Propellant support unit
The propellant support unit addresses the issue of inconsistent propellant distribution in weapon systems by allowing precise and variable loading, enhancing accuracy and efficiency through consistent combustion and reduced waste.
Patent Information
- Authority / Receiving Office
- WO · WO
- Patent Type
- Applications
- Current Assignee / Owner
- BAE SYSTEMS PLC
- Filing Date
- 2025-12-15
- Publication Date
- 2026-07-23
AI Technical Summary
Existing weapon systems provide limited flexibility in propellant amount and distribution, leading to inconsistent firing results due to fixed propellant quantities and inconsistent spacing of combustion charges.
A propellant support unit with a chamber and sub-chambers that allows for precise and variable loading of propellant, enabling consistent and accurate propulsion of projectiles by allowing for a desired distribution and amount of propellant to be loaded into a weapon system.
Enables precise and infinitely variable propellant use, improving accuracy and efficiency by ensuring consistent combustion and reducing waste, while being compatible with existing weapon systems and safer for handling and automated loading.
Smart Images
Figure GB2025052697_23072026_PF_FP_ABST
Abstract
Description
[0001] XA23410 Draft for filing
[0002] - 1 -
[0003] PROPELLANT SUPPORT UNIT
[0004] FIELD
[0005] The present disclosure relates to a propellant support unit.
[0006] In particular, the disclosure is concerned with a propellant support unit for a weapon system.
[0007] BACKGROUND
[0008] Weapon systems, such as artillery weapon systems (for example shown in figure 1) are well known. These are configured to contain a charge containing a propellant which, when ignited, will fire a projectile.
[0009] In some examples the projectile and propellant may be provided in one unit (for example in an ammunition round) prior to being loaded in the weapon. Such systems inherently provide limited flexibility as the amount of propellant is fixed.
[0010] In other examples the projectile and propellant may be loaded separately into the weapon, with the propellant loaded as one or more charges comprising a fixed amount of propellant. Such systems inherently provide limited flexibility as the amount of propellant can only be provided in multiples of each charge. Also, it may not be possible to fix the relative distribution of multiple charges nor provide consistent spacing for combustion to develop, which may lead to inconsistent firing results.
[0011] Hence an arrangement which allows for a precise amount of propellant in a desired distribution to be loaded into a weapon to propel a projectile is highly desirable.
[0012] SUMMARY
[0013] According to the present disclosure there is provided an apparatus, system and methods as set forth in the appended claims. Other features of the invention will be apparent from the dependent claims, and the description which follows.XA23410 Draft for filing
[0014] - 2 -
[0015] Accordingly, there may be provided a propellant support unit (100) for a weapon system (200). The propellant support unit (100) may extend along a propellant support unit axis (102). The propellant support unit (100) may comprise a side wall (104) extending between a first end (106) and a second end (108) along the length L of the propellant support unit (100). The side wall (104) may define a chamber (110). The chamber (110) may be closed at the first end (106) by a first end wall (112). The propellant support unit (100) may comprise an internal wall structure (114). The internal wall structure (114) may extend from the side wall (104) to define a plurality of sub-chambers (116). At least one of the sub-chambers (116) may be configured for containing a propellant (300).
[0016] The chamber (110) may be open at the second end (108).
[0017] The chamber (110) may be closed at the second end (108) by a second end wall (118).
[0018] Each of the sub-chambers (116) may extend from the first end (106) of the propellant support unit (100) to the second end (108) of the propellant support unit (100) in a direction along the propellant support unit axis (102).
[0019] At least some of the sub-chambers (116) may have the same cross-sectional shape and area along their length. Each sub-chamber (116) may have a circular cross-section.
[0020] Each sub-chamber (116) may have a polygonal cross-section.
[0021] At least one of the first end (106) of the propellant support unit (100) or the second end (108) of the propellant support unit (100) may be configured for the passage therethrough of a propellant (300).
[0022] The first end wall (112) may comprise a porous material (120) which closes one or more of the sub-chambers (116).
[0023] The first end wall (112) of the propellant support unit (100) may comprise a valve (122) through which a propellant (300) is deliverable to at least one of the sub-chambers (116).
[0024] The side wall (104) and the first end wall (112) may comprise at least one of paper, cellulose and / or waxed fibre.
[0025] The propellant support unit may comprise a propellant (300). The propellant (300) may be a solid or fluid.XA23410 Draft for filing
[0026] - 3 -
[0027] The propellant (300) may comprise a solid nitro cellulose based, triplebased and / or multi-based propellant. The propellant (300) may comprise a liquid ammonium perchlorate, hydrazine, propylene glycol dinitrate, and / or nitric acid based fuel.
[0028] The propellant support unit (100) may comprise a primer (400).
[0029] The propellant support unit (100) may comprise a stub case (500). The stub case (500) may comprise a base member (502) located on the first end (106) of the propellant support unit (100). The stub case (500) may comprise a support housing (504) which extends from the base member (502) along part of the length of the propellant support unit (100).
[0030] The propellant support unit (100) may define a projectile support chamber (130) which extends from the second end (108) of the propellant support unit (100) at least part of the way to the first end (106) of the propellant support unit (100).
[0031] Accordingly, there may be provided an ammunition round (600) comprising a cartridge case (602), a projectile (604) and a propellant support unit (100). The cartridge case (602) may extend from a base plate (606) to a projectile support feature (608). The projectile (604) may be mounted to the projectile support feature (608). The propellant support unit (100) may be housed within the cartridge case (602) between the base plate (606) and the projectile (604).
[0032] Accordingly, there may be provided a weapon system (200) comprising a barrel (202) with a bore (204) that extends along a barrel axis (206) from a breech (208) to a muzzle (210). The breech (208) may comprise an ammunition loading chamber region (212). The ammunition loading chamber (212) may be configured to receive a propellant support unit (100). The barrel (202) may comprise a location feature (140) configured to engage with the propellant support unit (100) to thereby locate the propellant support unit (100) in place.
[0033] Hence there is provided an arrangement which allows for a precise amount of propellant in a desired distribution to be loaded into a weapon to propel a projectile.XA23410 Draft for filing
[0034] - 4 -
[0035] BRIEF DESCRIPTION OF THE FIGURES
[0036] Embodiments of the invention will now be described by way of example only with reference to the figures, in which:
[0037] Figure 1 shows a known example of an artillery weapon;
[0038] Figure 2 shows an external perspective view of a propellant support unit according to the present disclosure;
[0039] Figure 3 shows an end cross-sectional view of a propellant support unit according to the present disclosure;
[0040] Figure 4 shows a side cross-sectional view of an example of an ammunition round comprising a propellant support unit according to the present disclosure;
[0041] Figure 5 shows side a cross-sectional view illustrating the ammunition round of figure 4 loaded into a barrel of a weapon system;
[0042] Figure 6 shows a side cross-sectional view of an example of a propellant support unit according to the present disclosure with a stub case;
[0043] Figure 7 shows a side cross-sectional view illustrating the propellant support unit of figure 6 loaded into a barrel of a weapon system;
[0044] Figure 8 shows a side cross-sectional view of a further example of a propellant support unit according to the present disclosure with a stub case;
[0045] Figure 9 shows side a cross-sectional view illustrating the propellant support unit of figure 8 loaded into a barrel of a weapon system;
[0046] Figure 10 shows a side cross-sectional view of a propellant support unit according to the present disclosure in combination with a primer and projectile;
[0047] Figure 11 shows a side cross-sectional view illustrating the parts illustrated in figure 10 loaded into a barrel of a weapon system;
[0048] Figure 12 shows an end cross-sectional view of a further example of a propellant support unit according to the present disclosure, loaded into a barrel of a weapon system;
[0049] Figure 13 shows a side cross-sectional view illustrating the propellant support unit of figure 12 loaded into a barrel of a weapon system with a primer and projectile;XA23410 Draft for filing
[0050] - 5 -
[0051] Figure 14 shows a cross-sectional view of a breech of a barrel of a weapon system of the present disclosure; and
[0052] Figure 15 shows a propellant support unit of the present disclosure loaded into the breech shown in figure 14.
[0053] DETAILED DESCRIPTION
[0054] The present disclosure relates to a propellant support unit 100 for an ordnance (i.e. a weapon system) 200.
[0055] The present disclosure relates to an ammunition round 600. Examples of an ammunition round 600 are shown in figures 4, 5, 8, 9. The ammunition round 600 may comprise a propellant support unit 100 according to the present disclosure. The ammunition round 600 may comprise a projectile 604.
[0056] The weapon system 200 may be a projectile launch system, for example an artillery gun. As illustrated in figures 5, 7, 9, 11, 13, 15, the ordnance / weapon system 200 may comprise a barrel 202 with a bore 204 that extends along a barrel axis 206 from a breech 208 to a muzzle 210. The breech 208 may comprise an ammunition loading chamber region 212. The ammunition loading chamber 212 may be configured to receive a propellant support unit 100 according to the present disclosure. The ammunition loading chamber 212 may be configured to receive an ammunition round 600 according to the present disclosure.
[0057] As illustrated in figures 14, 15, the barrel 202 may comprise a location feature 140 configured to engage with the propellant support unit 100 to thereby locate the propellant support unit 100 in place. Hence the propellant support unit axis 102 may be aligned and / or parallel with the barrel axis 206.
[0058] The location feature 140 may be configured to engage with the ammunition round 600 to thereby locate the ammunition round 600 in place. Hence the propellant support unit axis 102 may be aligned and / or parallel with the barrel axis 206.
[0059] The location feature 140 may be a recess. The recess may be configured to receive an edge of a first end 106 of the propellant support unit 100 to thereby locate the propellant support unit 100 in place. The recess may be configured toXA23410 Draft for filing
[0060] - 6 -
[0061] receive an edge of an ammunition round 600 to thereby locate the ammunition round 600 in place.
[0062] The propellant support unit 100 may be sized to have a sliding fit within the chamber 212. The ammunition round 600 may be sized to have a sliding fit within the chamber 212.
[0063] As illustrated in figures 2, 4, 6, 8, 10 the propellant support unit 100 may extend along a propellant support unit axis 102. The propellant support unit 100 may comprise a side wall 104 extending between a first end 106 and a second end 108 along the length L of the propellant support unit 100. The first end 106 and the second end 108 are spaced apart from one another by the side wall 104. The side wall 104 may define a chamber 110, the chamber 110 being closed at the first end 106 by a first end wall 112.
[0064] The side wall 104 may be circular when viewed along the propellant support unit axis 102 (as shown in figure 3). Hence the propellant support unit 100 may be substantially cylindrical, centred on the propellant support unit axis 102.
[0065] As illustrated in figures 12, 13, the propellant support unit 100 may be substantially semi-cylindrical along its length. In figures 12, 13 the semi-circular propellant support unit 100 is shown used in an example similar to that of the example of figures 10, 11 in which the propellant support unit 100, projectile 604 and / or a primer 400 are provided individually / separately in the barrel 202. The semi-circular propellant support unit 100 may be incorporated with the other example arrangements of the present disclosure.
[0066] The side wall 104 may be polygonal in cross-section, for example when viewed along the propellant support unit axis 102.
[0067] The propellant support unit 100 may be at least 20mm but no more than 200mm in diameter. The propellant support unit 100 may be at least 20mm but no more than 100mm in diameter. The propellant support unit 100 may be at least 30mm but no more than 90mm in diameter. The propellant support unit 100 may be at least 35mm but no more than 70mm in diameter. The propellant support unit 100 may be at least 40mm but no more than 100mm in diameter.XA23410 Draft for filing
[0068] - 7 -
[0069] As shown in figures 3 to 11 , the propellant support unit 100 may comprise an internal wall structure 114 which extends from the side wall 104 to define a plurality of sub-chambers 116. The sub-chambers 116 may extend along the length L of the propellant support unit 100 between the first end 106 and the second end 108. The sub-chambers 116 may extend along at least part of the length L of the propellant support unit 100 between the first end 106 and the second end 108. The sub-chambers 116 may extend along part, but not all, of the length L of the propellant support unit 100 between the first end 106 and the second end 108.
[0070] At least some of the sub-chambers 116 may be closed at the first end 106 by the first end wall 112. At least some, but not all, of the sub-chambers 116 may be closed at the first end 106 by the first end wall 112. All of the sub-chambers 116 may be closed at the first end 106 by the first end wall 112.
[0071] At least one of the sub-chambers 116 is configured for containing a propellant 300. At least one of the sub-chambers 116 is configured for being empty.
[0072] The chamber 110 may be open at the second end 108. At least some of the sub-chambers 116 may be open at the second end 108. At least some, but not all, of the sub-chambers 116 may be open at the second end 108. All of the sub-chambers 116 may be open at the second end 108.
[0073] The chamber 110 may be closed at the second end 108 by a second end wall 118. At least some of the sub-chambers 116 may be closed at the second end 108 by the second end wall 118. At least some, but not all, of the subchambers 116 may be closed at the second end 108 by the second end wall 118. All of the sub-chambers 116 may be closed at the second end 108 by the second end wall 118.
[0074] Each of the sub-chambers 116 may extend from the first end 106 of the propellant support unit 100 to the second end 108 of the propellant support unit 100 in a direction along the propellant support unit axis 102.
[0075] At least some of the sub-chambers 116 may have the same cross-sectional shape and area along their length. At least some of the sub-chambers 116 may have a constant cross-sectional shape and area along their length.XA23410 Draft for filing
[0076] - 8 -
[0077] At least some of the sub-chambers 116 may have a circular cross-section. At least some of the sub-chambers 116 may be cylindrical.
[0078] At least some of the sub-chambers 116 may have a polygonal crosssection. At least some of the sub-chambers 116 may be prismatic. At least some of the sub-chambers 116 may be hexagonal.
[0079] Hence the sub-chambers 116 may form a tessellating shape or group of tessellating shapes. The sub-chambers 116 may form a tessellating structure. For example, the sub-chambers 116 may form a honeycomb structure.
[0080] At least one of the first end 106 of the propellant support unit 100 or the second end 108 of the propellant support unit 100 may be configured for the passage therethrough of a propellant 300.
[0081] The first end wall 112 may comprise a porous material 120 (e.g. a porous membrane) which closes one or more of the sub-chambers 116.
[0082] The first end wall 112 of the propellant support unit 100 may comprise a flow port (e.g. a valve) 122 through which propellant 300 is deliverable to at least one of the sub-chambers 116. A port / valve 122 may be provided in the first end wall 112 which provides fluid communication between one of the sub-chambers 116 and a region external to the propellant support unit 100. A plurality of ports / valves 122 may be provided in the first end wall 112, one for each of a plurality of the sub-chambers 116.
[0083] There may be provided one flow port / valve 122 for each sub-chamber 116 that is provided with a flow port / valve 122.
[0084] The side wall 104, internal wall structure 114, first end wall 112 and / or second end wall 118 may comprise a combustible material. The side wall 104, internal wall structure 114, first end wall 112 and / or second end wall 118 may comprise at least one of paper, cellulose and / or waxed fibre (for example cotton).
[0085] The propellant support unit 100 may further comprise a propellant 300. A propellant 300 is a fast burning substance / fuel. The propellant 300 may be a solid or fluid.
[0086] The propellant 300 may comprise a solid nitro cellulose based, triplebased and / or multi-based propellant 300. The propellant 300 may comprise aXA23410 Draft for filing
[0087] - 9 -
[0088] liquid ammonium perchlorate, hydrazine, propylene glycol dinitrate, and / or nitric acid based fuel.
[0089] The propellant support unit 100 may comprise one or more primers 400. A primer 400 may comprise a chemical compound and / or a device (e.g. a percussion or an electrical discharge device) operable for initiating combustion of the propellant 300. Any conventional primer 400 may be provided.
[0090] The primer 400 may extend along at least part of the length of one of the sub-chambers 116.
[0091] As illustrated in figures 6 to 9, the propellant support unit 100 may further comprise a stub case 500. The stub case 500 may comprise a base member 502 located on the first end 106 of the propellant support unit 100.
[0092] The stub case 500 may comprise a support housing 504 which extends from the base member 502 along part of the length of the propellant support unit 100. The stub case 500 (i.e. support housing 504 and base member 502) may be made from a different material to the propellant support unit 100. For example, the stub case 500 may be made from a metal or metallic alloy. The stub case 500 may be made from brass or steel.
[0093] The support housing 504 may extend from the base member 502 along part but not all of the length of the propellant support unit 100. The support housing 504 may extend from the base member 502 along no more than 50% of the length of the propellant support unit 100. Hence the support housing 504 may partially house the propellant support unit 100. The propellant support unit 100 and support housing 504 may be sized so the propellant support unit 100 is a close fit in the support housing 504.
[0094] As shown in figures 8, 9 the propellant support unit 100 may define a projectile support chamber 130 which extends from the second end 108 of the propellant support unit 100 at least part of the way to the first end 106 of the propellant support unit 100. The other sub-chambers 116 may be located around the projectile support chamber 130. Hence, in this example, not all of the subchambers 116 may extend the full length of the propellant support unit 100. The projectile 604 may be mounted in the projectile support chamber 130 to form an ammunition round 600. Hence the projectile support chamber 130 may define aXA23410 Draft for filing
[0095] - 10 -
[0096] recess in which a projectile 604 may be located to form an ammunition round 600 (i.e. so that the ammunition round 600 may be loaded into the barrel 202 of the ordnance 200 as one assembly.)
[0097] In the example of figures 4, 5, the ammunition round 600 may comprise a cartridge case 602, a projectile 604 and a propellant support unit 100 according to the present disclosure. As shown in figures 4, 5, the cartridge case 602 may extend from a base plate 606 to a projectile support feature 608. The projectile 604 may be mounted to the projectile support feature 608. The propellant support unit 100 may be housed within the cartridge case 602 between the base plate 606 and the projectile 604 (i.e. so that the ammunition round 600 may be loaded into the barrel 202 of the ordnance 200 as one assembly).
[0098] The cartridge case 602 may be made from a different material to the propellant support unit 100. For example, the cartridge case 602 may be made from a metal or metallic alloy. The cartridge case 602 may be made from brass or steel.
[0099] The propellant support unit 100 may be provided (e.g. manufactured) with each of the sub-chambers 116 empty (e.g. without any propellant 300).
[0100] When needed, the propellant 300 may be provided into one or more subchambers 116 manually by an operator / user. The propellant 300 may be provided / delivered into one or more sub-chambers 116 by an automated system. In either case, propellant 300 is provided / delivered in one or more of the subchambers 116 as required. For example, propellant 300 may be provided / delivered in one or more of the sub-chambers 116 as to generate the necessary pressure to fire a projectile 604 a desired range and / or force.
[0101] The sub-chambers 116 to which propellant 300 are added may be selected in a pattern to ensure that there is suitable fuel / air mix (for example as shown in figure 3).
[0102] The sub-chambers 116 provided with propellant 300 may be spaced apart from sub-chambers 116 which have no propellant 300 (for example, which are empty) around at least part of their circumference.XA23410 Draft for filing
[0103] - 11 -
[0104] The sub-chambers 116 provided with propellant 300 may be spaced apart from sub-chambers 116 which have no propellant 300 (for example, which are empty) around part, but not all, of their circumference.
[0105] At least some of the sub-chambers 116 provided with propellant 300 may be spaced apart from sub-chambers 116 which have no propellant 300 (for example, which are empty).
[0106] The sub-chambers 116 provided with propellant 300 may be spaced apart from sub-chambers 116 which have no propellant 300 (for example, which are empty) on at least one of their sides.
[0107] The sub-chambers 116 provided with propellant 300 may be spaced apart from sub-chambers 116 which have no propellant 300 (for example, which are empty) on at least one, but not all, of their sides.
[0108] Hence propellant 300 may be delivered into one or more sub-chambers 116. For example, the propellant 300 may be delivered through the first end 106 and / or second end 108. The propellant 300 may be delivered through the first end 106 and / or second end 108 in examples in which the first end 106 and / or second end 108 are open.
[0109] The propellant 300 may be delivered through the first end 106 and / or second end 108 in examples in which the first end 106 and / or second end 108 are closed. In such an example, the propellant 300 may be delivered through the first end wall 112 or second end wall 118. The propellant 300 may be delivered through the first end wall 112 or second end wall 118 via a respective flow port (e.g. valve) 122. The propellant 300 may be delivered through the first end wall 112 or second end wall 118 by injecting or inserting the propellant 300 through the first end wall 112 or second end wall 118 (for example using a syringe or funnel type arrangement in examples in which the propellant 300 is a fluid, a powder, particulate and / or granular).
[0110] The propellant 300 may be delivered through the first end wall 112 or second end wall 118 by forcing / urging the propellant 300 through the first end wall 112 or second end wall 118. For example, the first end wall 112 or second end wall 118 may be porous with respect to the propellant 300. Alternatively, the propellant 300 may be a solid and pushed through the first end wall 112 or secondXA23410 Draft for filing
[0111] - 12 -
[0112] end wall 118 tearing / breaking the material of the first end wall 112 or second end wall 118 to allow the propellant 300 to pass through.
[0113] The propellant 300 may be provided in predetermined units for delivery to each sub-chamber 116, where each unit is of the same volume and / or mass. This may be advantageous as it may provide certainty over the amount of propellant 300 delivered to each sub-chamber 116.
[0114] The or each sub-chambers 116 may be partially filled. The or each subchambers 116 may be completely filled. In examples in which propellant 300 is provided / delivered to a plurality of sub-chambers 116, the same amount of propellant 300 may be delivered to each. In examples in which propellant 300 is provided / delivered to a plurality of sub-chambers 116, the amount of propellant 300 delivered to each of the plurality of sub-chambers 116 may be the same or different. In examples in which propellant 300 is provided / delivered to a plurality of sub-chambers 116, the amount of propellant 300 delivered to some of the plurality of sub-chambers 116 may be the same.
[0115] Hence the amount of propellant 300 provided may be infinitely variable, enabling an infinite variation in propulsion output.
[0116] Once a suitable amount of charge had been provided into the propellant support unit 100, the propellant support unit 100 may be loaded (manually and / or by an automated process) into the ordnance 200 and fired using a primer 400.
[0117] In the example of figures 4, 5 in which the propellant support unit 100 is provided as part of an ammunition round 600 (i.e. within a cartridge case 602), the propellant support unit 100 may be provided with propellant 300 before or after is it fitted into the cartridge case 602.
[0118] In the example of figures 6, 7 in which the propellant support unit 100 is provided with a stub case 500, the propellant support unit 100 may be provided with propellant 300 before or after is it fitted with the stub case 500.
[0119] In the example of figures 8, 9 in which the propellant support unit 100 is provided with a stub case 500 and with a projectile 604, the propellant support unit 100 may be provided with propellant 300 before or after is it fitted with the stub case 500 and / or projectile 604.XA23410 Draft for filing
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[0121] In the examples of figures 4 to 9 the propellant support unit 100 may be provided with the propellant 300 before or after is it fitted with the primer 400.
[0122] In the examples of figures 10, 11 the propellant support unit 100 may be loaded into the ordnance 200 separately to the projectile 604 and / or primer 400.
[0123] The primer 400 may be located / provided in a sub-chamber 116 in the centre of the propellant support unit 100.
[0124] As illustrated in figure 3, a primer 400 may be located in a central subchamber 124 of the sub-chambers 116 of the propellant support unit 100.
[0125] As illustrated in figures 4 to 11 , the primer 400 may be located / fixed at the first end 106 of the propellant support unit 100.
[0126] As illustrated in figures 6 to 9, the primer 400 may be located / provided in a recess in the centre of the first end 106 of the propellant support unit 100.
[0127] There may be provided a method of operating a weapon system 200. The method of operating a weapon system 200 may comprise the step of loading a propellant support unit 100 of the present disclosure and a projectile 604 into the barrel 202 with the propellant support unit 100 spaced apart from the muzzle 210 by the projectile 604.
[0128] The method of operating a weapon system 200 may comprise the step of loading an ammunition round 600 according to the present disclosure into the barrel 202.
[0129] When the propellant 300 is ignited, the propellant support unit 100 disintegrates (e.g. is destroyed by burning and / or by the force of the pressure change caused by the propellant 300).
[0130] Hence there is provided an arrangement which allows for a precise amount of propellant 300 in a desired distribution to be loaded into a weapon system 200 to propel a projectile 604.
[0131] The propellant support unit 100 of the present disclosure provides a structure which will carry / support a predetermined / desired amount of propellent and also be completely destroyed by the firing of the weapon, thus making it compatible with any existing weapon system.XA23410 Draft for filing
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[0133] The propellant support unit 100 of the present disclosure allows for a precise and infinitely variable amount of propellant 300 to be used when preparing to file a projectile which increases accuracy of the weapon and results in more efficient use to the propellant 300 since only the amount of propellant needed is used.
[0134] The propellant support unit 100 enables the use of fluid (e.g. liquid) propellants 300, which means a precise amount of propellant may be used, resulting in greater projectile delivery accuracy. With fluids there may be no waste as only the required volume of propellant 300 would be used. Additionally, it may be easier to prevent degradation of the propellant 300 due to environmental factors (such as humidity / oxidization) as it may inherently be stored in a sealed tank.
[0135] Conventionally the use of liquid propellants 300 was problematic, as they may be highly corrosive to obturation and / or barrel seals required for safe gun operation. Also, the liquid would pool in the base of the firing chamber, resulting in poor fuel / air mixing. However, the propellant support unit 100 of the present disclosure avoids these issues by retaining a fluid propellant in a preferred location in the weapon relative to the projectile as well as keeping the propellant 300 spaced apart from the material / parts of the weapon.
[0136] The propellant support unit 100 also lends itself to automated loading systems, for both manned crews and remotely operated and / or autonomous systems. For example, the propellant support unit 100 makes manned crewed systems safer as it may keep users away from dangerous materials (i.e. the propellant 300), and also reduces human error in loading the correct amount of charge (for example when distracted in a battlefield scenario because of long exposure to cold, wet and hostile environments).
[0137] The system of the present disclosure thus enables consistent and accurate use of propellants 300, with easier handling for users and automated systems than possible with examples of the related art.
[0138] Attention is directed to all papers and documents which are filed concurrently with or previous to this specification in connection with this application and which are open to public inspection with this specification, andXA23410 Draft for filing
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[0140] the contents of all such papers and documents are incorporated herein by reference.
[0141] All of the features disclosed in this specification (including any accompanying claims, abstract and drawings), and / or all of the steps of any method or process so disclosed, may be combined in any combination, except combinations where at least some of such features and / or steps are mutually exclusive.
[0142] Each feature disclosed in this specification (including any accompanying claims, abstract and drawings) may be replaced by alternative features serving the same, equivalent or similar purpose, unless expressly stated otherwise. Thus, unless expressly stated otherwise, each feature disclosed is one example only of a generic series of equivalent or similar features.
[0143] The invention is not restricted to the details of the foregoing embodiment(s). The invention extends to any novel one, or any novel combination, of the features disclosed in this specification (including any accompanying claims, abstract and drawings), or to any novel one, or any novel combination, of the steps of any method or process so disclosed.
Claims
XA23410 Draft for filing- 16 -CLAIMS1. A propellant support unit for a weapon system, wherein the propellant support unit extends along a propellant support unit axis and comprises:a side wall extending between a first end and a second end along the length L of the propellant support unit, wherein the side wall defines a chamber, the chamber being closed at the first end by a first end wall;an internal wall structure which extends from the side wall to define a plurality of sub-chambers, wherein at least one of the sub-chambers is configured for containing a propellant.
2. A propellant support unit as claimed in claim 1 wherein:the chamber is open at the second end, orthe chamber is closed at the second end by a second end wall.
3. A propellant support unit as claimed in claim 1 or claim 2 wherein each of the sub-chambers extend from the first end of the propellant support unit to the second end of the propellant support unit in a direction along the propellant support unit axis.
4. A propellant support unit as claimed in any one of claims 1 to 3 wherein: each sub-chamber has a circular cross-section; oreach sub-chamber has a polygonal cross-section;wherein at least some of the sub-chambers have the same cross-sectional shape and area along their length.
5. A propellant support unit as claimed in any one of claims 1 to 4 wherein at least one of the first end of the propellant support unit or the second end ofXA23410 Draft for filing- 17 -the propellant support unit is configured for the passage therethrough of a propellant.
6. A propellant support unit as claimed in claim 5 wherein the first end wall comprises a porous material which closes one or more of the sub-chambers.
7. A propellant support unit as claimed in claim 5 wherein the first end wall of the propellant support unit comprises a valve through which a propellant is deliverable to at least one of the sub-chambers.
8. A propellant support unit as claimed in any one of claims 1 to 7 wherein the side wall and the first end wall comprise at least one of paper, cellulose and / or waxed fibre.
9. A propellant support unit as claimed in any one of claims 1 to 8 further comprising a propellant, wherein the propellant is a solid or fluid.
10. A propellant support unit as claimed in claim 9 wherein the propellant comprises a solid nitro cellulose based, triple-based and / or multi-based propellant; orwherein the propellant comprises liquid ammonium perchlorate, hydrazine, propylene glycol dinitrate, and / or a nitric acid based fuel.
11. A propellant support unit as claimed in any one of claims 1 to 10 further comprising a primer.
12. A propellant support unit as claimed in any one of claims 1 to 11 further comprising a stub case, the stub case comprising:a base member located on the first end of the propellant support unit; andXA23410 Draft for filing- 18 -a support housing which extends from the base member along part of the length of the propellant support unit.
13. A propellant support unit as claimed in any one of claims 1 to 12 wherein the propellant support unit defines a projectile support chamber which extends from the second end of the propellant support unit at least part of the way to the first end of the propellant support unit.
14. An ammunition round comprising:a cartridge case;a projectile; anda propellant support unit as claimed in any one of claims 1 to 11 , wherein the cartridge case extends from a base plate to a projectile support feature; the projectile is mounted to the projectile support feature; andthe propellant support unit is housed within the cartridge case between the base plate and the projectile.
15. A weapon system comprising:a barrel with a bore that extends along a barrel axis from a breech to a muzzle; the breech comprising an ammunition loading chamber region;the ammunition loading chamber configured to receive a propellant support unit as claimed in any one of claims 1 to 13;the barrel comprises a location feature configured to engage with the propellant support unit to thereby locate the propellant support unit in place.