|Publication number||USH2265 H1|
|Application number||US 11/805,264|
|Publication date||Dec 6, 2011|
|Filing date||May 16, 2007|
|Priority date||Aug 9, 2006|
|Publication number||11805264, 805264, US H2265 H1, US H2265H1, US-H1-H2265, USH2265 H1, USH2265H1|
|Inventors||Timothy M. Fouse, Michael M. Canaday, Steven W. Mundell, John R. Bowen, Jr., Michael John Hamel|
|Original Assignee||The United States Of America As Represented By The Secretary Of The Navy|
|Export Citation||BiBTeX, EndNote, RefMan|
|Patent Citations (8), Referenced by (1), Classifications (14), Legal Events (1)|
|External Links: USPTO, USPTO Assignment, Espacenet|
Pursuant to 35 U.S.C. §119, the benefit of priority from provisional application 60/838,531, with a filing date of Aug. 9, 2006, is claimed for this non-provisional application.
The invention described was made in the performance of official duties by one or more employees of the Department of the Navy, and thus, the invention herein may be manufactured, used or licensed by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.
The invention relates generally to instrumentation for measuring acceleration in a gun-launched projectile, and more particularly to a fuse-mounted differential variable resistance transducer disposed aft of the simulated warhead.
Destruction of underground hardened targets may require deep penetration munitions. Such devices can include gun-launched projectiles. Tests to correlate penetration depth with deceleration of an instrumented shell into a simulated target may incorporate displacement sensors, such as accelerometers and proximity detectors. A Hall effect probe, which responds to Lorentz force reaction to a magnetic field perpendicular to the current flow, represents an exemplary proximity sensor without physical contact with a neighboring object. Further details on these principles can be found in http://hyperphysics.phyastr.gsu.edu/hbase/magnetic/hall.html.
In the presence of a magnetic field, the path of an electric current curves perpendicular to the magnetic field due to the Lorentz force producing an asymmetric distribution of charge density across the Hall effect probe or device that generates an electric potential. In response to voltage applied across two terminals of the Hall device, a third terminal provides a voltage proportional to the induced current. Hall devices have no mechanically moving parts and thus provide enhanced reliability in extreme environments, such as for projectiles subject to high accelerating and decelerating conditions.
Conventional test devices yield disadvantages addressed by various exemplary embodiments of the present invention. In particular, a test projectile for propelled ejection from a launch mechanism is used to evaluate penetration into a concrete target. The projectile includes a casing having a cavity bore, an explosive simulant disposed at a fore end of the bore, an instrumentation canister aft of the simulant and rigidly mounted to the casing, and a data recorder. The bore is substantially coaxial with the casing's longitudinal centerline. The canister includes an electronic displacement measuring instrument that faces a conductive aft surface of the simulant. The instrument provides an electronic signal to measure a translation parameter supplied to the recorder.
Preferably, a differential variable reluctance transducer (DVRT) represents the instrument for measuring the translation parameter, such as acceleration and/or deceleration, of the explosive stimulant contained in the projectile warhead. As employed in the specification and claims, the term “acceleration” encompasses both positive (i.e., velocity increasing) acceleration and negative (i.e., velocity decreasing) deceleration, unless otherwise indicated.
In various exemplary embodiments, the test projectile is used to evaluate penetration into a concrete target. The projectile includes the DVRT that includes a cylindrical housing and an electronics module. The housing defines a cavity containing insulation and a bobbin around which a wire coil is wrapped.
Various exemplary embodiments provide for the housing as having an attachment end and a distal end that faces the acceleration indicator. The bobbin is disposed substantially parallel to the housing. The wire coil is helically disposed around the bobbin. The insulation fills the remainder of the cavity. The electronics module receives electric current from the wire coil and terminates in an electrical connector to a data recorder. A cable connects the housing to the electronics module.
These and various other features and aspects of various exemplary embodiments will be readily understood with reference to the following detailed description taken in conjunction with the accompanying drawings, in which like or similar numbers are used throughout, and in which:
In the following detailed description of exemplary embodiments of the invention, reference is made to the accompanying drawings that form a part hereof, and in which is shown by way of illustration specific exemplary embodiments in which the invention may be practiced. These embodiments are described in sufficient detail to enable those skilled in the art to practice the invention. Other embodiments may be utilized, and logical, mechanical, and other changes may be made without departing from the spirit or scope of the present invention. The following detailed description is, therefore, not to be taken in a limiting sense, and the scope of the present invention is defined only by the appended claims.
Efforts to improve shock hardening of the Hall device for a penetration test projectile or shell 100 have yielded improvements described in the embodiments described herein. An illustration of a forward portion of the projectile 100 is shown in FIG. 1A. The projectile 100 includes a booster 110 within which a differential variable reluctance transducer (DVRT) fuse (or sensor) 120 may be disposed. The fuse 120 includes the Hall device. Exemplary non-contact DVRT devices are provided by MicroStrain®, Inc. at Williston, Vt., such as various models cursorily described at http://www.microstrain.com/ncdvrt.aspx. The projectile 100 includes an outer case or housing 130 composed of hardened 4340-steel and being 4-inches in diameter, for example. The booster 110 is disposed aft of the breech end of a forward cavity 140.
A detail of the booster 110 is shown in
The forward bore 210 may include a nylon insert 220 into which an explosive simulant 230 may be disposed. The insert 220 may then be threaded into the cavity 140. In this example, the simulant 230 is 1.5 inches in diameter and 3.5 inches in height and may be composed of gelatinous material having analogous mass properties of AFX-757 explosive. The aft side of the simulant 230 facing the DVRT fuse 120 may be covered by four layers aluminum tape, thereby presenting a highly conductive face layer 235.
A DVRT canister 240 may be disposed aft of the insert 220 and the simulant 230. The DVRT canister 240 may be secured to the casing of the projectile 100 by a radially extending flange 245. The DVRT fuse 120 may be disposed within a tube 250 within the DVRT canister 240. A recorder canister 260 may be disposed within the aft bore 215 to contain a data recorder. An accelerator mount 265 with a data coupling transfer interface may connect the recorder canister 260 with accelerometer transducers 270, 275 for longitudinal and transverse directional velocity changes, respectively.
The DVRT canister 240 houses the DVRT fuse 120 together with circuitry for electronic demodulation and signal conditioning. The sensor coils may be disposed in the forward end of the canister 240. The circuitry may be packed among glass impact beads in the middle of the canister 240 for shock resistance. The data recorder can typically record four channels of data at a sample rate of 8.6 μs (microseconds) per channel in high shock environments up to ±50,000 G.
The data recorder, in conjunction with the DVRT, operates on an alkaline 10.5 Vdc (volts-direct-current) battery pack and stores data for 48 hours providing time to recover the projectile 100. The accelerator mount may contain a piezoresistive 200 kG accelerometer to sense the G (Earth's-gravitational-acceleration-at-mean-radius-equivalent) levels. The accelerometer may be mounted on a 10 kHz low-pass mechanical (polysulfide) filter to reduce ringing and mitigate against damage. The instrumentation may be calibrated to an accuracy of 0.0005 inch to measure distance between the DVRT fuse 120 and the simulant aft face layer 235.
The DVRT transducer operates on the principle of comparing signals from a pair of coils for sense and compensation. When the face of the transducer is brought in close proximity to a ferrous or highly conductive material, the reluctance of the sense coil changes, while the compensation coil acts as a reference. High frequency alternating current (AC, e.g., sine wave) excitation (e.g., by an oscillator) drives the coils, and a sensitive demodulator measures the differential reluctance of the coils. Reluctance represents the opposition in a circuit to magnetic flux from the induced electric current by ratio of the magnetic potential difference to the corresponding flux.
Differencing the outputs from the two coils provides a sensitive measure of the position, while canceling variations caused by temperature drift. Ferrous targets change the sense coils'reluctance by altering the magnetic circuit's permeability. By contrast, conductive targets (e.g., aluminum) operate by the interaction of eddy currents induced in the target's skin (i.e., aft face layer 235) with the magnetic field around the sense coil.
Although the DVRT measures linear displacement, the electronics in the DVRT recorder can differentiate the displacement with respect to time to obtain velocity, and can further differentiate the velocity with respect to time to obtain acceleration. Thus, the system may measure and record a translation parameter that includes at least one of displacement, velocity and acceleration of the gap.
This gap distance between the aft face layer 235 of the simulant 230 and a forward face of the booster 110 may be substantially negligible upon installation. For this configuration, the calibration voltage may be between about 3-to-5 Vdc. After acceleration on launch and deceleration on target impact, the simulant 230 may deformably compress, while the DVRT fuse 120 remains fixed within the projectile 110 by the flange 245 and a threaded ring behind the recorder 260. The relative motion between the layer 235 and the booster 110 increases the separation therebetween. The Hall effect technique enables accurate measurement to about 10 mVdc corresponding to an effective distance of about 0.3 inch.
The housing 320 has a diameter of 0.75 inch and a length of 1.25 inches. A wire sense coil (see
A cable 340 having a diameter of 0.070 inch and a length of 10 inches connects the housing 320 from an attachment end opposite the distal end to an electronics module 350 having a diameter of 0.61 inch and a length of 2.00 inches terminated by a #24 American Wire Gauge (AWG) hookup 360 for electrical conduction. The electronics module 350 communicates with the housing 320 for receiving induced voltage potential from the wire coil. The electronics module 350 communicates with a data recorder by means of the hookup 360. Deficiencies in the first embodiment's physical integrity led to further refinements.
The membrane 430 and the grooves in the housing 420 inhibit ejection from the housing 420 of the wire coil within the epoxy 415. Alternatively, the housing 420 may incorporate ridges (instead of grooves) on its inside surface to increase structural integrity there. The larger diameter of the housing 420 as compared to the first embodiment housing 320 enables the sensor coil's diameter to be enlarged, thereby increasing sensitivity and range.
A 440 cable having a diameter of 0.070 inch and a length of 2.5 inches connects the housing 420 to an electronics module 450 having a diameter of 0.61 inch and a length of 2.60 inches terminated by a #24 AWG hookup 460. The membrane 430 and the housing grooves inhibit ejection from the housing 420 of the wire coil within the epoxy 415. The shorter cable 440 between the fuse and the electronics module reduces impedance.
The larger diameter 525 of the housing 520 as compared to the first and second embodiment housings 320, 420 enables the sensor coil's diameter to be enlarged, thereby increasing sensitivity and range of travel for the fuse 120. The housing 520 includes grooves cut into its inside surface. The membrane 530 and the housing grooves inhibit ejection from the housing 520 of the wire coil within the epoxy 515. A cable 540 having a diameter of 0.065 inch and a length of 2.5 inches connects the housing 520 to an electronics module 550 having a diameter of 0.38 inch and a length of 2.50 inches terminated by a #24 AWG hookup 560.
The lessened mass and volume of the electronics module 550 reduces the stress imposed on the cable 540 and the hookup 560. In combination, these design augmentations for the third embodiment 500 enable impact of the projectile 100 from an 8-inch gun into a concrete target at decelerations of 8.5 kG (kilo-gravity-accelerations) for a duration of 18 ms (milliseconds) on launch and 4-to-6 kG on impact for a duration of 20 ms.
The frequency of the RC oscillator 820 can be selected via values for the resistor and capacitor of the selector 810 connected in parallel. The RC oscillator provides signal stability (in frequency and/or amplitude) against influence by mechanical forces. An example oscillator integrated circuit is LTC6900 from Linear Technology in Milpitas, Calif. having acceptable drift and acceleration insensitivity for gun-projectile test purposes. The oscillator 820 generates an AC signal that drives an inductor pair 830 from a center tap. A grounded resistance, pair 840 combined with the inductor pair 830 forms a DVRT Wheatstone bridge.
Signals A and B at the ends of the DVRT Wheatstone bridge may be demodulated and amplified to provide the DC voltage output 890 as being proportional to the logarithm of the distance to the target, e.g., the aft face layer 235. The demodulator includes a matching pair of semiconductor diodes in parallel connecting the Signals A and B to the positive and negative inputs of the DC amplifier 870. The semiconductor diodes can be chosen to have matched characteristics. The offset potentiometer 860 removes offset voltages from the demodulator's output. Gain of the amplifier 870 may be selected using the gain potentiometer 890.
The frequency of the AC excitation may be selected to operate the DVRT below its self-resonant frequency, yet high enough to provide a reasonable load impedance to the oscillator for a given DVRT inductance. This AC excitation may be fed to a center tap in the inductance pair 830, where the measurement coil and the reference coil connect together. In addition, the resistance coils terminate together in the resistance pair 840, with the two connections forming the Wheatstone bridge.
In the absence of a metallic target within the measurement range of the DVRT, the inductance of the measurement coil equals that of the reference coil, thereby producing no differential signal. A metallic target (e.g., the aft face layer 235) in the proximity of the DVRT fuse 120 changes the inductance of the measurement coil resulting in voltage differences between Signals A and B.
These signals may be demodulated or rectified to remove the high frequency AC component. This process yields a differential DC signal that may be approximately proportional to the logarithm of the proximity distance to the target and the measurement coil. The DVRT may be designed so that ambient temperature variations affect both reference and measurement coils equally, thereby cancelling temperature effects on distance measurements.
Upon launch, the sabot petals 905 separates to release the projectile 100 traveling at between 2500 ft/sec and 4000 ft/sec a distance of 40 feet past a video backdrop 930 and an angle-of-attack mirror 935. High-speed cameras 940 visually record the projectile's travel, while a radar transmitter and receiver 945 on the gun 910 uses Doppler measurements for complementary tracking data.
The isometric illustration 950 shows the gun 910 positioned on a ramp 960 for stability. The barrel 915 points to the target 925 located in the facility 920. The gun 910 and the facility 920 are flanked by a platform 970 and are separated by a rail track 980 onto which the target 925 may be positioned.
The initial impact portion 1010 is composed of cellular concrete having a density of 90 lb/ft3 (pounds-mass-per-cubic-foot) and an unconfined compressive strength (UCS) of 3000 psi (pounds-force-per- square-inch). UCS is used for borability predictions and is based on the ASTM-D2938 standard. The intermediate portion 1020 is composed of low strength having a density of 125 lb/ft3 and a UCS of 3300 psi.
The low-strength concrete is based on a formula from the Engineer Research and Development Center (ERDC) of the U.S. Army Corps of Engineers. The terminal portion 1030, which may include only a single module, may be composed of high-strength concrete having a density of 150 lb/ft3 and a UCS of 9000 psi.
For the second plot 1200, the abscissa 1210 represents penetration depth (feet) into the target, while the ordinate 1220 represents acceleration (kG). The acceleration-depth plot 1200 illustrates acceleration measurements shown as a trace 1230 that are filtered for transient noise and a trace 1240 for displacement of the stimulant 230. Additionally, the plot 1200 shows a prediction trace 1250 using a transient dynamics finite element code named PRONTO used for smooth particle hydrodynamics (SPH) predictions. The plot 1200 also denotes a dash line 1260 showing the actual depth of penetration for the test about 22 feet.
While certain features of the embodiments of the invention have been illustrated as described herein, many modifications, substitutions, changes and equivalents will now occur to those skilled in the art. It is, therefore, to be understood that the appended claims are intended to cover all such modifications and changes as fall within the true spirit of the embodiments.
|Cited Patent||Filing date||Publication date||Applicant||Title|
|US4813435||Apr 25, 1988||Mar 21, 1989||Micro Strain Company||Implantable displacement sensor means|
|US5383368||Nov 16, 1992||Jan 24, 1995||Southwest Research Institute||Deflection sensor for robot links|
|US5497147 *||Jun 21, 1993||Mar 5, 1996||Microstrain, Company||Differential variable reluctance transducer|
|US5777467||Jan 24, 1996||Jul 7, 1998||Microstrain, Inc.||Miniaturized displacement transducer assembly|
|US6463813||Jun 25, 1999||Oct 15, 2002||Weatherford/Lamb, Inc.||Displacement based pressure sensor measuring unsteady pressure in a pipe|
|US6499368||Apr 28, 1998||Dec 31, 2002||Microstrain, Inc.||Miniaturized pressure equalized displacement sensor assembly|
|US6647253 *||Dec 29, 2000||Nov 11, 2003||Alps Electric Co., Ltd.||High gain intermediate frequency input circuit with satisfactory trap characteristics|
|US20050093537 *||Dec 2, 2004||May 5, 2005||Microstrain, Inc.||Circuit for compensating for time variation of temperature in an inductive sensor|
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US8910515 *||Sep 13, 2011||Dec 16, 2014||The United States Of America As Represented By The Secretary Of The Army||Instrumented magnetic projectile|
|Cooperative Classification||F42B15/08, G01P15/16, G01D5/202, G01D5/2013, G01P3/52, F42B35/00, F42B12/365|
|European Classification||G01P15/16, G01P3/52, F42B35/00, F42B12/36C, F42B15/08|
|May 16, 2007||AS||Assignment|
Effective date: 20070509
Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:MUNDELL, STEVEN W.;HAMEL, MICHAEL J.;REEL/FRAME:019400/0397
Owner name: MICROSTRAIN, INC., VERMONT
Effective date: 20070503
Owner name: NAVY, UNITED STATES OF AMERICA, REPRESENTED BY SEC
Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:FOUSE, TIMOTHY M.;CANADAY, MICHAEL M.;BOWEN, JOHN R., JR.;REEL/FRAME:019400/0332