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MEMORANDUM REPORT ARBRL-MR-03210

(Supersedes IMR No. 737)

AEROBALLISTIC TESTING OF THE XM825

PROJECTILE: PHASE IV. VER IF I CAT ION OF

FLIGHT STABILITY FOR HIGH MUZZLE

VELOCITIES/HIGH QUADRANT ELEVATIONS

William P. D'Amico, Jr. Rao J. Yalamanchili

November 1982

US ARMY ARMAMENT RESEARCH AND DEVELOPMENT COMMAND BALLISTIC RESEARCH LABORATORY

ABERDEEN PROVING GROUND, MARYLAND

Approved for public release; distribution unlimited.

DTIC QUALITY mSESOTBP 8

Destroy this report when it is no longer needed. Do not return it to the originator.

Secondary distribution of this report is prohibited.

Additional copies of this report may be obtained from the National Technical Information Service, U. S. Department of Commerce, Springfield, Virginia 22161.

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

The use of trade names or manufacturers' names in this report- does not constitute indorsement of any aormercial product.

UNCLASSIFIED SECURITY CLASSIFICATION OF THIS PAGE (Whan Data Bntmed)

REPORT DOCUMENTATION PAGE 1. REPORT NUMBER

Memorandum Report ARBRL-MR-03210

2. GOVT ACCESSION NO.

READ INSTRUCTIONS BEFORE COMPLETING FORM

3. RECIPIENT'S CATALOG NUMBER

4. TITLE (and Subtitle)

Aeroballistic Testing of the XM825 Projectile: Phase IV. Verification of Flight Stability for High Muzzle Velocities/High Quadrant Elevations

7. AUTHORf*;

William P. D'Amico, Jr. Rao J. Yalamanchili

9. PERFORMING ORGANIZATION NAME AND ADDRESS

US Army Ballistic Research Laboratory ATTN: DRDAR-BLL Aberdeen Proving Ground, MD 21005

5. TYPE OF REPORT 4 PERIOD COVERED

Final 6. PERFORMING ORG. REPORT NUMBER

8. CONTRACT OR GRANT NUMBERfa)

RDT&E 1X464614D373

10. PROGRAM ELEMENT. PROJECT, TASK AREA ft WORK UNIT NUMBERS

It. CONTROLLING OFFICE NAME AND ADDRESS

US Army Armament Research and Development Command US Army Ballistic Research Laboratory (DRDAR-BL) Ab'erdeen Proving Ground. MD 21005

12. REPORT DATE

November 1982

U. MONITORING AGENCY NAME ft AODRESS<7/dl«aranr from Controllint OIHce)

13. NUMBER OF PAGES

60 15. SECURITY CLASS, (of thlm report)

Unclassified tSa. DECLASSIFICATION/DOWN GRADING

SCHEDULE

16. DISTRIBUTION STATEMENT (of thfa Report)

Approved for public release; distribution unlimited.

17. DISTRIBUTION STATEMENT (of the abmtract entered in Block 30, If dftferent from Report)

18. SUPPLEMENTARY NOTES

Supersedes BRL IMR 737 dated February 1982.

19. KEY WORDS (Continue on reverae aide if neceaaaiy and Identify by block number)

White Phosphorous Felt Wedges Yawsonde

20. ABSTRACT (XSaotBtua an ravaraa attta ft neeematr "* identify by block number) ( 1 C b )

A short series of yawsonde-instrumented tests were conducted for the XM825 white phosphoroiis/felt wedge projectile at Yuma Proving Ground, AZ, on 3 November 1981. Previous testing had shown that unstable flight behavior can occur for high quadrant elevation and high muzzle velocity launches when the white phosphorous was in a liquid state. Preliminary bounds were established for the unstable behavior at that time. This yawsonde test was aimed at verifying the maximum

(Continued)

DD , FORM JAN 73

1473 EDITION OF • NOV 65 IS OBSOLETE UNCLASSIFIED SECURITY CLASS!FICATtOK OF THIS PAGE (When Data Entered)

UNCLASSIFIED SECURITY CLASSIFICATION OF THIS PAOEflWun Dmta Bnfnd)

20. ABSTRACT (Continued);

allowable quadrant elevations for the Ml 19 and PXR6297 propel 1 ant charges. It was found that 1240 and 950 mils were the maximum quadrant elevations for stable flights of liquid XM825 projectiles for the M119 and PXR6297 charges, respective- ly.

UNCLASSIFIED SECURITY CLASSIFICATION OF THIS PAGEfWhen Data Entartd)

TABLE OF CONTENTS

Page

LIST OF FIGURES 5

I. INTRODUCTION 7

II. BACKGROUND ^

III. TEST MATRIX AND INSTRUMENTATION 8

IV. TEST RESULTS 10

A. Preliminary Discussion 10

B. M119/1240 mils 10 C. PXR6297/950 mils 11

V. CONCLUSIONS 11

VI. ACKNOWLEDGEMENTS 12

REFERENCES 13

DISTRIBUTION LIST 59

LIST OF FIGURES

Figure Page

la. Sigma-N History - YPG 259, XM825/Solid 14

lb. Spin History - YPG 259, XM825/So1id 15

lc. Expanded Sigma-N History - YPG 259, XM825/Solid 16

2a. Sigma-N History - YPG 260, XM825/Liquid 17

2b. Spin History - YPG 260, XM825/Liquid 18

2c. Expanded Sigma-N History - YPG 260, XM825/Liquid 19

2d. Expanded Sigma-N History - YPG 260, XM825/Liquid 20









5a. Sigma-N History -YPG 263, XM825/Liquid 29








LIST OF FIGURES (Continued)

Figure Page

7a. Sigma-N History - YPG 267, M483A1 37

7b. Spin History - YPG 267, M483A1 38

7c. Expanded Sigma-N History - YPG 267, M483A1 39

7d. Expanded Sigma-N History - YPG 267, M483A1 40












lib. Spin History - YPG 271, XM825/Liquid 52

lie. Expanded Sigma-N History - YPG 271, XM825/Liquid 53

lid. Expanded Sigma-N History - YPG 271, XM825/Liquid 54





I. INTRODUCTION

The 155mm XM825 projectile carries a single canister that is loaded with white phosphorous (WP) and felt wedges. Unstable flight behavior was observed for high quadrant elevations and high muzzle velocities when the WP was in a liquid state1. A test program was conducted at Yuma Proving Ground (YPG) on 3 November 1981 to determine the maximum allowable quadrant elevation for the M119 and PXR6297 charges. Two six round groups were fired, and all projectiles were instrumented with fuze configured yawsondes2. A solid projectile was fired within each group. All other XM825 shell were condi- tioned to 63 deg C so that the WP would be in a liquid state. Two launch conditions were selected: Ml 19/1240 mils and PXR6297/950 mils. PXR6297 is the proof charge for the M203 charge, while no official proof charge exists for the M119 charge. All rounds were stable. A very small amount of fast mode precession was produced past apogee, but that motion decayed. No other unusual or unwanted behavior was noted in the yawsonde data.

II. BACKGROUND

The XM825 projectile had almost completed DTII, when poor flight behavior was observed for high quadrant elevation and high muzzle velocity conditions. Previous aeroballistic testing had not been conducted under these extreme conditions3»lt. A large yawsonde program was conducted at YPG with yawsonde-instrumented shell to verify that the flight instabilities were associated only with rounds where the WP was in a liquid state and to provide detailed information as to the yaw and spin behavior under a wide variety of launch conditions. Poor flight behavior with large yaw and rapid despin occurred for the following conditions: PXR6297/1180 mils, PXR6297/1100 mils, M203/1180 mils, and M203/1050 mils. Stable performance was observed for M119/1180 mils. Unstable behavior was not found on any of the solid XM825 shell. Unstable behavior was precipitated shortly after apogee and was always associated with the fast precessional mode. Payload/projectile interactions that produce poor projectile performance normally destablize the fast precessional mode of the yawing motion. The exact nature of the mechanism for the unstable flights is unknown, however.

1. W, P, D'Amiao and V. Oskay, "Aerohdllistio Testing of the XM825 Pvojeo- tile: Phase III. High Muzzle Velocity and High Quadvant Elevation BRL Memorandum Report ARBRL-MR-03196, September 1982.

2. W. H. Mermagen and W. H. Clay, "The Design of a Second Generation Yaw- sonde," BRL Memorandum Report 2368, April 1974. AD No. 780064.

3. W. P. D'Amiao and V. Oskay, "Aeroballistic Testing of the XM825 Projec- tile: Phase II," BRL Memorandum Report ARBRL-MR-030 72, January 1981. AD No. A098036.

4. W, P, D'Amico, Jr., "Aeroballistic Testing of the XM825 Projectile: Phase l" BRL Memorandum Report ARBRL-MR-02911, March 1979. AD No. B037680L.

In order to complete the safety requirements for DTI I, the limits for stable performance must be established. For the M203 charge, the proof charge PXR6297 would be utilized. Previous yawsonde tests for M203/1050 mils showed persistent, small amplitude fast precessional motion. However, at these conditions only one out of six XM825 shell were unstable. Based upon these data, stable performance should exist for PXR6297/950 mils. Although no unusual behavior was observed for M119/1180 mils, further testing at the maximum allowable quadrant elevation was required. Modified-point mass tra- jectories were computed with an 80% standard atmosphere (no winds) for the XM825. Effects of the WP/felt wedge payload when the WP is liquid can not be modeled, so the payload was assumed to be solid. For these conditions, the maximum allowable quadrant elevation at which proper flight performance was predicted for the M119 charge was 1260 mils. An additional 20 mil decrement in quadrant elevation was absorbed as a small safety margin, and a launch condition of M119/1240 mils was selected.

III. TEST MATRIX AND INSTRUMENTATION

Two launch conditions were tested: PXR6297/950 mils and M119/1240 mils. All projectiles were instrumented with yawsondes, and a round-by-round history is provided in Table I. Only eleven XM825 shell were available for the test at YPG, hence, an M483A1 (YPG267, BRL1699) was used to establish baseline data for the PXR6297/950 mils rounds. A solid XM825 (YPG259, BRL1579) provided baseline data for the M119/1240 mils rounds.

Standard range instrumentation was provided by YPG to include a telemetry receiving van and a time-position radar, the DIR. The DIR was located down range. The DIR tracked the M119/1240 mils group, but was unable to track the PXR6297/950 mils group. The MPS-25 radar which had been used on previous XM825 tests was under extensive repairs.

The data obtained by the yawsonde package is in the form of the comple- mentary solar aspect angle (Sigma N) and the spin. Sigma N is the complement of the solar aspect angle, the angle between a vector drawn to the sun and the spin axis of the projectile. Local excursions in Sigma N represent the yawing motion of the projectile about the trajectory. Spin data are in the form of the time-derivative of the Eulerian roll angle (Phi) of the projectile. As long as the spin rate of the shell is substantially faster than the yawing frequencies and the angular motion is small, then Phi Dot is a good measure of spin. Oscillations will be present on the Phi Dot histories, but these oscillations are an artifact of the yawsonde measurement system and are produced by the yaw. The raw yawsonde transmissions were often contaminated by noise. This noise was processed out of the data and results in an intermittent loss of data. The source of this noise is probably the radiation pattern of the transmitting antenna of the yawsonde and cannot be avoided unless a new antenna is utilized. The high spin rates and long times of flight yielded large data arrays. High speed/low resolution plotters were utilized to obtain plots of the data for the entire trajectory. Typically spin plots will contain small ripples, but these are due to the resolution of the graphics system and are not caused by noise within the data. An error in the firing count down for YPG262 caused the gun time zero pulse to be lost. Hence, the zero time for this round may be slightly in error.

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IV. TEST RESULTS

A. Preliminary Discussion

Spin-stabilized projectiles when launched at high quadrant elevations can experience large angular motions near apogee. Murphy has considered the angular motion of a projectile under such conditions^. For high quadrant elevation launches, the nose of the projectile will not follow the trajectory curvature past apogee. During the down leg, the projectile will recover from this condition and may experience large amplitude motions. Normally these angular motions are at the slow precessional frequency. This type of behavior will be expected and is not abnormal. Angular motions at the fast precessional frequency are dangerous and are probably caused by the liquid WP payload. The fast precessional frequency may be as high as 20Hz, while the slow precessional is typically less than 1Hz.

B. M119/1240 mils

Figures la and lb show the yaw and spin behavior of the solid XM825 projectile, YP259. No unusual behavior was observed. Large amplitude motion at the slow precessional frequency occurred subsequent to 60s. This motion was produced by the summital maneuver. A small amplitude, fast precessional component was also observed during this time frame. The yawing motion prior to 15s (a loss in data occurred immediately after this time) also produced a fast precessional mode response. This type of dual-mode or epicyclic motion is common for the M483A1 family at transonic and subsonic Mach numbers. Trajectory analyses indicated subsonic Mach numbers from 15-75s. Figure 1c is an expanded plot of the data between 60-80s, and it indicates that the amplitude of the fast precessional mode k^ is less than 0.25 deg.

YPG260 was a liquid XM825 and the yawsonde data are shown in Figures 2a and 2b. The character of the yawing motion was similar to the solid round, except a slightly larger amplitude for kj occurred (kj - 0.5 deg as seen in

Figure 2c). However, the kj mode did damp as shown in Figure 2d. Figures 3a

and 3b show the yawsonde data for YPG261. These data are similar to the previous round. Slightly larger kj amplitudes were experienced during the 60s

time frame (see Figure 3c), but again the kj mode damped. Figure 3d shows an

expansion of the yaw data to expose the details of the motion. The frequency of kj is 17Hz between 60-61s. The yawsonde data for YPG262 are shown in

Figures 4a and 4b. Again the data are similar to the previously fired liquid XM825 projectiles. A maximum value of k^ = 1 deg occurred at approximately

72.5s (see Figure 4c). An expanded plot showing the details of the k^ motion

is provided Figure 4d. Figures 5a and 5b show the yawsonde data for YPG263. The data are again of similar character as the previous shell. A maximum value for ^ of 1 deg occurred during the 60-88s time frame, but the motion

5. Charles H. Murphy, "Gravity-Induced Angular Motion of a Spinning Missile, Joumal of Spaaearaft and Roakets, Vol, 8, August 1971, pp. 824-828. (Also BRL Report 1546 dated July 1971. AD No. 730641.)

10

was damped (see Figures 5c and 5d). Data from the last round of this group, YPG264, are shown in Figures 6a and 6b. The data are consistent with the other rounds within this group. Expanded plots within Figures 6c and 6d show a maximum k^ of less than 1 deg and indicate that the motion was damped.

C. PXR6297/950 mils

The first round in this group of shell was an M483A1 (YPG267. BRL1699). Figures 7a and 7b show the yawsonde data. No unusual behavior was noted and the lower quadrant elevation did not produce a large amplitude, slow precessional response as in the previous group of shell. A launch yaw of approximately 3 deg (Figure 7c) was observed, but the yaw quickly damped. Beyond 60s, the epicyclic motion characteristic of the M483A1 family of shell occurred. The kj amplitude during this portion of the trajectory was less than

0.25 deg (Figure 7d).

The first XM825 test round in this group was YPG268 (BRL1750). The yawsonde data are shown in Figures 8a and 8b. A small level of fast mode precession was present along most of the trajectory. The kj amplitude was

approximately 0.5 deg (Figures 8c and 8d). The kj motion did damp during the

final phases of the flight, however. YPG269 (BRL1746) was the next test round. Yawsonde data are shown in Figures 9a and 9b. As before a small amount of fast mode precession was present, but this amplitude was decreased prior to 60s into the flight. During the 60-80s time frame, the fast precessional mode was less than 0.25 deg (Figures 9c and 9d). The next test round (YPG270, BRL1748) had a very noisy data transmission (Figures 10a and 10b). YPG271 (BRL1749) was similar in nature to the previous test rounds (Figures Ua and lib). A maximum amplitude for k^ occurred approximately 60s

down range (kj= 1 deg as shown in Figures He and Ud). The last test round

in this series was YPG272 (BRL1682), and the data are shown in Figures 12a and 12b. The k^ amplitude at launch was approximately 1 deg and was less than 0.5

deg at 80s (Figures 12c and 12d).

V. CONCLUSIONS

Two launch conditions were tested for the XM825 when the WP was in a liquid state: PXR6297/950 mils and M119/1240 mils. Baseline data were also obtained at these conditions for solid shell. Liquid XM825 shell at both launch conditions produced very small amplitude fast precessional motion, but these motions always damped and no adverse effects occurred. The conditions that were tested represent the maximum allowable quadrant elevations for the XM825 projectile when the WP is in a liquid state. For the M119 charge, the maximum quadrant elevation for the M483A1 is 1320 mils for standard atmospher- ic conditions. Recall that the 1240 mils condition was for an 80% standard atmosphere. An 80 mil reduction (less than 5 deg) in the operational capa- bility of the projectile/weapon system should not be serious. For the M203 charge, however, a reduction in quadrant elevation to 950 mils is required. For this charge, the M483A1 has a maximum quadrant elevation of 1260 mils.

11

VI. ACKNOWLEDGEMENTS

The authors are indebted to Mr.S. Kushubar and Mr. D. Hepner for the reduction and plotting of the yawsonde data. Mr. D. Vasquez and Mr. D. Davis assembled the yawsondes, while Mr. M. Steele was responsible for the calibra- tion of the units. Mr. W. Tenly assisted YPG personnel in the operation of the ground receiving station. Trajectory computations were provided by Mr. R. Lieske and Mr. N. Roberts, Firing Tables Branch, LFD, BRL.

12

REFERENCES

1. W. P. D'Amico and V. Oskay, "Aeroballistic Testing of the XM825 Projec- tile: Phase III. High Muzzle Velocity and High Quadrant Elevation," BRL Memorandum Report ARBRL-MR-03196, September 1982.

2. W. H. Mermagen and W. H. Clay, "The Design of a Second Generation Yaw- sonde," BRL Memorandum Report 2368, April 1974. AD No. 780064.

3. W. P. D'Amico and V. Oskay, "Aeroballistic Testing of the XM825 Projec- tile: Phase II," BRL Memorandum Report ARBRL-MR-03072, January 1981. AD No. A098036.

4. W. P. D'Amico, Jr., "Aeroballistic Testing of the XM825 Projectile: Phase I," BRL Memorandum Report ARBRL-MR-02911, March 1979. AD No. B037680L.

5. Charles H. Murphy, "Gravity-Induced Angular Motion of a Spinning Missile," Journal of Spacecraft and Rockets, Vol. 8, August 1971, pp. 824-828. (Also BRL Report 1546, July 1971. AD No. 730641.)

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DISTRIBUTION LIST

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12 Administrator Defense Technical Info Center ATTN: DTIC-DDA Cameron Station Alexandria, VA 22314

1 Commander US Army Materiel Development

and Readiness Command ATTN: DRCDMD-ST 5001 Eisenhower Avenue Alexandria, VA 22333

1 Commander US Army Armament Research

and Development Command ATTN: DRDAR-TDC (Dr. D. Gyorog) Dover, NJ 07801


and Development Command ATTN: DRDAR-TSS (2 cys) Dover, NJ 07801


and Development Command ATTN: DRCPM-CAWS-AM

Mr. DellaTerga Dover, NJ 07801


and Development Command ATTN: DRDAR-LCA-F

Mr. D. Mertz Mr. A. Loeb

Dover, NJ 07801

1 Commander US Army Armament Materiel

Readiness Command ATTN: DRSAR-LEP-L, Tech Lib Rock Island, IL 61299

Organization

1 Di rector US Army Armament Research

and Development Command Benet Weapons Laboratory ATTN: DRDAR-LCB-TL Watervliet, NY 12189

1 Commander US Army Aviation Research

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ATTN: ATAA-SL, Tech Lib White Sands Missile Range m 88002

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