AU2014321144B2

AU2014321144B2 - Burn rate modifier

Info

Publication number: AU2014321144B2
Application number: AU2014321144A
Authority: AU
Inventors: Ashley Jones; Garry WARRENDER
Original assignee: Thales Australia Ltd
Current assignee: Thales Australia Ltd
Priority date: 2013-09-12
Filing date: 2014-09-11
Publication date: 2018-06-28
Anticipated expiration: 2034-09-11
Also published as: CA2922845C; EP3044190A1; AU2014321144A1; CA2922845A1; EP3044190A4; US20160221889A1; WO2015035458A1

Abstract

The invention relates generally to burn rate modifiers and propellants comprising a burn rate modifier. The Invention also relates to methods of producing a propellant comprising a burn rate modifier as well as an ammunition cartridge comprising the propellant. The bum rate modifier comprises a compound of formula 1 and the propellant comprises a compound of formula 1 and an energetic material.

Description

The invention relates generally to bum rate modifiers and propellants comprising a bum rate modifier. The Invention also relates to methods of producing a propellant comprising a bum rate modifier as well as an ammunition cartridge comprising the propellant. The bum rate modifier comprises a compound of formula 1 and the propellant comprises a compound of formula 1 and an energetic material.

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BURN RATE MODIFIER

Field

The Invention relates generally to burn rate modifiers and propellants comprising a burn rate modifier. The invention also relates to methods of producing a propellant comprising a burn rate modifier as well as an ammunition cartridge comprising the propellant.

Background

Propellant performance is determined from its ability to convert chemical energy lg into mechanical energy through the evolution of heat and gases that apply pressure to the base of a projectile moving it down the bore of a barrel. Many factors influence this process. Chemical composition is one important characteristic and another is grain morphology (shape and size) which has a profound effect on the burning rate. To arrive at an optimised propellant design it must be understood that the materials,

i.5 processing conditions, physical properties and chemical properties are all interlinked to determine propellant performance. The goal is to achieve efficient combustion with optimised loadability to deliver improved ballistic performance. In addition, other aspects such as improving shelf life of the propellant or ensuring ballistic consistency over temperature extremes are also important. It is also recognized that new propellant formulations and production processes are required in order to improve efficiency and meet more stringent safety, toxicity and environmental impact requirements.

To improve propellant performance, and to prevent dangerously high pressure build up, a burn deterrent (or burn rate modifier) is typically added to the propellant to regulate the burn rate in the initial part of the ballistic process, This Is typically achieved ’5 by coating a chemical onto a propellant grain. The chemical can penetrate to some extent into the grain matrix and acts to slow the burning reaction (by interrupting the chain reaction of burning) or the chemical is cooler burning. Burn deterrents that function by interrupting the chain reaction of burning do so by stabilising free radicals. This stabilisation extends the lifetime of the radicals, slows the rate of the radical bo processes and subsequently, there is less, or slower, combustion.

An example of a free radical stabilising burn deterrent is dinitrotoluene (DNT).

DNT is a good burn deterrent because it is stable over long periods and is chemically compatible with propellants such as nitrocellulose which Is the major energetic component of most small arms propellants. However, it is highly toxic and a suspected <5 carcinogen which makes it a chemical of concern. Recent legislation (such as

Registration, Evaluation, Authorisation and Restriction of Chemicals (REACH) under the European Union) has resulted in the use of DNT being highly regulated with the

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PCT/AU2014/000903 potential for DNT to be banned in Europe. Due to its characteristics, DMT has associated environmental problems In that it builds up in and around factory buildings, migrates very slowly Into the soil and breaks down slowly.

Other currently available burn rate modifiers, such as dibutyiphthaiate (DBP), are also on the substance of concern list and are likely to be banned, it is anticipated that materials such as DNT and DBP will also have tighter restriction applied as other countries adopt more stringent safety and environmental regulations.

There therefore exists a need for alternative burn deterrents to DNT and other burn rate modifiers currently in use, o Summary

Accordingly, in a first aspect of the present invention, there Is provided a burn rate modifier comprising a compound of formula 1

wherein

R^! is selected from the group consisting of -H, -C^aikyi, -OC-Maikyl, -NH₂, -NHCi^alkyl ?o and-N{Ci.₄alkyl)2: and

R^s is selected from the group consisting of -H, -C^aikyl and -CZ-CQC^aikyl.

The present applicant has conducted considerable research and development over an extensive period of time to develop a new burn rate modifier having burn rate modification properties making it a suitable substitute for DNT in propellants for <s ammunition. The applicant has developed this new burn rate modifier based on 3ethoxy-4-hydroxybenzaidehyde, and derivatives thereof within formula 1. The applicant has found that this new burn rate modifier has burn rate modification properties just as good as DNT, but without the drawbacks of toxicity and carcinogenicity. In fact, the new burn rate modifier has surprisingly better burn rate jo modification properties than even the industry-preferred DNT, making it suitable for use in propellants and ammunition cartridges.

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-3According to a second aspect, there is also provided the use of the compound of formula 1 as a burn rate modifier.

According to a third aspect, there is provided a compound of formula 1 for use as a burn rate modifier.

In some embodiments, the compound of formula 1 Is 3-ethoxy-4hydroxybenzaidehyde, Although this compound is preferred, it is appreciated that closely structurally and physical property-related compounds may also provide further alternative burn rate modifiers to DNT.

According to a fourth aspect, there is provided a propellant comprising an energetic material; and a com pound of formula 1

wherein

R¹ is selected from the group consisting of-H, -C^alkyl, -OC_Malkyl, -NH₂, -NHC^alkyl 15 and-N{C_Malky!)₂; and

R² is selected from the group consisting of -H, -Ci.«alkyl and -€(=O)C_t.₄alky!.

in a fifth aspect, there is provided an ammunition cartridge comprising the propellant according to the second aspect.

The ammunition cartridge typically comprises a casing, the propellant described / ο above, a primer and a projectile.

According to a sixth aspect, there Is provided a method of preparing a propellant, comprising coating granules of an energetic material with a compound of formula 1

wherein

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R^? is selected from the group consisting of -H, -C^alkyl, -OCMalkyl, -NH₂, -MHCi.₄alkyl and -N(Ci.₄alkyl);:; and

R²'is selected from the group consisting of -H, -Cs^alkyl and -C(=0)Ci.4alkyi.

These aspects are described more fully in the detailed description below.

Brief Descript ion of the Drawings

The invention will be described in further detail, by way of example only, with reference to the following Figures;

Figure 1 is a schematic illustration showing the composition of a propellant according to one embodiment of the invention.

l o Figure 2 is a graph showing ballistic comparison of variously deterred propellants with a compound of formula 1 fired from a ,300 Winchester Magnum proof barrel.

Figure 3 Is a graph showing a ballistic comparison of propellants deterred with DNT and a compound of formula 1 fired from a .308 Winchester proof barrel.

i.5 Figure 4 Is a graph showing a ballistic comparison of a typical commercial propellant deterred with DMT when fired from a ,50 calibre proof barrel and a small grain propellant deterred with a compound of formula 1.

Figure 5 is a graph showing the coating efficiency trend for compounds of formula 1 when coated Onto a single base propellant granule in a laboratory scale

-o sweetie barrel.

Detailed Description

The invention relates generally to burn rate modifiers and propellants comprising a burn rate modifier. The Invention also relates to methods of producing a propellant comprising a burn rate modifier as well as an ammunition cartridge

L5 comprising the propellant, in the following, we have described features of the method and the burn rate modifier and propellant. All features described below apply independently to the methods and the products of the invention.

Compounds bo The present invention Involves the use of a compound of formula 1

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wherein

R¹ is selected from the group consisting of -H, -CM^Ikyl, -OC_Malkyi, -NH_2s -NHC^talkyi and -N(C^alkyl)₂; and

R² is selected from the group consisting of ~H, -C^alkyl and -Ci'^OjCi.^aikyl.

in some embodiments R¹ is selected from the group consisting of -H, -C^alkyl and -OCMalkyl. In other embodiments, R¹ is selected from the group consisting of-H and -Chalky!. In a particularly preferred embodiment, R^! is -H,

In some embodiments, R² is selected from the group consisting of -H and -C₄. o ₄alkyl. In other embodiments R² is -Cw^lkyl. In particularly preferred embodiments, R² is “ethyl.

The substituent OR² may be in any position around the aromatic ring. For example, OR² may be in the ortho, meta or para position. In some embodiments, OR²is in the meta position. In a particularly preferred embodiment, R^s is -ethyl and GR² is in the meta position.

The substituent OH may be in any position around the aromatic ring. For example, the OH may be in the ortho, meta or para position. In a particularly preferred embodiment, the OH is in the para position.

The term C^alkyl refers to a branched or unbranched alkyl group having from io one to four carbon atoms inclusive. Examples of Ci^alkyi groups include methyl, ethyl, π-propyl, isopropyl, n-butyl, isobutyl, sec-butyl and tert-butyl. This definition applies to references to C-i^aikyl alone or as part of a substituent such as ~0(Ci4alkyl), ₄alkyl_f or ”N{Ci.₄alkyl)₂.

The compound of formula 1 functions as a burn rate modifier, The burn rate <5 modifier may specifically be a bum rate deterrent. The burn rate modifier or burn rate deterrent may alternatively be referred to as a burn deterrent.

The compound of formula 1 preferably has a melting point of about 50 to about 90°C. For example, the melting point may be about 55 to about 85°C, such as about 60 to about 80°C, or about 65 to about 75°C, In some embodiments, the compound of io formula 1 has a melting point of af least about SOX. For example, the melting point may be at least about 60°C, such as af least about 65°C, or at least about 70°C.

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- 6 in some embodiments, the compound of formuia 1 is 3-ethoxy-4hydroxybenzaldehyde.

Although this compound is preferred, it is appreciated that closely structurally arsd physical property-related compounds may also perform as per 3-ethoxy-4~ hyd roxy benza ide h yd e.

Tests were conducted by the applicant demonstrating the efficacy of 3-ethoxy4-hydrcxybenzaidehyde as a burn rate modifier. The tests showed that 3-ethoxy-4o hyd roxy benzaldehyde has surprisingly better burn rate modification properties than even the industry-preferred DNT, but without the drawbacks of toxicity and carcinogenicity. In particular, 3-ethoxy-4-hydroxybenzaldehyde enhances small grain propellant performance to the point where ballistic performance of the small grain is similar to a significantly larger granule that is coated with DNT. This enables more s propellant to be loaded into a cartridge case, resulting in improved performance. The application of smaller grains for larger loads improves the efficiency of burning of the overall load, meaning less wastage of propellant, less flash from the muzzle and cleaner burning propellant loads a desirable outcome for military ammunition. Previous grain formulations reliant on DNT as the burn rate modifier could not deliver ; o these outcomes simultaneously.

Energetic material

The propellant of the present invention comprises an energetic material. The term energetic material includes any material which can be burned to generate a propellant gas to propel a projectile.

in some embodiments, the energetic material is selected from the group consisting of black powder, ammonium perchlorate, hexogen, butanetrioltrinilrate, ethyleneglycol dintrate, diethyieneglycoi dinitrate, erithritol tetranitrate, octogen, hexanitroisowurtzitane, metriol trinitrate, N-Methyinitramine, pentaerythritoi tetranitrate, fetranltrobenzolamine, trinitrotoluene, nitroglcerine, nitrocellulose, mannitol hexanitrate, triethyleneglycol dinitrate, guanidine, nitroguanidine, 3-nitro-1,2,4-triazoi-5-one,

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ammonium nitrate, propanediol dinitrate, hexamine, 5-aminotetrazole, methyltetrazole, phenyltetrazole, poiygiycidylnitrate, polygiycidyfazide, poly[3-niiratomethyl-3methyloxitane], poiy[3-azidomethyi-3~methyioxitanej, poiy[3,3-bis(azidomethyi)oxitane], nitrated cyciodextrin polymers, poly glyeidySnitrate, and combinations thereof.

In some specific embodiments, the energetic material is selected from the group consisting of nitroglycerin, nitrocellulose and combinations thereof.

in some embodiments, the propellant comprises a single energetic material. For example, the propellant may only comprise nitrocellulose. In such circumstances, the energetic material may be referred to as “single base and the propellant may be lo referred to as “a single base propellant”. In other embodiments, the propellant may comprise two energetic materials. For example, the propellant may comprise nitrocellulose and nitroglycerin. In such cases, the energetic material may be referred to as “double base” and the propellant may be referred to as “a double base propellant⁹. In still other embodiments, the propellant may comprise more than two ls energetic materials. For example, the propellant may comprise nitrocellulose.

nifroquanidine and nitroglycerin. In such circumstances, the energetic material may be referred to as “multiple base” and the propellant may be referred to as “a multiple base propellant”, in one embodiment, the energetic material is nitrocellulose.

? o The energetic material may be in any form that is suitable for incorporation into an ammunition cartridge for a firearm.

In some embodiments, the energetic material is in the form of granules. The term “granule” may also be referred to as “kemei” or “pellet”.

The granules energetic material may be prepared by any method known in the ’5 art. For example, a slurry or dough of energetic material may be extruded, or energetic material in particulate form may be compressed info a granule of energetic material. In another embodiment, particulates of energetic material may be coalesced and shaped info agglomerates by pumping a slurry through shaping tubes, in some embodiments, the agglomerates may be substantially spherical in shape. The agglomerates may be ?o referred to as particles.

In one embodiment, the energetic, material is prepared by extruding a slurry or dough of energetic material to form an extrudate and granulating the extrudate. The term “granulating” refers to the process of dividing, or cutting, an extrudate into granules. In some embodiments, the slurry or dough of energetic material Is extruded vs to form an extrudate cord and the extrudate cord is cut to the desired length to form granules. The granules may be of any size suitable for use in ammunition.

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-8As a consequence of the processing steps described above, the granules may also be referred to as agglomerates, grains or particies.

The grannies can be of any shape. In some embodiments, the granules have an axial dimension with a consistent cross-section. For example, the granule may have a substantially circular cross-section or the cross-section may be elliptical or any other similar shape, in some embodiments the granules are cylindrical in shape.

The granules may be of any size suitable for use In ammunition, in some embodiments, the granules are about 0.1 to about 25mm in length. For example, the granules may be about 0.3 to about 20mm in length, such as about 0.5 to about 12mm lg In length, or about 0.7 to about 5mm in length, or about 1 to about 2mm in length.

In some embodiments, the granules have a diameter of about 0,1 to about 20mm. For example, the granules may have a diameter of about 0.2 to about 15 mm, such as about 0.4 to about 12mm, or about 0.5 to about 10mm, or about 0.6 to about 5mm, or about 0.7 to about 1mm,

i.5 The granules may have a greater length than diameter. In these embodiments, the granules may be referred to as sticks. In some embodiments, the length of the sticks may be about 6 to about 14mm, such as about 8 to about 12mm. In some embodiments, the diameter of the sticks may be about 0.6 to about 1.,2mm, such as about 0.7 to about 1mm.

< o After granulation, the granules are dried during which they may contract slightly.

This contraction can be taken info account when granulating the granules or compressing the particulates of energetic material. The contracted granules may be of any size suitable to be used in ammunition. In some embodiments, the granules are about 0.1 to about 25mm in length. For example, the granules may be about 0.3 to ’5 about 20mm in length, such as about 0.5 to about 12mm in length, or about 0,7 to about 5mm in length, or about 1 to about 2mm In length.

When the contracted granules are sticks, the length of the sticks may be about 6 to about 14mm, such as about 8 to about 12mm. In some embodiments, the diameter of the sticks may be about 0.6 to about 1.2mm, such as about 0.7 to about /0 imm.

In some embodiments, the granules have a diameter of about 0.1 to about 20mm. For example, the granules may have a diameter of about 0,2 to about 15mm, such as about 0.4 to about 12mm, or about 0.5 to about 10mm, or about 0.6 to about 5mm, or about 0,7 to about 1mm, /5 in some embodiments, the granules comprise a perforation to enhance burning rates later in the burning cycle and to make the granules more progressive in burning. Expressed another way, in some embodiments, the granules comprise one or more

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-9perforations, Perforations increase the surface area of the granule and can result in a further moderated burn rate upon application of the compound of formula 1. In some embodiments, the perforations result in further moderated burn rate in the early stages of the ballistic cycle.

The term “perforation” refers to an aperture In the granule. Alternative terms for “perforation are channel, bore and cavity. The perforation may extend ail the way through the granule. In some embodiments, the perforation extends axially through the granule.

The perforation may be of any diameter suitable for the size of the granule, in lg some embodiments, the perforation has a diameter of about 50 to about 1000 pm. For example, the perforation may have a diameter of about 50 to about 700 pm, such as about 50 to about 500 pm, or about 100 to about 300 pm.

There may be more than one perforation in each granule. In some embodiments, there is a single perforation, in other embodiments, there are multiple

i.5 perforations, in one particular embodiment, there is a single central perforation. In other embodiments there are at least 2 perforations, for example, at least 3 perforations, or at least 4 perforations, or at least 5 perforations.

When the energetic material is made by extrusion, the extrudate may be extruded with one or more perforations.

The propellant comprises an energetic material and a compound of formula 1. The energetic material and compound of formula 1 may be combined in anyway. In some embodiments, the compound of formula 1 is in the form of a coating on granules of the energetic material. Therefore, in one embodiment, there Is provided a method of preparing a propellant comprising coating granules of an energetic material with a compound of formula 1.

The propellant may comprise additional layers. Suitable layers include a finishing layer, an ignition layer and/or a layer of a second energetic material, in embodiments where there is a layer of second energetic material, the ? o energetic material that forms the core of the propellant will be referred to as a first energetic material. The layer of second energetic material can be selected from the range of energetic materials described above. The layer of second energetic material is suitably different to the first energetic material.

In embodiments where the propellant comprises an ignition layer, the ignition <5 layer comprises an ignition component. The ignition component may comprise a group

I metal salt of nitrate.

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-10 in embodiments where the propellant comprises a finishing layer, the finishing layer may be in the form of a graphite layer. Surface-graph sting is typically the final finishing step, yet graphiting may be completed prior to or after drying the propellant, in some embodiments, the graphite finishing layer may comprise an Ignition component. Examples of suitable ignition components include one or more group I metal salt of nitrate.

The finishing layer is generally the outermost layer on the propellant. The additional layers may be complete layers around the propellant or they may be partial layers, l o Coating

The coating of the energetic material may be performed by any method known in the art. For example, the granules of energetic material may be immersed in the compound of formula 1, or the compound of formula 1 may be fumble coated or spray coated onto the granules of energetic material. The compound of formula 1 may be is applied as a neat liquid, powder or as a solution.

in some embodiments, the energetic material is coated with the compound of formula 1 in a vessel. Suitable vessels include, but are not limited to, a tumble coaler, granulators, shaping tubes, augers and ribbon blenders based on the half-pipe shape with sigmoidal or helical mixing blades.

> o In some embodiments, the coating is applied to the granules of energetic material in a vessel known in the art as a “sweetie barrel” or ’’tumbler”. This vessel may also be known as a rotating tumbler or a fumble coaler. Such a vessel will be referred to herein as a “tumble coater. In these embodiments, the granules of energetic material are added to the tumble coaler, the tumble coater drum is rotated to cause ’5 tumbling ofthe granules, and then the compound of formula 1 Is added to coat the granules as they tumble. In some embodiments, the compound of formula 1 is added in one portion. In other embodiments, the compound of formula 1 is added portion-wise so that the granules are coated gradually. Heat may be applied as required to warm the ingredients in the tumble coater and melt the compound of formula 1. Heat may be ?o applied by any method known in the art. In some embodiments, steam heating is used. In other embodiments, heating is effected by heat jacketing ofthe vessel. The application of heat enables the compound of formula 1 to coat the granules, and may enhance diffusion of the compound of formula 1 into the surfaces of the propellant granules.

<5 in some embodiments, the granules of energetic material and compound of formula 1 are mixed in a vessel under ambient conditions. Preferably, the vessel is a fumble coater or a ribbon blender. The vessel may be of any size suitable to coat a

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-11 desired quantity of granules. For example, the vessel may be of a size suitable to coat several hundred kilograms of granules per batch, or up to one or more tonnes of granules per batch. The vessel is then closed and heated, for example by adding steam, or through use of a heat jacketed vessel. The heat (steam) softens and melts the compound of formula 1 to enable it to form a coating on granules of energetic material. Any clumps forming are broken up in situ through the process of tumbling and the presence of moisture or solvent. This process is continued until the coated product is produced. Moisture or solvent may be present in sufficient quantity to reduce the stickiness of the grains one to another while the compound of formula 1 is being lg melted onto the grains. In some embodiments the process is continued for up to about 150 minutes (“run time”). For example, the process may be continued for up to about 120 minutes, such as up to about 90 minutes, or up to about 60 minutes, or up to about 30 minutes.

The temperature to which the vessel needs to be heated (and therefore the

i.5 amount of steam that needs to be added) depends upon the temperature required to soften and melt the compound of form ula 1. In some embodiments, the vessel is heated to a temperature of at least about 50°C, For example, the temperature may be at least about 60°C, such as at least about 65°C, or at least about 70‘ C, or at least about 80°C. In some embodiments, the temperature is at least about 85°C, for < o example, at least about 90°C, or at least about 95°C.

The coating of the compound of formula 1 need not stay as a separate outer layer on the surface of the energetic material granule. The compound of formula 1 may diffuse, or penetrate, partly, or entirely, into a surface or sub-surface layer of the energetic material. In such cases, the compound of formula 1 extends from within the ' 5 grain to the surface layer. The compound of formula 1 may be distributed evenly from the surface or may be distributed unevenly within the granules. The compound of formula 1 may be in a band or region of the granule that is largely of uniform size per granule.

If the compound of formula 1 has been applied In a manner such that it diffuses ?o into the energetic material, the compound of formula 1 may come into contact with a number of the propellant components.

The term coating will be understood to refer to all such forms of coating including coating that remains on the surface ofthe granule and coating that has diffused into the surface. In particular, the expression “coating on the surface of the <5 granules includes coating that remains on the surface of the granule and coating that has diffused into the granule.

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Where diffusion of the compound of formula 1 occurs into the granule of energetic material, the layer of diffused compound of formula 1 may be referred to as a deterred band or deterred region. In the following, where we refer to a thickness of a coating, this is the equivalent to the thickness of the deterred band for embodiments where the coating has diffused into the surface of the granule.

The thickness of the coating (i.e, the thickness of the deterred band) may be any thickness which allows the compound of formula 1 to slow the burn rate of the energetic material in an appropriate manner. In some embodiments, the thickness of the coating is about 10 to about 700 pm. For example, the thickness may be about 15 lg to about 500 pm, such as about 20 to 400 pm, or about 50 to 300 pm,

The depth to which the compound of formula 1 diffuses into the granule of energetic material may depend on how long the granule is In contact with the compound, the concentration of the compound being applied, the temperature at which the coating is being performed and/or the; chemical interaction between the propellant

i.5 matrix and the compound. For example, to obtain a thinner deterred band, a rapid initial temperature ramp can be used and/or a shorter run time may be used. To obtain a thicker deterred band, a slower initial temperature ramp and/or a longer run time can be used. Furthermore, changing the propellant matrix composition may change the depth of penetration, and therefore the thickness of the deterred band, under

- o p redeterm i ned q pe ra ti ng cond itio ns.

Additional means of managing diffusion of the compound into the granule are available, including the non-limiting technique of solvation. During solvation, compounds of formula 1 may be dissolved in various organic solvents and applied to the granules as a solution that diffuses into the granules, carrying with it the compound ’5 of formula 1 which is deposited within the granules at a depth that is related to temperature, solubility and the concentration of solution. The solvation techniques include the application to granules of propellant of solutions of compounds of formula 1, solvents to manage the transport of compounds of formula 1 and emulsions of compounds of formula 1.

?o Preferably, the compound of formula 1 is diffused into the granules of energetic material with an exponential concentration profile such that the exponential decay curve approximates the concentration profile, in other words, the concentration of the burn rate modifier is at a maximum some point below the granular surface, and the concentration decreases approximately exponentially as measured at increasing depth <5 of penetration into the deterred region and outward from the deterred region.

The compound of formula 1 is present In the propellant in an amount which is sufficient to retard the burn rate of the outer surface of the granule of energetic material

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-13compared with the burn rate without the presence of the compound, in some embodiments, the compound of formula 1 is present In amounts of from about 0.1 to about 10% by weight of the propellant For example, the compound of formula 1 may be present in an amount of about 0.2 to about 8%, such as about 0.5 to about 6.5%, or about 0,7 to about 6%, Most preferably, the compound of formula 1 Is present in an amount of about 1 to about 5% by weight of the propellant.

The compound of formula 1 may coat the whole surface of the granule. Alternatively, the compound of formula 1 may coat part of the surface of the granule. For example, the compound of formula 1 may coat the outer surface of the granule, or lg the compound of formula 1 may coat the surface of the granule within the perforated region, or the compound of formula 1 may coat both the outer and inner surfaces of the granule.

The application of the compound of formula 1 as a coating does not preclude the inclusion of the compound as a coolant throughout the composition, in some

i.5 embodiments there may be no coating and the compound of formula 1 is dispersed evenly throughout the granule, in this case, the compound of formula 1 can function as a burn rate modifier.

In some embodiments, the propellant may comprise a second layer of a different burn rate modifier. In some embodiments, the second layer may comprise a

- o compound of formula 1 which is different to the compound of formula 1 in the first layer, in other embodiments, the second layer may comprise any burn rate modifier known in the art. Examples of suitable burn rate modifiers include, but are not limited to, dintirotoiuene, Acetyl triethyl citrate, Triethyl citrate, Tri-n-butyl citrate. Tributyl acetyl citrate, Acetyl tri-n-butyl citrate, Acetyl tri-n-hexyl citrate, n-Butyryl tri-n-hexyicitrate, Dt¢5 n-butyl adipate, diisopropyl adipate, Diisobutyl adipate, Diethyihexyl adipate, Nonyl undecyl adipate n-Decyl-n-ocfyi adipate, Di butoxy ethoxy ethyl adipate Dimethyl adipate, Hexyl octyl decyl adipate Diisononyl adipate, Dibutyl phthalate-, Diethyl phthalate, Diamyl phthalate, Nonyiundecyl phthalate, Bis(3,5,5~trimethyihexyi) phthalate, Di-n-propyladipate, Di-n-butyl sebacate, Dioctyl sebacate, Dimethyl ?o sebacate, Diethyl diphenyl urea. Dimethyl diphenyl urea, Di-n-butyl phthalate, Di-nhexyl phthalate, Dinonyl undecyl phthalate, Nonyl undecyl phthalate, Dioetyl terephthalate, Dioctyi isophthaiate, 1,2-Cyclohexane dicartoonic acid diisononylester, Dibutyl maleate, Dinonyl maleate, Diisooctyi maleate, Dibutyl fumarate, Dinonyl fumaraie, Dimethyl sebacate, Dibutyl sebacate, Diisooctyi sebacate, Dibutyl azeiate, Diethylene glycol dibenzoate, Trioctyl trimeliiate, Trioctyl phosphate, Butyl stearate, Methylphenyiurethane, N-methyl-N-phenyiurethane, Ethyl diphenyl carbamate, camphor, gum Arabic, gelatin, rosin, modified rosin esters, resins of dibasic acids and

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PCT/AU2014/000903 alkyl fatty alcohols, polyesters of molecular weight 1500 - 30,000 based on dihydrlc alcohols and dibasic acids, and combinations thereof.

Additives

In some embodiments, the propellant further comprises an additive selected from the group consisting of plasticisers, stabilisers, flash suppressants, barrel-wear ameliorants and combinations thereof.

in some embodiments, the additive is incorporated within the energetic, material granules. In other embodiments, the additive is incorporated with the compound of formula 1. In still other embodiments, the additive may be incorporated within the l o energetic material granules and with the compound of formula 1. Incorporation of the additive within the energetic material granules can be achieved by adding the additive to the slum/ or dough of energetic material, which is then formed into granules.

The term “plasticiser refers to any compound which imparts homogeneity and plasticity to the energetic material. In some embodiments, the plasticiser may be

i.5 selected from the group consisting of diethyl phthalate, camphor, dlbuty I phthalate, di-npropyl adipate, methylphenyl urethane, calcium stearate, butyl stearate, nitroglycerin and combinations thereof.

The term “stabilizer refers to any compound which can be used to stabilize the energetic material. In some embodiments, the stabilizer may be selected from the o group consisting of sodium hydrogen carbonate, calcium carbonate, magnesium oxide akardites, centralites, 2-nitrosodlphenylamlne, diphenylamine, N-methyi-p-nitroaniline and combinations thereof.

The term “flash suppressant”, refers to any compound which can be used to suppress the muzzle flash of a firearm, in some embodiments, the flash suppressant ’5 may be selected from the group consisting of potassium salts of organic acids, potassium sulphate, potassium carbonate, potassium bicarbonate and combinations thereof.

The term barrel-wear ameliorants” refers to any compound which can be used to reduce barrel-wear. In some embodiments, the barrel-wear ameliorant may be bo selected from the group consisting of bismuth, bismuth oxide, bismuth citrate, bismuth subcarbonate, lead, lead carbonate, other salts of lead and bismuth and combinations thereof.

Ammunition in one embodiment, there is provided an ammunition cartridge comprising the <5 propellant. The ammunition cartridge typically comprises a casing, the propellant described above, a primer and a projectile.

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-15 The propellant of the present invention is suitable for use in a wide range of firearms, it is particularly suitable for use in ,22 - ,224 calibre firearms, .243 calibre firearms, .27 calibre firearms, 6mm calibre firearms, 7mm calibre firearms .30 calibre firearms. 8mm calibre firearms, .338 calibre firearms up to .50 calibre firearms and is even suitable for medium to large calibre firearms.

The casing may be made of any material which is tough enough and thick enough to not rupture during burning of the propellant. The casing may be of any size and the size will depend upon the firearm in which the cartridge is to be used. Conventional casing materials and construction Is well known in the art and applies to lg the present application,

The primer, or priming compound, may be comprised of any substance which is capable of producing heat to ignite the propellant. Examples of priming compounds include but are not limited to lead azide (dextrinated), lead styphnate, mercury fulminate and combinations thereof. In some embodiments, the priming compound is

i.5 ASA (aluminium, lead styphnate, lead azide).

The prolectlie may be any object which can be projected from the muzzle of a firearm system (or gun) upon burning of the propellant. Examples of projectiles include, but are not limited to, bullets, shot, pellets, slugs, shells, balls, buckshot, bolts, rockets and cannon balls, in some embodiments, the projectile is selected from the group o consisting of a bullet, pellet, slug and ball.

Advantages

The compounds of formula 1 contain only carbon, hydrogen, oxygen and in some cases nitrogen molecules and do not contain any potentially toxic or hazardous elements such as halogens. The compounds are less toxic than DNT, are compatible ¢5 with energetic materials such as nitrocellulose and are stable over time (both chemically and baliistically), The compounds of formula 1 have burn rate modification properties just as good as DNT, but without the drawbacks of toxicity and carcinogenicity. In fact, the compounds of formula 1 have surprisingly better burn rate modification properties than even the industry-preferred DNT, making them suitable for bo use in propellants and ammunition cartridges.

Examples

The invention will now be described with reference to the following non-limiting Examples.

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The burn rate modifier 3-ethoxy-4-hydroxybenzaldehyde was subjected to comparative tests against DNT. The results of one set of tests are set out in Table 1 above. The comparative test work involved preparing granules of nitrocellulose energetic material having an average length of about 1.4 mm and an average diameter of about 0.7 mm. The granules had a single central perforation of approximately 50 pm diameter. The granules were coated with DNT or 3-ethoxy-4-hydroxybenzaidehyde in the amounts outlined in the Table to form propellant. The test results showed that the propellant oxygen balance for the 3-ethoxy~4-hydroxybenza!dehyde propellant

G was -30.0% compared with -34.0% for the DNT propellant. The test results also showed that the gas at standard temperature and pressure for the 3-ethoxy-4hydroxyhenzaldehyde propellant was 0.93 L/g compared with 0.96 L/g for the DNT propellant and the gas at 2950K for 3-efhoxy-4-hydroxybenzalttehyde propellant was 9.22 L/g compared with 9.47 L/g for the DNT propellant.

These data demonstrate that 3-ethoxy-4-hydroxybenzaldehyde is a good substitute for DNT. In fact, 3-ethoxy-4-hydroxybenzaidehyde can be used in lower amounts than DNT and achieve a similar result.

The propellants were subsequently loaded into cartridges and fired under test conditions in an indoor range measuring case-conformal chamber pressure with o electronic piezometers and projectile velocity with electronic shot-traverse-detection screens connected to an analytical apparatus that processes the raw sensor data for each shot. The ballistic comparisons are seen in Figures 2, 3 and 4.

Figure 1 Is a schematic illustration showing the composition of a propellant according to one embodiment of the invention. The propellant shown in Figure 1 is in the form of a granule having a single, central perforation. The energetic material (1) has been coated in a layer of the burn rate modifier of the invention (3). The propellant may comprise a second layer of a different burn rate modifier (2) or this region may represent more energetic material. In this embodiment, the burn rate modifier is coated on foe outside surface of the granule and the surface of the granuie within the perforated region. The propellant further comprises an Ignition layer (4), which is optionally covered with a surface glaze of graphite, but may contain other materials known to those familiar with the art ~ for example metal salts of nitrate.

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- 17The propellant granule of Figure 1 may be prepared by extruding a dough or slurry of energetic material with a single central perforation to form an extrudate cord, and by then cutting the extrudate cord to the required length. The granule may then be dried during which it may contract slightly. The granule may then be coated in a first layer of burn rate modifier (and optionally a second layer of a different burn rate modifier) and finally coated with the ignition layer.

Figure 2 shows a ballistic comparison, in a ,300 Winchester Magnum proof barrel, of nitrocellulose propellant granules having one perforation (1.5mm long, 0.8mm diameter and 140 micron perforation) and including a coating of 3-ethoxy-4~

LG hydroxybenzaldehyde at various levels (2.8% to 3.9%). The pressure-velocity trends show that additional amounts of 3-ethoxy~4~hydroxybenzaldehyde in the propellant formulations has a marked effect on inferior and exterior ballistics. For example, the more 3-ethoxy-4-hydroxybenzaldehyde used, the lower the pressure in the system to achieve the same projectile velocity. The ammunition build included case and primer of

i.5 Winchester manufacture and the projectile was a 180 grain Sierra hollow point boat tail design.

Figure 3 shows a ballistic comparison, in a .308 Winchester proof barrel, between a DNT-coated: nitrocellulose propellant (6,5% DNT) and a nitrocellulose propellant including a coating of 3-ethoxy-4-hydroxybenzaldehyde at a level of 1.5%, < o The propellants were made from equivalent granules having one perforation (1,5mm long. 0.8mm diameter and 140 micron perforation) and so the similarity of the outcome shows the deterrent efficiency difference between 3-ethoxy-4-hydroxybenzaldehyde as compared to DNT, The ammunition build included case and primer of Winchester manufacture and the projectile was a 168 grain Sierra hollow point boat tail design.

’5 Figure 4 shows a ballistic comparison, in a .50 calibre proof barrel, between

AR2218, a large granule (approximatelyl ,9mm long by 1,4mm diameter and a perforation of 180 microns) coated with about 8% DNT, with a small granule (1,5mm long, 0.8mm diameter and 140 micron perforation) coated with 6.8% 3-ethoxy~4hydroxybenzaldehyde. The Figure shows the much smaller granule was able to bo outperform the larger granule, proving the impressive progressivity gains obtainable through the application of a compound of formula 1. The case and primer were supplied as a unit by Australian Munitions and the projectile was the Australian 855 grain ball (FI).

Figure 5 shows the coating efficiency curve for 3-ethoxy-4<5 hydroxybenzaldehyde (expressed as a percentage) onto single base nitrocellulose propellant granules (approximately 1.5mm by 0,8mm), in a laboratory scale sweetie

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-18 barrel. This graph shows that an increased applied deterrent results in improved coating efficiency.

ft will be appreciated by persons skilled in the art that numerous variations and/or modifications may be made to the Invention as shown in the specific embodiments without departing from the spirit or scope of the invention as broadly described. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive.

The us© of the terms “a” and “an” and “the and similar referents In the context of describing the invention (especially in the context of the following claims) are to be . 0 construed to cover both the singular and the plural, unless otherwise indicated herein or clearly contradicted by context.

in the claims which follow and in the preceding description of the invention, except where the context requires otherwise due to express language or necessary implication, the word “comprise” or variations such as “comprises” or “comprising” is .5 used In an inclusive sense, i.e. to specify the presence of the stated features but not to preclude the presence or addition of further features in various embodiments of the invention.

A propellant comprising:

an energetic material in the form of granules; and a compound of formula 1

2014321144 30 Apr 2018

Claims

00,000 2200 en s'ft«nq 2300 Claims 30 4 wherein R1 is selected from the group consisting of -H, -Ci^alkyl, -OCi-4alkyl, -NH2, NHCi-4alkyl and -N(Ci-4alkyl)2; and R2 is selected from the group consisting of -H, -Ci^alkyl and -C(=O)Ci-4alkyl, and wherein the compound of formula 1 is in the form of a coating on the surface of the granules that has diffused or penetrated partly or entirely into the granules of the energetic material. The propellant according to claim 1, wherein the granules comprise a perforation. The propellant according to any one of claims 1 to 2, wherein the energetic material is selected from the group consisting of carbon black powder, ammonium perchlorate, hexogen, butanetrioltrinitrate, ethyleneglycol dintrate, diethyleneglycol dinitrate, erithritol tetranitrate, octogen, hexanitroisowurtzitane, metriol trinitrate, N-Methylnitramine, pentaerythritol tetranitrate, tetranitrobenzolamine, trinitrotoluene, nitroglcerine, nitrocellulose, mannitol hexanitrate, triethylene glycol dinitrate, guanidine, nitroguanidine, 3-nitro-1,2,4triazol-5-one, ammonium nitrate, propanediol dinitrate, hexamine, 5aminotetrazole, methyltetrazole, phenyltetrazole, polyglycidylnitrate, polyglycidylazide, poly[3-nitratomethyl-3-methyloxitane], poly[3-azidomethyl-3methyloxitane], poly[3,3-bis(azidomethyl)oxitane], nitrated cyclodextrin polymers, polyglycidylnitrate, and combinations thereof. The propellant according to any one of claims 1 to 3, wherein the energetic material is nitrocellulose. 10208753_1 (GHMatters) P94405.AU.1 2014321144 30 Apr 2018 -205. The propellant according to any one of claims 1 to 4, further comprising a graphite layer. 6. Use of a compound of formula 1 °%ar1 xa 7. 8. wherein R1 is selected from the group consisting of -H, -Ci^alkyl, -OCi-4alkyl, -NH2, NHCi-4alkyl and -N(Ci-4alkyl)2; and R2 is selected from the group consisting of -H, -Ci 4alkyl and -C(=O)Ci-4alkyl; as a burn rate modifier. The use according to claim 6, wherein the compound is 3-ethoxy-4hyd roxybe n za Id e h yd e. A method of preparing a propellant, comprising coating granules of an energetic material with a compound of formula 1 so that the compound of formula 1 diffuses or penetrates partly or entirely into the granules of energetic material, wherein the compound of formula 1 is \χ Xa wherein 20 R1 is selected from the group consisting of -H, -Ci 4alkyl, -OCi-4alkyl, -NH2, NHCi-4alkyl and -N(Ci-4alkyl)2; and R2 is selected from the group consisting of -H, -Ci4alkyl and -C(=O)Ci-4alkyl. 9. The method of claim 8, wherein the coating involves applying the compound of formula 1 as a neat liquid or as a solution. 25 10. The method of claim 8 or claim 9, wherein the coating involves the application 10208753_1 (GHMatters) P94405.AU.1 2014321144 30 Apr 2018 -21 of heat to enhance diffusion of the compound of formula 1 into the granules. 11. The method of any one of claims 8 to 10, wherein the granules of energetic material are formed by extruding a slurry of the energetic material to form an extrudate cord and cutting the extrudate cord. 5 12. The method according to claim 11, wherein the energetic material is extruded with a perforation. 13. An ammunition cartridge comprising a propellant according to any one of claims 1 to 5. 14. An ammunition cartridge comprising a casing, a propellant according to any one io of claims 1 to 5, a primer and a projectile. 10208753_1 (GHMatters) P94405.AU.1 WO 2015/035458 PCT/AU2014/000903

-1/3- <4

Chamber Pressure (psi)

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JC3383 «5.083
- 2/3 cr

2400· 2500 280

Projsct::<? Veiccity 'it s^-1!

275)0

2800

CflBWfsw Prsssufe· (MPa)

FIGURE 3

Wtasity (m $-^})

S;

FIGURE 4

WO 2015/035458

PCT/AU2014/000903 ftSeaetifed Deterrent /Appliesi Deterrent ♦ tab sc;;:» coating curve

0.0

2 550,803

E ·§ 40,000
3.0 4.0 SO 0.0

Appteil Deterrent f%wr'« dry propellants

SO

FIGURE 5