WO1988008510A1 - Propellant case with temperature compensating ballistic control - Google Patents

Propellant case with temperature compensating ballistic control Download PDF

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Publication number
WO1988008510A1
WO1988008510A1 PCT/US1988/000475 US8800475W WO8808510A1 WO 1988008510 A1 WO1988008510 A1 WO 1988008510A1 US 8800475 W US8800475 W US 8800475W WO 8808510 A1 WO8808510 A1 WO 8808510A1
Authority
WO
WIPO (PCT)
Prior art keywords
substance
piston
volume
projectile
casing
Prior art date
Application number
PCT/US1988/000475
Other languages
French (fr)
Inventor
Steven P. Neubauer
Original Assignee
Honeywell Inc.
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Honeywell Inc. filed Critical Honeywell Inc.
Publication of WO1988008510A1 publication Critical patent/WO1988008510A1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/045—Cartridges, i.e. cases with charge and missile of telescopic type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/10—Cartridges, i.e. cases with charge and missile with self-propelled bullet
    • F42B5/105—Cartridges, i.e. cases with charge and missile with self-propelled bullet propelled by two propulsive charges, the rearwardly situated one being separated from the rest of the projectile during flight or in the barrel; Projectiles with self-ejecting cartridge cases

Definitions

  • PROPELLANT CASE WITH TEMPERATURE COMPENSATING BALLISTIC CONTROL PROPELLANT CASE WITH TEMPERATURE COMPENSATING BALLISTIC CONTROL.
  • the present invention relates generally to munitions and particularly to control of propellants 5 of projectiles. More particularly, the invention pertains to control of propellants to effect greater performance of projectiles under adverse environmental conditions.
  • Propellants 15 of the munitions typically provide high performance under high ambient temperatures. Under cold conditions such munitions exhibit low performance due to the slower burn rate or degradation of propellants. To increase performance of cold 20 munitions, the temperature of propellants may be increased. However, such heated munitions may be dangerous if designed for maximum performance under colder environmental conditions. So for reasons of safety of firing crews and of avoiding excessive 25 stress on firing mechanisms, most munitions are designed for high ambient temperatures, such a design results in low performance munitions at medium or low temperature climatic conditions.
  • One solution has been to warm up munitions in such environments. However, combatant conditions afford little luxury in maintaining munitions at a desirable temperature. To obtain needed performance of munitions in cool combatant environments, such munitions have been "toasted" over an open fire or like means. Such a technique is hazardous and cumbersome. The related art does not afford a direct solution to the problems associated with cold munitions.
  • the present invention solves the problem of munitions' inability to maintain full performance characteristics under any temperature condition of an environment.
  • the degrading effect of cold temperatures upon propellants of munitions is noted.
  • Compensation in the present invention utilizes the degrading effect of increased volume upon stored propellants.
  • the primary object of the invention is to provide munitions with optimal performance at all environmental temperatures.
  • the invention varies the volume of the container of the main propellant for the projectile according to ambient temperature of the propellant. If the temperature is low, the volume of the propellant case is kept at a minimum. For a relatively high temperature, the volume of the case is enlarged proportionately. The enlargement is achieved by moving the projectile forward from the main charge or propellant case with an internal piston within a ballistic control tube put into motion by a secondary charge or propellant.
  • the secondary charge or propellant is also temperature sensitive, that is, the higher the temperature the greater the force created by the charge.
  • the secondary charge or propellant is contained in a relatively constant volume thereby ensuring a greater force at higher temperature.
  • the invention enables the projectile to have optimal performance at all environmental temperatures, i.e., temperature independent performance.
  • a tremendous advantage of the invention includes projectiles' having much more performance at nominal ..temperatures.
  • Another feature of the invention is the greater movement of the projectile within the case allowed by a slotted mechanical interlock system between the projectile and the piston within the ballistic control tube.
  • This feature allows increased piston movement for greater volume change of the main propellant case or, in the alternative, reduced ballistic control tube length for similar volume change of the case.
  • the mechanical interlock system provides positive and rigid rear support of the projectile assembly. The piston is retained and not propelled out with the projectile.
  • Still another feature of the invention is the igniting of the main propellant by the secondary charge or propellant thereby eliminating the need of separate ignition of the main charge or propellant.
  • the ignited secondary charge or propellant moves the piston full distance within the ballistic control tube, the piston passes venting holes in the control tube, through which the gases of the secondary charge escape into the case of the main charge or propellant, thereby igniting the latter.
  • FIG. 2 shows an application of one embodiment of the invention.
  • FIG. 3a shows another embodiment of the invention.
  • Figure 3b is a section view along line 3b-3b of Figure 3a.
  • Figure 4 shows an application of the other embodiment of the invention.
  • Figure 1 shows a piece of artillery 10 having 120 millimeter ammunition 30 positioned in a cannon or gun 20.
  • Barrel 22 of gun 20 is designed so that projectile 12 may move through barrel 22.
  • Volume 16 within case 24 consists of the main propellant or charge 36.
  • the base case 18 supports the ballistic control tube 26. At the base end of control tube 26 is igniter 34 for igniting secondary charge or propellant 28.
  • Piston 32 is supported against fins 14 of projectile 12.
  • Ammunition 30 is designed so that projectile 12 exits the barrel 22 at a optimal velocity under environments of various temperatures.
  • Main propellant 36 for a given volume provides greater average pressures behind the propellant at higher temperatures. If the same amount of main propellant 36 is in a volume 16 that is increased, then the pressure behind projectile 12 is reduced. If the amount of main propellant 36 packed into volume 16 is such that volume 16 is at its minimum for maximum performance of projectile 12 at the coldest temperature that ammunition 30 is subjected to, then maximum performance of projectile 12 also may be maintained for any operating temperature higher than the coldest temperature.
  • This operability of peak performance without exceeding the safety limits of munition 30 at various temperatures above the coldest temperature that munition 30 is designed to operate at is accomplished by increasing volume 16 which in turn reduces the effect of main propellant 36 upon projectile 12 for a given temperature.
  • This volume 16 increase is accomplished by the movement of projectile 12 down barrel 22.
  • the forward movement of projectile 12 for increasing volume 16 is accomplished by secondary propellant or charge 28 which is itself temperature sensitive.
  • Secondary propellant 28 forces piston 32 down ballistic control tube 26. Piston 32 pushes against fins 14 of projectile 12 thereby accomplishing a movement of projectile 12 down barrel 22.
  • the temperature of secondary propellant 28 is the same as the ambient temperature of munition 30.
  • FIG. 2 shows an embodiment in which piston 32 pushes projectile 12 with greater force, thereby sending projectile 12 further down barrel 22, increasing volume 16 and reducing the effect of main propellant 36 on projectile 12, thus compensating for the higher ambient.temperature of munition 30.
  • Figure 2 shows an embodiment in which piston 32 pushes projectile 12 with greater force, thereby sending projectile 12 further down barrel 22, increasing volume 16 and reducing the effect of main propellant 36 on projectile 12, thus compensating for the higher ambient.temperature of munition 30.
  • Figure 2 shows an embodiment in which piston
  • piston 32 is propelled by secondary propellant 28 when ignited by igniter 34. Piston 32 pushes on fins 14 and pushes projectile 12 down barrel 22 thereby increasing the volume 16 of main propellant 36.
  • piston 32 leaves ballistic control tube 27. As piston 32 leaves control tube 27, ignited secondary propellant 28 ignites main propellant 16 which gives the main impetus to projectile 12. Piston 32 leaves with projectile 12 if attached to fins 14. Alternatively, piston 32, if not attached to fins 14, leaves casing 24 as a second projectile.
  • the temperature compensating principles of this embodiment are the same as those described for munition 30 of Figure 1.
  • Figure 3a shows is another embodiment of the invention, similar to that depicted in Figure 1. This embodiment is referred to as the mechanical interlock system for ballistic control tube 26.
  • Figure 3a differs from Figure 2 in that piston 32 cannot leave ballistic control tube 26 when secondary charge or propellant 28 is ignited by igniter 34. Shoulders 42 on ballistic control tube 26 prevent piston 32 from leaving control tube 26. Contact by piston 32 with fins 14 of projectile 12 is made through hole 44. Primary propellant 36 in volume 16 is ignited by ignited secondary propellant 28 flowing through vents 38 when piston 32 is moved to shoulders 42 by expanding propellant 28 in control tube 26.
  • Igniter bag 46 as shown in Figure 3a, may be incorporated in all embodiments.
  • FIG. 3a shows the interaction of fins 14 of projectile 12 with the embodiment described in Figure 3a.
  • Primary propellant or charge 36 is ignited by ignited secondary charge or propellant 28 moving through vents 38 into volume 16.
  • One advantage of the mechanical interlock system for ballistic control tube 26 is that the total length of munition 30 need not be increased for an increased length of ballistic control tube 26, thereby providing a longer path on which piston 32 may move for providing a greater increase in volume 16. Further, the interlock system for control tube 26 retains piston 32 which might be used in future case reloadings. Disadvantages of a second projectile or heavier projectile 12 due to piston 32 attached to projectile 12 are avoided. Hence, the interlock system prevents the exit of a second projectile which may damage the gun barrel or tube. Also prevented is the ejection of a stray projectile moving toward an unintended target. Secondary charge or control tube charge or propellant 28 is composed of a small web JA2 propellant.
  • Main propellant 36 is a JA2 stick propellant.
  • Ignition element 34 is an M83 igniter.
  • Igniter bag 46 in conjunction with main propellant 36 as depicted in Figure 3a maybe incorporated.
  • Igniter bag 46 is a black powder or benite igniter charge.
  • the propellants and other elements of the above described embodiments may be composed of other ingredients or parts.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

A temperature compensating ballistic control tube for varying the volume containing primary propellant, for the purpose of affecting the effect of the propellant on the projectile in order to compensate for ambient temperature. The volume (16) containing the primary propellant (36) is changed by a piston (32) which is moved by an ignited secondary charge (28) which is temperature sensitive. The control tube has a mechanical interlock system (42) for retaining the secondary charge piston (32) after ignition, and orifices (38) for venting ignited secondary charge into volume of primary propellant for ignition of the latter.

Description

PROPELLANT CASE WITH TEMPERATURE COMPENSATING BALLISTIC CONTROL.
The present invention relates generally to munitions and particularly to control of propellants 5 of projectiles. More particularly, the invention pertains to control of propellants to effect greater performance of projectiles under adverse environmental conditions.
The United States Government has rights in 0 this invention pursuant to Contract No.
DAAK11-84-C-0102, awarded by AMCCOM of the United States Army.
Projectile munitions have varied performance - dependent on environmental temperatures. Propellants 15 of the munitions typically provide high performance under high ambient temperatures. Under cold conditions such munitions exhibit low performance due to the slower burn rate or degradation of propellants. To increase performance of cold 20 munitions, the temperature of propellants may be increased. However, such heated munitions may be dangerous if designed for maximum performance under colder environmental conditions. So for reasons of safety of firing crews and of avoiding excessive 25 stress on firing mechanisms, most munitions are designed for high ambient temperatures, such a design results in low performance munitions at medium or low temperature climatic conditions. One solution has been to warm up munitions in such environments. However, combatant conditions afford little luxury in maintaining munitions at a desirable temperature. To obtain needed performance of munitions in cool combatant environments, such munitions have been "toasted" over an open fire or like means. Such a technique is hazardous and cumbersome. The related art does not afford a direct solution to the problems associated with cold munitions.
SUMMARY OF THE INVENTION The present invention solves the problem of munitions' inability to maintain full performance characteristics under any temperature condition of an environment. The degrading effect of cold temperatures upon propellants of munitions is noted. Compensation in the present invention utilizes the degrading effect of increased volume upon stored propellants.
The primary object of the invention is to provide munitions with optimal performance at all environmental temperatures. The invention varies the volume of the container of the main propellant for the projectile according to ambient temperature of the propellant. If the temperature is low, the volume of the propellant case is kept at a minimum. For a relatively high temperature, the volume of the case is enlarged proportionately. The enlargement is achieved by moving the projectile forward from the main charge or propellant case with an internal piston within a ballistic control tube put into motion by a secondary charge or propellant. The secondary charge or propellant is also temperature sensitive, that is, the higher the temperature the greater the force created by the charge. The secondary charge or propellant is contained in a relatively constant volume thereby ensuring a greater force at higher temperature. This greater force moves the projectile via the internal piston within the ballistic control tube at a greater initial velocity resulting in a greater distance forward from the case at the time the main propellant is ignited, thereby increasing the case volume and, in turn, decreasing the potential explosive force of the main.propellant for a given temperature. At lower temperatures, the force of the secondary charge or propellant is lower, thus moving the projectile a smaller distance forward by the time of ignition of the main propellant, thereby not increasing the case volume of the main propellant very much and, in turn, maintaining a potential explosive force similar in magnitude to that at higher temperatures of the main charge or propellant. Therefore, the invention enables the projectile to have optimal performance at all environmental temperatures, i.e., temperature independent performance. A tremendous advantage of the invention includes projectiles' having much more performance at nominal ..temperatures.
Another feature of the invention is the greater movement of the projectile within the case allowed by a slotted mechanical interlock system between the projectile and the piston within the ballistic control tube. This feature allows increased piston movement for greater volume change of the main propellant case or, in the alternative, reduced ballistic control tube length for similar volume change of the case. Further, the mechanical interlock system provides positive and rigid rear support of the projectile assembly. The piston is retained and not propelled out with the projectile.
Still another feature of the invention is the igniting of the main propellant by the secondary charge or propellant thereby eliminating the need of separate ignition of the main charge or propellant. When the ignited secondary charge or propellant moves the piston full distance within the ballistic control tube, the piston passes venting holes in the control tube, through which the gases of the secondary charge escape into the case of the main charge or propellant, thereby igniting the latter.
BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 shows a munition incorporating the present invention.
Figure 2 shows an application of one embodiment of the invention.
Figure 3a shows another embodiment of the invention.
Figure 3b is a section view along line 3b-3b of Figure 3a. Figure 4 shows an application of the other embodiment of the invention.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
Figure 1 shows a piece of artillery 10 having 120 millimeter ammunition 30 positioned in a cannon or gun 20. Barrel 22 of gun 20 is designed so that projectile 12 may move through barrel 22. Volume 16 within case 24 consists of the main propellant or charge 36. The base case 18 supports the ballistic control tube 26. At the base end of control tube 26 is igniter 34 for igniting secondary charge or propellant 28. Piston 32 is supported against fins 14 of projectile 12.
Ammunition 30 is designed so that projectile 12 exits the barrel 22 at a optimal velocity under environments of various temperatures. Main propellant 36 for a given volume provides greater average pressures behind the propellant at higher temperatures. If the same amount of main propellant 36 is in a volume 16 that is increased, then the pressure behind projectile 12 is reduced. If the amount of main propellant 36 packed into volume 16 is such that volume 16 is at its minimum for maximum performance of projectile 12 at the coldest temperature that ammunition 30 is subjected to, then maximum performance of projectile 12 also may be maintained for any operating temperature higher than the coldest temperature. This operability of peak performance without exceeding the safety limits of munition 30 at various temperatures above the coldest temperature that munition 30 is designed to operate at is accomplished by increasing volume 16 which in turn reduces the effect of main propellant 36 upon projectile 12 for a given temperature. This volume 16 increase is accomplished by the movement of projectile 12 down barrel 22. The forward movement of projectile 12 for increasing volume 16 is accomplished by secondary propellant or charge 28 which is itself temperature sensitive. Secondary propellant 28 forces piston 32 down ballistic control tube 26. Piston 32 pushes against fins 14 of projectile 12 thereby accomplishing a movement of projectile 12 down barrel 22. The temperature of secondary propellant 28 is the same as the ambient temperature of munition 30. For a higher temperature of secondary propellant 28, piston 32 pushes projectile 12 with greater force, thereby sending projectile 12 further down barrel 22, increasing volume 16 and reducing the effect of main propellant 36 on projectile 12, thus compensating for the higher ambient.temperature of munition 30. Figure 2 shows an embodiment in which piston
32 is propelled by secondary propellant 28 when ignited by igniter 34. Piston 32 pushes on fins 14 and pushes projectile 12 down barrel 22 thereby increasing the volume 16 of main propellant 36. In this particular embodiment, piston 32 leaves ballistic control tube 27. As piston 32 leaves control tube 27, ignited secondary propellant 28 ignites main propellant 16 which gives the main impetus to projectile 12. Piston 32 leaves with projectile 12 if attached to fins 14. Alternatively, piston 32, if not attached to fins 14, leaves casing 24 as a second projectile. The temperature compensating principles of this embodiment are the same as those described for munition 30 of Figure 1.
Figure 3a shows is another embodiment of the invention, similar to that depicted in Figure 1. This embodiment is referred to as the mechanical interlock system for ballistic control tube 26. Figure 3a differs from Figure 2 in that piston 32 cannot leave ballistic control tube 26 when secondary charge or propellant 28 is ignited by igniter 34. Shoulders 42 on ballistic control tube 26 prevent piston 32 from leaving control tube 26. Contact by piston 32 with fins 14 of projectile 12 is made through hole 44. Primary propellant 36 in volume 16 is ignited by ignited secondary propellant 28 flowing through vents 38 when piston 32 is moved to shoulders 42 by expanding propellant 28 in control tube 26. Igniter bag 46, as shown in Figure 3a, may be incorporated in all embodiments. If so incorporated, ignited secondary propellant 28 ignites bag 46 and, in turn, bag 46 ignites primary propellant 36. The principles of operation of the embodiment in Figure 3a are the same as those described for the operation of the invention in Figure 1. Figure 4 shows the interaction of fins 14 of projectile 12 with the embodiment described in Figure 3a. A feature of the mechanical interlock system for ballistic control tube 26, as illustrated in Figure 3b, incorporates slots 48 in control tube 26 so that fins 14 may fit down tube 26 onto shortenend piston 32. Shoulders 42 in Figure 4 retain piston 32 when secondary propellant 28 is ignited forcing piston 32 against fins 14 and thus moving projectile 12. Primary propellant or charge 36 is ignited by ignited secondary charge or propellant 28 moving through vents 38 into volume 16. One advantage of the mechanical interlock system for ballistic control tube 26 is that the total length of munition 30 need not be increased for an increased length of ballistic control tube 26, thereby providing a longer path on which piston 32 may move for providing a greater increase in volume 16. Further, the interlock system for control tube 26 retains piston 32 which might be used in future case reloadings. Disadvantages of a second projectile or heavier projectile 12 due to piston 32 attached to projectile 12 are avoided. Hence, the interlock system prevents the exit of a second projectile which may damage the gun barrel or tube. Also prevented is the ejection of a stray projectile moving toward an unintended target. Secondary charge or control tube charge or propellant 28 is composed of a small web JA2 propellant. Main propellant 36 is a JA2 stick propellant. Ignition element 34 is an M83 igniter. Igniter bag 46 in conjunction with main propellant 36 as depicted in Figure 3a maybe incorporated. Igniter bag 46 is a black powder or benite igniter charge. However, the propellants and other elements of the above described embodiments may be composed of other ingredients or parts.

Claims

CLAIMS The embodiments of the invention in which an exclusive property or right is claimed are defined as follows:
1. A temperature compensating ballistic control tube system comprising: a first substance; a second substance; • first containing means for containing said first substance, having variable volume; second containing means for containing said second substance, having variable volume; and interconnecting means for interconnecting said first containing means to said second containing means so that volume variation of said first containing means causes volume variation of said second containing means.
2. Apparatus of claim 1 wherein said second substance is a conventional munition explosive having typical performance characteristics that vary with ambient temperature change.
3. Apparatus of claim 2 wherein said first substance is a munition explosive having performance characteristics that vary with ambient temperature change sufficiently similar to said performance characteristics of said second substance for temperature compensation of said second substance performance characteristics, achieved by varying volume of said second containing means.
4. Apparatus of claim 3 wherein said first containing means comprises a first hollow cylinder having one closed end, one open end, and a first moveable piston means for'-varying volume of said first cylinder, positioned between said closed end and said open end.
5. Apparatus of claim 4 wherein said second containing means comprises a second hollow cylinder having one closed end, one open end, and a second moveable piston means for varying volume of said second cylinder, positioned between said closed end and beyond said open end of said second containing means.
6. Apparatus of claim 5 wherein said interconnecting means comprises contact between said first and second pistons wherein movement of said first piston causes movement of said second piston.
7. Apparatus of claim 6 wherein said first containing means and said interconnecting means are enclosed within said second containing means.
8. Apparatus of claim 7 wherein: said second containing means is a munition casing; and said se"cond piston is a munition projectile slideably positioned between said open end of said casing and beyond said open end along longitudinal axis of said casing.
9. Apparatus of claim 8 wherein said projectile has a fin assembly extending into said casing and being in contact with said first piston.
10. Apparatus of claim 9 wherein said first cylinder has slots running longitudinally from said open end to part-way toward said closed end, wherein said fins slide into said slots allowing for a long first cylinder, and for said first piston to be in a moveable position initially close to said closed end of said first cylinder and for said fins to maintain continual contact with said first piston throughout movement of said first piston from near said closed end to said open end of said first cylinder upon where contact of said fins with said piston may break and allow said projectile to continue movement in the same direction.
11. Apparatus of claim 10 wherein said open end of said first cylinder has stop means for preventing said first piston from leaving said first cylinder.
12. Apparatus of claim 11 wherein said first cylinder has venting means for venting ignited said first substance from said first cylinder into said second cylinder.
13. A temperature compensating ballistic control tube comprising: a container having one open end; a piston slideably positioned in said container closing said open end such that movement of said piston corresponds to changes of volume within said container; an explosive substance having performance characteristics that vary with the temperature of said substance, situated in said container; igniting means for igniting said explosive substance, situated in said container; transferring means for transferring said piston movement due to ignited said explosive substance to an external object; venting means for venting said ignited explosive substance from said container; and stop means for preventing movement of said piston along longitudinal axis of said container beyond said open end of said container.
14. Apparatus of claim 13 further comprising: munition casing means having said container situated at base extremity inside said casing; a munition substance, having rapidly expanding gas properties when ignited, situated in said munition casing means; and a projectile, situated in open end of said munition casing means, having contact with said transferring means such that upon ignition of said explosive substance said projectile is set into initial motion thereby increasing volume of munition casing in which said munition substance is located, and subsequent to said initial motion said projectile is set into greater motion upon ignition of said munition substance by said ignited explosive substance from said venting means.
15. Apparatus of claim 13 further comprising a unit of ammunition having a casing, closed at a first end with a base, having said container situated inside said" casing, having munition substance with explosive properties subject to ignition by vented said ignited explosive substance, and having a projectile closing second end of said casing, wherein said projectile is initially moved by said piston upon ignition of said explosive substance thereby increasing volume of said casing wherein said munition substance is situated, and wherein said projectile is further and more rapidly moved from said second end beyond said casing at time of said ignition of said munition substance due to said vented ignited explosive substance.
16. A method for compensating ballistic performance according to temperature comprising the steps of: containing a first substance within a first volume; containing a second substance within a second volume; igniting said first substance which results in a first pressure according.to an ambient temperature of said first and second substances prior to said igniting; expanding said first volume according to said
' first pressure; expanding said second volume according to said first volume; and igniting said second substance which results in a second pressure according to said ambient temperature and said second volume wherein said second pressure is substantially constant for any given said ambient temperature due to said expanding second volume according to said first volume.
17. Method of claim 16 wherein said igniting said second substance results in propelling a projectile at a velocity proportional to said second pressure.
18. Method of claim 17 wherein said igniting said second substance is caused by venting ignited said first substance from said first volume into said second volume.
19. Method of claim 18 wherein: said containing said first substance is performed with a cylindrical container having a closed end, having an igniter, having an open end blocked with a piston moveable along longitudinal axis of said cylindrical container, and having venting ports for said venting"ignited . said first substance; said containing said second substance is performed with a casing having one closed end, having said cylindrical container mounted inside of said casing at said closed end, and having an open end blocked with a projectile moveable along longitudinal axis of said casing; said expanding said first volume is performed by said first pressure moving said . piston of said cylindrical container toward said open end of said container; and said expanding said second volume is performed by a pushing by said piston of said moveable projectile in a direction away from said casing.
20. Method of claim 19 wherein said pushing by said piston is restricted by stopping means, situated at said open end of said cylindrical container, for limiting distance of movement of said piston from said closed end toward said open end of said container.
21. Method of claim 20 wherein said pushing of said moveable projectile is facilitated by slots in wall of said cylindrical container along longitudinal axis of said cylindrical container and by a fitting of fins of said projectile in said slots for achieving greater distance of said pushing of said projectile without increasing length of said casing.
PCT/US1988/000475 1987-04-23 1988-02-19 Propellant case with temperature compensating ballistic control WO1988008510A1 (en)

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Application Number Priority Date Filing Date Title
US4149987A 1987-04-23 1987-04-23
US041,499 1987-04-23

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2679994A1 (en) * 1991-07-31 1993-02-05 Giat Ind Sa Device for igniting the propulsive charge of a munition, especially a telescoped munition, and munition initiated by such an igniting device
US6257148B1 (en) * 1997-01-24 2001-07-10 Patria Vammas Oy Arrangement for supporting mortar shell into barrel

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1310607A (en) * 1969-04-19 1973-03-21 Lutz E Caseless ammunition
US3977324A (en) * 1964-01-13 1976-08-31 The United States Of America As Represented By The Secretary Of The Army Sabotless micro projectile
GB1465550A (en) * 1973-10-10 1977-02-23 Valinor Anstalt Projectile launching device
US4063486A (en) * 1974-05-13 1977-12-20 General Electric Company Liquid propellant weapon system
GB2018405A (en) * 1978-04-07 1979-10-17 Ford Aerospace & Communication Ammunition of said and method of firing a projectile of said round
US4335657A (en) * 1980-08-13 1982-06-22 Ford Aerospace & Communications Corp. Ammunition round with retained piston

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3977324A (en) * 1964-01-13 1976-08-31 The United States Of America As Represented By The Secretary Of The Army Sabotless micro projectile
GB1310607A (en) * 1969-04-19 1973-03-21 Lutz E Caseless ammunition
GB1465550A (en) * 1973-10-10 1977-02-23 Valinor Anstalt Projectile launching device
US4063486A (en) * 1974-05-13 1977-12-20 General Electric Company Liquid propellant weapon system
GB2018405A (en) * 1978-04-07 1979-10-17 Ford Aerospace & Communication Ammunition of said and method of firing a projectile of said round
US4335657A (en) * 1980-08-13 1982-06-22 Ford Aerospace & Communications Corp. Ammunition round with retained piston

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2679994A1 (en) * 1991-07-31 1993-02-05 Giat Ind Sa Device for igniting the propulsive charge of a munition, especially a telescoped munition, and munition initiated by such an igniting device
US5192829A (en) * 1991-07-31 1993-03-09 Giat Industries Initiation device for the propulsive charge of ammunition, for example telescoped ammunition, and ammunition ignited by such an ignition device
US6257148B1 (en) * 1997-01-24 2001-07-10 Patria Vammas Oy Arrangement for supporting mortar shell into barrel

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