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Vtm-m BIRD IMPACT QUALIFICATION TEST

FOR A-1O WINDSHIELD /

T. L. Buchanan

Calspan Corporatton/AEDC Division

DTICELECTE

April 1g87 S APR 22 87J1

Final Report for December 9, 1986

Approved for public release; distribution is unlimited.

ARNOLD ENGINEERING DEVELOPMENT CENTER

ARNOLD AIR FORCE STATION, TENNESSEE

AIR FORCE SYSTEMS COMMAND

UNITED STATES AIR FORCE

821 09]

NOTICES

When U. S. oovernment drawinp, specifications, or other data are used for any purpose other than a definitelyrelatel Government procurement operation, the Government thereby incurs no responsibility nor anyobligation whatsoever, and the fact that the Government may have formulated, furnished, or in any waysupplied the said drawings, specifications, or other data, is not to be regarded by implication or otherwise,or in any manner licenon the holder or any other person or corporation, or conveying any rights or permissionto manufacture, use, or sell any patented invention that may in any way be related thereto.

References to named commercial products in this report are not to be considered in any sense as an endorsementof the product by the United States Air Force or the Government.

APPROVAL STATEMENT

This report has been reviewed and approved.

FRED J. SACKLEHAeronautical Systems DivisionDirectorate of Aerospace Flight Dyn TestDeputy for Operations

Approved for publication:

FOR THE COMMANDER

Dir, Aerospace Fit Dyn TestDeputy for Operations

'Z rq6 .'4Z e . -tZa -zZ z-fz Z

UNCLASSIFIEDSECURITY CLASSIFICATION OF THIS PAGE

REPORT DOCUMENTATION PAGE 4I& REPORT SECURITY CLASSIFICATION 1b. RESTRICTIVE n

UNCLASSIFIED Y iji,2 SECURITY CLASSIFICATION AUTHORITY" 3. OISTRIBUTION/AVAILABILIT'VM REPORT

Approved for public release; distributionb6 OgCLASISPICATIONIOOWNGRAOINO SCHEDULE is unlimited.

. PERFORMING ORGANIZATION REPORT NUMUIRI) S. MONITORING ORGANIZATION REPORT NUMBER($)

AEDC-TSR-86-V57

BNAME Of PERPORMING ORGANIZATION OPICE SYMBOL 7. NAME OP MONITORING ORGANIZATIONArnold Engineering IfaidiUcablet-Development Center DOFA ;%

Be. ADORESS (City. Slal. ard ZIP Code) 7b. ADORESS (City. Stowt &nd ZIP Code)

Air Force Systems CommandArnold Air Force Station, TN 37389-5000

I ,

61 NAME OP PUNOINGdSPONSORING OFPICE SYMBOL 9. PROCUREMENT INSTRUMENT IDENTIFICATION NUMBERORGANIZATION (if app1cabt)

SM-ALC/4MfIEA r_0. ADDRESS (City. Stait ond ZIP Code) 10. SOURCE OF FUN0ING NOB.

PROGRAM PROJECT TASK WORK UNITMcClellan AFB, CA 95652-5609 ELEMENT NO. NO. NO. NO.

921A4011. TITLE (nIctdiU Secuity Clamiflea.on)

SEE REVERSE OF THIS PAGE

12. PERSONAL AUTHOR($)Buchanan, T.L., Calspan Corporation/AEDC Division

13& TYPE OF REPORT 13b. TIME COVERED 14. OATS OF REPORT (Yr.. Mo.. Day) IS. PAGE COUNT

Final PROM9Dnor .9. TO __ Apri I 1987 18Is. SUPPLEMENTARY NOTATION

Available in Defense Technical Information Center (DTIC).

17. COSATI CODES l SUBJECT TERMS (Continue on mwern if neeem,-y and identify by block number)

FIGlO GROUP SUs. GR. A-10 Aircraft - bird impact testing01 02 windshield ,, ,

19. ABSTRACT (Coninue oan miey ift ncemry and identify by block numbr#

One shot was made on the A-10's left side windshield for this program. The objectiveof this shot was to qualify the windshield. The shot was at a nominal velocity of 360knots using a 4-lb bird. Descriptions of the test facility, test articles, and testprocedures are presented.

2C OISTRIBUTION/AVAILAILITY OF ABSTRACT 21. ABSTRACT SECURITY CLABSIFICATION

UNCLASSIPIED/UNLIMITED C SAME AS RPT. U OTIC USERS C1 UNCLASSIFIED

22& NAME OF RESPONSIBLE INDIVIDUAL 22b. TELEPHONE NUMBER 22c. OFFICE SYMBOL

W. 0. Cole (include A re Cod*)(615) 454-7813 DOS

D0 FORM 1473,83 APR EDITION OF i JAN 73S OSOoLETE. _. L.SSI"ISECURITY CLASSIFICATION OF THIS PAGE

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UNCLUSSIFIEDSECURITY CLA1SIP1CATIO OP THIS PACE

11. TITLE

Bird impact Qualification Test for A-lO Windshield

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CONTENTS

S Page

1.0 INTRODUCTION. .. . . . . . . . . . . . . . . . .. . 22.0 APPARATUS

2.1 Test Facility. .. . . . . . . . . . . . . ... 22.2 ProJectile and Sabot . . . . . . . . . . .. . 22.3 Test Article . . . . . . . . . . . . . . . ... 32.4 Test Instrumentation ................ 3

3.0 TEST DESCRIPTION3.1 Test Procedure and Conditions ............... 33.2 Data Reduction .i ............ 43.3 Measurement Uncertainty ...... .............. 4

4.0 DATA PACKAGE PRESENTATION ................... 45.0 REFERENCES ........ ........................ 4

I LLUSTRAT IONS

F igure

1. AEDC Birdstrike Facility . . . . . .. .. .. .. .. .... 52. Test Ar Arrannt. ge. .. nt... .. .. .. ..... 63. Bird Velocty Measuri St.. ... .. .. .. .. .... 74. Camera Locations. . . . . . . . . . . ........ 95. Bird Impact Location.......... . 106. Still Photographs for Shot 930. . . . . . . . . . . . .. 11

TABLES

Table

1. Test Summary ......... ... ................ 132. Estimated Measurement Uncertainties ........... . 14

TAB 1

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1.0 INTRODUCTION

The work reported herein was performed by the Arnold EngineeringDevelopment Conter *(AEDC), Air Force Systems Commnd (AFSC), underProgram Element 921A40, Control Number 9A4D at the request ofSacramento Air Logistic Center (SM-ALC), McClellan Air Force Base, CA.The project manager for the sponsoring agency was Mr. Greg Steuer, SM-ALC/MMIEA. The results were obtained by Calspan Corporation/AEDCDivision, operation contractor for the Aerospace Flight DynamicsTesting effort at AEDC, AFSC, Arnold Air Force Station, TN. This testwas performed in the Bird Impact Test Unit (Range S-3) in the vonKarman Gas Dynamics Facility (VKF) during the period December 9, 1986under Project Number CI09VJ (V41J-1E).

The objective of this test was to qualify the bird impactresistance of a left side windshield for the A-10 aircraft. One shotwas made using a 4-lb bird at a nominal velocity of 360 knots.

a

The final data package was transmitted under separate coverto Mr. Greg Steuer, SM-ALC/MMIEA, the sponsor of the test program.Request for copies of these data should be addressed to the sponsor,McClellan Air Force Base, CA 95652-5609. A copy of the final datapackage is on file on microfilm at AEDC.

2.0 APPARATUS

2.1 TEST FACILITY

The Range S-3 test facility is comprised of a compressed air-driven launcher, a sabot stripper, an X-ray system, a high-speedphotographic system, and a universal mounting platform. The testfacility and test area arrangement are shown in Figs. I and 2 and adetailed description of the test unit and its capabilities is containedin Refs. I and 2.

2.2 PROJECTILE AND SABOT

The projectile launched during this test program was a 4-lbchicken carcass. The bird was asphyxiated, placed inside apolyethyleme bag, quick-frozen, and stored at OOF until needed. Priorto testing, the carcass was thawed in still air at room temperature(750F) for approximately 24 hours or until the body cavity temperaturewas 70 +10F. Adjustments to the bird carcass weight were required toachieve the desired weight tolerance of +0.1 lb. The adjustments wereaccomplished by clipping carcass appendages. The adjustment did notexceed 10 percent of the carcass weight.

The packaged bird was mated to the launch tube using a balsa woodsabot. The sabot material density was nominally 10 lb/ft3 providing acombined bird/sabot launch weight of 5.7 lb. Separation of the bird

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and sabot was accomplished by a tapered and grooved sabot strippersection attached to the vent section of the launch tube (Fig. 2).

2.3 TEST ARTICLE

The test article was an A-10 windshield assembly consisting of athree panel windshield. The windshield tested was the left handpanel fabricated of polycarbonate approximately 0.58 In. thick. Thewindshield was fabricated and installed in the assembly by TEXSTAR,Inc. The assembly was mounted on a table to simulate an A-10 fuselage.

2.4 TEST INSTRUMENTATION

Bird position, orientation, and velocity prior to impact weredetermined using the bird velocity measuring system. This system usesthree 105 KV X-ray shadowgraph units and three electronic chronographs.The X-ray stations were nominally 3.5 ft apart with the first stationlocated approximately 3 feet from the muzzle ot the sabot stripper.Each X-ray pulser and electronic chronograph was triggered by a delayamplifier which was activated when the bird flew through break wireswhich were located under each X-ray unit (see Fig. 3).

Photographic coverage of the impact event and resultingtransparency response was recorded by 16-rm motion picture cameras(Hycam Model No. 41-004) operating at 5000 frames per sec. Fourcameras were used and the configuration is shown in Fig. 4. Eachcamera was started two seconds prior to launch and operated for aduration of five seconds. During operation, the 16-mm color film wasmarked with an event light (activated by the third breakwire of the X-ray system) and timing marks at 1 ms intervals providing a time basefor analysis of the dynamic response.

Test area temperature was measured using two copper-constantanthermocouples positioned to monitor air temperature at points near thetransparency. Temperature data were obtained manually from remotedigital readouts.

3.0 TEST DESCRIPTION

3.1 TEST PROCEDURE AND CONDITIONS

The procedure used for bird impact testing during this testconsisted of launching the bird carcass at a specified velocity into apredefined impact location on the test article. Prior to the shot, thetest article was positioned angularly and transversely relative to thebird flight path. Following the shot, the test article was inspectedfor damage, still photographs were taken, and the test article and testarea were thoroughly cleaned and disinfected.

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Figure 5 shows the impact location used during this test. Theshot was made on this location with the windshield frame at zero pitchand yaw angles. A. test summary of the shot is given in Table 1.3.2DATA REDUCTION

Pre- and posttest still photographs were obtained for the shot.Motion picture film was processed and available for viewing within 24hours after the shot. The film was then edited, titled, and duplicatedin quantities specified by the SM-ALC test director.

Bird velocity values were computed from displacement-timemeasurements obtained from in-flight X-rays and the chronograph system.

3.3 MEASUREMENT UNCERTAINTY

Measurement uncertainty is a combination of bias and precisionerrors defined as (Ref. 3):

U=+ (B + t95S)

where B is the bias limit, S is the sample standard deviation, and t95is the 95th percentile point for the two-tailed Student's "t"distribution and depends on the sample size. Estimates of the measureddata uncertainties for this test are given in Table 2.

4.0 DATA PACKAGE PRESENTATION

The final data package for this project was assembled underseparate cover. The data package includes a test summary log listingtest conditions and posttest observations along with pre- and postteststill photographs. High speed motion picture film was provided to thesponsor following the shots. A sample of the still photography isshown in Fig. 6.

5.0 REFERENCES1. Test Facilities Handbook (Twelfth Edition), "von Karman Gas

Dynamics Facility, Vol. 3." Arnold Engineering Development Center,March 1984.

2. Sanders, E. J. "The von Karman Gas Dynamics Facility Range S3 -

Description and Capabilities." AEDC-TR-76-9, January 1976.

3. Abernethy, R. B., and Thompson, J. W., Jr., et. al. "Handbook ofUncertainty in Gas Turbine Measurements." AEDC-TR-73-5(AD755356), February 1973.

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