GB2394029A - Drag reduction devices for projectiles and the like - Google Patents
Drag reduction devices for projectiles and the like Download PDFInfo
- Publication number
- GB2394029A GB2394029A GB0220444A GB0220444A GB2394029A GB 2394029 A GB2394029 A GB 2394029A GB 0220444 A GB0220444 A GB 0220444A GB 0220444 A GB0220444 A GB 0220444A GB 2394029 A GB2394029 A GB 2394029A
- Authority
- GB
- United Kingdom
- Prior art keywords
- base
- projectile
- drag reduction
- drag
- fluid
- 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- Withdrawn
Links
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
- F42B10/38—Range-increasing arrangements
- F42B10/42—Streamlined projectiles
- F42B10/44—Boat-tails specially adapted for drag reduction
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
A drag reduction device for an artillery shell 5 comprises a deployable cone 7 collapsed and releasably retained within the aft, bluff, end 4 of the shell by a cover plate 12. A spring 13, initially compressed by the cover plate 12, urges the cone to a deployed position when freed to extend by a deployment device (11, 15). In the deployed position the cone 7 forms a continuous aerodynamic shape with the forward end of the shell 5 having reduced base-drag. The invention has application to certain air dropped stores and towed decoys. In principle it is applicable to hydrodynamic bodies for reducing hydrodynamic base-drag.
Description
Is DRAG REDUCTION DEVICES FOR PROJECTILES AND THE LIKE
The present invention relates to drag reduction devices for bluff ended bodies such as projectiles, artillery shells, rounds of ammunition, air dropped stores and the like. The term 'projectile' is used in this specification generically
to mean any of these bodies, however launched.
The invention relates in particular to projectiles which have a base-drag reduction unit. In the case of gun launched projectiles such base-drag reduction units increase the range and decrease dispersion of projectiles.
It has long been known that base-drag contributes generally to a ... 10 relatively large part of the total aerodynamic drag on a projectile in flight (or to the total hydrodynamic drag of an underwater projectile). A basic consideration of the problem is given in French patent number 510, 303 (Huguenard) which goes on to describe side and rear venting propellant gas arrangements for enhancing the performance of a projectile in flight.
Base-drag arises because the base pressure at the aft end of a bluff ended projectile is lower than the ambient air or static water pressure due to the resultant wake flow in the base region.
Thus a conventional bluff-ended projectile in flight, or in water, forms a partial vacuum, or region of reduced pressure, immediately behind it. This 20 partial vacuum or low pressure area creates a force which acts on the projectile in a direction opposite to its motion thereby lessening the velocity of the projectile and its range. This force is commonly referred to as "base-drag".
Drag may be defined as that force acting on the projectile in a direction opposite its motion. Base-drag is that drag acting on the projectile at its base, and this z invention concerns itself primarily with base-drag and the reduction thereof.
In the case of artillery shells, known methods of overcoming the low base pressure effect and the turbulence behind a bluff-ended projectile, comprise ejecting a gaseous mass flow from a base-drag reduction unit located at the base of the projectile into the near wake so as to affect the air flow pattern 30 behind the projectile in flight in such a way that the base pressure is increased and thereby the base-drag is reduced. If the ejection of mass flow is combined
- 2 with liberation of heat, for example by combustion, the base pressure can be further increased.
It was observed that tracer bullets have reduced total drag when compared with inert rounds, with attendant increases of velocity due to the 5 rearward pressure exerted by the reaction gases formed during combustion of the tracer compositions. The "base-bleed" concept was based on this observation and directed at reducing or substantially eliminating basedrag by increasing the rearward pressures exerted by reaction gases generated by an internally carried pyrotechnic device.
to Examples of such baste-bleed projectiles are described in US patent numbers 3,886,009 (Puchalski), 4,003,313 (Puchalski) and 3,988,990 (MacDonald Jnr. and Tietz) and in UK patent number 1,507,865 (Gunners and Heligren). These base-bleed patents variously describe: improved pyrotechnic compositions for reducing projectile drag; improved nozzle arrangements for 15 the base-bleed exhaust; optimising the relationship between propellant grain size and gas outlet nozzle area; controlling the rate of discharge of the propellant gas; and, reducing base-bleed velocities.
These known base-bleed solutions to the base-drag problem have disadvantages. The need to provide a pyrotechnic and a means of ignition of so that pyrotechnic for base-drag reduction adds weight and complexity to the projectile. Providing an additional pyrotechnic adjacent high explosive material in the body of the shell requires careful design so as to avoid unwanted premature detonations. Moreover, in order to withstand the high mechanical stresses and strains induced in the gas generating propellant the configuration 25 and characteristics of the propellant used must be carefully designed. It is also difficult to design ignition means for the propellant which ensures ejection of mass flow precisely when the projectile exits the launching gun's muzzle, which is necessary since aerodynamic drag is highest during the first part of the projectile's trajectory. Using the high temperature combustion gases in the gun So barrel for such ignition also is not reliable since ignition often will be extinguished due to the steep pressure drop in the combustion chamber of the
- 3 base-drag reduction unit when the projectile leaves the gun muzzle. Hence sustaining igniting systems are necessary.
Despite the above disadvantages base-bleed solutions to the base-drag problem have been pursued mainly because they offer a means of reducing 5 after body drag of a projectile without the need to effect changes in the basic shape of the projectile's body. The need to preserve the basic shape of the projectile body has been seen to be a constraint on the design of such drag reduction units because of the overall requirement to match the shape of the body to the design of the gun barrel. Furthermore the bluff end of the projectile to is dictated by the need for cooperation between the projectileand its launching cartridge or bag charge.
It is an object of our invention to provide an alternative additional solution to base-bleed drag reduction devices and to approach the problem of base-drag from a hitherto unexplored viewpoint.
s According to the present in one aspect thereof a base-drag reduction device for a projectile comprises a deployable fluid-dynamic surface adapted for storage in a non-deployed state substantially within an aft bluff end of the projectile and a deployment device actuatable in response to the launching of the projectile to deploy the deployable fluid-dynamic surface to a deployed state no in which it complements the fluid-dynamic shape of a forward end of the projectile and together they form a continuous aerodynamic shape having reduced base-drag.
Although the applications of the invention described in this specification
all relate to aerodynamic projectiles, it will be appreciated that the invention could be applied to appropriate underwater projectiles to reduce hydrodynamic drag. Hence the deployable fluid-dynamic surface could be an aerodynamic surface or a hydrodynamic surface depending on the application concerned.
The deployable fluid-dynamic surface may be substantially conical in shape having base dimensions corresponding to the dimensions of the aft bluff 30 end of the projectile and deployable such that in use the axis of rotation of the
- 4 surface of the cone is an extension of the longitudinal axis of the projectile and its base is adjacent the aft end of the projectile.
The deployable fluid-dynamic surface may comprise a plurality of telescopically interconnected elements which may be collapsed to minimise 5 their longitudinal length in the non deployed state and, when deployed by the deployment device, may be expanded telescopically to form in the deployed state the required fluid-dynamic shape.
The deployment device may comprise a plurality of telescopically interconnected rings the surfaces of which, when expanded telescopically, form to a conical surface, or piece-wise stepped conical surface.
It will be appreciated that it is preferable for the base-drag reduction devices to be self contained units which may be manufactured and supplied independently of the manufacture and supply of the projectiles themselves.
They may be supplied with different dimensions to suit different calibres of s projectiles. They may be designed to be interchangeable with conventional base-bleed drag reduction units. The fluid-dynamic surfaces deployed may be of different shapes so that selected range enhancement may be given to each projectile. According to the present invention in a further aspect thereof a projectile 20 includes any of the drag reduction devices mentioned above.
An embodiment of the invention will now be described by way of example only and with reference to the following drawings of which: Figure 1 is a longitudinal section of the aft part of a gun projectile, round of ammunition or shell showing a base-drag reduction device according to the 2 invention in a first, non-deployed, position, Figure 2 is a longitudinal section through the rear of the shell shown in Figure 1 showing the base-drag reduction device in a second, deployed, position,
Figure 3a is a perspective view of a shell incorporating the non-deployed base-drag reduction device as shown in Figure 1, in flight shortly after firing, and Figure 3b shows the shell shown in Figure 3a moments later with the 5 base-drag reduction device deploying as shown in Figure 2.
In the drawings, for ease of reference, common elements have been indicated by the same reference numerals. In Figure 1 a base-drag reduction device shown generally at 1 comprises a cup-shaped cylindrical casing 2 adapted for location within a corresponding cylindrical bore 3 in a solid steel end to 4 of an otherwise conventional round of ammunition or shell indicated generally at 5. The shell is packed with explosive within a cavity 6 which is detonated on impact or by the action of a proximity fuse (not shown). The front end of the shell 5 is of a conventional shape and construction as shown in Figures 3a and 3b. 15 The casing 2 of the drag reduction device 1 is bonded into the bore 3. In an alternative arrangement it may be located therein by means of a screw thread on its outer surface co-operating with a corresponding thread in the bore 3, or, location by means of a split ring fixing the unit to the internal bore at the rear of the projectile. The latter arrangements are particularly advantageous 20 since this enables the drag reduction devices to be manufactured and supplied independently of the shells to which they may be assembled during a final stage of production.
The drag reduction device 1 further comprises a collapsible conical unit 7 comprising a plurality of concentric rings 8 each slidably engaged with its 25 neighbour and increasing in size in direct proportion to their diameter. The outermost ring 8' has a flange 8" extending in a radially outward direction and engaging with an inner surface of a fixed retaining ring 9 secured to an inner surface of the bore 3. The outermost ring is thus constrained in its fore and aft movement by the closed end of the casing 2 and the fixed retaining ring 9 So respectively.
- 6 The outer ring 8' has a radially inwardly directed flange 8"' at its outer end which slidably engages with the outer surface of the next innermost ring 8.
Each successive ring in the concentric set has similar radially outwardly extending flanges at their forward ends and radially inwardly extending flanges 5 at their aft ends, each said flange being slidably engaged with the neighbouring outer and inner ring surfaces respectively.
The innermost ring 8, of smallest diameter, is closed at its aft end 20.
The closed end 20 of the innermost ring 8 has a central bore 21 through which extends a shaft 11 centrally located on a cover plate 12 from which it extends to perpendicularly. The shaft 11 has a diametrical transverse bore extending through it at its innermost end for receiving a locking shear pin 15. A helical spring 13 surrounds the shaft 11 and extends from the closed end 20 of the innermost ring 8 to the inner surface of the closed end of the casing 2. A bush 14 having a central bore 22 for receiving the shaft 11 is secured to the inner surface of the closed end of the casing 2 and its outer surface acts as a guide and centralising element for the spring 13.
The inner surface of the cover plate 12 engages with all the radially inwardly directed flanges of the rings 8 and, in a non-deployed position of the drag reduction device, it aligns all the rings 8 and partially compresses the So spring 13. In this compressed position the shaft 11 extends through the casing 2 and bush 14 and the whole assembly is locked into position by means of the shear pin 15 which is passed through the bore 22 in the end of the shaft 11.
To deploy the drag reduction device the cover plate 12 is jettisoned, in a manner to be described later, so that the spring 13 extends and urges the 25 innermost ring 8 rearwardly of the shell 5 by a distance equivalent to the length of the extended spring. As the innermost ring moves aft axially its outwardly extending flange slides over the surface of the adjacent ring until it engages with the inwardly extending flange of that neighbouring ring. The two rings are then constrained to move aft axially together until the outwardly extending 30 flange of the neighbouring ring engages with the inwardly extending flange of the next neighbouring ring and so on. The rings 8 are thus all moved axially
- 7 rearwardly of the shell by distances inversely proportional to their diameters.
Deployment of the drag reduction device is arrested when the inwardly extending flange 8"' of the outermost, fixed, ring 8' engages with the outwardly extending flange of the next innermost ring. In this deployed position, shown in Figure 2, the outer surfaces of the deployed concentric rings form a conical extension 7 of the shell body 4.
It will be noted from Figure 1 that in the non-deployed position of the drag reduction device the cover plate 12 is not in contact with the rear of the shell or the casing 2 of the drag reducing device 1. A small annular gap 16 between Jo cover plate and casing is deliberately provided when the cover plate is locked to the casing 2 by means of the pin 15. The reason for this is explained below.
In operation the shell 5 and its propellant charge - which may be cased or separate - (not shown) are loaded into the breach of a field or Naval gun (not
shown) with the drag reduction element secured at the aft end 4 in the non-
b deployed position. When the charge is ignited by the firing mechanism the cover plate 12 and its shaft 11 is initially propelled in an axially forward direction against the resilience of the spring 13, closing the gap 16 and breaking the securing shear pin 15. Alternatively, It may be that shearing of the retaining pin 15 is achieved by central deformation of the cover plate 12 or by rotational 20 forces.
The whole shell then emerges from the barrel of the gun (not shown) and begins its trajectory as shown in Figure 3a with the drag reduction device still held in its non-deployed position by the force of the propellant charge. As the shell continues to move along its trajectory the pressure of the propellant 25 charge on the cover plate 12 reduces and the spring 13 is able to extend. The cover plate 12 is no longer restrained from axial movement by the pin 15 and is moved axially rearwardly of the shell and is discarded in flight as shown in Figure 3b. The rings 8 of the drag reduction device are fully deployed by the extending spring 13. Their combined conical surface 7 at the rear of the shell 30 reduces the aerodynamic drag of the shell for all of the flight duration. The range achieved by the shell is thus significantly greater than would have been the case had the drag reduction device not been fitted.
- 8 It will now be appreciated that, in comparison to base-bleed devices for achieving base-drag reduction, our drag reduction devices occupy less room in the projectile and are relatively simple, safe, mechanical devices, with an expected reduced cost of manufacture.
Many modifications to and variations of the embodiment of our invention described above will now suggest themselves to those skilled in the art. For example the number of rings forming the deployable aerodynamic cone could be reduced. We believe as little as three rings would be sufficient to give significant drag reduction despite the relatively crude tapering of the o aerodynamic surface that would result.
The deployment mechanism need not comprise a helical spring and shear pin; gas actuation is possible. The aerodynamic cone shape could be formed by the surface of a helical coil spring which in the non-deployed state is compressed to a concentric coiled state held in place by a release mechanism actuated pyrotechnically or electro-mechanically.
The aerodynamic surface need not be an expanding mechanical device but could be pre-formed and retained wholly within the projectile body and extended rearward longitudinally by a suitable actuator after firing. However, an advantage of the expanding devices we have described is that they take up little so room in the projectile thus enabling an optimum amount of explosive to be carried. The invention could be applied to certain air dropped stores such as song-buoys, or to deployable towed decoys. Where such stores or decoys are required to be stored before use in a limited space within the aircraft carrying 2s them, they may be collapsed to bluff-ended cylinders to reduce their lengths.
On deployment, when an optimum aerodynamic profile is needed to enhance accuracy of delivery or to prevent tumbling, aerodynamic surfaces may be deployed substantially in the manner according to our invention.
Claims (8)
1. A base-drag reduction device for a projectile comprises a deployable fluid-dynamic surface adapted for storage in a non-deployed state substantially within an aft bluff end of the projectile and a deployment device actuatable in response to the launching of the projectile to deploy the deployable fluid-dynamic surface to a deployed state in which it complements the fluid-dynamic shape of a forward end of the projectile and together they form a continuous fluid-dynamic shape having reduced base-drag. to
2. A base-drag reduction device as claimed in claim 1 and wherein the deployable fluid-dynamic surface is substantially conical in shape having base dimensions corresponding to the dimensions of the aft bluff end of the projectile and deployable such that in use the axis of rotation of the surface of the cone is an extension of the longitudinal axis of the projectile and its base is adjacent the aft end of the projectile.
3. A base-drag reduction device as claimed in claim 1 or claim 2 and wherein the deployable fluid-dynamic surface comprises a plurality of telescopically interconnected elements which may be collapsed to minimise their longitudinal length in the non deployed state and, when so deployed by the deployment device, may be expanded telescopically to form in the deployed state the required fluid-dynamic shape.
4. A base-drag reduction device as claimed in claim 3 and wherein the deployable fluid-dynamic surface comprises a plurality of telescopically interconnected rings the surfaces of which, when expanded telescopically, form a conical surface.
5. A base-drag reduction device as claimed in any previous claim and wherein the deployment device comprises a resilient member interconnecting, in use, the deployable fluid-dynamic surface and the projectile, the resilient member being releasably compressed to maintain so the surface in the non deployed state and when released extends to maintain the surface in the deployed state.
- 10
6. A base-drag reduction device substantially as hereinbefore described with reference to the accompanying drawings.
7. A projectile including a base-drag reduction device according to any previous claim.
8. An airborne device released from an aircraft that requires to be compact whilst in storage (on the aircraft) but which deploys a drag reducing device when released or propelled from the aircraft.
....CLME:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0220444A GB2394029A (en) | 2002-09-03 | 2002-09-03 | Drag reduction devices for projectiles and the like |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0220444A GB2394029A (en) | 2002-09-03 | 2002-09-03 | Drag reduction devices for projectiles and the like |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB0220444D0 GB0220444D0 (en) | 2003-01-29 |
| GB2394029A true GB2394029A (en) | 2004-04-14 |
Family
ID=9943417
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB0220444A Withdrawn GB2394029A (en) | 2002-09-03 | 2002-09-03 | Drag reduction devices for projectiles and the like |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2394029A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110024549A1 (en) * | 2009-07-31 | 2011-02-03 | Raytheon Company, General Dynamics Ordnance and Tactical Systems (OTS) | Deployable fairing and method for reducing aerodynamic drag on a gun-launched artillery shell |
| US7997205B2 (en) * | 2009-05-08 | 2011-08-16 | Raytheon Company | Base drag reduction fairing |
| RU2535379C1 (en) * | 2013-06-18 | 2014-12-10 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Тульский государственный университет" (ТулГУ) | Device of transformation of stern compartments of artillery projectile |
| US10184762B2 (en) * | 2015-12-01 | 2019-01-22 | Raytheon Company | Base drag reduction fairing using shape memory materials |
| WO2023192694A1 (en) * | 2022-03-28 | 2023-10-05 | Raytheon Company | Extended range projectile and method for propelling an extended range projectile |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1817377A (en) * | 1928-08-15 | 1931-08-04 | James Roy Walter | Projectile |
| US2297130A (en) * | 1940-08-13 | 1942-09-29 | Raymond E Bomar | Drag preventing means for projectiles |
| GB2181823A (en) * | 1985-10-08 | 1987-04-29 | British Aerospace | Projectiles |
| US4674706A (en) * | 1986-02-21 | 1987-06-23 | Hall Robert C | Projectile with an extendable boattail |
| EP0296735A2 (en) * | 1987-06-26 | 1988-12-28 | Hughes Aircraft Company | Splitter plates for alleviation of missile hook drag |
| DE4010631A1 (en) * | 1990-04-03 | 1991-10-10 | Diehl Gmbh & Co | Subsidiary missile for dispenser unit - has extending mechanism at tail to reduce flow resistance |
| WO2001035046A1 (en) * | 1999-11-10 | 2001-05-17 | Bofors Defence Ab | Method and design for increasing the firing range of artillery shells |
-
2002
- 2002-09-03 GB GB0220444A patent/GB2394029A/en not_active Withdrawn
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1817377A (en) * | 1928-08-15 | 1931-08-04 | James Roy Walter | Projectile |
| US2297130A (en) * | 1940-08-13 | 1942-09-29 | Raymond E Bomar | Drag preventing means for projectiles |
| GB2181823A (en) * | 1985-10-08 | 1987-04-29 | British Aerospace | Projectiles |
| US4674706A (en) * | 1986-02-21 | 1987-06-23 | Hall Robert C | Projectile with an extendable boattail |
| EP0296735A2 (en) * | 1987-06-26 | 1988-12-28 | Hughes Aircraft Company | Splitter plates for alleviation of missile hook drag |
| DE4010631A1 (en) * | 1990-04-03 | 1991-10-10 | Diehl Gmbh & Co | Subsidiary missile for dispenser unit - has extending mechanism at tail to reduce flow resistance |
| WO2001035046A1 (en) * | 1999-11-10 | 2001-05-17 | Bofors Defence Ab | Method and design for increasing the firing range of artillery shells |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7997205B2 (en) * | 2009-05-08 | 2011-08-16 | Raytheon Company | Base drag reduction fairing |
| US20110024549A1 (en) * | 2009-07-31 | 2011-02-03 | Raytheon Company, General Dynamics Ordnance and Tactical Systems (OTS) | Deployable fairing and method for reducing aerodynamic drag on a gun-launched artillery shell |
| WO2011014889A1 (en) * | 2009-07-31 | 2011-02-03 | General Dynamics Ordnance And Tactical Systems, Inc. | Deployable boat-tail device for use on projectiles |
| EP2459957A1 (en) * | 2009-07-31 | 2012-06-06 | General Dynamics Ordnance and Tactical Systems, Inc. | Deployable boat-tail device for use on projectiles |
| US8312813B2 (en) * | 2009-07-31 | 2012-11-20 | Raytheon Company | Deployable fairing and method for reducing aerodynamic drag on a gun-launched artillery shell |
| EP2459957A4 (en) * | 2009-07-31 | 2012-12-19 | Gen Dynamics Ordnance & Tactic | Deployable boat-tail device for use on projectiles |
| RU2535379C1 (en) * | 2013-06-18 | 2014-12-10 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Тульский государственный университет" (ТулГУ) | Device of transformation of stern compartments of artillery projectile |
| US10184762B2 (en) * | 2015-12-01 | 2019-01-22 | Raytheon Company | Base drag reduction fairing using shape memory materials |
| WO2023192694A1 (en) * | 2022-03-28 | 2023-10-05 | Raytheon Company | Extended range projectile and method for propelling an extended range projectile |
| US11781842B1 (en) | 2022-03-28 | 2023-10-10 | Raytheon Company | Extended range projectile and method for propelling an extended range projectile |
Also Published As
| Publication number | Publication date |
|---|---|
| GB0220444D0 (en) | 2003-01-29 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |