CA1266796A - Short range tubular projectile - Google Patents
Short range tubular projectileInfo
- Publication number
- CA1266796A CA1266796A CA000466025A CA466025A CA1266796A CA 1266796 A CA1266796 A CA 1266796A CA 000466025 A CA000466025 A CA 000466025A CA 466025 A CA466025 A CA 466025A CA 1266796 A CA1266796 A CA 1266796A
- Authority
- CA
- Canada
- Prior art keywords
- projectile
- spin
- tubular body
- speed
- stup
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
- 238000013016 damping Methods 0.000 claims abstract description 7
- 230000005484 gravity Effects 0.000 claims abstract description 5
- 238000010304 firing Methods 0.000 claims description 6
- 239000000700 radioactive tracer Substances 0.000 claims description 3
- 230000007423 decrease Effects 0.000 claims description 2
- 239000000463 material Substances 0.000 claims description 2
- 238000000034 method Methods 0.000 claims 1
- 230000035945 sensitivity Effects 0.000 abstract description 6
- 230000000694 effects Effects 0.000 abstract description 4
- 238000009987 spinning Methods 0.000 abstract description 3
- 208000000884 Airway Obstruction Diseases 0.000 description 4
- 206010008589 Choking Diseases 0.000 description 4
- 230000015572 biosynthetic process Effects 0.000 description 4
- 238000005755 formation reaction Methods 0.000 description 4
- 230000003247 decreasing effect Effects 0.000 description 2
- 101100379067 Caenorhabditis elegans anc-1 gene Proteins 0.000 description 1
- 101100179591 Caenorhabditis elegans ins-22 gene Proteins 0.000 description 1
- 230000002301 combined effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 101150034433 terC gene Proteins 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
- F42B10/54—Spin braking means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/34—Tubular projectiles
Abstract
ABSTRACT
A spinning tubular projectile (STUP) is subcalibre to reduce retardation. It is fired with low spin to reduce the gyroscopic stability. The total effect is to reduce crosswind sensitivity and to obtain a better ballistic match with a simulated armour piercing for stabilized, discarding sabot (APFSDS) round. To reduce the range to that desired for a limited range practice round, the STUP is equipped with spin-damping fins on its surface near the projectile centre of gravity.
A spinning tubular projectile (STUP) is subcalibre to reduce retardation. It is fired with low spin to reduce the gyroscopic stability. The total effect is to reduce crosswind sensitivity and to obtain a better ballistic match with a simulated armour piercing for stabilized, discarding sabot (APFSDS) round. To reduce the range to that desired for a limited range practice round, the STUP is equipped with spin-damping fins on its surface near the projectile centre of gravity.
Description
The preser1t invention relates -to prac-tice a~nmunition a1~d more partic~llarly -to short rar1cJe projectiles for artillery -training .
A signi3cant problem în artillery raininy is limiting the danyer ~one createcl b~ the projec~ile, including ricochets, while maintaining a reasonable simulation of act~al artillery trajectories. Attempt~ -to sol~e ~his problem ha~e lnvo1~ed -the design o various types oE practice or ~raining rounds that are intended to follow the trajectory of the simulated round up to a fixed distance and then relatively abrup~ly to end their ~light.
One type oE training round that has bee}1 designed for this purpose is the spinnincJ tub1l]ar projectile (STUP~. Pro jecti:Les of this type are (1escribed ir1 Lav;o1ette Canacl:iar1 ~at~nts 956,17~, lssued 15 Octo~er 197~; I,013,L'~7 iss~1e(l 5 J~1ly 1977 anc1 L, n~ 32 issuecl L6 October 1~379. Of Particu1ar interest is the S'I`11P
deslgnated "C-62s', which is a Eull bore projectile designecl to simulate a 105 millimeter armour piercing, discarding sabot (APDS) round. The C-6~ STUP is Eired at a supersonic muæzle velocity.
The flow throucJh the center of the STUP is supersonic and the trajectory is a close match to that of the simulated round. After the speed o~ the sTue pro~ectile is reduced below a critical level, the ELow through tihe hollow core of the projectile is choked and the projecti]e develops a bow shock wave. rrhis produces a sharp rise in the dra~ on the projectile and a much curtailed -trajec-tory, a9 descr:ibed in the patents referred to above.
lt is now desired to s:imulate an armo~lr piercing, Ein stabilized, discarding sabot ~APF`SDS~ rour1d ancl otherwise to improve on so~1e of the characteristics of the known STUE' ~ ~,6~7~
projectile.
One area of potential improvement is a reduction in cross wind sensitivity. As cross wind sensitivity decreases with decreasing gyroscopic stability and retardation~ this implies that the STUP should be subcaliber for low retardation and with just enough gyroscopic stability for flight. However, with a STUP
designed to these criteria the choking effect alone is not sufficient to limit the range as desired. The present invention is concerned with an alternative or additional mechanism that, combined with the choking effect provides the desired characteristics in a practice projectile.
According to the present inven-tion a short range practice projectile comprises a hollow tubular body and spin damping formations on a surface oE the body.
The spin damping formations cause the STUP to lose spin in flight and to become unstable at a predetermined range. The onset of instability from spin decay causes a gradual increase in the angle of attack until the projectile begins to tumble. In the presently preferred embodiments, the STUP is designed with an internal wedge at the leading edge to produce either supersonic or choked flow through the core, according to the teachings of the Laviolette Patents previously discussed. An increasing angle of attack provokes early choking of the flow, so that the high drag from both the tumbling of the projectile and the choked flow causes high retardation and a short range. Additionally, the flow choking effect prevents any return to a low drag flight regime even if the STUP becomes stable again. This could occur if the velocity decreased faster than the spin rate in the tumbling phase.
~2667~
, The spin damping formations are desirably three fins on the outside of the tubular body adjacent its center of gravity~
~ efore firing, the STUP will preferably be mounted in a sabot that is discarded when the STUP leaves the muzzle of the firing gun.
It has also been very desirable to construct the tubular body of the projectile with a fineness ratio (length of projectile/diameter of projectile) of approximately 4. Where desired, the projectile may be equipped with a tracer.
In the accompanying drawings, which illustrate exemplary embodiments of the present invention:
Figure 1 is a perspec-tive view of a STUP according to the present invention;
Figure 2 is a cross sectional view of the ':TU~ of Figure 1 mounted in a sabot;
Figures 3, 4 and 5 are plots showing the accuracy of firings at lOOOm. range of three different projectiles, one of which is constructed according to the presen-t invention;
Figures 6, 7 and 8 are Figures like Figures 3, 4 and 5 respectively, displaying accuracy of firings at 2500m. range;
Figure 9 is a plot showing the comparison oE maximum ranges of different projectiles launched at an elevation of 15.
Referring to the accompanying drawings, and particularly to Figures 1 and 2, there is illustrated a spinning tubular projectile 10. The projectile has a hollow tubular body 12 with a leading section 1~ that tapers to a sharp or slightly rounded leading edge 16. The hollow core 18 of the tubular body is configured to present an internal wedge 20 adjacent to the leading edge 16. The area ratio of the projectile, that is the ratio of the smallest open area in the hollow core to the area of the core ~26~67~
~-assage at t'lle ed(-le 16 is selected to provide a supersonic flow on firillg ancl subs2q-len-t cho~ecl 1OW when the spee(l of the projectile reduces to a desired critica:L level, or else ~ihen the angle of attack is larcJe. This characteris~ic is described more ully in Canadian Patent 1,064,321 -t-ha~ has beel-l reEerred to in ~'ne foregoing.
The STUP constructecl according to the present invention has three small ~ins 22 spaced equally about the tubular body 12 of the projectile adjacent to the center of gravity of the projectile. The fins serve to clamp the sPin oE the projectile in Eligh-t. They are located adjacen-t to the center of gravity of the projectile so as not to contribute excessive]~r-to ei~he-r the cJtab~ .a-t:ic>n or destabili~,cltion o~ t'he projectile other than b~
~pin darnphlq~
E`icJIlre 2 ol tlle accompanylncJ drawirl~Js illnstrates the finned STUP moun-ted in a full bore sabot 24~ The sabot has a base 26 to which -the STUP ls securecl by pins 28 iCit-ted into aligned 'bores in the base and the trailing end of the STUP~ The trailing end of the STUP also has a bore 30 filled with a tracer material 32 for providing a visual indica-tion of the trajectory on f:iring.
The sabot has a main body 34 connec-ted to the base 26 that extends forwardly over t'he STUP~ A leading section 36 of the .sabot body has a series of radlal t'hroug'h slo-ts 38 tha-t end adjacent external and internal circumferential ~rooves 40 and 42 respectively. rrhe radial slots and the circumferential grooves perlnit the break-up of t;he sabot body due to the aerodynamic forces exerted on i-t on launch of the projectile. The base 26 of -the ~abot carries an obturator 44 for c:losing the bore of the ~un d~ring ~lring o~-the projec-~ile. ~ driving band 46 ls fitted .~ 67~i 'o the main body of the sabot just ahead of the obturator and a centering band 48 surrounds the leading end of the main body.
On launch of the projectile-sabot combination as illustrated in Figure 2, the sabot breaks up releasing the STUP so that the STUP carries on alone. This arrangement is known and will not be described further.
The illustrated STUP has a fineness ratio of 4 to mlnimize drag and retardation. It is desired to minimize retardation as this is a factor in reducing cross wind sensitivity. Another factor affecting the cross wind sensitivity is the gyroscopic stability, the sensitivity increasing with the increasing gyroscopic stability. It is therefore desired to reduce the gyroscopic stability by reducing the spin rate of the STUP. The combined effects of the low re-tardation and low gyroscopic stability is a delay in the onset Oe chokin~ ancl thus an extension of the range of the projectile beyond its desired iimited range.
To re-establish the desired short range, the fins 22 are applied to the STUP to damp the spinning of the STUP and bring about the onset of unstable flight.
Figures 3 through 5 i]lustrate the accuracy of firings at a 1000m range of a training projectile with a discarding sabot (TPDS) (Figure 3), a STUP identified as "Model 59" without spin damping fins (Figure 4), and the same STUP "Model 59" with spin damping fins (Figure 5). The circle at the center of each chart indicates the aim poin-t, the small cross indicates the mean point of intersection of the projectiles with the measuring plane and the other markings, circles, squares or triangles, show the points of intersection of the individual projectiles. Figures 6, 7 and 8 are like Figures 3, 4 and 5, but illustrate the accuracy ~6i~
.It: 25()0 meierC; r.n(;e. As wil:L be sp,p,lrent t}le s'ruP Model. 59 wikh fins is rnore accurate thati-l:he 59 ~ thollt fin~ and roughly comparable :in accuracy tO the con~entiollal train:irlg projectile.
I~igure 9 illustra~:es, the cornparat..ive maxiTIlurn ra~ger~3 o various trajectiles ~ en fire~l u~lder the r;ame conditiorls. Curv~ A
represen~s the l~ro~ectory c~E t11e armour ple.Lc.irlg fin stabil:ized, discarding sabot ~APFSDS) roun(l -that .is -io ~e simulated. Curve l3 represents the tra]ectory o the traininq pro-jectile, dir;cardiricJ
sabot C-74fTPDS C-74) tnat is referred in E'igu~eF~ 3 and 6. Cur~e C designates the trajectorv oE a STUP C6~ which is a ul:L bore and unEinned. Curve D :is the t~ajectory of STU~ Model 5~ wi.-th fins.
~; will be appcii-ent from 1:he clraw.irl~3, t'he trajcc-tory of the 'l'PDS
and of e.lc'l~ S'L'IJl? is a qood Ina~ h to th? t.raject-ol-y o:l the si.lnul~teci ~PISI)S .~or tt1(? j.~l i.t.i.C~ ?drt: o th~ :roj?c~ ].i.yllt.
The f.inned STUl~.however~ COmeS (10~rl at abOilt 7 .2 k1 LOTI~terC; rathe.r -t'han 30 k:iloTIieters for the ac-tual round, l4.~l k:i.lometers for the TP~S and 7.7 kilorneters fc)r the 5TVP C-62.
While orle embodimellt of the inven-t:ion has been described in the foregoing, it 15 t0 be understood that other embodiments are possible. F~or exarnpl.e, surface ~ormations on the srruP other than f.ins, may be :Evund to d~inE) the spi.n o: the projectlle adequately. The formations m-)s-t orlly interact with the air làyer around t'he projectlle suf~icierltly to dalllp t.~-le spin at -the desi:red rate. Some tests have indi.cate~ that grooves in the sur:Eace of a STUP do not produce enough skin Ericti.on to d~1mP the spin in an efec-tive way and thus are not spin dampi.ny formcltionc; for the ' purpo~es of the present inventiorlO
A signi3cant problem în artillery raininy is limiting the danyer ~one createcl b~ the projec~ile, including ricochets, while maintaining a reasonable simulation of act~al artillery trajectories. Attempt~ -to sol~e ~his problem ha~e lnvo1~ed -the design o various types oE practice or ~raining rounds that are intended to follow the trajectory of the simulated round up to a fixed distance and then relatively abrup~ly to end their ~light.
One type oE training round that has bee}1 designed for this purpose is the spinnincJ tub1l]ar projectile (STUP~. Pro jecti:Les of this type are (1escribed ir1 Lav;o1ette Canacl:iar1 ~at~nts 956,17~, lssued 15 Octo~er 197~; I,013,L'~7 iss~1e(l 5 J~1ly 1977 anc1 L, n~ 32 issuecl L6 October 1~379. Of Particu1ar interest is the S'I`11P
deslgnated "C-62s', which is a Eull bore projectile designecl to simulate a 105 millimeter armour piercing, discarding sabot (APDS) round. The C-6~ STUP is Eired at a supersonic muæzle velocity.
The flow throucJh the center of the STUP is supersonic and the trajectory is a close match to that of the simulated round. After the speed o~ the sTue pro~ectile is reduced below a critical level, the ELow through tihe hollow core of the projectile is choked and the projecti]e develops a bow shock wave. rrhis produces a sharp rise in the dra~ on the projectile and a much curtailed -trajec-tory, a9 descr:ibed in the patents referred to above.
lt is now desired to s:imulate an armo~lr piercing, Ein stabilized, discarding sabot ~APF`SDS~ rour1d ancl otherwise to improve on so~1e of the characteristics of the known STUE' ~ ~,6~7~
projectile.
One area of potential improvement is a reduction in cross wind sensitivity. As cross wind sensitivity decreases with decreasing gyroscopic stability and retardation~ this implies that the STUP should be subcaliber for low retardation and with just enough gyroscopic stability for flight. However, with a STUP
designed to these criteria the choking effect alone is not sufficient to limit the range as desired. The present invention is concerned with an alternative or additional mechanism that, combined with the choking effect provides the desired characteristics in a practice projectile.
According to the present inven-tion a short range practice projectile comprises a hollow tubular body and spin damping formations on a surface oE the body.
The spin damping formations cause the STUP to lose spin in flight and to become unstable at a predetermined range. The onset of instability from spin decay causes a gradual increase in the angle of attack until the projectile begins to tumble. In the presently preferred embodiments, the STUP is designed with an internal wedge at the leading edge to produce either supersonic or choked flow through the core, according to the teachings of the Laviolette Patents previously discussed. An increasing angle of attack provokes early choking of the flow, so that the high drag from both the tumbling of the projectile and the choked flow causes high retardation and a short range. Additionally, the flow choking effect prevents any return to a low drag flight regime even if the STUP becomes stable again. This could occur if the velocity decreased faster than the spin rate in the tumbling phase.
~2667~
, The spin damping formations are desirably three fins on the outside of the tubular body adjacent its center of gravity~
~ efore firing, the STUP will preferably be mounted in a sabot that is discarded when the STUP leaves the muzzle of the firing gun.
It has also been very desirable to construct the tubular body of the projectile with a fineness ratio (length of projectile/diameter of projectile) of approximately 4. Where desired, the projectile may be equipped with a tracer.
In the accompanying drawings, which illustrate exemplary embodiments of the present invention:
Figure 1 is a perspec-tive view of a STUP according to the present invention;
Figure 2 is a cross sectional view of the ':TU~ of Figure 1 mounted in a sabot;
Figures 3, 4 and 5 are plots showing the accuracy of firings at lOOOm. range of three different projectiles, one of which is constructed according to the presen-t invention;
Figures 6, 7 and 8 are Figures like Figures 3, 4 and 5 respectively, displaying accuracy of firings at 2500m. range;
Figure 9 is a plot showing the comparison oE maximum ranges of different projectiles launched at an elevation of 15.
Referring to the accompanying drawings, and particularly to Figures 1 and 2, there is illustrated a spinning tubular projectile 10. The projectile has a hollow tubular body 12 with a leading section 1~ that tapers to a sharp or slightly rounded leading edge 16. The hollow core 18 of the tubular body is configured to present an internal wedge 20 adjacent to the leading edge 16. The area ratio of the projectile, that is the ratio of the smallest open area in the hollow core to the area of the core ~26~67~
~-assage at t'lle ed(-le 16 is selected to provide a supersonic flow on firillg ancl subs2q-len-t cho~ecl 1OW when the spee(l of the projectile reduces to a desired critica:L level, or else ~ihen the angle of attack is larcJe. This characteris~ic is described more ully in Canadian Patent 1,064,321 -t-ha~ has beel-l reEerred to in ~'ne foregoing.
The STUP constructecl according to the present invention has three small ~ins 22 spaced equally about the tubular body 12 of the projectile adjacent to the center of gravity of the projectile. The fins serve to clamp the sPin oE the projectile in Eligh-t. They are located adjacen-t to the center of gravity of the projectile so as not to contribute excessive]~r-to ei~he-r the cJtab~ .a-t:ic>n or destabili~,cltion o~ t'he projectile other than b~
~pin darnphlq~
E`icJIlre 2 ol tlle accompanylncJ drawirl~Js illnstrates the finned STUP moun-ted in a full bore sabot 24~ The sabot has a base 26 to which -the STUP ls securecl by pins 28 iCit-ted into aligned 'bores in the base and the trailing end of the STUP~ The trailing end of the STUP also has a bore 30 filled with a tracer material 32 for providing a visual indica-tion of the trajectory on f:iring.
The sabot has a main body 34 connec-ted to the base 26 that extends forwardly over t'he STUP~ A leading section 36 of the .sabot body has a series of radlal t'hroug'h slo-ts 38 tha-t end adjacent external and internal circumferential ~rooves 40 and 42 respectively. rrhe radial slots and the circumferential grooves perlnit the break-up of t;he sabot body due to the aerodynamic forces exerted on i-t on launch of the projectile. The base 26 of -the ~abot carries an obturator 44 for c:losing the bore of the ~un d~ring ~lring o~-the projec-~ile. ~ driving band 46 ls fitted .~ 67~i 'o the main body of the sabot just ahead of the obturator and a centering band 48 surrounds the leading end of the main body.
On launch of the projectile-sabot combination as illustrated in Figure 2, the sabot breaks up releasing the STUP so that the STUP carries on alone. This arrangement is known and will not be described further.
The illustrated STUP has a fineness ratio of 4 to mlnimize drag and retardation. It is desired to minimize retardation as this is a factor in reducing cross wind sensitivity. Another factor affecting the cross wind sensitivity is the gyroscopic stability, the sensitivity increasing with the increasing gyroscopic stability. It is therefore desired to reduce the gyroscopic stability by reducing the spin rate of the STUP. The combined effects of the low re-tardation and low gyroscopic stability is a delay in the onset Oe chokin~ ancl thus an extension of the range of the projectile beyond its desired iimited range.
To re-establish the desired short range, the fins 22 are applied to the STUP to damp the spinning of the STUP and bring about the onset of unstable flight.
Figures 3 through 5 i]lustrate the accuracy of firings at a 1000m range of a training projectile with a discarding sabot (TPDS) (Figure 3), a STUP identified as "Model 59" without spin damping fins (Figure 4), and the same STUP "Model 59" with spin damping fins (Figure 5). The circle at the center of each chart indicates the aim poin-t, the small cross indicates the mean point of intersection of the projectiles with the measuring plane and the other markings, circles, squares or triangles, show the points of intersection of the individual projectiles. Figures 6, 7 and 8 are like Figures 3, 4 and 5, but illustrate the accuracy ~6i~
.It: 25()0 meierC; r.n(;e. As wil:L be sp,p,lrent t}le s'ruP Model. 59 wikh fins is rnore accurate thati-l:he 59 ~ thollt fin~ and roughly comparable :in accuracy tO the con~entiollal train:irlg projectile.
I~igure 9 illustra~:es, the cornparat..ive maxiTIlurn ra~ger~3 o various trajectiles ~ en fire~l u~lder the r;ame conditiorls. Curv~ A
represen~s the l~ro~ectory c~E t11e armour ple.Lc.irlg fin stabil:ized, discarding sabot ~APFSDS) roun(l -that .is -io ~e simulated. Curve l3 represents the tra]ectory o the traininq pro-jectile, dir;cardiricJ
sabot C-74fTPDS C-74) tnat is referred in E'igu~eF~ 3 and 6. Cur~e C designates the trajectorv oE a STUP C6~ which is a ul:L bore and unEinned. Curve D :is the t~ajectory of STU~ Model 5~ wi.-th fins.
~; will be appcii-ent from 1:he clraw.irl~3, t'he trajcc-tory of the 'l'PDS
and of e.lc'l~ S'L'IJl? is a qood Ina~ h to th? t.raject-ol-y o:l the si.lnul~teci ~PISI)S .~or tt1(? j.~l i.t.i.C~ ?drt: o th~ :roj?c~ ].i.yllt.
The f.inned STUl~.however~ COmeS (10~rl at abOilt 7 .2 k1 LOTI~terC; rathe.r -t'han 30 k:iloTIieters for the ac-tual round, l4.~l k:i.lometers for the TP~S and 7.7 kilorneters fc)r the 5TVP C-62.
While orle embodimellt of the inven-t:ion has been described in the foregoing, it 15 t0 be understood that other embodiments are possible. F~or exarnpl.e, surface ~ormations on the srruP other than f.ins, may be :Evund to d~inE) the spi.n o: the projectlle adequately. The formations m-)s-t orlly interact with the air làyer around t'he projectlle suf~icierltly to dalllp t.~-le spin at -the desi:red rate. Some tests have indi.cate~ that grooves in the sur:Eace of a STUP do not produce enough skin Ericti.on to d~1mP the spin in an efec-tive way and thus are not spin dampi.ny formcltionc; for the ' purpo~es of the present inventiorlO
Claims (6)
PROPERTY OR PRIVILEGE IS CLAIMED ARE DEFINED AS FOLLOWS:
1. A short range practice projectile comprising a subcalibre hollow cone tubular body having an annular leading edge with an internal wedge adjacent the leading edge, the area ratio of the smallest open area in the hollow core to the area of the core passage at the leading edge being such as to sustain a supersonic flow within the tubular body at a projectile speed above a selected supersonic speed and to produce a choked flow within the tubular body in response to reduction of the projectile speed to a speed lower than the selected speed; spin damping means comprising a plurality of fins on the external surface of the tubular body for slowing the spin of the body during flight at a selected rate greater than the rate of velocity decrease, whereby the flight of the projectile becomes unstable, the angle of attack of the projectile increases, and the flow within the tubular body becomes choked at a projectile speed above said selected supersonic speed; and a sabot carrying the body.
2. A projectile according to claim 1 including three fins spaced equally around the projectile.
3. A projectile according to claim 2 wherein the fins are located adjacent the projectile's center of gravity.
4. A projectile according to claim 1, wherein the tubular body has a fineness ratio of substantially 4.
5. A projectile according to claim 1, including a bore in a trailing end of the projectile and a tracer material accommodated in the bore.
6. A method of controlling the range of a practice projectile having a hollow, tubular configuration and an internal wedge at the leading end of the projectile, comprising: firing the projectile from a gun at a supersonic speed sufficient to cause supersonic flow through the projectile, and with sufficient spin to be gyroscopically stable; slowing the spin of the projectile, whereby the gyroscopic stability of the projectile is reduced and the angle of attack of the projectile is increased causing the flow through the projectile to choke in response to the increasing angle of attack.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA000466025A CA1266796A (en) | 1984-10-22 | 1984-10-22 | Short range tubular projectile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA000466025A CA1266796A (en) | 1984-10-22 | 1984-10-22 | Short range tubular projectile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1266796A true CA1266796A (en) | 1990-03-20 |
Family
ID=4128968
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000466025A Expired CA1266796A (en) | 1984-10-22 | 1984-10-22 | Short range tubular projectile |
Country Status (1)
| Country | Link |
|---|---|
| CA (1) | CA1266796A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1012526A2 (en) * | 1997-09-09 | 2000-06-28 | Primex Technologies, Inc. | Range limited projectile |
-
1984
- 1984-10-22 CA CA000466025A patent/CA1266796A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1012526A2 (en) * | 1997-09-09 | 2000-06-28 | Primex Technologies, Inc. | Range limited projectile |
| EP1012526A4 (en) * | 1997-09-09 | 2002-05-22 | Primex Tech Inc | Range limited projectile |
| USRE38261E1 (en) | 1997-09-09 | 2003-10-07 | General Dynamic Ordnance and Tactical System, Inc. | Ranged limited projectile using augmented roll damping |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKEX | Expiry |