EP0090888A1 - Übungsgeschoss mit ablösbarem Treibkäfig - Google Patents
Übungsgeschoss mit ablösbarem Treibkäfig Download PDFInfo
- Publication number
- EP0090888A1 EP0090888A1 EP82301142A EP82301142A EP0090888A1 EP 0090888 A1 EP0090888 A1 EP 0090888A1 EP 82301142 A EP82301142 A EP 82301142A EP 82301142 A EP82301142 A EP 82301142A EP 0090888 A1 EP0090888 A1 EP 0090888A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- sub
- projectile
- rod
- projectile according
- nose
- 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.)
- Withdrawn
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B8/00—Practice or training ammunition
- F42B8/12—Projectiles or missiles
- F42B8/14—Projectiles or missiles disintegrating in flight or upon impact
Definitions
- This invention relates to sub-projectiles for discarding sabot practice shot, and in particular to practice sub-projectiles which both closely match service devices in ballistic characteristics and have a limited range for safety of use on small firing ranges.
- Discarding sabot practice shot utilise a comparatively large calibre sabot to position a smaller calibre sub-projectile within the gun barrel.
- the large calibre provides a greater pressure area for propelling the shot than would be available with the sub-projectile alone.
- Once projected from the gun barrel the sabot is rapidly discarded to leave the sub-projectile free to continue its ballistic trajectory.
- One of the problems associated with discarding sabot practice shot is the relatively long range associated with their trajectory and ricochet characteristics. These limit the use of practice shot to firing ranges of large area, or may limit the use of a particular firing range to shots aimed in a particular direction.
- Prior art practice shot designed for break-up commonly incorporate a thermally deformable member which fails under aerodynamic heating during flight. Failure of the member initiates break-up. It is also known to employ aerodynamic or gas pressure to actuate break-up.
- US Pat, No 4,140,061 describes a practice shot comprising three 120 0 part-cylindrical body sections assembled around a central rod. The sections are retained on the rod by a heat- sensitive metal nose-cap. The nose-cap disintegrates during flight under aerodynamic heating to allow the sections to diverge radially producing break-up.
- US Pat No 3,747,533 relates to a practice shot having a missile head consisting partially of thermally deformable material.
- United Kingdom Pat Application No 2,010,452A describes a missile having three symmetrical 120° cylindrical body sections retained together either by a circumferential band or by a nose-cap. The band and cap melt under aerodynamic heating to allow the body segments to diverge radially and the missile to break-up.
- United Kingdom Pat No 1,581,108 also employs a practice shot or projectile having three 120° body sections, but uses the propellant gases generated at firing to initiate break-up via a delay mechanism.
- the prior art discarding sabot practice sub-projectiles exhibit a degree of complexity which leads to expense in manufacture.
- the prior art devices generally have only passive break-up characteristics, ie break up is produced aerodynamically after failure of a component. It is an object of the present invention to provide a simplified form of practice shot which has a ballistic geometry close to that of a service sub-projectile and has controlled and active fail-safe range characteristics.
- the present invention provides a sub-projectile for a discarding sabot practice shot, the sub-projectile including at least one annular cylindrical body portion slidably assembled on a longitudinally disposed central rod attached at one end to a tail member, and a nose member connected to the rod by a connection associated with resiliently biased thermally deformable separating means operative in response to in-flight aerodynamic heating.
- the thermally deformable separating means weakens under aerodynamic heating to permit separation of the rod from the nose member thereby initiating break-up.
- the provision of resilient biasing ensures that separation is positive and rapid.
- the invention simplifies the problems of engineering discarding sabot sub-projectiles by.
- the sub-projectile may include two or more discrete annular cylindrical body portions retained in longitudinal centiguity by the nose member.
- Conveniently resilient biasing of the separating means may be provided by a compression spring housed within the sub-projectile in the region of the nose member/body portion interface.
- the thermally deformable separating means may in one embodiment, comprise a layer of jointing material securing the nose member to the rod, the jointing material being designed to fail under aerodynamic heating.
- suitable jointing materials include solder, Woods metal and thermoplastic adhesive.
- a washer-shaped plug of material of relatively low thermal conductivity may be provide dbetween the nose member and the body portion to concentrate kinetic heating effects in the nose member of the sub-projectile.
- the body member and, if appropriate, part of the tail member may be provided with external thread-like projections to engage with corresponding recesses in the bore of the sabot.
- the sub-projectile comprises a central rod 10, a tail member 11 having fins 12, a main body assembly having annular cylindrical portions 13 and 14 and a nose member 15.
- the rod 10 is securely attached to the tail member 11 by a screw thread, brazing or any other suitable means.
- the main body assembly of the sub-projectile comprises the cylindrical body portions 13 and 14 which are arranged to be a sliding fit on the rod 10.
- the body portions 13 and 14 are maintained in place by the nose member 15, which is soldered with a jointing material to an end length of the rod member 10 having reduced diameter.
- the jointing material is designed to soften under aerodynamic heating to provide separating means.
- a washer-like plug 16 of thermo-setting plastic or other low thermal conductivity material is located between the nose member 15 and the forward cylindrical portion 13.
- Resilient biasing means 17 in the form of an axially compressed coil spring is located in a tubular recess 18 in the forward end region of the cylindrical body portion 13.
- the diameter of the rod 10 is stepped over a first length in the region of the recess 18 and over a second and final length where it is attached to the nose member 15, the stepping being compatible with the reducing cross-section of the sub-projectile.
- the reduced diameters also facilitate nose member separation and subsequent break-up as the body portions slide forwardly. along the rod 10 as will be described later.
- the assembled sub-projectile is located within a conventional sabot 19 by means of external thread-like or annular projections 20 en, as shown, the cylindrical portion 14 and part of the tail member 11.
- the sub-projectile In operation the sub-projectile is located within the sabot 19 and fired, the sabot 19 discarding in the conventional manner once free of the gun barrel. The sub-projectile then assumes a ballistic trajectory. As the sub-projectile moves through the atmosphere, it is subjected to aerodynamic heating particularly in the forward region of the nose member 15. The provision of the low conductivity plug 16 inhibits thermal conduction to the body portions 13 and l4. This concentrates the effects of aerodynamic heating in the nose member 15.
- Aerodynamic heating melts the jointing material or separating means by which the nose member 15 is retained on the rod 10, and these separate under resilient biasing from the coil spring 17 initiating break-up.
- the cylindrical body portions 13 and 14 of the sub-projectile are considerably heavier than the combined rod 10 and tail member 11, and their consequently greater forward momentum persists longer after break-up is initiated. Accordingly the portions 13 and 14 slide forwardly off the rod 10. Aerodynamic drag on the fins 12 of the tail member 11 also contributes to separation. The stepping of the rod 10 as previously described assists clean separation of the individual component parts, since less sliding resistance is presented by the reduced diameter lengths of the rod 10. Aerodynamic integrity of the sub-projectile is lost after break-up is initiated, and its component parts tumble to the ground.
- nose member 15 incorporating a thermal trigger as part of the separating means is shown in Figure 3, like reference numerals being used for identical or similar integers.
- the nose member 15 is hollow and thin-walled, and is attached to a thermally insulating nylon sleeve 21 mounted on the rod member 10.
- the sleeve 21 is secured to the nose member 15 and rod 10 by thread or adhesive means.
- the nose member 15 includes an annular relieved section 22.
- a recess 18 in the cylindrical portion 13 of the body member houses a stack of belleville washers (disc springs) 17, these being retained in a substantially fully compressed condition to prevent further compression during acceleration.
- aerodynamic heating is concentrated in the forward tip region of the nose member 15 and is particularly effective in the relieved section 22, and this section radiply overheats.
- the low conductivity nylon insulating sleeve 21 also increases in temperature to some extent, but inhibits heat loss to the rod 10.
- the nose member 15 is manufactured from aluminium alloy which loses strength quite dramatically above a threshold temperature. The nose member 15 consequently fails in the region of the relieved section 22 and separates from the body portion 13 under resilient bias from the belleville washers 17.
- the insulating sleeve 21 is also designed to fail at the appropriate time, and in an optimum design would fail simultaneously with failure of the relieved section 22. At failure the cylindrical portions 13 and 14 of the body member sequentially separate longitudinally as in operation of the embodiment of Figures 1 and 2..
- the sub-projectile described with reference to Figures 1 to 3 has two annular cylindrical body portions 13 and 14, although in some arrangements it might be preferred to have one or more than two.
- the particular construction of the invention allows a very close ballistic match and similar handling and appearance characteristics as compared with the in-service sub-projectile.
- the cylindrical construction is very advantageous, since the body portions may be produced from bar stock.
- prior art sub-projectiles have employed complex and expensive nested arrangements of symmetrical part-cylindrical sections. The invention avoids the need for such complex geometry by resiliently biasing apart components of the sub-projectile giving active break-up initiation.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP82301142A EP0090888A1 (de) | 1982-03-05 | 1982-03-05 | Übungsgeschoss mit ablösbarem Treibkäfig |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP82301142A EP0090888A1 (de) | 1982-03-05 | 1982-03-05 | Übungsgeschoss mit ablösbarem Treibkäfig |
Publications (1)
Publication Number | Publication Date |
---|---|
EP0090888A1 true EP0090888A1 (de) | 1983-10-12 |
Family
ID=8189593
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP82301142A Withdrawn EP0090888A1 (de) | 1982-03-05 | 1982-03-05 | Übungsgeschoss mit ablösbarem Treibkäfig |
Country Status (1)
Country | Link |
---|---|
EP (1) | EP0090888A1 (de) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2138549A (en) * | 1983-04-23 | 1984-10-24 | Rheinmetall Gmbh | Descarding salot penetrator |
EP0253423A1 (de) * | 1986-07-10 | 1988-01-20 | Koninklijke Philips Electronics N.V. | Verfahren zum Steuern eines Anzeigegerätes und Anzeigegerät, geeignet für ein solches Verfahren |
JPS6375494A (ja) * | 1986-09-18 | 1988-04-05 | ダイキン工業株式会社 | 訓練用戦車砲弾 |
US5001986A (en) * | 1989-03-03 | 1991-03-26 | Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag | Short-range projectile containing means for producing a short flight path |
EP0987513A2 (de) * | 1999-02-25 | 2000-03-22 | Oerlikon Contraves Pyrotec AG | Unterkalibergeschoss |
US6747930B1 (en) | 1996-12-24 | 2004-06-08 | Hide & Seek Technologies, Inc. | Data protection on an optical disk |
US9157713B1 (en) | 2013-03-15 | 2015-10-13 | Vista Outdoor Operations Llc | Limited range rifle projectile |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE734429C (de) * | 1939-07-20 | 1943-04-15 | Ing Bohdan Pantoflicek | UEbungsgeschoss mit verkuerzter Flugbahn |
US3747533A (en) * | 1970-12-08 | 1973-07-24 | Oerlikon Buehrle Ag | Short trajectory missile |
US4140061A (en) * | 1977-06-06 | 1979-02-20 | The United States Of America As Represented By The Secretary Of The Army | Short-range discarding-sabot training practice round and self-destruct subprojectile therefor |
GB2010452A (en) * | 1977-12-17 | 1979-06-27 | Rheinmetall Gmbh | Missile with an automatic self-disintegration effect |
DE2846998A1 (de) * | 1978-10-28 | 1980-05-08 | Fritz Werner Ind Ausruestung | Patrone |
GB2084703A (en) * | 1980-03-26 | 1982-04-15 | Secr Defence | Practice shot |
US4334478A (en) * | 1980-03-03 | 1982-06-15 | The United States Of America As Represented By The Secretary Of The Army | Fluidic range-safe device |
-
1982
- 1982-03-05 EP EP82301142A patent/EP0090888A1/de not_active Withdrawn
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE734429C (de) * | 1939-07-20 | 1943-04-15 | Ing Bohdan Pantoflicek | UEbungsgeschoss mit verkuerzter Flugbahn |
US3747533A (en) * | 1970-12-08 | 1973-07-24 | Oerlikon Buehrle Ag | Short trajectory missile |
US4140061A (en) * | 1977-06-06 | 1979-02-20 | The United States Of America As Represented By The Secretary Of The Army | Short-range discarding-sabot training practice round and self-destruct subprojectile therefor |
GB2010452A (en) * | 1977-12-17 | 1979-06-27 | Rheinmetall Gmbh | Missile with an automatic self-disintegration effect |
DE2846998A1 (de) * | 1978-10-28 | 1980-05-08 | Fritz Werner Ind Ausruestung | Patrone |
US4334478A (en) * | 1980-03-03 | 1982-06-15 | The United States Of America As Represented By The Secretary Of The Army | Fluidic range-safe device |
GB2084703A (en) * | 1980-03-26 | 1982-04-15 | Secr Defence | Practice shot |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2138549A (en) * | 1983-04-23 | 1984-10-24 | Rheinmetall Gmbh | Descarding salot penetrator |
US4624187A (en) * | 1983-04-23 | 1986-11-25 | Rheinmetall Gmbh | Penetrator projectiles |
EP0253423A1 (de) * | 1986-07-10 | 1988-01-20 | Koninklijke Philips Electronics N.V. | Verfahren zum Steuern eines Anzeigegerätes und Anzeigegerät, geeignet für ein solches Verfahren |
JPS6375494A (ja) * | 1986-09-18 | 1988-04-05 | ダイキン工業株式会社 | 訓練用戦車砲弾 |
US5001986A (en) * | 1989-03-03 | 1991-03-26 | Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag | Short-range projectile containing means for producing a short flight path |
US6747930B1 (en) | 1996-12-24 | 2004-06-08 | Hide & Seek Technologies, Inc. | Data protection on an optical disk |
EP0987513A2 (de) * | 1999-02-25 | 2000-03-22 | Oerlikon Contraves Pyrotec AG | Unterkalibergeschoss |
EP0987513A3 (de) * | 1999-02-25 | 2000-04-05 | Oerlikon Contraves Pyrotec AG | Unterkalibergeschoss |
US9157713B1 (en) | 2013-03-15 | 2015-10-13 | Vista Outdoor Operations Llc | Limited range rifle projectile |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Designated state(s): BE CH DE FR GB IT LI SE |
|
17P | Request for examination filed |
Effective date: 19840316 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
18D | Application deemed to be withdrawn |
Effective date: 19851001 |
|
RIN1 | Information on inventor provided before grant (corrected) |
Inventor name: GREENHOUGH, JAMES MICHAEL Inventor name: GUNN, BASIL VICTOR |