CA1192443A - Training projectile - Google Patents
Training projectileInfo
- Publication number
- CA1192443A CA1192443A CA000394708A CA394708A CA1192443A CA 1192443 A CA1192443 A CA 1192443A CA 000394708 A CA000394708 A CA 000394708A CA 394708 A CA394708 A CA 394708A CA 1192443 A CA1192443 A CA 1192443A
- Authority
- CA
- Canada
- Prior art keywords
- projectile
- fins
- grooves
- intermediate portion
- training
- 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
- 239000000543 intermediate Substances 0.000 claims 6
- 238000010304 firing Methods 0.000 abstract description 14
- 230000000694 effects Effects 0.000 abstract description 3
- 108091006146 Channels Proteins 0.000 description 5
- 230000004323 axial length Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- MLGCXEBRWGEOQX-UHFFFAOYSA-N tetradifon Chemical compound C1=CC(Cl)=CC=C1S(=O)(=O)C1=CC(Cl)=C(Cl)C=C1Cl MLGCXEBRWGEOQX-UHFFFAOYSA-N 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
Abstract
ABSTRACT
The invention relates to a training projectile stabilized by its own rotation and which comprises a conical nose section, a cylindrical intermediate portion and a tail section and which is provided with aerodynamic surfaces in the form of fins or grooves on the cylindrical intermediate portion. The fins or grooves are substantially radially directed and parallel to the symmetrical axis of the projectile. By the fins or grooves arrangement a braking effect is imparted to the projectile to reduce its rotational velocity after launching, so that the projectile at a specific, critical rotational speed becomes unstable and tips or tilts. This means a substantial increase of air resistance and a corresponding reduction of the projectile velocity forwards. By an appropriate adjustment of the fins or grooves it is possible to locate the instability just behind the target distance when training. The ballistic properties of the training projectile are maintained up to the target distance but the maximal firing range is reduced compared with normal live ammunition.
The invention relates to a training projectile stabilized by its own rotation and which comprises a conical nose section, a cylindrical intermediate portion and a tail section and which is provided with aerodynamic surfaces in the form of fins or grooves on the cylindrical intermediate portion. The fins or grooves are substantially radially directed and parallel to the symmetrical axis of the projectile. By the fins or grooves arrangement a braking effect is imparted to the projectile to reduce its rotational velocity after launching, so that the projectile at a specific, critical rotational speed becomes unstable and tips or tilts. This means a substantial increase of air resistance and a corresponding reduction of the projectile velocity forwards. By an appropriate adjustment of the fins or grooves it is possible to locate the instability just behind the target distance when training. The ballistic properties of the training projectile are maintained up to the target distance but the maximal firing range is reduced compared with normal live ammunition.
Description
~2'~ 3 The present invention relates to a training projectile which is s~abili~ed by i~s own rotational velocity and which comprises a conical nose section~ a cylindrical intermediate portion and a tail section and which projectile is provided with braking means for reducing said rotational velocity after it has been launchedO
For military training purposes the normal live ammunition is commonly substituted by specific training ammunition for economic reasons. Such training ammunition often has a more simple design than normal live ammunition in order to reduce the firing costs. In order to enable military personnel to be trained under substantially normal iring conditions it is important that the ballistic properties of the training ammunition substantially correspond to those of the substituted live ammunition. As a result, the r~;m~l firing range of the training ammunition corresponds to the r~ l firing range of the live ammu~i-tion in question. This also means, however) ~hat the military training sessions must take place on the fe~ very wide proving grounds and that comparatively large areas must be closed off in order to allow the firing.
As a consequence~ a new type of training projectiles has recently been proposed which up to a predetermined firing distance has substantially the same ballistic properties as the live ammLmition in question, but which has a substantially reduced r~;m~l firing range compared with normal live ammunition.
The advantage of using this new type of training ammunition is that such amm~mition allows realistic military training sessions on substantially smaller proving grounds than previouslyO
One example of such training projectile is shown in German ~atent 16 78 197. This type of training projectile is provided with a number o chan-nels on its nose section3 which channels are made in such a way that an air stream is formed in the channels and gives the projectile an impulse opposite ~ 4l ~L1 ~
to its direc~ion of rotation. In one alternative embodiment said chann~ls may be replaced by a n~ber o~ blades but also in thls case :it is the axial air stream which is utilized to impart to thc projectile an impulse in a direction which is opposite to the d;rection of rotation of the projectile.
By orming the projectile wi~h such means for deflecting the axial air stream it is possible to reduce the rotational velocity of the projectile so much that finally 2 critical value for the rotational velocity is reached where the projectile is no longer stable in its trajectory but tips or tilts. When this happens the air resistance is increased considerably, with the result that the firing range is reduced.
One disadvantage with this type of projectile is that the deflec~ing channels as well as the blades make the projec~ile comparatively complicated and expensiveO Furthermore it is difficult to modify the projectile for diferent firing di.stances. By making such arrangements in the front section of the projectile there is also a risk that the ballistic properties o~ the projectile even up to the actual firing distance are changed.
Accordingly, the primary object of the present invention is to provide a training projectile which is more simple to manufacture and which can be easily modified for diferent firing distances In accordance with the present invention the cylindrical intermediate portion of the projectile is provided with a number of aerodynamic sur~aces radially directed and parallel to the symmetrical axis of the projectile. The aerodynamic surfaces may be made in the form of fins, which is appropriate for a sub caliber projectile, or formed by grooves or notches made directly on the cylindrical surface, for instance in the case of a full caliber projectileO Common for both of ~he types is that the air resistance is increased in the direction of rotation which means that the ro~ational velocity of the projectile is reduced after launching. For a specific rotating speed -the projectile becomes ~mstable and tips. By adjust:ing the location, size and/or n~ber of the surfaces it is possible to make this critical speed happen at a specific distance~ preferably just behind the target distance for the practice firing.
In the following the invention will be described more in detail with reference to the following drawings in which Figure 1 shows three different examples with the aerodynamic surfaces made in the form of fins on the cylin-drical intermediate portion and Figure 2 shows an alternative embodiment in ~hich the aerodynamic surfaces are formed by grooves on the cylindrical surface.
1~ The projectile body shown on the drawings is an example of an appro-priate projectile design and is basically identical for the different embodi-ments and comprises a conical nose section 1, a cylindrical intermediate portion ~'waist") 2 and a tail section 3O In this case the projectile is intended to be launched by means of a separate driving band ~not shown) and is therefore provided with a tail section ~ith grooves for the driving. For a full caliber projectile the tail section may have another design.
On the cylindrical intermediate portion 2 four fins 4 are distributed symmetrically over the periphery of the projectile body but in three different axial positions: at the front tFigure la), in the middle (Figure lb) and at the back ~Figure lc) of the cylindrical portion 20 The fins are directed axially, parallel to the symmetrical axis 5 of the projectile, extending radially out from the surface of the cylindrical portion 2. In the axial direction the fins are extended to about one third of the length of the cylindrical portion 2 and in its radial direction extended to about one fifth of the radius of the cylindrical portion 20 For aerodynamic reasons the front end surface 6 of the fins has been cut so that it forms an angle of approximately 45 with the symmetrical axis 5 of the projectile and fur~hermore the edges of this end surface have been machined at appro~lmately ~5 so that the fin has a sharp forward edge.
The rotational velocity which has been given to the projectile on leaving the gun barrel is reduced by the braking effect of the side sur~aces of the fins due to ai~ resistance. When the rotation has been reduced so much that the ro~ational speed has reached a specific critical value the projectile is no longer stable but tips or tilts~ which means a significant and sudden increase of air resistance for the projectile so that also its movement forwards in its trajectory is bra~ed~ This in turn means a significant reduction of the ~im~l firing range compared with normal live ammunition. By varying the size o the fins, i~eO their extension radially and axially, as well as their axial positions it is possible to make said instability happen just behind the present target distance.
~ ompared with the previous types of projectiles with channels or sur-faces for deflecting an air stream axially, this ne~ type of projectile means a more simple constructionO The basic form of the projectile body is maintained.
~ach of the fins may be arranged on the cylindrical intermediate portion 2 but as an alternative they may also be arranged on a replaceable ring which is threaded on the cylindrical portion 2. Said last-mentioned alternative is preferred as then a plurality of replaceable rings with different fin configura-tions adapted to different firing ranges may be used. Such ring 7 has been indicated in Figure la and in this case the ring is arranged in a corresponding recess on the cylindrical surface of the intermediate portion 2 In Pigure 2 an alternative embodiment is illustrated in which the aerodynamic surfaces for braking the rotational velocity of the projectile are formed by grooves 8 on the cylindrical intermediate portion 2. In conformity ~ith the corresponding fins in Figure 1 the grooves 8 are distributed symmetri-_~ _ cally over the periphery oE the projectile body and the location, depths andaxial extension ma~ be easily adjusted to the d0sired braking effect. If the grooves ~ are not extended over the entire axial length of the cylindrical intermediate portion the rear end ~ of the groove is pre-ferably cut to form an angle of ~5 ~Yith the symmetrical axis of the projectile for aerodynamic reasons.
The embodimen~ illustrated in Figure 2 may be used for sub-caliber as well as full-caliber projectiles, but the embodiment of Figure 1 with fins ca~
be used for sub-caliber projectiles only. Sub-caliber projectiles are provided ~th separate driving bands and the fins or grooves of the intermediate portion may~be used as a support for the driving band.
The invention is not limited to the above embodiments but can be modified within the scope of the following claims. By way of example, four symmetrically distributed fins have been illustrated but another number of fins may be used, if a~r~riateO Furthermore the fins or the grooves may have an axial extension which corresponds to the length of the cylindrical intermediate portion 2.
~5 -.
v
For military training purposes the normal live ammunition is commonly substituted by specific training ammunition for economic reasons. Such training ammunition often has a more simple design than normal live ammunition in order to reduce the firing costs. In order to enable military personnel to be trained under substantially normal iring conditions it is important that the ballistic properties of the training ammunition substantially correspond to those of the substituted live ammunition. As a result, the r~;m~l firing range of the training ammunition corresponds to the r~ l firing range of the live ammu~i-tion in question. This also means, however) ~hat the military training sessions must take place on the fe~ very wide proving grounds and that comparatively large areas must be closed off in order to allow the firing.
As a consequence~ a new type of training projectiles has recently been proposed which up to a predetermined firing distance has substantially the same ballistic properties as the live ammLmition in question, but which has a substantially reduced r~;m~l firing range compared with normal live ammunition.
The advantage of using this new type of training ammunition is that such amm~mition allows realistic military training sessions on substantially smaller proving grounds than previouslyO
One example of such training projectile is shown in German ~atent 16 78 197. This type of training projectile is provided with a number o chan-nels on its nose section3 which channels are made in such a way that an air stream is formed in the channels and gives the projectile an impulse opposite ~ 4l ~L1 ~
to its direc~ion of rotation. In one alternative embodiment said chann~ls may be replaced by a n~ber o~ blades but also in thls case :it is the axial air stream which is utilized to impart to thc projectile an impulse in a direction which is opposite to the d;rection of rotation of the projectile.
By orming the projectile wi~h such means for deflecting the axial air stream it is possible to reduce the rotational velocity of the projectile so much that finally 2 critical value for the rotational velocity is reached where the projectile is no longer stable in its trajectory but tips or tilts. When this happens the air resistance is increased considerably, with the result that the firing range is reduced.
One disadvantage with this type of projectile is that the deflec~ing channels as well as the blades make the projec~ile comparatively complicated and expensiveO Furthermore it is difficult to modify the projectile for diferent firing di.stances. By making such arrangements in the front section of the projectile there is also a risk that the ballistic properties o~ the projectile even up to the actual firing distance are changed.
Accordingly, the primary object of the present invention is to provide a training projectile which is more simple to manufacture and which can be easily modified for diferent firing distances In accordance with the present invention the cylindrical intermediate portion of the projectile is provided with a number of aerodynamic sur~aces radially directed and parallel to the symmetrical axis of the projectile. The aerodynamic surfaces may be made in the form of fins, which is appropriate for a sub caliber projectile, or formed by grooves or notches made directly on the cylindrical surface, for instance in the case of a full caliber projectileO Common for both of ~he types is that the air resistance is increased in the direction of rotation which means that the ro~ational velocity of the projectile is reduced after launching. For a specific rotating speed -the projectile becomes ~mstable and tips. By adjust:ing the location, size and/or n~ber of the surfaces it is possible to make this critical speed happen at a specific distance~ preferably just behind the target distance for the practice firing.
In the following the invention will be described more in detail with reference to the following drawings in which Figure 1 shows three different examples with the aerodynamic surfaces made in the form of fins on the cylin-drical intermediate portion and Figure 2 shows an alternative embodiment in ~hich the aerodynamic surfaces are formed by grooves on the cylindrical surface.
1~ The projectile body shown on the drawings is an example of an appro-priate projectile design and is basically identical for the different embodi-ments and comprises a conical nose section 1, a cylindrical intermediate portion ~'waist") 2 and a tail section 3O In this case the projectile is intended to be launched by means of a separate driving band ~not shown) and is therefore provided with a tail section ~ith grooves for the driving. For a full caliber projectile the tail section may have another design.
On the cylindrical intermediate portion 2 four fins 4 are distributed symmetrically over the periphery of the projectile body but in three different axial positions: at the front tFigure la), in the middle (Figure lb) and at the back ~Figure lc) of the cylindrical portion 20 The fins are directed axially, parallel to the symmetrical axis 5 of the projectile, extending radially out from the surface of the cylindrical portion 2. In the axial direction the fins are extended to about one third of the length of the cylindrical portion 2 and in its radial direction extended to about one fifth of the radius of the cylindrical portion 20 For aerodynamic reasons the front end surface 6 of the fins has been cut so that it forms an angle of approximately 45 with the symmetrical axis 5 of the projectile and fur~hermore the edges of this end surface have been machined at appro~lmately ~5 so that the fin has a sharp forward edge.
The rotational velocity which has been given to the projectile on leaving the gun barrel is reduced by the braking effect of the side sur~aces of the fins due to ai~ resistance. When the rotation has been reduced so much that the ro~ational speed has reached a specific critical value the projectile is no longer stable but tips or tilts~ which means a significant and sudden increase of air resistance for the projectile so that also its movement forwards in its trajectory is bra~ed~ This in turn means a significant reduction of the ~im~l firing range compared with normal live ammunition. By varying the size o the fins, i~eO their extension radially and axially, as well as their axial positions it is possible to make said instability happen just behind the present target distance.
~ ompared with the previous types of projectiles with channels or sur-faces for deflecting an air stream axially, this ne~ type of projectile means a more simple constructionO The basic form of the projectile body is maintained.
~ach of the fins may be arranged on the cylindrical intermediate portion 2 but as an alternative they may also be arranged on a replaceable ring which is threaded on the cylindrical portion 2. Said last-mentioned alternative is preferred as then a plurality of replaceable rings with different fin configura-tions adapted to different firing ranges may be used. Such ring 7 has been indicated in Figure la and in this case the ring is arranged in a corresponding recess on the cylindrical surface of the intermediate portion 2 In Pigure 2 an alternative embodiment is illustrated in which the aerodynamic surfaces for braking the rotational velocity of the projectile are formed by grooves 8 on the cylindrical intermediate portion 2. In conformity ~ith the corresponding fins in Figure 1 the grooves 8 are distributed symmetri-_~ _ cally over the periphery oE the projectile body and the location, depths andaxial extension ma~ be easily adjusted to the d0sired braking effect. If the grooves ~ are not extended over the entire axial length of the cylindrical intermediate portion the rear end ~ of the groove is pre-ferably cut to form an angle of ~5 ~Yith the symmetrical axis of the projectile for aerodynamic reasons.
The embodimen~ illustrated in Figure 2 may be used for sub-caliber as well as full-caliber projectiles, but the embodiment of Figure 1 with fins ca~
be used for sub-caliber projectiles only. Sub-caliber projectiles are provided ~th separate driving bands and the fins or grooves of the intermediate portion may~be used as a support for the driving band.
The invention is not limited to the above embodiments but can be modified within the scope of the following claims. By way of example, four symmetrically distributed fins have been illustrated but another number of fins may be used, if a~r~riateO Furthermore the fins or the grooves may have an axial extension which corresponds to the length of the cylindrical intermediate portion 2.
~5 -.
v
Claims (5)
PROPERTY OR PRIVILEGE IS CLAIMED ARE DEFINED AS FOLLOWS:
1. A rotation stabilized training projectile comprising a conical nose section, a cylindrical intermediate portion and a tail section and provided with braking means for reducing the rotational velocity of the projectile after launching characterized in that said braking means comprises a plurality of aerodynamic surfaces located on the cylindrical intermediate portion, radially directed and parallel to the symmetrical axis of the projectile.
2. Projectile according to claim 1 characterized in that said aero-dynamic surfaces are formed by fins arranged on the cylindrical surface of said intermediate portion.
3. Projectile according to claim 1 characterized in that said aero-dynamic surfaces are formed by grooves on the cylindrical surface of said inter-mediate portion.
4. Projectile according to claim 2 or 3 characterized in that said fins or grooves are distributed symmetrically about the periphery of said intermediate portion.
5. Projectile according to claim 2 characterized in that the fins are arranged on a replaceable ring on said cylindrical intermediate portion.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SE8100385A SE442445B (en) | 1981-01-23 | 1981-01-23 | OPENING PROJECTIL WITH LONG-TERM PERODYNAMIC SURFACES |
| SE81.00385-7 | 1981-01-23 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1192443A true CA1192443A (en) | 1985-08-27 |
Family
ID=20342962
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000394708A Expired CA1192443A (en) | 1981-01-23 | 1982-01-22 | Training projectile |
Country Status (13)
| Country | Link |
|---|---|
| BE (1) | BE891866A (en) |
| CA (1) | CA1192443A (en) |
| CH (1) | CH656218A5 (en) |
| DE (1) | DE3201629C2 (en) |
| ES (1) | ES271926Y (en) |
| FR (1) | FR2498749B1 (en) |
| GB (1) | GB2091856B (en) |
| IL (1) | IL64791A (en) |
| IN (1) | IN157560B (en) |
| IT (1) | IT1149306B (en) |
| NL (1) | NL8200213A (en) |
| NO (1) | NO150095C (en) |
| SE (1) | SE442445B (en) |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3122320A1 (en) * | 1981-06-05 | 1983-01-27 | Dynamit Nobel Ag, 5210 Troisdorf | SPIRAL-STABILIZED EXERCISE BODY |
| IL78434A0 (en) * | 1985-05-16 | 1986-08-31 | Action Mfg Co | Spin decay projectile |
| DE3737997A1 (en) * | 1986-04-29 | 1996-05-30 | Royal Ordnance Plc | Swirl-damped practice floor with selectable safety flight range |
| DE3737708A1 (en) * | 1987-11-06 | 1989-05-18 | Diehl Gmbh & Co | DRIVING MIRROR FLOOR FOR A PLUG-IN RUNNER |
| DE8717995U1 (en) * | 1987-12-07 | 1992-04-23 | Diehl Gmbh & Co, 8500 Nuernberg, De | |
| DE3932952A1 (en) * | 1989-10-03 | 1991-04-11 | Rheinmetall Gmbh | BULLET STOCK |
| DE3933534C2 (en) * | 1989-10-07 | 1995-01-19 | Diehl Gmbh & Co | Practice bullet for target shooting without explosives with large-caliber weapons |
| US5125344A (en) * | 1991-08-28 | 1992-06-30 | Kline Roy W | Limited range training projectile |
| US5476045A (en) * | 1994-11-14 | 1995-12-19 | The United States Of America As Represented By The Secretary Of The Army | Limited range projectile |
| US5932836A (en) * | 1997-09-09 | 1999-08-03 | Primex Technologies, Inc. | Range limited projectile using augmented roll damping |
| DE102019126585A1 (en) | 2019-10-02 | 2021-04-08 | Rwm Schweiz Ag | Shortened range bullet |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR18862E (en) * | 1913-02-24 | 1914-07-27 | Louis Alard | Device for modifying the trajectory of a projectile |
| FR726843A (en) * | 1931-01-24 | 1932-06-03 | Method and device for controlling the rate of turn of a projectile | |
| FR728605A (en) * | 1931-12-10 | 1932-07-08 | Syndicat Vaproc | Projectile comprising a jacket or parts connected to this jacket, the shape of which produces a depression |
| FR2286364A1 (en) * | 1974-09-26 | 1976-04-23 | France Etat | Target practice ammunition for reduced length rifle range - simulates trajectory and accuracy of real ammunition of same calibre |
| DE2856859A1 (en) * | 1978-12-30 | 1980-07-17 | Dynamit Nobel Ag | Gyroscopically stabilised practice missile - has braking system composed of fins hinged circumferentially around body which fly out under centrifugal force |
| DE3064795D1 (en) * | 1979-03-10 | 1983-10-20 | Schirnecker Hans Ludwig | Projectile, e.g. for hunting, and method of manufacturing same |
-
1981
- 1981-01-23 SE SE8100385A patent/SE442445B/en not_active IP Right Cessation
-
1982
- 1982-01-15 IN IN32/DEL/82A patent/IN157560B/en unknown
- 1982-01-15 IL IL64791A patent/IL64791A/en unknown
- 1982-01-19 GB GB8201428A patent/GB2091856B/en not_active Expired
- 1982-01-20 DE DE3201629A patent/DE3201629C2/en not_active Expired
- 1982-01-20 IT IT47608/82A patent/IT1149306B/en active
- 1982-01-21 NL NL8200213A patent/NL8200213A/en not_active Application Discontinuation
- 1982-01-22 CA CA000394708A patent/CA1192443A/en not_active Expired
- 1982-01-22 NO NO820195A patent/NO150095C/en not_active IP Right Cessation
- 1982-01-22 ES ES1982271926U patent/ES271926Y/en not_active Expired
- 1982-01-22 BE BE0/207113A patent/BE891866A/en not_active IP Right Cessation
- 1982-01-22 CH CH417/82A patent/CH656218A5/en not_active IP Right Cessation
- 1982-01-22 FR FR8201016A patent/FR2498749B1/en not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| FR2498749B1 (en) | 1986-11-28 |
| NO150095B (en) | 1984-05-07 |
| NL8200213A (en) | 1982-08-16 |
| IT1149306B (en) | 1986-12-03 |
| SE8100385L (en) | 1982-07-24 |
| ES271926Y (en) | 1984-10-01 |
| NO820195L (en) | 1982-07-26 |
| IN157560B (en) | 1986-04-26 |
| IL64791A (en) | 1988-06-30 |
| NO150095C (en) | 1984-08-15 |
| IT8247608A0 (en) | 1982-01-20 |
| GB2091856B (en) | 1984-09-19 |
| SE442445B (en) | 1985-12-23 |
| BE891866A (en) | 1982-05-17 |
| CH656218A5 (en) | 1986-06-13 |
| GB2091856A (en) | 1982-08-04 |
| ES271926U (en) | 1984-02-01 |
| FR2498749A1 (en) | 1982-07-30 |
| DE3201629A1 (en) | 1982-09-02 |
| DE3201629C2 (en) | 1985-11-28 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKEX | Expiry |