CA2155399C - Spin-stabilized projectile with a payload - Google Patents
Spin-stabilized projectile with a payloadInfo
- Publication number
- CA2155399C CA2155399C CA 2155399 CA2155399A CA2155399C CA 2155399 C CA2155399 C CA 2155399C CA 2155399 CA2155399 CA 2155399 CA 2155399 A CA2155399 A CA 2155399A CA 2155399 C CA2155399 C CA 2155399C
- Authority
- CA
- Canada
- Prior art keywords
- projectile
- payload
- projectile body
- subprojectiles
- chamber
- 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 - Fee Related
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
- F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
- F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
- F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
Spin stabilized projectile with a payload. In such projectiles, the further trajectory of the payload (5) should not be unfavorably influenced during the expulsion thereof by parts of the projectile body (1). In order to achieve the most effective trouble-free expulsion of the payload (5) in accordance with this invention, the bursting charge is an explosive charge (17), wherein the explosive charge, in the radial direction, is in tight contact with the projectile body (1) and, in the axial direction, is provided with a damping space (18) relative to a web (7).
Description
21S~399 P13931.TRl The invention pertains to a spin stabilized projectile with a payload as per the preamble of patent claim 1.
In actual practice, the use of such projectiles, in combination with an antimissile defense system, has become known, wherein a flying target is detected and pursued with fire-control equipment, with automatic followup via an artillery piece. The projectile flight time calculations are carried out and at the discharge of the artillery piece in each projectile, the updated fuse response time is inductively transferred via a programming spool to the delayed action fuse in order to assure the expulsion of the payload, for example, subprojectiles, directly in front of the flying target.
However, during the expulsion of the payload, there is the danger that the trajectory of the payload will be unfavorably influenced by either parts of the projectile body or subjected to an excessive compressive stress by the bursting charge.
It is the task or object of this invention, to assure a substantially trouble free and uniform expulsion of the payload. This is accomplished, in accordance with this invention via the features in the characterizing portion of patent claim 1.
Also advantageous are the placement of reference fracture locations in the longitudinal direction in the functional or utility chamber, as well as the use of a payload of subprojectiles, the special coaxial arrangement of the subprojectiles and the securing of same against rotation, during the projectile acceleration, via recesses in the projectile body in the region of the utility chamber.
- ` 2155399 P13931.TR1 One exemplary embodiment of the spin stabilized projectile with a payload is described in detail hereinafter with reference to the several drawings. Shown are:
Fig. 1 is a longitudinal sectional view through the spin stabilized projectile of this invention with the projectile having a payload of subprojectiles;
Fig. 2 is a lateral cross section taken along line II-II
of Fig. 1; and Fig. 3 is a dispersion diagram of a projectile in accordance with Figs. 1 and 2.
In accordance with Fig. 1, a spin stabilized projectile includes a projectile body 1, a ballistic cover or cone 2 attached to a front portion of projectile body 1 and an ignitor or fuse 3 attached to the aft body or rear section of projectile body 1, wherein fuse 3, in this example, takes the form of a programmable delay time fuse 3. It is however quite feasible to utilize a different fuse or igniter, for example a distance fuse, whose firing or ignition is accomplished via a transmission means. Projectile body 1 further includes a functional or utility chamber 4 for a fixedly retained payload 5, an igniter chamber 6, located behind or aft of utility chamber 4 and partially separated therefrom by a web 7, a rotating band 8 and slots or grooves 9, for the attachment of a non-illustrated but known cartridge case. A holding or retaining screw 10 fixedly secures payload 5 in the axial direction and also unites projectile body 1 and ballistic cover or cone 2. Known delay time fuse 3, affixed in ignition chamber 6, includes a fuse body 11, a data receiver spool 12, an energy supply system 13, including a power generator for example, an electronic delay ignition or time fuse module, an igniter 15, a detonator 16 and a bursting charge 17.
P13931.TR1 In accordance with this invention, the bursting charge 17 is an explosive charge 17, wherein the explosive charge, in the radial direction, is in tight contact with the igniter or rather the delay time fuse 3 and/or with the projectile body 1 and, in the axial direction, is provided with a damping or attenuating space 18 relative to web 7. If desired, explosive charge 17 can be located directly in projectile body 1, in which the ignition chain or circuit must be assured to the igniter or the delay ignition fuse 3 or the detonator 16. The damping space 18 can be in the form of an air gap between web 7 and explosive charge 17 in the manner illustrated in Fig. 1, or, for example, while not illustrated, in the form of a material, arranged between web 7 and explosive charge 17, having damping properties for the detonation impulse wave.
In accordance with Figs. 1 and 2, in this exemplary embodiment, payload 5 is comprised of a plurality of cylindrical subprojectiles 20 of heavy metal, with the subprojectiles forming coaxially arranged subprojectile columns 21 in utility chamber 4. Eight superposed subprojectiles 20 form one column 21 and nineteen such columns 21, as best seen in Fig. 2, are fixedly secured in the axial direction in utility chamber 4 via holding screw 10.
Preferably, at the same time, the projectile body 1, in the region of utility chamber 4, has the shape of a hollow cylinder 22, with the hollow cylinder additionally having recesses 23 in the axial direction. As shown in Fig. 2, in cross section, six eccentric recesses 23, in the form of sectors of circles, are utilized. By means of these recesses, on one hand, subprojectiles 20 or rather subprojectile columns 21, are retained adjacently together and, in addition, are secured against rotation via holding screw 10, as well as' on the other hand, forming reference fracture locations 24, in P13931.TR1 the axial direction, at the thinnest wall portions of projectile body 1.
The mode of operation of the spin stabilized projectile is as follows: Once igniter 16 is ignited, there occurs, via detonator 16 and explosive charge 17, the expulsion of payload 5, i.e., subprojectiles 20. As a result of the arrangement of explosive charge 17, the impulse waves of the detonation function or operate immediately in the radial direction, in terms of time, and operate in a delayed manner, in terms of time, in the axial direction. As a result thereof, projectile body 1 is ripped open laterally in the region of rotating band 8, and the utility chamber 4 is opened laterally, along reference fracture locations 24 from a rear or aft portion of the projectile body, for example much in the manner in which a banana is peeled, and the side portions thereof, aided by the centrifugal force are flung away. Limited via damping space 18, payload 5 is only subjected to slight compression, as a result of which the release of subprojectiles 20 is time delayed and occurs substantially without interference. The heavy metal subprojectiles of illustrated payload 5 then fly singly, in a spin stabilized manner, toward the target in an acute scattering angle.
Illustrated very well in Fig. 3 is the dispersion diagram of such a projectile having 152 subprojectiles 20 and shows the coaxial arrangement of the nineteen subprojectile columns 21, each having eight subprojectiles 20 in utility chamber 4, together with the substantially trouble free expulsion thereof. For example, the bordered point or dot spiral 25 emanates from a subprojectile column 21 located at the largest or greatest coaxial distance from the projectile axis and point 26 emanates from a subprojectile 20 that abuts web 7.
21~399 P13931.TR1 As a payload S, other subprojectiles in other formations and other arrangements can be utilized or be utilized for the generation of false targets or rather for blinding or dazzling of a flying target, or for CHAFF or FLARE payloads.
In actual practice, the use of such projectiles, in combination with an antimissile defense system, has become known, wherein a flying target is detected and pursued with fire-control equipment, with automatic followup via an artillery piece. The projectile flight time calculations are carried out and at the discharge of the artillery piece in each projectile, the updated fuse response time is inductively transferred via a programming spool to the delayed action fuse in order to assure the expulsion of the payload, for example, subprojectiles, directly in front of the flying target.
However, during the expulsion of the payload, there is the danger that the trajectory of the payload will be unfavorably influenced by either parts of the projectile body or subjected to an excessive compressive stress by the bursting charge.
It is the task or object of this invention, to assure a substantially trouble free and uniform expulsion of the payload. This is accomplished, in accordance with this invention via the features in the characterizing portion of patent claim 1.
Also advantageous are the placement of reference fracture locations in the longitudinal direction in the functional or utility chamber, as well as the use of a payload of subprojectiles, the special coaxial arrangement of the subprojectiles and the securing of same against rotation, during the projectile acceleration, via recesses in the projectile body in the region of the utility chamber.
- ` 2155399 P13931.TR1 One exemplary embodiment of the spin stabilized projectile with a payload is described in detail hereinafter with reference to the several drawings. Shown are:
Fig. 1 is a longitudinal sectional view through the spin stabilized projectile of this invention with the projectile having a payload of subprojectiles;
Fig. 2 is a lateral cross section taken along line II-II
of Fig. 1; and Fig. 3 is a dispersion diagram of a projectile in accordance with Figs. 1 and 2.
In accordance with Fig. 1, a spin stabilized projectile includes a projectile body 1, a ballistic cover or cone 2 attached to a front portion of projectile body 1 and an ignitor or fuse 3 attached to the aft body or rear section of projectile body 1, wherein fuse 3, in this example, takes the form of a programmable delay time fuse 3. It is however quite feasible to utilize a different fuse or igniter, for example a distance fuse, whose firing or ignition is accomplished via a transmission means. Projectile body 1 further includes a functional or utility chamber 4 for a fixedly retained payload 5, an igniter chamber 6, located behind or aft of utility chamber 4 and partially separated therefrom by a web 7, a rotating band 8 and slots or grooves 9, for the attachment of a non-illustrated but known cartridge case. A holding or retaining screw 10 fixedly secures payload 5 in the axial direction and also unites projectile body 1 and ballistic cover or cone 2. Known delay time fuse 3, affixed in ignition chamber 6, includes a fuse body 11, a data receiver spool 12, an energy supply system 13, including a power generator for example, an electronic delay ignition or time fuse module, an igniter 15, a detonator 16 and a bursting charge 17.
P13931.TR1 In accordance with this invention, the bursting charge 17 is an explosive charge 17, wherein the explosive charge, in the radial direction, is in tight contact with the igniter or rather the delay time fuse 3 and/or with the projectile body 1 and, in the axial direction, is provided with a damping or attenuating space 18 relative to web 7. If desired, explosive charge 17 can be located directly in projectile body 1, in which the ignition chain or circuit must be assured to the igniter or the delay ignition fuse 3 or the detonator 16. The damping space 18 can be in the form of an air gap between web 7 and explosive charge 17 in the manner illustrated in Fig. 1, or, for example, while not illustrated, in the form of a material, arranged between web 7 and explosive charge 17, having damping properties for the detonation impulse wave.
In accordance with Figs. 1 and 2, in this exemplary embodiment, payload 5 is comprised of a plurality of cylindrical subprojectiles 20 of heavy metal, with the subprojectiles forming coaxially arranged subprojectile columns 21 in utility chamber 4. Eight superposed subprojectiles 20 form one column 21 and nineteen such columns 21, as best seen in Fig. 2, are fixedly secured in the axial direction in utility chamber 4 via holding screw 10.
Preferably, at the same time, the projectile body 1, in the region of utility chamber 4, has the shape of a hollow cylinder 22, with the hollow cylinder additionally having recesses 23 in the axial direction. As shown in Fig. 2, in cross section, six eccentric recesses 23, in the form of sectors of circles, are utilized. By means of these recesses, on one hand, subprojectiles 20 or rather subprojectile columns 21, are retained adjacently together and, in addition, are secured against rotation via holding screw 10, as well as' on the other hand, forming reference fracture locations 24, in P13931.TR1 the axial direction, at the thinnest wall portions of projectile body 1.
The mode of operation of the spin stabilized projectile is as follows: Once igniter 16 is ignited, there occurs, via detonator 16 and explosive charge 17, the expulsion of payload 5, i.e., subprojectiles 20. As a result of the arrangement of explosive charge 17, the impulse waves of the detonation function or operate immediately in the radial direction, in terms of time, and operate in a delayed manner, in terms of time, in the axial direction. As a result thereof, projectile body 1 is ripped open laterally in the region of rotating band 8, and the utility chamber 4 is opened laterally, along reference fracture locations 24 from a rear or aft portion of the projectile body, for example much in the manner in which a banana is peeled, and the side portions thereof, aided by the centrifugal force are flung away. Limited via damping space 18, payload 5 is only subjected to slight compression, as a result of which the release of subprojectiles 20 is time delayed and occurs substantially without interference. The heavy metal subprojectiles of illustrated payload 5 then fly singly, in a spin stabilized manner, toward the target in an acute scattering angle.
Illustrated very well in Fig. 3 is the dispersion diagram of such a projectile having 152 subprojectiles 20 and shows the coaxial arrangement of the nineteen subprojectile columns 21, each having eight subprojectiles 20 in utility chamber 4, together with the substantially trouble free expulsion thereof. For example, the bordered point or dot spiral 25 emanates from a subprojectile column 21 located at the largest or greatest coaxial distance from the projectile axis and point 26 emanates from a subprojectile 20 that abuts web 7.
21~399 P13931.TR1 As a payload S, other subprojectiles in other formations and other arrangements can be utilized or be utilized for the generation of false targets or rather for blinding or dazzling of a flying target, or for CHAFF or FLARE payloads.
Claims (5)
1. A spin stabilized projectile having a payload (5) comprising:
a projectile body (1);
a ballistic cone (2) attached to a front portion of the projectile body (1);
a utility chamber (4) located within the projectile body (1), for fixedly retaining the payload (5);
an igniter chamber (6) located behind the utility chamber (4) of the projectile body (1);
an igniter (3) retained in the igniter chamber (6); and a bursting charge, separated from the utility chamber (4) of the projectile body (1) via a web (7), for expelling the payload (5), therein characterized, that the bursting charge (17) is an explosive charge (17), wherein the explosive charge, in the radial direction, is in tight contact with the projectile body (1) and, in the axial direction, is provided with a damping space (18) relative to the web (7).
a projectile body (1);
a ballistic cone (2) attached to a front portion of the projectile body (1);
a utility chamber (4) located within the projectile body (1), for fixedly retaining the payload (5);
an igniter chamber (6) located behind the utility chamber (4) of the projectile body (1);
an igniter (3) retained in the igniter chamber (6); and a bursting charge, separated from the utility chamber (4) of the projectile body (1) via a web (7), for expelling the payload (5), therein characterized, that the bursting charge (17) is an explosive charge (17), wherein the explosive charge, in the radial direction, is in tight contact with the projectile body (1) and, in the axial direction, is provided with a damping space (18) relative to the web (7).
2. The spin stabilized projectile of claim 1, therein characterized, that in the region of the utility chamber (4), reference fracture locations (24) are provided on the projectile body (1) in the longitudinal direction in order to achieve a lateral opening of the utility chamber (4), from an aft portion of the projectile body, via the explosive charge (17).
3. The spin stabilized projectile of claim 2, therein characterized, that the payload (5) is comprised of a plurality of cylindrical subprojectiles (20) of heavy metal, with the subprojectiles forming coaxially-arranged subprojectile columns (21) in the utility chamber (4).
4. The spin stabilized projectile of claim 3, therein characterized, that the projectile body (1), in the region of the utility chamber (4), has the shape of a hollow cylinder (22), with the hollow cylinder having additional recesses (23) in the axial direction, in order, on one hand, to retain the subprojectiles (20) against rotation, and on the other hand, to form the reference fracture locations (24).
5. The spin stabilized projectile of claim 4, therein characterized, that the subprojectiles (20) are fixed, in the axial direction, via a holding screw (10), provided at the front portion of the projectile body (1).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH02614/94-3 | 1994-08-26 | ||
| CH02614/94A CH688727A5 (en) | 1994-08-26 | 1994-08-26 | Spin-stabilized projectile with a payload. |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2155399A1 CA2155399A1 (en) | 1996-02-27 |
| CA2155399C true CA2155399C (en) | 1999-06-01 |
Family
ID=4237730
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA 2155399 Expired - Fee Related CA2155399C (en) | 1994-08-26 | 1995-08-03 | Spin-stabilized projectile with a payload |
Country Status (6)
| Country | Link |
|---|---|
| EP (1) | EP0698774B1 (en) |
| JP (1) | JPH08170899A (en) |
| CA (1) | CA2155399C (en) |
| CH (1) | CH688727A5 (en) |
| DE (1) | DE59505486D1 (en) |
| NO (1) | NO302671B1 (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5817969A (en) * | 1994-08-26 | 1998-10-06 | Oerlikon Contraves Pyrotec Ag | Spin-stabilized projectile with payload |
| DE102007021451A1 (en) * | 2007-04-05 | 2008-10-09 | Rwm Schweiz Ag | Sub-projectile with energetic content |
| DE102011109658A1 (en) | 2011-08-08 | 2013-02-14 | Rheinmetall Air Defence Ag | Device and method for protecting objects |
| FR2998659B1 (en) | 2012-11-23 | 2017-06-23 | Nexter Munitions | GYROSTABILIZED PROJECTILE PROJECTING A PAYLOAD |
| FR3100610B1 (en) * | 2019-09-06 | 2023-11-03 | Cta Int | Anti-aircraft shell for telescoped ammunition with double unlocking |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE42925C (en) * | 1900-01-01 | societe anonyme des Anciens Etablissements hotchkiss & Cie. in Paris | Innovation in artillery - explosive projectiles to secure the systematic fragmentation of the same | |
| DE119324C (en) * | 1900-01-01 | |||
| US3954060A (en) * | 1967-08-24 | 1976-05-04 | The United States Of America As Represented By The Secretary Of The Army | Projectile |
| SE339647B (en) * | 1970-01-08 | 1971-10-11 | Bofors Ab | |
| DE2638920A1 (en) * | 1976-08-28 | 1978-03-02 | Dynamit Nobel Ag | Spreader for radiation reflecting or emitting material - has central tube with holes, connected to compressed gas which disperses material |
| DE3326877A1 (en) * | 1983-07-26 | 1985-02-07 | Diehl GmbH & Co, 8500 Nürnberg | Method and device for combating targets by means of submunition ejected above a target zone |
| DE8436168U1 (en) * | 1984-12-11 | 1985-05-09 | Heide, Marion, 4030 Ratingen | Container that can be inserted into a projectile |
| FR2637065B1 (en) * | 1988-09-02 | 1993-10-15 | Thomson Brandt Armements | AMMUNITION PROTECTIVE COVER COMPRISING MEANS FOR CUTTING IT |
-
1994
- 1994-08-26 CH CH02614/94A patent/CH688727A5/en not_active IP Right Cessation
-
1995
- 1995-06-22 EP EP19950109690 patent/EP0698774B1/en not_active Expired - Lifetime
- 1995-06-22 DE DE59505486T patent/DE59505486D1/en not_active Expired - Fee Related
- 1995-07-12 NO NO952770A patent/NO302671B1/en not_active IP Right Cessation
- 1995-08-03 CA CA 2155399 patent/CA2155399C/en not_active Expired - Fee Related
- 1995-08-24 JP JP21600195A patent/JPH08170899A/en not_active Withdrawn
Also Published As
| Publication number | Publication date |
|---|---|
| CH688727A5 (en) | 1998-01-30 |
| NO952770L (en) | 1996-02-27 |
| EP0698774A1 (en) | 1996-02-28 |
| CA2155399A1 (en) | 1996-02-27 |
| DE59505486D1 (en) | 1999-05-06 |
| EP0698774B1 (en) | 1999-03-31 |
| NO952770D0 (en) | 1995-07-12 |
| JPH08170899A (en) | 1996-07-02 |
| NO302671B1 (en) | 1998-04-06 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| MKLA | Lapsed |