UNCLASSIFIED

AD 296 301ARMED SERVICES TECHNICAL INFORMATION AGENCY ARLINGTON HALL STATION ARLINGTON 12, VIRGINIA

UNCLASSIFIED

NOTICE: 1fen goverment or other dravings, specifications or other data are used for any purpose other than in connection with a definitely related government procurement operation. the U. S. Government thereby incurs no responsibility, nor any obligation vhatsoever and the fact that the Government may have formalated, furnished, or in any way supplied the said drawingso specificationsp 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 conveying any rights or permission to manufacture, use or sell any patented invention that my in any way be related thereto.

0

-4

296 301

FEBRUARY 1963

AMRMUNITIONS TEST REPORTSHELF LIFE TEST ON ROCKET MOTORS, 15-KS-IOOO, MK 6 MODS

i'

FEB i.

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SHELF LIFE TEST ON ROCKET MOTORS, 15-KS-1000, MK 6 MODS

by Robert M. Cavett

PUBLICATION REVIEW This report has been reviewed and is approved

ALXI.PERESI CH Chief, Engineering and Test Division 2705th Airmunitions Wing

FEBRUARY 1963 2705TH AIH14UNITIONS WING OGDEN AIR MATERIEL AREA AIR FORCE LOGISTICS COMMAND UNITED STATES AIR FORCE Hill Air Force Base, Utah

OOY-TR-63-4 NOTICES The information furnished herewith is made available for study with the understanding that the Government's proprietary interests in and relation thereto shall not bc impaired. It is desired that the Judge Advoeate's Office, WCJ, Aeronautical Systems Division, Wright-Patterson Air Force Base, Ohio, be promptly notified of any apparent conflict between the Government's proprietary interests and those of others. The conclusions and recommendations made in this report are not to be considered directive in nature. This type information becomes official only when published in Technical Orders or other applicable Air Force publications.

ii

OOY-TR-63-4 ADMINI STRATI VE DATA PURPOSE OF TEST: This test was to verify the existing nine year shelf life and determine if any extension is possible. MANUFACTURER: Aerojet General Corporation, Azusa, California MANUFACTURER'S TYPE OR MODEL DESIGNATION: MOTOR: IGNITER: Rocket Motor, 15-KS-1OO, Mk 6 Mods (FSN 1340-309-5092-H340)

Igniter for 15-KS-1000 Rocket Motor, Mk 165 (FSN 1340-309-5095-H403)

DRAWINGS AND SPECIFICATIONS: Specification ATS-S2.109 Aerojet-General Corporation Igniter Drawing 39415 Aerojet-General Corp Igniter Specification ATP-SA-1OI.005k Aerojet-General Motor Drawing 39060 Aerojet-General Corp QUANTITY OF ITEMS TESTED: 24 each motors and igniters SECURITY CLASSIFICATION: Unclassified TESTS CONDUCTED BY: OOAMA (OOYET - 2705th Airmunitions Wing) Tisi Director: Hoyt 0. Brown, Major, USAF Robert M. Cavett, Chemical Engineer

Project Engineer: DISPOSITION OF SPECIMENS:

All metal parts generated from this operation were inspected, certified inert and turned over to the Redistribution and Marketing Division in accordance with Technical Order 11C3-1-3 and HAFBR 136-2. iii

OOY-TR-63-4 ABSTRACT This investigation was one phase of a series established to determine the ultimate life of the 15-KS-100 Rocket Motor. To accomplish this, 24 motors were visually and radiographically inspected and fired using static facilities at Hill Air Force Base, Utah.In order to best evaluate serviceability, temperature conditioning was accomplished at both high and low extremes of 1500F and -75 0 F. The motors, as in the past, continued to function without incident. Some small drift of the data from normality toward the specifications limits was noted but was not significantly detrimental to effect serviceability. The previous established life of 9 years was confirmed and an extension to 10 years is recommended.

iv

OOY-TR-63-4 TABLE OF CONTENTS PAGE Notices ........ ....................... ii Administrative Data ....... ................ .. iii Abstract ......... ...................... iv Table of Contents ........ ................... v

Introduction ......Description .........Figure 1 .........

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

113

Legend for Figure 2 ....... ................. Figure 2 ........ .......................Figure 3 ........... Test Pro edures .... ...... Figure 4.... . .. . . . Test Results .......... Table . . . . . . . ....... Tableitionof .ar.meters . . Figure 5 .Tal . . . . . . . . Figure 6 . . . . . . . . . . . .................... .............. .

4 5. . .. .. . . .

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

2

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

.

6 7 9 7 8 10 11 12

Figure 7

Table 3 . . . . . . . . . Definition of Parameters Table / . . . . . . . . . Key for Table 5 . .. . . Table 5 . . . . . . . . .

. .. ..

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

. . . . . 9.. .. . . . . . . . .. . . . . .

Conclusions . .. . . . . . ...Recommendations . .. Distribution Lit .

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

.. .. .. ....

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

13

15 16 17 18 19

2020 21

.. .. . . . . . ........ * ..................

v

OOY-TR-63-4

THIS PAGE INTENTIONALLY LEFT BLANK

vi

O0Y-TR-63-4 INTRODUCTION A total of 120 15-KS-1000 Rocket Motors were initially reserved for shelf life testing purposes. These units were stored at Eielson Air Force Base, Alaska until 1959, at which time they were shipped to Hill AF Base, Utah. Prior to this test, the established shelf life of 5 years had been extended, by previous test, to nine years. This test is the latest phase in determining the maximum life of this motor. The tests were accomplished in accordance with OOYEE Test Directive C-1-509-Y-2, 11 April 1961 and OOYEG SOP C-I-509-Y-2, 18 April 1962. Any inquiries on this report should be addressed to the Ground Launch Missiles Branch (OOYEG), Engineering and Test Division (OOYE), 2705th Airmunitions Wing (OOY). This document is the final report for Project C-1-509-Y-2. DESCRIPTION The 15-KS-IOOO Rocket Motor consists of a chamber assembly and an Aft-cap assembly which contains an outside restrieted, Internal burning, slotted propellant grain. The various components and dimensions of the motor are shown in Figures 1 and 2. Principle data on motor manufacture are as follows: Rocket Motor: Overall Length (Avg) Diameter (Principal) Diameter (Maximum) 33.45 Inches 10.30 Inches 11.45 Inches 144 Pounds 72 Pounds

Weight (Avg):Loaded Expended

Design Safety Data of the 15-KS-1000 Rocket Motor: Temperature range Ultimate strength of chamber Operating pressure range Pressure-release diaphragm range Allowable acceleration along axis Allowable acceleration normal to axis -65 0 F to 140OF 2400 psi 447 to 735 psi 1200 to 1600 psi 18 g 12 g

1

OOY-TR-63-4Propellant Grain Manufacture: Type Manufacture method Grain Design Propellant Grain Dimensions: Length Diameter Web Thickness 26.5 Inches 9.7 Inches 3.4 Inches Aeroplex AN-583AF Cast Slotted, Internal Burning

Propellant Composition (% by weight) is classified Confidential, therefore it has been omitted from this report. It can be found in OOYEE Confidential Report OOY-TR-61-11, February 1961 or in the Solid Propellant Information Agency Manual, M-1 The igniter used with the 15-KS-100 Rocket Motor is the Mk 165 which is also manufactured by the Aerojet-General Corporation. The electrical characteristics of the Mk 165 Igniter are: Resistance Recommended Firing Current Maximum No-Fire Current 0.25 (_1 0.06) ohm 25 amp 0.04 amp

The Mk 165 Igniter uses a glow plug to ignite a charge of black powder which in turn ignites the main charge of alclo pellets. The internal configuration of the Mk 165 Igniter is shown in Figure 3.

2

OOY-TR-63-*4

33.77

/2.23

Mark 6 Mod 0

Aft-End View

Mark 6 mod 1 All Dimensions are in Inches

FIGURE 1.

External Dimensions of' the Rocket Motor, 15-KS5-1000

3

OOY-TR-63-4

LEGEND for FIGURE 2

Nozzle Pressure Release Diaphragm Safety Diaphragm Deflector Cone Retainer Ring

Propellant Grain Mounting Lugs

(

Insulating Boot Chamber Assembly Handling Stand

O

Aft-Cap Assembly

44

OOY-TR-63-4

FIGURE 2. Cutaway View of a 15-KS-1000 Rocket Motor Showing its Major Components. 5

OOY-TR-63-4

43

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fr

6

OOY-TR-63-4 TEST PROCEDURES Twenty-four 15-KS-1OOO Rocket Motors were visually and radiographically inspected. Five motors were disassembled and a thorough internal inspection performed. Ten motors were 0 temperature conditioned to -75 F, four to 70F and ten to 150 0 F. All were fired and the results evaluated. The equipment used for the static firings are shown in Figure 4. TEST RESULTS VISUAL INSPECTION The visual inspection, both internal and external, was accomplished with no defects found. The five motors which were disassembled were in excellent condition. These motors were reassembled and fired with the others. RADIOGRAPHIC INSPECTION Each motor was X-rayed in two positions with a 2NEV unit. The defects (voids) found are listed in Table 1. These voids are normal in size and quantity for this motor and have never been known to produce adverse results during static tests. IGNITER CHECK All igniters were examined and tested for continuity prior to conditioning. Seven of the 24 igniters had high resistances by from 0.03 to 0.26 ohm. These slightly high values had no effect on motor performance. All others were within allowable limits.

7

OOY-TR-63-4

MOTOR NO.1

QTY

FORWARD END INCHES

QTY,2

2 3

1 1.125 X .125

I

CENTER SECTION INCHES

QTY1

AFT END INCHES.125 X .125

1

.5 X.5

3 2.5 X .25

i.125 X .125

56

30 Seattered

.25 X .25.125 X .125 1 1 1 .25 X .25 .25 X .25 .5 X,5 1 3 3

.125 X .125

5

Voids .25 X .25

78 9

5 .25 X .25

.125 X .125 .125 X .125 .125 X .125

1011

1

.75 X .75

1

.125 X .125

22

.125 X .125.125 X .125

1213 3 .25 X .25

22

.25 X .25.125 X .125

15 17

2

1 1

.25 X .25 .5 X .5

2

.25 X .25

.125 X .125

181920 21

1 .125 X .125

211

.25 X .25.25 X .25.125 X .125 .125 X .125

1 .125 X .125

1.25

X .25

1

1 1

.125 X .125 .125 X .125

2223 24.5 X .5

1

.125 X .125

11 1 2

.5 X .5

.125 X .125 .5 X .5 .125 X .125

1

1.5 X .5

All defects are internal voids. TABLE 1. Results of Radiographic Inspection.

OOY-TR-63-4

4

CIV,

001-TR-63-4 A graphical representation of the 15-KS-1000 performance specifications is shown in Figure 5. This data is also in numerical form in Table 2.

PARAMETERS Duration, Maximum (Sec) Duration, Nominal (Sec) Duration, Minimum (Sec) Thrust, Maximum (Lb) Thrust, Nominal (Lb) Thrust, Minimum (Lb) TABLE 2.

0 -75 F 19.45

70F 14.65 13.7 12.8 1160 1080 1010

150F 12.0 11.2 10.55 1460 1360 1260

18.3 16.9 890 790 670

Specification Data for Rocket Motors, 15-KS-000.

STATIC FIRING. All 24 test motors were fired without malfunction. Thrust and duration data were all within specification limits. Pressure and impulse data were satisfactory and all ignition delays were within the 0.5 second maximum allowable. A graphical comparison of test data with specification limits is shown in Figures 6 and 7. Data on motor manufacture and performance is outlined in Tables 3 and 4. A statistical evaluation of the data is covered in Table 5.

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OOY-TR-63-4

MOTOR

MOTOR

ITER

IGNITER

WEIGHT (LB) 137 137 137 136 137 136 137 136 136 137136

WT. (LB) 64 64 64 63 63 63 63 62 63 6463

PROP.

BATCHNO. 1-287 1-287 1-307 1-287 1-307 1-287 1-307 1-287 1-287 1-2871-287

MOTORNO. 8 10 11 13 14 15 16 17 18 193

TE4P MFG.(OF) -75 -75 -75 -75 -75 -75 -75 -75 -75 -7570

MFG.DATE 8-54 8-54 8-54 8-54 8-54 8-54 8-54 8-54 8-54 8-548-54

RESIST.(fl.) 0.25 0.24 0.56 0.24 0.34 0.23 0.37 0.21 0.57 0.230.-4

LOADED HMPTY

WT.(LB) 73 73 73 73 74 73 74 74 73 7373

DATE 5-53 5-53 5-53 5-53 5-53 5-53 5-53 5-53 5-53 5-535-53

1-307 1-287 1-287 1-2871-287

4 6 12 1F

70 70 70 150150

5-53 5-53 5-53 5-535-53

8-54 8-54 8-54 8-54$-54

0.29 0.24 0.26 0.250.27

137 136 136 137136

64 63 63 6463

73 73 73 7373

1-287 1-287 1-287 1-287 1-287 1-287 1-287 1-287 1-287

5 7 9 20 21 22 23 22 24

150 150 150 150 150 150

5-53 5-53 5-53 5-53 5-53 5-53

8-54 8-54 8-54 8-54 8-54 8-54 8-54 -54

0.36 0.21 0.24 0.36 0.26 0.37 0.25 0.37 0.30

136 136 137 136 137 137 137 137 137

64 63 64 63 64 64 63 64 63

72 73 73 73 73 73 74 7 744

150 5-53 1150 15-53 150 5-53

TABLE 3. Manufacture Data.

15

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OOY-TR-63-4 KEY FOR TABLE 5 The statistical dqta in Table 5 was calculated using the following definitions and Nrmulas: Xn X' cn is the average value of the samples used. is the estimated average range of the represented population. is the standard deviation of the sample group

' is the estimated standard deviation of the represented population. S.E. is the standard error of the mean which is used for determination of the range of average values to be expected for the represented Dopulation. are the maximum and minimum individual values which are expected for represented population.

Xi Maximum and Minimum

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is calculated from the following formula:o"= 6'n

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is calculated from:

S.E.

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Xi maximum and minimum values were calculated by: Xi Max & Min = 2 (ar I + S.E.) All statistical calculation was accomplished at the 95 per cent confidence level.

18

OOY-TR-63-4

PARAMETERDuration (sec)

TEMP(OF)-75 70 150 -75150

QUANTITY OF

SAMPLES10 3 10 1010

On18.58 13.96 10.89 416734

S.E..033 .126 .088 1.26.3

HIGH18.85 14.65 11.62 426786

Xi

LOW18.31 13.27 10.16 405681

.098 .178 .263 3.718.9

Presure (psi) Thrust (lb.)

-75 70 150 -75 70150

10 3 10 10 310

737 1031 1348 13716 1439314677

11.3 13.8 36.5 180 27132

3.8 10.4 12.2 60 1944

769 1088 1449 14214 1449715043

706 974 1247 13218 1428914311

Total Impulse (Lb.Sec) TABLE 5.

Statistical Evaluation of Data.

19

OOY-TR-63-4 CONCLUSIONS 1. 15-KS-1000 Rocket Motors of age 10 years or less will perform within specification limits when subjected to tempera0 tures now lower than -65 F or higher than 1400 F. 2. The 15-KS-1000 units exhibit excellent resistance to damage caused by thermal shock or rough handling. 3. 15-KS-1000 Rocket Motors have a reliability of 99% at a 95% Confidence Level. RECOMMENDATIONS 1. Recommend that the operational shelf life of the 15-KS-1000 Roeket Motors be extended to 10 years. 2. Recommend that tests be conducted annually to attempt further extension of the shelf life of this motor.

20

OOY-TR-63-4 DISTRIBUTION LIST 3 1 2 1 20 1 1 1 1 1 1 1 1 10 Dop IG for Safety, Hq USAF (AFIGS-3), Norton AFB, Calif Hq USAF (AFSSS-AE), Wash 25, DC AFLC (MCSW and MCAS), Wright-Patterson AFB, Ohio AUL, Maxwell AFB, Ala ASTIA (TISIA-2), Arlington Hall Stn, Arlington 12, Va Bureau of Naval Wpns (Code RMMO-5), DeO of the Navy, Wash 25,DC CO, US Army Mtel Comd Field Safety Agcy, Charlestown, Ind Safety Div (AMCAD-SA), US Army Mtel Cemd, Wash 25, DC US Army Ammunition Procurement and Sup Agcy (SMJAP-Q), Joliet, Ill Hq AFSC (SCMMS-3), Andrews AFB, Wash 25, DC CO, Picatinny Arsenal (Tech Info Lib), Dover, NJ MATS (MAMSS/SBG), Scott AFB, Ill Tech Lib (Code T2), US Naval Propellant Plant, Indian Head, Md OOAMA (1-OOY, 1-OOYIT, 1-OOYID, 1-OOYS, 1-OOYE0, 5-OOYEG, 1-OOAEP) Hill AFB, Utah 1 TAC (Dir of Requirements), Langley AFB, Va 1 SAC (Mt4E), Offutt AFB, Nebr 1 ADC (ADhI-EC), Ent AFB, Colo 1 ATC (ATMSS-CA), Randolph AFB, Tax 1 CONAC (MSS-2WM), Robins AFB, Ga 1 USAFE (MOD-H), APO 633, New York, NY 3 PACAF (PFORQ, PFNSS-W, PFWE-WSA), APO 953, San Francisco, Calif 1 AAC(ALDMS-1), APO 942, Seattle, Wash 1 NGB, Air Sys & Log Div (NG-AFSS), Wash 25, DC 1 CO (QE Lab), US Naval Weapons Stn, Seal Beach, Calif 1 CO (QE Lab), Naval Ammunition Depot, Concord, Calif 1 Comdr, US Naval Ord Test Stn (Code 556), China Lake, Calif 1 CO, US Naval Ammunition Depot (Code 35), Crane, Ind 1 Det 4, ASD (ASQWW), Eglin AFB, Fla 1 AFSC Engineering Office (ASNPESD), Hill AFB, Utah 1 Dep IG for Safety, Hq USAF (AFIMS-2), Norton AFB, Calif 1 6593d Test Gp (Devel)(DGSMS), Edwards, Calif 1 eiI I Blistics Lab (Tech Lib), P 0 Box 210, Cumberland, Md 3 anfo Agcy, John Hopkins Univ, Applied Physics Lab, p (Attn: P.J. Martin, Asst Gp Suprv), 8621 Georgia Ave, SLir; " Spring, Md

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