In-line annular piston fixed bolt regenerative liquid propellant gun

• US 4,523,508 A
• Filed: 11/02/1983
• Issued: 06/18/1985
• Est. Priority Date: 11/02/1983
• Status: Expired due to Fees

• Current Assignee: General Dynamics Armament Systems, Inc. (General Dynamics Corporation)
• Original Assignee: General Electric Company
• Inventors: Mayer, Robert E., West, Herbert J., Magoon, Inder K.
• Primary Examiner(s): BROWN, DAVID
• Application Number:
  US06/547,959
• Time in Patent Office: 594 Days
• Field of Search: 89/7, 89/8, 89/11, 89/1 R
• US Class Current: 89/7
• CPC Class Codes: F41A 1/04 Missile propulsion using the combustion of a liquid, loose powder or gaseous fuel, e.g. hypergolic fuel

Abstract

A regenerative liquid propellant gun structure in which the differential area piston is annular, having a peripheral cylindrical skirt extending away from the combustion chamber to define a propellant reservoir, and has an aperture permitting overrunning of a fixed bolt. The fixed bolt is shaped to define with the edge of the aperture a variable annual orifice for propellant injection as the piston moves. There is a second free piston overrunning the bolt and mating with the inside of the differential area piston to complete and provide for emptying of the reservoir. The structure also contains a spring to allow components to move responsive to increased combustion chamber pressure to provide for an initial movement of differential area piston relative to the bolt to start propellant injection and a fluid pressure means for movement of pistons after firings to facilitate reloading.

Claims

1. In a direct injection regenerative liquid propellant gun structure having a breech casing containing a breech bore attachable at the forward end to a gun barrel and constituting a breech end at the other, the combination of:

a. a hollow differential area piston having an annular discoidal head moveably journaled in the bore to define with said casing a variable capacity combustion chamber in the forward end of said bore and having a cylindrical skirt extending from the outer portion of said head rearwardly to define an included propellant reservoir, the area of said head exposed to said combustion chamber being larger than the area of said head exposed to said reservoir; and

b. an axial bolt fixed in said bore by supporting means and extending through said reservoir and through the hole in said annular discoidal head, said bolt being generally cylindrical with a base portion, a terminal nose portion journaled into the hole in said annular discoidal head when said head is in its forward most position to preclude flow of a liquid through said hole from said reservoir to said combustion chamber and an intermediate portion between said base and nose portions, said intermediate portion having a shaped surface causing one or more spaces to occur between said bolt and said annular discoidal head as said head moves rearwardly from its forward most position to permit a flow of liquid through said hole from said reservoir to said combustion chamber.

2. The gun structure of claim 1 wherein:

said shaped intermediate portion of said bolt is generally cylindrical with one or more cut away portions running longitudinally of said bolt;

whereby, during firing, propellant will be injected from said reservoir through said hole into said combustion chamber in one or more streams.

3. The gun structure of claim 2 wherein:

the number and spacing of the plurality of cut away portions are selected to limit acoustic resonance whereby acoustic resonance is limited.

4. The gun structure of claim 1 wherein:

said shaped intermediate portion of said bolt is a generally cylindrical portion having reduced radii;

whereby said one or more spaces between said bolt and said annular discoidal head is an annulus.

5. The gun structure of claim 4 wherein:

said shaped portion of said bolt having reduced radii has a plurality of radii which define a surface which will cause said annulus to be of a size at each piston position as required to produce a predetermined flow rate during piston movement;

whereby, when the gun is operated, propellant will be injected from said reservoir into said combustion chamber in an annular sheet which changes in thickness during piston travel.

6. The gun structure of claim 5 wherein:

said shaped portion is also scalloped;

whereby said annular sheet of propellant is varied in thickness around its extent.

7. The gun structure of claim 1 further comprising the combination of:

c. a second piston located in said breech bore between said annular hollow piston and said breech end, said second piston is a free piston having a forward portion configured for mating reception within said annular hollow piston to constitute a moveable rear wall to said propellant reservoir, a rear portion journaled in said breech bore and an axial bore through which said bolt extends;

d. sealing means cooperating with said nose portion of said bolt and said annular discoidal cylinder head to facilitate seating of said head on said nose portion and precluding flow of liquid propellant as long as said head is seated;

e. force transfer means for moving said second piston forward to mating position within said hollow piston and for moving said hollow piston forward to seat on said nose portion; and

f. conduit means for introducing a liquid propellant between said pistons to create and fill said propellant reservoir by forcing said second piston rearwardly in response to introduction of said propellant;

whereby said reservoir can be filled by reservoir expansion rather than by displacement of another substance.

8. The gun structure improvement of claim 7 wherein:

said sealing means cooperating to facilitate seating of said head on said nose portion is caused to leak by pressure in the combustion chamber created by the firing of an ignition charge in said combustion chamber.

9. The gun structure improvement of claim 7 wherein:

said shaped intermediate portion of said bolt is generally cylindrical with one or more longitudinal cut away portions,

whereby during firing, propellant will be injected from said reservoir through said hole into said combustion chamber in one or more streams.

10. The gun structure improvement of claim 9 wherein:

the number and spacing of said plurality of longitudinal cut away portions are selected to limit acoustic resonance.

11. The gun structure of claim 7 wherein:

said shaped intermediate portion of said bolt is a generally cylindrical portion having reduced radii;

whereby said one or more spaces between said bolt and said annular discoidal head is an annulus,

12. The gun structure improvement of claim 11 wherein:

said shaped portion of said bolt having reduced radii has a plurality of radii which define a surface which will cause said annulus to be of a size at each position of said differential area piston to produce a predetermined flow rate and pattern of propellant.

whereby, when the gun is operated, propellant will be injected from said reservoir through said hole into said combustion chamber in an annular sheet of a thickness determined to produce the desired ballistics.

13. The gun structure improvement of claim 12 wherein:

said shaped portion is also scalloped;

whereby said annular sheet of propellant is of nonuniform thickness around it.

14. An annular piston breech assembly for a direct injection regenerative liquid propellant gun having a breech casing containing a breech bore having a forward end for joining to a gun barrel and a breech end comprising:

a. an annular hollow differential area piston having an annular discoidal head moveably journaled in the breech bore, defining with said casing a variable capacity combustion chamber in the forward end of said bore and having a cylindrical skirt extending from the outer portion of said head rearwardly defining an including propellant reservoir, the area of said head exposed to said combustion chamber being larger than the area of said head exposed to said reservoir,

b. a second piston located in said breech bore between said annular hollow piston and said breech end, said second piston having a forward portion configured for mating reception within said annular hollow piston to constitute a moveable rear wall to said propellant reservoir and an axial bore;

c. an axial bolt fixed in said bore and extending through said second piston, said reservoir and said annular discoidal head, said bolt being generally cylindrical with a base portion, a terminal nose portion journaled into the hole in said annular discoidal head when said head is in its forward most position to preclude flow of a liquid from said reservoir to said combustion chamber and an intermediate portion running rearwardly from said nose portion, said intermediate portion having a shaped surface causing one or more spaces to occur between said bolt and said annular discoidal head to permit a flow of liquid through said hole from said reservoir to said combustion chamber as said head is driven rearwardly from its forward most position by combustion pressures overrunning said intermediate portion of said bolt;

e. force means for moving said second piston forward to mating position within said hollow piston and thereafter moving both said pistons forward to seat said hollow piston on said nose portion of said bolt;

f. valved supply conduit means for introducing a liquid propellant between said pistons to create and fill said propellant reservoir by forcing said second piston rearwardly in response to introduction of said propellant and for maintaining said propellant in said reservoir against back pressure created by firing;

g. sealing means cooperating with said nose portion of said bolt and said annular discoidal cylinder head to facilitate seating of said head on said nose portion and precluding flow of liquid propellant as long as said head remains seated, said sealing means being disruptable by a predetermined pressure in said combustion chamber to permit flow of liquid propellant from said reservoir to said combustion chamber; and

h. igniter means in said combustion chamber for creating an initial pressurization of the combustion chamber and igniting liquid propellant forced from the reservoir into said combustion chamber;

whereby activation of the igniter means causes a combustion chamber pressure which ignites a flow of propellant from reservoir to combustion chamber.

whereby the propellant in the reservoir will be forced from the reservoir by the differential area piston with a flow rate and pattern as predetermined by the configuration of said intermediate portion of said bolt.

15. The annular piston breech assembly of claim 14 wherein:

said cylindrical skirt of said annular hollow differential area piston extending from outer portion of said discoidal head within said breech bore is spaced from the breech casing wall bounding the breech bore to define a cylindro-annular space between said skirt and said casing wall defined at one end by the rim of said discoidal head,

said assembly also includes a mechanical barrier means on said breech casing wall extending into said breech bore bearing on said skirt closing the end of said cylindro-annular space remote from said discoidal head, and valved conduit means communicating with said cylindro-annular space for charging said space with a fluid substance,

whereby said skirt is supported against deformation during firing by equalizing the pressure on both sides of said skirt, and

whereby said substance is pumped past said rim into said combustion chamber.

16. The annular piston breech assembly of claim 14 wherein:

said bolt includes valved relief conduit means for removing fluid from said reservoir through said breech during the process of filling the reservoir with liquid propellant.

17. The annular piston breech assembly of claim 14 wherein:

said shaped intermediate portion of said bolt is generally cylindrical with one or more longitudinal cut away portions,

whereby, when operated, propellant will be injected from said reservoir into said combustion chamber in a stream from each said cut away portion.

18. The annular piston breech assembly of claim 14 wherein:

said sealing means cooperating to facilitate seating of said head on said nose portion has a predetermined resistance to pressure which is caused to leak by pressure in the combustion chamber created by the firing of an ignition charge in said combustion chamber.

19. The annular piston breech assembly of claim 14 wherein:

said shaped intermediate portion of said bolt is a portion having reduced radii,

whereby said one or more spaces between said bolt and said annular discoidal head is an annulus.

20. The annular piston breech assembly of claim 19 wherein:

said shaped portion of said bolt having reduced radii is a contoured portion having a plurality of radii,

whereby said annulus changes in size as said differential area piston is driven by combustion pressure,

whereby, when the gun is operated, propellant will be injected from said reservoir into said combustion chamber in an annular sheet which changes in thickness during movement of said annular piston to vary the rate of injection to implement a predetermined plan.

21. In a direct injection regenerative liquid propellant gun structure having a breech casing defining a breech bore having a barrel end and a breech end, the improvement comprising the combination of:

a shaped member within said vore extending from a base portion near said breech end to a nose portion nearer said barrel end of said bore;

mechanical means for supporting said shaped member and fixing said member with respect to said casing;

a differential area piston dividing the space in said breech bore between a combustion chamber at said barrel end on one side of said piston and a propellant reservoir on the second side of said piston, said differential area piston having a cut out portion for overrunning said shaped member as said piston moves along said shaped member from a gun charged postion to a discharged position in response to pressure created in said combustion chamber to compress said reservoir to force propellant from said reservoir between said shaped member and the edge of said cut out portion of said piston,

said shaped member being shaped along a substantial portion of its extent within said reservoir so as to define one or more spaces between said member and said edge of said cut out portion, the shape and dimension of said one or more spaces at any piston position being a function of the shape of said shaped member,

whereby the quantity, flow rate and flow pattern of propellant injected into the combustion chamber can be programmed by establishing the shape of the shaped member; and

said shaped member is elongated, is spaced from said casing so as to be surrounded by material in said reservoir, and extends sufficiently toward said barrel end of said casing so that said nose portion is within said cut out portion of said piston when said piston is in its gun charged position;

said mechanical means supports said shaped member by its base portion;

said nose portion of said shaped member conforming to said cut out portion of said piston so as to reduce said spaces between the two to zero;

whereby when said piston is in a gun charged position, the interface between said shaped member and said piston precludes flow of propellant to said combustion chamber; and

whereby said one or more spaces between said shaped member and said edge of said cut out portion meters propellant flowing from said reservoir to said combustion chamber as said piston is driven from its gun charged position to its discharged position; and

said shaped member is generally cylindrical and has a reduced turned portion of one or more radii extending from said nose portion toward said base portion;

said cut out portion of said piston is defined by a generally cylindrical surface of said piston fitting the unreduced nose portion of said shaped member;

whereby said one or more spaces comprise an annular space defined by said reduced portion and said surface defining said cut out portion;

whereby the flow of propellant from reservoir to combustion chamber is in the form of an annular sheet of thickness determined by the relationship of said radii to the size of the unturned portion of said shaped member.

22. The gun structure improvement of claim 21 wherein:

said differential area piston is an annular piston having a discoidal head containing said cut out portion and a cylindrical skirt portion extending from proximate the rim of said head toward said breech end of said bore, said annular piston defining said propellant reservoir as an open ended cylinder.

23. The gun structure improvement of claim 22 further comprising:

d. a second piston journaled on said shaped member having a forward portion journaled into said annular piston defining the remaining end of the cylindrical reservoir, the forward portion of said second piston having a shape mating to the inside of said differential area piston so that the reservoir can be substantially emptied;

e. conduit means for filling said reservoir with a liquid monopropellant; and

f. igniter means in said combustion chamber.

24. The gun structure improvement of claim 21 wherein:

said annular space is determined by a reduced turned portion having a plurality of radii which cause said reduced portion to have a contoured surface;

whereby the thickness of said annular sheet changes according to the contoured surface during travel of said piston from its gun charged position to gun discharged position during firing.

25. The gun structure improvement of claim 24 wherein:

said differential area piston is an annular piston having a discoidal head containing said cut out portion and a cylindrical skirt portion extending from proximate the rim of said head toward said breech end of said bore, said annular piston defining said propellant reservoir as an open ended cylinder.

26. The gun structure of claim 25 further comprising:

d. a second piston journaled on said shaped member having a base portion journaled into said breech bore and a forward portion journaled into said annular piston defining the remaining end of the cylindrical reservoir, the forward portion of said second piston having a shape mating to the inside of said differential area piston so that the reservoir can be substantially emptied;

e. cooperating mechanical means mounted on the exterior of said skirt and on the inside of said casing wall for holding and for dispensing into said combustion chamber, responsive to movement of said differential area piston during firing, materials facilitating lubrication, heat transfer, and cleaning;

f. conduit means for filling said reservoir with a liquid monopropellant; and

g. igniter means in said combustion chamber.

27. In a direct injection regenerative liquid propellant gun structure having a breech casing defining a breech bore having a barrel end an a breech end, the improvement comprising the combination of:

a shaped member within said bore extending from a base portion near said breech end to a nose portion nearer said barrel end of said bore;

mechanical means for supporting said shaped member and fixing said member with respect to said casing;

a differential area piston dividing the space in said breech bore between a combustion chamber at said barrel end on one side of said piston and a propellant reservoir on the second side of said piston, said differential area piston having a cut out portion for overrunning said shaped member as said piston moves along said shaped member from a gun charged position to a discharged position in response to pressure created in said combustion chamber to compress said reservoir to force propellant from said reservoir between said shaped member and the edge of said cut out portion of said piston,

said shaped member being shaped along a substantial portion of its extent within said reservoir so as to define one or more spaces between said member and said edge of said cut out portion, the shape and dimension of said one or more spaces at any piston position being a function of the shape of said shaped member,

whereby the quantity, flow rate and flow pattern of propellant injected into the combustion chamber can be programmed by establishing the shape of the shaped member; and

said shaped member is elongated, is spaced from said casing so as to be surrounded by material in said reservoir, and extends sufficiently toward said barrel end of said casing so that said nose portion is within said cut out portion of said piston when said piston is in its gun charged position;

said mechanical means supports said shaped member by its base portion;

said nose portion of said shaped member conforming to said cut out portion of said piston so as to reduce said spaces between the two to zero;

whereby when said piston is in a gun charged position, the interface between said shaped member and said piston precludes flow of propellant to said combustion chamber; and

whereby said one or more spaces between said shaped member and said edge of said cut out portion meters propellant flowing from said reservoir to said combustion chamber as said piston is driven from its gun charged position to its discharged position; and

said shaped member is generally cylindrical and has one or more recesses in its surface between said nose portion and its base portion;

said cut out portion of said piston is defined by a generally cylindrical surface of said piston fitting the surface of the generally cylindrical shaped member;

whereby said one or more spaces are defined by said one or more recesses;

whereby the flow of propellant from reservoir into said combustion chamber is in the form of one or more streams corresponding in number and size to said recesses; and

said one or more recesses comprise a plurality of elongated recesses spaced around the surface of said shaped member;

whereby said flow of propellant is in the form of a plurality of discrete streams spaced around said nose of said shaped member within said combustion chamber; and

said elongated recesses each vary in one or more of its dimensions over its length;

whereby said plurality of streams each vary in flow rate as said piston travels; and

said differential area piston is an annular piston having a discoidal head containing said cut out portion and a cylindrical skirt portion extending from proximate the rim of said head toward said breech end of said bore, said annular piston defining said propellant reservoir as an open ended cylinder.

28. The gun structure of claim 27 further comprising:

d. a second piston journaled on said shaped member having a base portion journaled into said breech bore and a forward portion journaled into said annular piston defining the remaining end of the cylindrical reservoir, the forward portion of said second piston having a shape mating to the inside of said differential area piston so that the reservoir can be completely emptied;

e. conduit means for filling said reservoir with a liquid monopropellant; and

f. igniter means in said combustion chamber.

29. The gun structure of claim 28 further comprising:

g. cooperating mechanical means on the exterior of said skirt and on the inside of said casing wall defining a dispenser for holding and for dispensing into said combustion chamber responsive to movement of said differential area piston during firing, materials facilitating lubrication, heat transfer, and cleaning; and

h. hydraulic conduit means communicating with said dispenser for charging said space with a fluid substance to support and reinforce said skirt against deformation during firing by transfer of forces on said reservoir to said casing and for dispensing said materials into said combustion chamber.

30. In a direct injection regenerative liquid propellant gun structure having a breech casing defining a breech bore having a barrel end and a breech end, the improvement comprising the combination of:

a shaped member within said bore extending from a base portion near said breech end to a nose portion nearer said barrel end of said bore;

mechanical means for supporting said shaped member and fixing said member with respect to said casing;

a differential area piston dividing the space in said breech bore between a combustion chamber at said barrel end on one side of said piston and a propellant reservoir on the second side of said piston, said differential area piston having a cut out portion for overrunning said shaped member as said piston moves along said shaped member from a gun charge position to a discharged position in response to pressure created in said combustion chamber to compress said reservoir to force propellant from said reservoir between said shaped member and the edge of said cut out portion of said piston;

said shaped member being shaped along a substantial portion of its extent within said reservoir so as to define one or more spaces between said member and said edge of said cut out portion, the shape and dimension of said one or more spaces at any piston position being a function of the shape of said shaped member;

whereby the quantity, flow rate and flow pattern of propellant injected into the combustion chamber can be programmed by establishing the shape of the shaped member;

said shaped member is elongated, is spaced from said casing so as to be surrounded by material in said reservoir, and extends sufficiently toward said barrel end of said casing so that said nose portion is within said cut out portion of said piston when said piston is in its gun charged position;

said mechanical means supports said shaped member by its base portion;

said nose portion of said shaped member conforming to said cut put portion of said piston so as to reduce said spaces between the two to zero;

whereby when said piston is in a gun charged position, the interface between said shaped member and said piston precludes flow of propellant to said combustion chamber; and

whereby said one or more spaces between said shaped member and said edge of said cut out portion meters propellant flowing from said reservoir to said combustion chamber as said piston is driven from its gun charged position to its discharged position;

said shaped member is generally cylindrical and has one or more recesses in its surface between said nose portion and its base portion;

said cut out portion of said piston is defined by a generally cylindrical surface of said piston fitting the surface of the generally cylindrical shaped member;

whereby said one or more spaces are defined by said one or more recesses;

whereby the flow of propellant from reservoir into said combustion chamber is in the form of one or more streams corresponding in number and size to said recesses; and

said one or more recesses comprise a plurality of elongated recesses spaced around the surface of said shaped member;

whereby said flow of propellant is in the form of a plurality of discrete streams spaced around said nose of said shaped member within said combustion chamber; and

said elongated recesses each vary in one or more of its dimensions over its length;

whereby said plurality of streams each vary in flow rate as said piston travels; and

there are a sufficient number of said elongated recesses to cause said streams to join as the propellant disperses to approximate an annular sheet of propellant of nonuniform thickness.

31. In a direct injection regenerative liquid propellant gun structure in which a differential area annular piston journaled in a breech bore in a casing is forced away from the barrel end of the breech bore by pressure in a combustion chamber during firing to exert pressure on a propellant reservoir also in said bore, the improvement comprising:

material holding and dispensing means interposed between said piston and said casing for injecting a material into the combustion chamber responsive to movement of the piston during firing; and

said material holding and dispensing means comprising;

a first mechanical means on the interior surface of said casing;

a second mechanical means on the exterior of said piston;

a space between said piston and said bore between said mechanical means defining a variable capacity container; and

conduit means for introducing a fluid to said container,

said mechanical means being separated longitudinally of said bore so that, during travel of said piston during firing, said container is substantially reduced.

33. The improvement of claim 31 wherein:

said first mechanical means is a more effective barrier to passage of a fluid substance in said container than is said second mechanical means,

whereby said container may be used as a dispenser to force a material past said second mechanical means to said combustion chamber during firing.

34. The improvement of claim 31 wherein:

said first mechanical means includes a ring set into a groove in said casing;

said second mechanical means is the rim of the head of said piston;

said space is defined in part by a portion of said piston having a smaller diameter than the rim of said piston head.

32. In a direct injection regenerative liquid propellant gun structure having a breech casing defining a breech bore having a barrel end and a breech end, the improvement comprising the combination of:

a breech end bore obturator, which is releasably fixed to said casing;

a shaped member within said bore extending from a base portion near said breech end to a nose portion nearer said barrel end of said bore;

mechanical means supporting said shaped member and not-releasably fixing said member to said obturator;

a differential area piston dividing the space in said breech bore between a combustion chamber at said barrel end on one side of said piston and a propellant reservoir on the second side of said piston, said differential area piston having a cut out portion for overrunning said shaped member as said piston moves along said shaped member from a gun charged position to a discharged position in response to pressure created in said combustion chamber to compress said reservoir to force propellant from said reservoir between said shaped member and edge of said cut out portion of said piston,

said shaped member being shaped along a substantial portion of its extent within said reservoir so as to define one or more spaces between said member and said edge of said cut out portion, the shape and dimension of said one or more spaces at any piston position being a function of the shape of said shaped member,

whereby the quantity, flow rate nd flow pattern of propellant injected into the combustion chamber can be programmed by establishing the shape of the shaped member.

35. In a direct injection regenerative liquid propellant gun structure having a breech casing defining a breech bore having a barrel end and a breech end, the improvement comprising the combination of:

a breech end bore obturator which is releasably fixed to said casing;

a shaped member within said bore extending from a base portion near said breech end to a nose portion nearer said barrel end of said bore;

a mechanical means supporting said shaped member and not-releasably fixing said member to said obturator;

a differential area piston dividing the space in said breech bore between a combustion chamber at said barrel end on one side of said piston and a propellant reservoir on the second side of said piston, said differential area piston having a cut out portion for overrunning said shaped member as said piston moves along said shaped member from a gun charged position to a discharged position in response to pressure created in said combustion chamber to compress said reservoir to force propellant from said reservoir between said shaped member and the edge of said cut out portion of said piston,

said shaped member being shaped along a substantial portion of its extent within said reservoir so as to define one or more spaces between said member and said edge of said cut out portion, the shape and dimension of said one or more spaces at any piston position being a function of the shape of said shaped member,

whereby the quantity, flow rate and flow pattern of propellant injected into the combustion chamber can be programmed by establishing the shape of the shaped member.

said shaped member is elongated, is spaced from said casing so as to be surrounded by material in said reservoir, and extends sufficiently toward said barrel end of said casing so that said nose portion is within said cut out portion of said piston when said piston is in its gun charged position;

said mechanical means supports said shaped member by its base portion;

said nose portion of said shaped member conforming to said cut out portion of said piston so as to reduce said spaces between the two to zero;

whereby when said piston is in a gun charged position, the interface between said shaped member and said piston precludes flow of propellant to said combustion chamber; and

whereby said one or more spaces between said shaped member and said edge of said cut out portion meters propellant flowing from said reservoir to said combustion chamber as said piston is driven from its gun charged position to its discharged position.