| Wind Tunnel Experiments of the Effect of Near-Wake Combustion on the Base Drag of Supersonic Projectiles. |
FEB 1976 |
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| Authors:
J. Richard Ward; Frank P. Baltakis; Theresa A. Elmendorf; Dennis J. Mancinelli; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
 | A series of fumers based on magnesium/strontium peroxide was tested at the Naval Surface Weapon Center's Hypersonic Tunnel to see the effect of varying the parameters that control the rate of combustion of pyrotechnics. The parameters that were varied included spin rate, fuel content, fuel particle size, the oxidizer, and the addition of burning rate additivies (calcium resinate, polyvinylchloride, oxamide, and gelatin). The base drag reductions measured for all the ... |
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| Critical Evaluation and Stress Analysis of the 5 in./54 HI-FRAG Projectile. |
JUL 1974 |
62 pages |
| Authors:
Robert A. Lindeman; NAVAL WEAPONS LAB DAHLGREN VA
|
 | This report presents a detailed analysis of the loading conditions to which the 5-in./54 HI-FRAG Projectile is subjected. These loading conditions include the following: press fit, gun ramming or rebound upon exit from the barrel. The analyses are based on finite element, analytical, and experimental results. Were applicable, various results are correlated to show their validity. The analyses show that the joint region is the most highly stressed region in ... |
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| Long Range Dynamics Flight Experiments with the 155 MM Projectile, M483. |
JUL 1974 |
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| Authors:
William H. Mermagen; Vural Oskay; BALLISTIC RESEARCH LABS ABERDEEN PROVING GROUND MD
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| Three series of flight tests have been made with yawsonde instrumented 155mm, M483 projectiles to determine the long range aerodynamic behavior and stability of the shell. Conducted over a two year period, these tests confirmed the stable behavior of the M483 under normal launch conditions, even at subsonic velocities. The results of efforts to induce yaw at launch, however, produced dramatic short flights in which large amplitude, unstable motions were ... |
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| An Investigation into the Flight Characteristics of Rotating Discs. |
OCT 1973 |
25 pages |
| Authors:
F. J. Brandon; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
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| Disc shaped parts that are ejected from Beehive and canister rounds have been found in areas well outside of the expected safety zone. These discs represent a potential danger to friendly troops. The flight characteristics that may have caused the disc to fly errant paths are not known; therefore, a simple test program was undertaken by the Ballistic Research Laboratories to investigate the flight characteristics of a rotating disc. This ... |
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| Transverse Motion of 8 Inch Projectile, XM673, in the XM201, M2A2 Gun Tube, Mk-16 and MCLG Gun. |
AUG 1973 |
166 pages |
| Authors:
Szu Hsiung Chu; PICATINNY ARSENAL DOVER N J
|
| The dynamic behavior of a projectile during acceleration in the gun tube requires a quantitative description, since, if balloting becomes excessive, undesirable conditions such as damage to fuzing, shell body engraving, inaccuracy of fire due to yaw, and yaw velocity at the muzzle may result. The approach taken in this report utilizes the equations of motion derived in an earlier report titled, 'Transverse Motion of an Accelerating Shell' to describe ... |
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| Feasibility Flight Testing of Rocket Impelled Projectile (RIP). |
01 MAY 1973 |
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| Authors:
E. M. Tomlinson; LTV AEROSPACE CORP WARREN MI MICHIGAN DIV
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| This test program was conducted to demonstrate the minimum tip-off tube launcher concept, evaluate the real-time radar registration technique, and evaluate rocket precision for the 6-inch diameter, 218-pound RIP Rocket. The program has been completed with the launch of all eight rockets, and has provided data to indicate successful accomplishment of all objectives. In addition, this flight program has uncovered specific areas for further investigation, and has strengthened the position ... |
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| An Investigation of External Burning Propulsion for the 75mm Projectile. |
JAN 1973 |
175 pages |
| Authors:
Harvey L. Fein; Dwight E. Shelor; ATLANTIC RESEARCH ALEXANDRIA VA
|
| Twenty external burning combustion tests were conducted with a 75mm half-model using the exhausts from fuel-rich solid propellants as the fuels. Test conditions simulated Mach 2.5 and Mach 2.0 flight at both sea level and an altitude of 15,000 ft. Base pressure ratios up to 0.85 were obtained at sea level, while at altitude these ratios were greater than unity. There was strong evidence that a wind tunnel interference effect ... |
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| Technical Evaluation Plan for the Improved 5 in/54 Projectile. |
OCT 1972 |
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| Authors:
J. W. DUCH; NAVAL WEAPONS LAB DAHLGREN VA
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| A plan is presented for the technical evaluation of the Improved 5-in./54 Projectile. The schedule is based on completing certain high priority safety, structural, environmental, fragmentation, and rapid fire tests prior to recommending a Release to Production to the Naval Weapons Laboratory Design Review Committee on 1 April 1973. (Author) |
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| NUMERICAL, ANALYTICAL, AND EXPERIMENTAL INVESTIGATION OF PENETRATION BY KINETIC ENERGY PROJECTILES. |
MAR 1972 |
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| Authors:
R. T. SEDGWICK; L. J. Hageman; SYSTEMS SCIENCE AND SOFTWARE LA JOLLA CA
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| The HELP code has been modified to better model impact situations for which the target fails in the plugging mode. The model is described in detail, and the results of five impact calculations are presented and compared with Lagrangian and analytical predictions as well as with experiment. The HELP predictions were found to be in excellent agreement with experiment. (Author) |
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| 20 Millimeter Projectile Safety Tests, |
04 FEB 1972 |
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| Authors:
B. E. White; NAVAL ORDNANCE LAB WHITE OAK MD
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| As a result of a critical accident at NAD, McAlester, Oklahoma, tests were conducted with obsolete 20 millimeter ammunition furnished from rounds remaining in storage. Tests included bullet impact, drop and chemical analysis for copper azide formation. The results of all tests were negative in establishing any undue sensitivity of the ammunition. Recommendations are made for further tests to help in the preparation of disposal plans for millions of rounds ... |
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| Performance of 20mm Ablative Ammunition. |
DEC 1971 |
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| Authors:
W. R. Brown; E. B. Fisher; D. J. Sudlik; F. A. Vassallo; CORNELL AERONAUTICAL LAB INC BUFFALO NY
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| M55 A2, 20mm ammunition was modified by placing five cubic centimeters of gelled dimethyl silicone compound between the propellant charge and the projectile. The function of the silicone was to reduce barrel heating and erosion by coating the bore surface, forming an insulative and ablative shield against the hot propellant gases. Several thousand silicone-modified and standard rounds were fired in thermocouple-instrumented M39 and M61 (Vulcan) cannons. Very substantial reductions in ... |
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| Effect of Spin on the Aerodynamics of the 20mm Projectile, |
24 SEP 1971 |
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| Authors:
John A. Darling; Joseph Knott; NAVAL ORDNANCE LAB WHITE OAK MD
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| The effect of spin on the aerodynamics of the 20mm projectile was studied from experimental measurements of static stability, axial force, roll damping, Magnus forces and base-pressure surveys made in the NOL Supersonic Tunnel Numers 1 and 2 over a Mach number range of 0.8 to 5 and at Reynolds numbers high enough to ensure a turbulent wake. (Author) |
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| Mechanics of Impact and Crack Propagation. Phase 1. Development of an Analytical Fracture Model of Projectile Penetration. |
AUG 1971 |
114 pages |
| Authors:
G. C. Sih; G. T. Embley; LEHIGH UNIV BETHLEHEM PA INST OF FRACTURE AND SOLID MECHANICS
|
| The report is concerned with the application of fracture mechanics theory to the problem of projectile penetration and the situation where an excessive amount of energy is available to damage the target material in the form of fracture followed by crack propagation. The conditions under which this phenomenom takes place depend on several parameters, such as the speed and shape of the projectile and the geometry and material of the ... |
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| Exploratory Development Plan for 8-in. Guided Projectiles. |
FEB 1971 |
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| Authors:
J. Max Massey Jr; NAVAL WEAPONS LAB DAHLGREN VA
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| Most of the guided projectile components have been gun fired and have survived 8000 g's acceleration. The shroud, guidance and control assembly, and telemetry assembly are designed to withstand 8000 g's and have survived 4000 g's. Three gun fired, guided, functional system tests have been conducted. The first two did not guide because of mechanical failures. The third guided toward the target; but, because of aerodynamic incompatabilities it did not ... |
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| Electron Beam Controlled Fragmentation of A 5 In./38 Projectile. |
DEC 1970 |
20 pages |
| Authors:
George A. Williams; NAVAL WEAPONS LAB DAHLGREN VA
|
| The design, fabrication and testing of a 5 in./38 projectile are described in this report. |
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| Natural Missile Distributions for High Explosive Craters in Hard Rock. Volume III. Multiple Threat Cratering Experiment. |
JUN 1970 |
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| Authors:
R. W. Henny; R. H. Carlson; AIR FORCE WEAPONS LAB KIRTLAND AFB NM
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| Natural missile distributions resulting from high explosives detonated on or near the surface of basalt are analyzed for 14 events ranging in yield from 2,000 to 16,000 pounds of TNT. Spherical charges were detonated in three different coupling modes: half-buried, tangent to but above the rock surface, and tangent to but below the rock surface. Hemispherical charges were detonated on the rock surface. A computer program was developed to analyze ... |
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| Projectile, 'Beehive'. |
27 JAN 1970 |
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| Authors:
ARMY TEST AND EVALUATION COMMAND ABERDEEN PROVING GROUND MD
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| This Army Service Test Procedure describes test methods and techniques for evaluating the performance and characteristics of a 'beehive' type of artillery projectile, and to determine suitability of the item for service use by the US Army. The evaluation is related to criteria as specified in UALITATIVE Materiel Requirements (QMR), or Small Development Requirements (SDR). |
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| Two Aspects of Earth Penetration: Measurement of Resistance to Burial and Theoretical Prediction of Penetration in Stratiform Soil, |
01 JUL 1969 |
47 pages |
| Authors:
Albert J. Faulstich Jr.; Harold J. Herring; NAVAL ORDNANCE LAB WHITE OAK MD
|
| Within the scope of the work conducted in the discipline of controlled penetration in soils, techniques are outlined and suggested which should help the investigator estimate the resistance to penetration (soil factor) at a location in a few minutes using portable equipment. Included is a compilation of soil penetration data from various locations. Additional work has also been completed which enables the researcher to theoretically predict burial depths of impacting ... |
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| AEROSPACE APPLICATION OF GUN LAUNCHED PROJECTILES AND ROCKETS, |
20 MAR 1967 |
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| Authors:
Charles H. Murphy; Gerald V. Bull; MCGILL UNIV MONTREAL (QUEBEC) SPACE RESEARCH INST
|
| Project High Altitude Research Program (HARP) is directed toward the use of guns for scientific probing of the upper atmosphere. The attractive features of guns for this purpose are the basic economy of such a system and the high inherent accuracy of guns for placement at altitude as well as accuracy in ground impact. The basic liability for such an approach lies in the very high acceleration experienced by gun-launched ... |
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| ARTILLERY PROJECTILE SHOCK (FEASIBILITY STUDY OF HARDWIRE AND MECHANICAL GAGE RECORDING). |
04 JAN 1967 |
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| Authors:
Valmore F. DeVost; Luigi A. Vagnoni; Peter S. Hughes; NAVAL ORDNANCE LAB WHITE OAK MD
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| Results of continuous setback shock and pressure measurements made in a shortened 5 in/54 gun are presented, and the test apparatus, hardwire instrumentation and data analysis equipment are described. Single and multiple copper-ball accelerometer measurements of setback and other shocks in several 5 in/54 guns are discussed, and two artillery projectile copper-ball accelerometers are described. Response spectra computed and extrapolated from the recorded shock transients show the effect of setback ... |
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| A MODEL FOR DETERMINING TARGET LOCATION ACCURACY REQUIREMENTS, |
JUN 1966 |
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| Authors:
Otis S. Spears; ARMY COMBAT DEVELOPMENTS COMMAND ARTILLERY AGENCY FORT SILL OKLA
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| The study encompasses a method of determining target location accuracy requirements when other components of the weapon system are specified. The method is primarily developed for surface-to-surface artillery weapons, but is adaptable to other systems. |
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| FREE-FLIGHT RANGE TESTS OF THE 20-MM M56A2 SHELL WITH THE M505E3 FUZE. |
JAN 1966 |
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| Authors:
G. L. Winchenbach; R. M. Watt; C. J. Welsh; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
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| Results of free-flight range tests of the 20-mm M56A2-M505E3 shell over a Mach number range from 1.24 to 4.67 and at simulated altitudes up to 60,000 ft are presented. Measurements indicate that the arming ball rotor of the M505E3 fuze can have a pronounced adverse effect on the damping characteristics of the shell, with the severity becoming greater with increasing altitude. (Author) |
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| ACCURACY PARAMETERS FOR FREE FLIGHT PROJECTILES WITH MAXIMUM RANGES UP TO 75 KILOMETERS, |
06 AUG 1965 |
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| Authors:
H. R. Oswell; M. B. Jackson; ARMY MISSILE RESEARCH DEVELOPMENT AND ENGINEERING LAB REDSTONE ARSENAL AL AER OBALLISTICS DIRECTORATE
|
| This report is a compilation of graphs which will permit estimation of the free flight errors of projectiles for ranges up to 75 kilometers, provided the ballistic coefficient and initial velocity are known. The effects of variations in initial velocity, departure angle, ballistic coefficient, wind, and density have been examined parametrically, and the results are presented for both impact and time-fusing. (Author) |
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| THE EFFECT OF VARIOUS BOATTAIL SHAPES ON BASE PRESSURE AND OTHER AERODYNAMIC CHARACTERISTICS OF A 7-CALIBER LONG BODY OF REVOLUTION AT M EQUALS 1.70. |
AUG 1965 |
|
| Authors:
Boris G. Karpov; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| Models, 7 calibers long, with a variety of conical, ogival (convex) and concave boattails were free-flight tested at M = 1.70, for drag and other aerodynamic characteristics. The total drag decreases monotonically for boattails longer than 0.5 calibers. For shorter boattails, the drag is higher than that of the square based body. For boattail lengths between 0.5 and 1.5 calibers, conical boattails have lower drag than either the ogival or ... |
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| SOME AERODYNAMIC PROPERTIES OF A LOW-VELOCITY PROJECTILE WITH HEMISPHERICAL NOSE AND L/D OF 4.3. |
APR 1965 |
|
| Authors:
Maynard J. Piddington; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
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| A limited test program of the projectile was conducted for analysis of its aerodynamic characteristics. The results of this test are presented and disucssed. (Author) |
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| THE ZERO-YAW DRAG COEFFICIENT FOR PROJECTILE, 4.2-INCH; HE, M329A1, |
OCT 1964 |
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| Authors:
Elizabeth R. Dichinson; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
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| This report presents an analytical fit of experimentally determined drag coefficients of the mortar shell designated as Projectile, 4.2inch; HE, M329A1. Both a tabular and a graphical representation of the fitted coefficients are included. (Author) |
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| OPTIMUM LETHALITY STUDY OF THE T22E12 CANISTER ROUND. |
FEB 1959 |
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| Authors:
Allen Berman; Louis Wiesenfeld; FELTMAN RESEARCH LABS PICATINNY ARSENAL DOVER N J
|
| This Report covers a study to obtain the optimum angle of gun elevation between the ranges of 250 feet to 1000 feet for the T22E12 Flapper Round. (Author) |
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| SOME AERODYNAMIC PROPERTIES OF TWO 90MM SPIKED NOSE SHELL T300E53 AND T316E6. |
JUN 1957 |
|
| Authors:
Maynard J. Piddington; BALLISTIC RESEARCH LABS ABERDEEN PROVING GROUND MD
|
| The drag, spin histories, and some yaw properties of the spike nosed 90-mm T300E53 and 90-mm T316E6 shell are presented. These data were obtained from Transonic Range firings. The dual flow phenomenon which was observed on shadowgraphs of the T300E53 in free flight is also briefly discussed. (Author) |
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| DYNAMIC MEASUREMENTS ON THE 81MM SHELL M56 IN NBS WIND TUNNEL |
OCT 1953 |
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| Authors:
S.J. ZAROODNY; R.S. MOTT; BALLISTIC RESEARCH LABS ABERDEEN PROVING GROUND MD
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| REDUCTION OF DRAG OF A PROJECTILE IN A SUPERSONIC STREAM BY THE COMBUSTION OF HYDROGEN IN THE TURBULENT WAKE, |
04 JUN 1951 |
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| Authors:
W. T. Baker; T. Davis; S. E. Matthews; JOHNS HOPKINS UNIV SILVER SPRING MD APPLIED PHYSICS LAB
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| An experimental evaluation was made of the effect of combustion of hydrogen with the wake air on the drag of a projectile. The base drag was reduced by about two-thirds, and hence total drag of a flight unit may possibly be reduced one-third, by the use of a minimum of 6.4 per cent of the stoichiometric requirement of the air swept by the maximum cross-sectional area. No difficulty was experienced ... |
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| 3-IN./50 Projectiles Mk. 33 - Cook-off Tests. |
21 JUL 1950 |
|
| Authors:
V. Wilson; NAVAL PROVING GROUND DAHLGREN VA
|
| This test was conducted to determine the cook-off times for 3-in./50 caliber loaded and fuzed projectiles subjected to temperatures resulting in a gun after various numbers of rapid-fire bursts. |
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| APPARATUS FOR OBTAINING LARGE SINGLE AND MULTIPLE SPARK SHADOWGRAPHS OF PROJECTILES AT SUPERSONIC VELOCITIES. |
10 OCT 1947 |
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| Authors:
S. Fellman; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| The apparatus for obtaining single and multiple spark shadowgraphs of large dimensions for use in airflwo studies is described. The chief features are a point source of light of great brilliance and short photographic duration, reliable timing and triggering circuits, and a multiple (four) spark circuit employing a common spark head. (Author) |
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| EFFECT OF VARIOUS DRIVING BANDS ON THE AERODYNAMIC PERFORMANCE OF PROJECTILES AT HIGH VELOCITIES, |
19 FEB 1946 |
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| Authors:
Hyman Stein; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| A comparison is presented of the drag and moment coefficients at high velocities of a series of similar projectiles with varying driving band shapes. Included is a projectile without any driving band. The data were obtained from firings in the Aerodynamics Range. A variation of K sub M with yaw is observed and its magnitude evaluated. |
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| SOME COMMENTS ON THE FORM OF THE DRAG COEFFICIENT AT SUPERSONIC VELOCITY, |
20 APR 1942 |
45 pages |
| Authors:
Richard N. Thomas; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| A form of representation of the drag curve at supersonic velocity is suggested. Only two unknown constants are required for each shell, hence firings at two velocities fix the function. For the case of a conical head and square base, the problem can be reduced to one constant. Good experimental confirmation is found. (Author) |
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