REPORT DUMBER 147

MARCH 1964

MAIN LANDING GEAR DROP TEST REPORT

/

M LIFT FAN FlieNT'RESEARCH AIRCRAFT PROGRAM

CONTRACT NUMBER DA44-177-TC-7?5

GENERAL^) ELECTRIC

DDC AVAILABIIITY NOTICES

Distribution of this document is unlimited.

2 This document is subject to special export controls and each trans- mi ttal to foreigr governments or foreign nationals may be made only with prior approval of US Army Aviation Materiel Laboratories^ Fort Eustis, Virginia 23604

3. In addition to security requirements which must be met, this docu- ment is subject to special export controls and each transmittal to foreign gcvernmems or f c re i E" .nationals may be made only with prior approval of USAAVLABS, Fort Eustis, Virginia 23604

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DISCLAIMER

10,, The findings in this report are not to be construed as an official Department cf the Army position unless so designated by other authorized documents.

/ 11 „ When Government, drawings, specifications, or other data are used for any purpose other than in connection with a definitely related Ccvernment procurement operation , the United States Government thereby incurs no responsi- bility ncr a-.y obligation whatsoever; and the fact that the Gcvernir.ert may have formulated, furnished; or in any way supplied the said drawings, speci ficaticns or other data is not to be regarded by implication or otherwise as

in any manner licensing the holder or any other person or corporation, or ronveying any rights or permission, to manufacture, use, or sell any patented invention that may in any way be related thereto«

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DISPOSITION INSTRUCTIONS

^ I'Sy) Destroy this report when no longer needed. Do not return it to origtrtator.

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REPORT NUMBER 147 MARCH, 1964

MAIN LANDING GEAR

DISTü: .J DROP TEST REPORT

7i

XV-5A LIFT FAN

FLIGHT RESEARCH AIRCRAFT PROGRAM

ADVANCED ENGINE AND TECHNOLOGY DEPARTMENT

GENERAL ELECTRIC COMPANY

CINCINNATI, OHIO 45215

r r r

1S10LTR-1 DROP TEST REPORT

K W. LOUD MACHINE WORKS. Inc POMONA CAUFORN1A

Pag« 1

r REVISIONS

DaU

11-6.63

Chang« L«tt«r D««crlyClon

Pag« 2: Addcid App«adlx "A" Drop T««t R«quir«m«ntf Add«d App«ndix "B" Basic Strut Air Pr«isar« Carv«

Pag« 5: Corr«ct«d Mats Trav«! Valuss Addad: Aircraft Configuration Aircraft Sign Convention Not«s 167 Psig Drop T«st Inflation Prassur«. "8«« also Appondix "B" Added: 167 Psig Inflation Prassur«

: Addod: 167 Psig Inflation Prassur« : Add«d: 167 Psig Inflation Pr«ssur< : Add«d: 167 Psig Inflation Prsssun 3. U, 15, k 16: Added Calibration

Paga 9: Pag« 10 Pag« 11 Pag« 12 Pag«s 1

Approval«

/.; /

7

Values. 167 Psig Inflation Pressur«

1510LTR-1 DROP TEST REPORT

H. W LOUD MACHFNE WORKS. Inc POMONA. CALIFORNIA

Page 2

TABLE OF CONTENTS

Paragrapn

1.0

2. Ü

3.0

4.0

5.0

Figure I

Figure II

Figure III

Figure IV

Figure V

Figure VI

Figure VII

Appendix A

Appendix B

General

Applicable Documents

Summary

Discussion

Results

Table I

Drop Tost Tower

Reaction Platform

Orifice and Metering Pin Configuration.

Record #9770, Strut Stroke or Mass Travel-Inches

Record ^9772, Strut Stroke or Mass Travel-Inches

Record #9785, Strut Stroke or Mass Travel-Inches

Record #97d7, Strut Stroke or Mass Travel-Inches

Oscillograph Records #9770. #9772. #978S. #9787

Drop Test Requirements

Basic Strut Air Pressure Curve

Pag<

3

3

3

4

4

5

b

7

8

9

10

11

12

13 thru 16

17

19

1510LTR-1 DROP TEST REPORT

H. W. LOUD MACHINE WORKS. Inc POMONA. CALIFORNIA

Page 3

1.0 GENERAL:

The shock absorber portion of the HlOLlOO Main Landing Gear, but

using a dummy cylinder was tested on 2 August 1963, in accordance

with the H. W. Loud Test Procedure 1S10LTP-4. Revision "A". This

report presents the successful completion of the established test

requirement».

The tests were witnessed by H. W. Loud Quality Control and Mr.

Heinz J. Kowaczek of Federal Aviation Agency.

2.0

2. 1

2.2

APPLICABLE DOCUMENTS:

1510LTP-4, Revision "A . H. W. Loud Drop Test Procedure.

SCDLÜ001, Ryan Main Gear Specification.

3.0 SUMMARY:

The results of the tests demonstrate satiafactory energy absorption

characteristics of the shock absorber. (See Table I)

1510LTR-1 DROP TEST REPORT

H. W. LOUD MACHINE WORKS. Inc POMONA, CALIFORNIA

Page 4

4. 0 DISCUSSION:

The shock absorber was mounted in the drop tower (See Figure I).

The ground roactions were meaaured with a reaction platform (See

Figure II). 'x he strut was serviced with hydraulic fluid «und extended

\v ith 167 pbig air pressure. The tire waa inflated to 180 paig.

5.0

The teats were performed in accordance w th the 1510LTP-4, Rev-

ision "A" Test Procedure. See Appendix "A" for a copy of the test

requirameata taken from the procedure.

Figure III shows the configuration of the metering pin and oriiice.

RESULTS:

The test results are given in Table I. The curves of vertical load vs

stroke and vertical load vs mass travel after contact are given in

Figures IV, V, VI, and VII. The actual tost oscillograph traces are

fcld out pages

1510LTR-1 DROP TEST REPORT

H. W. LOUD MACHINE WORKS Inc POMONA. CALIFORNIA

Page 5

TABLE I

Drop Serie« Record No.

Aircraft Configuration

Drop Height (Inches)

Actual Jig Wt. (lbs)

Energy Abeorbad (Ft. Ibi)

Wheel Speed (rpm)

3 9770

1 9772

2 9785

^

4 9787

2 PT Level 2 PT Level Tail Down 2PTVTOL! Gear Fwd. Gear Fwd. Gear Fwd. Gear Aft I 12500 lb. 9200 lb. 9200 lb. 9200 lb. !

6.80

6238

2983

2292

18.70

4638

5985

1971

18.70

4638

6210

1971

18.70

4638

6363

Sinking Velocity (Ft/sec)

6 10 10 10

Mats Travel (Inches) 6.89 8.61 8. 37 9.35

Tire Deflection (Inches) 1.52 1.64 1.65 1.66

Oleo Stroke (Inches)

5.54 7.02 6.78 7. 50

Platform Vert. Reaction (lbs)

7050 11370 12100 10840

Plat. Drag Fore 1450 2820 2000 o Reaction (lbs)Ait 3270 4090 4640

Strul Efficiency (%)

81.4 82.4 81.3 8x6

(a) 167 psig drop test inflation pressure

(b) See aUo Appendix "B"

1-ilOLTR- 1 DROP TEST REPORT P a g e 6

H. W. LOUD MACHINE WORKS. Inc POMONA. CALIFORNIA

F I G U R E I

D R O P T E S T T O W E R

XVSA MAIN LANDING G E A R

1 5 1 0 L T R - 1 D R O P T E S T R E P O R T P a g e 7

1510LTR-1 DROP TEST REPORT Page 8

) K W. LOUD MACHINE WORKS. Inc. POMONA. CAIJP0KN1A

FIGURE III

- r~ .320/ . 310

< rk — ( } \ V

120R Typ. i •i '. 300 301 DU.

1310L113 ORIFICE CONFIGURATION (HALF SIZE)

10. 34

9. 360

1.915 —

9. #40

8.800

— M i 5 -STRAIGHT TAPER

) f \ -T -» -4

It Ff Vrj r J I T

.445

.443

.481

.479

DU.

DU.

J /

.451

.449

.376

.374

12°

DU.

DU.

)

-I

1510L112 METERING PIN CONFIGURATION (HALF SIZE)

DROP TEST REPORT M10LTR-1 P*I« *

7 - r v l ^ j 7 v . ? . 3 j / \

f510L.TR-1 DROP TEST REPORT Page 10

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1510LTR-1 DROP TEST REPORT

H. W LOUD MACHINE WORKS. Inc POMONA. CMJFORNIA

Appendix A

Ptiiiv 17

APPENDIX A

DROP TEST REQUIREMENT

ISlOLTR-l DROP TEST REPORT Appendix A

1S10LTF-Ü

U p M '^ H M A H tA

U C

DROP TEST fflOCETURE

H. W LOIJD MAO^NE WORKS Im POMONA. CMJffJRNIA

P*t* 18

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H. W. LOUD MACHINE WORKS. Inc POMONA. CAUFORNIA

Appendix B

Pa^r ID

APPENDIX B_

BASIC STRUT AIR PRESSURE CURVE

I

I 1 I.

mOLTR-1 DROP TEST REPORT Pago 21)

Appendix B Q

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