant No.

NAS l-16010

Contractor Report

14. Sponsoring Agency Code

15. Supplementary Notes

16. Abstract

A study was conducted under Drones for Aerodynamic and Structural Testing .

(DAST) program to accomplish the final design and hardware fabrication for

four active control systems compatible with and ready for installation in

the NASA Aeroelastic Research Wing No. 2 (ARW-2) and Firebee II drone flight

test vehicle. The wing structure was designed so that Active Control Systems

(ACS) are required in the normal flight envelope by integrating control

system design with aerodynamics and structure technologies. The DAST ARW-2

configuration uses flutter suppression, relaxed static stability and gust

and maneuver load alleviation ACS systems, and an automatic flight control

system. Performance goals and criteria were applied to individual systems

and the systems collectively to assure that vehicle stability margins,

flutter margins, flying qualities and load reductions were achieved.

17. Key Words (Sugg_t_ by Authors(s))

Flutter Suppression

Relaxed Static Stability

Maneuver Load Alleviation

Gust Load Alleviation

18. Distribution Statement

Until January 1988

19. S_urity Cl_sif.(of this report) [ 20. S_urit Classif.(of this page) 21. No. of Pag_ 22. Price

Unclassified I Unclassified 387