EP0321102A2 - Canon à charge propulsive liquide - Google Patents

Canon à charge propulsive liquide Download PDF

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Publication number
EP0321102A2
EP0321102A2 EP88311043A EP88311043A EP0321102A2 EP 0321102 A2 EP0321102 A2 EP 0321102A2 EP 88311043 A EP88311043 A EP 88311043A EP 88311043 A EP88311043 A EP 88311043A EP 0321102 A2 EP0321102 A2 EP 0321102A2
Authority
EP
European Patent Office
Prior art keywords
bore
gun
aft
liquid propellant
projectile
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP88311043A
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German (de)
English (en)
Other versions
EP0321102B1 (fr
EP0321102A3 (en
Inventor
Melvin John Bulman
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
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
Priority claimed from US07/150,350 external-priority patent/US4852459A/en
Priority claimed from US07/150,351 external-priority patent/US4852458A/en
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP0321102A2 publication Critical patent/EP0321102A2/fr
Publication of EP0321102A3 publication Critical patent/EP0321102A3/en
Priority claimed from CA000616678A external-priority patent/CA1333669C/fr
Application granted granted Critical
Publication of EP0321102B1 publication Critical patent/EP0321102B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A1/00—Missile propulsion characterised by the use of explosive or combustible propellant charges
    • F41A1/04—Missile propulsion using the combustion of a liquid, loose powder or gaseous fuel, e.g. hypergolic fuel

Definitions

  • This invention relates to weapon systems employing a liquid propellant, and particularly to such systems wherein the propellant is progressively combusted aft of the projectile as the projectile advances along the firing bore, i.e. a traveling charge system.
  • This invention also relates to such a system utilizing an initial source of combustion gas to provide an initial acceleration to the projectile and its traveling charge.
  • the accelerating force on the projectile and the traveling charge is made up of two terms.
  • the first term can be referred to as the "pressure” term, where the combustion of the charge produces an elevated pressure at the exit of the combustion zone.
  • the second term can be referred to as the “thrust” term, where the thrust is the result of the momentum of the combustion gas exiting the combustion zone:
  • the total thrust divided by the mass consumption rate is referred to as the "specific impulse" (a rocket term).It can be shown that this parameter is a maximum when the gas velocity is greatest. Since this combustion is taking place in a constant area duct (Rayleigh flow) the maximum velocity is the sonic velocity. Under these conditions, typically 200 pounds of total thrust is generated for each pound of propellant consumed per second. For a 30mm weapon to produce 50,000 lbs. of thrust, a consumption rate of 250 lb./sec. is required. This consumption rate requires a linear burn rate of approximately 300 ft./sec. Since normal solid propellants only burn at approximately 1 foot per second at gun pressures, it is apparent why the concept of solid propellant traveling charge propulsion has yet to be made workable.
  • FIG 3A shows a typical bulk loaded liquid propellant Gun prior to ignition.
  • the cylindrical chamber is completely filled with liquid propellant.
  • the forward end of the chamber is closed by the base of the projectile.
  • the projectile is seated in the forcing cone of the barrel.
  • the rear of the chamber is closed by a bolt containing the igniter.
  • a jet of hot gases emerges from the igniter vent (see FIG 3B).
  • This jet as it enters the chamber must displace propellant in the chamber. Since the chamber is initially constant in volume, this displaced propellant must compress the remaining liquid. Even a small compression will produce a large pressure rise in the liquid. For example, if the igniter jet occupies 1% of the chamber volume, a pressure rise of several thousand pounds per square inch results.
  • Ignition of the main charge of liquid propellant occurs on the surface of this expanding bubble of hot igniter gases.
  • the projectile starts moving when the gas bubble has grown to no more than a few percent of the chamber volume with a nominal surface area which is less than the area of the base of the projectile.
  • the actual burning surface In order to sustain a rising pressure in the face of the rapid acceleration of the projectile, the actual burning surface must be 100-1000 times the nominal value. This is achieved in the bulk loaded cycle by the violent interaction between the igniter jet and the liquid propellant.
  • the shearing of the liquid surface by the penetration of the igniter jet produces a rough surface akin to ocean waves on a windy day (the Helmholtz instability - see FIGS 3C and 3D).
  • FIG 4 shows a typical bulk loaded pressure time curve.
  • the present invention provides a bulk loaded, liquid propellant gun system having controlled ignition and combustion which provide an improved traveling charge to propel the projectile.
  • liquid propellant gun system with an improved control over ignition and combustion which avoids the strong feedback present in the conventional bulk loaded cycle.
  • a feature of this invention is the provision of a liquid propellant gun system having a travelling charge which is ignited after both such charge and the projectile have been accelerated forwardly.
  • This invention may be embodied in what may be denominated a Fractional Travelling Charge [FTC] propulsion system.
  • FTC Fractional Travelling Charge
  • a bulk loaded liquid propellant travelling charge and the respective projectile are both provided with an initial acceler­ation and the charge is not ignited until both the charge and projectile have achieved significant velocity. This delayed ignition provides two benefits:
  • the initial acceleration of the combined masses of the traveling charge and the projectile can be provided by any convenient means.
  • liquid propellant If liquid propellant is chosen, it may be utilized in a regenerative injection liquid propellant combuster built into the overall gun system. This combuster is made of a size adequate to accelerate the combined masses of both the traveling charge and the projectile to a velocity of approximately 1 km/sec before ignition of the traveling charge. This requires the volume of the initial charge to be of the same order of magnitude as the volume of the traveling charge. (The traveling charge will normally be between 1/3 and 2/3 of the total charge depending on the performance level of the gun system.)
  • FIGS 5 through 12 A first embodiment of this invention is shown in FIGS 5 through 12.
  • This first embodiment is a gun having a totally integrated, two stage propulsion system incorporating a regeneratively injected first stage and a traveling charge second stage.
  • the gun includes a breech 10 which is fixed, as by mutual threads 12, to a gun barrel 14.
  • the barrel has an aft chamber 16, an intermediate forcing cone 18, and a forward, not necessarily rifled, bore 20.
  • the breech 10 has an aperture 22 which may be closed by a gun bolt 24 having a truncated cone forward portion.
  • the breech has a groove 26 and the bolt has a groove 28 which may mutually receive a guillotine type lock 30 to lock the bolt to the breech.
  • a cam controlled iris-slide of the type disclosed in US 3,772,959, issued Nov. 20, 1973 to D. P. Tassie, may be utilized.
  • An annular fill valve slide 32 is telescopically journaled on the breech end portion 14A of the barrel 14, and an annular regenerative piston 34 is telescopically journaled on the slide 32.
  • Liquid propellant may be provided into the gun from a supply 36, through a fill valve 38, through manifold 40, through a plurality of bores 42, through a manifold 44, and through a plurality of longitudinal bores 48.
  • An ignition device 50 may be mounted through the breech 10.
  • FIG 5 shows the loading of a projectile 52, having a driving band 54, through the aperture 22 by the gun bolt 24.
  • FIG 6 shows the bolt advancing forwardly and ramming the projectile into the chamber 16.
  • the fill valve 38 opens to admit liquid propellant under pressure from the supply 36, through the manifold 40 and the bores 42, displacing the slide 32 and the piston 34 aftwardly, through the manifold 44 and the bores 48 and through the interface gap between the aft face of the portion 14A and the forward face of the head of the fill valve slide 32 into the cavity defined between the projectile 52 and the forward end of the gun bolt 24.
  • the size of the gap is limited by a flange 32A on the valve 32 abuting a step 10A in the breech.
  • FIG 7 shows the flow of propellant displacing the projectile forwardly in the chamber 16 to lodge the band 54 against the forcing cone 18; and displacing the regenerative piston 34 aft.
  • the bolt 24 is displaced aftwardly and is locked to the breech 10 by the guillotine lock 30. Thereafter, the valve 38 is closed.
  • FIG 8 shows the gun ready to fire.
  • the traveling charge is that volume of liquid propellant substantially contained within the chamber 16 aft of the projectile.
  • the stationary (or initial) charge is that volume of liquid propellant substantially contained between the head of the regenerative piston 34 and the head of the fill valve slide 32.
  • FIG 9 shows the gun after ignition, provided by the ignition device 50, which has generated combustion gas in the combustion chamber 56 aft of the head of the regenerative piston 34, to push the piston forwardly against the initial charge contained between the heads, to generate increasing pressure in the stationary charge and the traveling charge.
  • the head of the piston moves forwardly away from the cone of the gun bolt head it opens up an annular gap 56A which serves as injection port for propellant to flow aftwardly into the combustion chamber 56.
  • This regenerative injection is a result of the forward face of the head of the piston 34 having a smaller transverse cross-sectional area than the aft face of the head, to provide a differential, forwardly directed force on the head.
  • This differential force generates a high pressure on the stationary charge which flows aftwardly, through the injection port 56A into the combustion chamber 56 to sustain, or to increase, the combustion gas pressure.
  • the pressure on the traveling charge exceeds the shot start pressure (i.e. the pressure to engrave the band 54) the traveling charge and the projectile begin to accelerate past the forcing cone and beyond under the hydraulic influence of the regenerative first stage.
  • the two volumes fore and aft of the head of the piston 34 and the gap 56A interconnecting them may be considered a complex, self feeding, self limiting, combustion engine, i.e., a means for providing combustion.
  • FIG 10 shows the head of the piston 34 near the end of its forward stroke towards the head of the fill valve slide 32.
  • the piston is decelerated by the flow exit area resulting from its shape and closing proximity to the head of the slide. This deceleration reduces the rate of flow of propellant from the stationary charge into the chamber 16 to cause the pressure in the volume of liquid propellant in the chamber 16 to fall below the pressure in the volume of combustion gas in the combustion chamber 56.
  • This pressure differential permits the combustion gases to flow forwardly from the combustion chamber 56 through the injection port 56A into the chamber 16 to form an initial cavity 58 in the aft face of the volume of the traveling charge of liquid propellant in the chamber 16.
  • FIG 11 shows the initial cavity advancing rapidly forwardly (down-bore) as the regenerative injection stage ceases and the demand for forward flow of liquid propellant by the accelerating projectile continues. This arrangement provides an inherent delay in the start of the traveling charge stage of operation.
  • FIG 12A shows the formation of a stabilized Taylor Cavity which moves forwardly with and towards the projectile.
  • Most of the combustion occurs on the side of the cavity where the relative velocity between the gas and the liquid is high, as shown in FIG 12B.
  • Combustion here is similar to the regenerative injection combustion.
  • the combustion rate adjusts to match the injection rate as shown in FIG 12C.
  • This quasi-injection is seen in the thin sheet of liquid trailing behind the main part of the cavity. If combustion is too fast, the sheet burns out sooner, reducing the combustion surface area and the burn rate. If the burn rate is too slow, the sheet trails further behind the cavity, increasing its burning surface until equilibrium is achieved.
  • the velocity of the combustion gas increases and the pressure of the combustion gas decreases.
  • this integrated system provides an inherent delay in the ignition of the traveling charge since such ignition can not begin until after the substantial completion of the combustion of the initial, stationary charge.
  • F B 4/6 ⁇ S F D3 BORE [ ⁇ L - ⁇ G ]A
  • A Acceleration (G's)
  • G Gas Density
  • D BORE Bore Dia (ft)
  • S F Shape factor (cavity volume compared to a sphere of Bore dia)
  • V c is independent of scale.
  • FIGS 13A and 13B A second embodiment of this invention is shown in FIGS 13A and 13B.
  • This embodiment is a gun having a solid propellant first stage and a liquid propellant second stage.
  • Such a system may be referred to as a Hybrid Traveling Charge (HTC) propulsion system.
  • HTC Hybrid Traveling Charge
  • FIG 13A shows a gun having a breech 100 with a chamber 102 and a gun barrel 104 with a bore 106, and a gun bolt 108 with a firing pin 110.
  • a telescoped round of ammunition 112 is disposed in the chamber 102 which is closed by the gun bolt 108.
  • the round of ammunition comprises a case 114 with a main portion 115, a forward, tubular, return bend 116 providing a sleeve portion 118, and a base portion 120 with a bore 122 in which is fixed a primer 124.
  • the outer diameter of the main portion 115 matches the inner diameter of the chamber 102.
  • the inner diameter of the sleeve portion 118 matches the inner diameter of the bore 106.
  • a sabot 126 with a projectile 128 is disposed in the forward portion of the sleeve portion 118.
  • a cavity generator 130 is disposed in the aft portion of the sleeve portion 118.
  • a charge 131 of liquid propellant is disposed in the sleeve portion forward of the generator and around the aft portion of the sabot.
  • the intermediate portion of the sabot has an annular seal 132, and the forward portion of the sabot has a bore rider 134.
  • the cavity generator 130 is also sealed to the sleeve, all to seal the charge of liquid propellant within the case 114.
  • the interior volume between the sleeve portion 118 and the main portion 115 and the base portion 120 of the case is filled with a charge 137 of solid propellant (which may be consolidated to improve the packing efficiency).
  • the propulsion operation begins with the energization of the primer 122 by the firing pin 110 to ignite the solid propellant 137. As the pressure developed by the combustion gas rises, the gas pushes, i.e. accelerates the cavity generator 130, the sabot 126 with its projectile 128, and the captured charge of liquid propellant 131 forwardly, as a unit, into the gun bore 106.
  • a traveling charge provides improved performance when the ignition of such traveling charge is delayed until the projectile and such charge have achieved significant velocity.
  • the cavity generator 130 serves to provide the necessary delay.
  • the cavity generator prior to firing, serves to seal the rear of the liquid propellant traveling charge 131 within the case 114.
  • the generator 130 serves to isolate the traveling charge 131 from the combustion gases generated by the stationary charge 137.
  • the generator 130 has a plurality of longitudinal bores 136, each extending from a substantially flat transverse front face 140 to a substantially concave transverse aft face 142, so that the bores vary in length.
  • bores 136 are obturated respectively with a material which has a density different from the density of the generator 130 and which is resistant to movement, e.g. grease or press-fitted pins.
  • this material does obturate the bores 136.
  • the acceleration forces acting on this material serve to extrude the material forward or aftward from the generator depending on their relative densities.
  • these bores 136 are thus sequentially opened in reverse order of their respective lengths.
  • FIG 14 shows a third embodiment of this invention.
  • This embodiment is a gun which combines features of the first and second embodiments of this invention.
  • the system includes a liquid propellant, regenerative injection, first stage, a liquid propellant, traveling charge, second stage, and a cavity generator to provide a delay prior to the ignition of the second stage.
  • This gun includes a breech 200, to which is secured a gun barrel 202 having a bore 204.
  • the gun barrel has an aftwardly projecting extension 206 on which is telescopically journaled an annular fill valve 208 having a head portion 210 and a tail portion 212.
  • Telescopically journaled on the fill valve is an annular, regenerative piston 214 having a head portion 216 and a tail portion 218.
  • a supply 220 of liquid propellant under pressure is coupled via an inlet valve 222 to a manifold 224 which communicates with an annular row of longitudinal bores 226 through the barrel extension 206.
  • the bores 226 may be obturated by a snap-action valve 228 (e.g., a belleville washer) and otherwise communicate with an annular row of longitudinal bores 230 through the fill valve head portion 210.
  • a snap-action valve 228 e.g., a belleville washer
  • the inner rim 216A of its head portion is seated on an annular projection 202A of the barrel to define a pumping chamber 232 between the fill valve head portion and the regenerative piston head portion.
  • Two annular rows 234 and 236 of radial bores through the barrel extension communicate between the pumping chamber 232 and the gun barrel bore 204.
  • the aft end of the breech has an opening 238 which is closed by a gun bolt 240 whose head rotates about its longitudinal axis to lock and unlock.
  • the face of the bolt has a pair of extraction lugs 242 to engage the extractor rim 244 of a stub case 246 which carries a booster cartridge 248.
  • the case has a primer 250 opening onto a conduit which leads to a booster charge 252 opening onto a plurality of radial bores 254, which open onto a combustion chamber 255 defined by the breech 200, the piston head 216, the barrel extension 206, and the cartridge 248.
  • the gun bolt has a firing pin 256 to actuate the primer 250.
  • the gun bolt In loading the gun, the gun bolt may be withdrawn and a projectile, here shown as a rod penetrator 257A with fins carried in a sabot 257B, may be inserted. Subsequently a cavity generator 258A with a plurality of bores 258B, extending from a planar front face 260 to a concave aft face 262, and filled with an obturating medium, may be inserted.
  • the front face may have an annular bevel 264, which when aligned with the bores 234 provides access from the pumping chamber 232 to the interface between the cavity generator and the projectile.
  • the annular piston 216 may be in its aftmost position, with the surface 216a on the projection 202a.
  • the annular fill valve may be in a forward disposition.
  • the inlet valve 222 is opened to admit liquid propellant from the supply 220 under pressure into the manifold 224, through the bores 226, past the snap action valve 228, through the bores 230, into the pumping chamber 232, through the bores 234, into the interface between the cavity generator and the projectile, pushing the projectile forwardly until it is halted by the forcing cone 204A in the bore 204.
  • An interface gap is provided between the forward face of the booster cartridge and the aft face of the cavity generator by suitable means, such as conical ridges on the booster face.
  • Combustion gas passes into the interface gap between the cavity generator and the booster and acts on the aft face of the cavity generator to displace the cavity generator forwardly to close off the bores 234 and through the medium of the liquid propellant in the bore to displace the sabot with its projectile past the forcing cone 204A.
  • traveling charge of liquid propellant and sabot and projectile is accelerated forwardly along the gun barrel bore 204.
  • FIG. 15 shows a fourth embodiment of this invention.
  • This embodiment is the most elemental embodiment of this invention comprising two combustion chambers.
  • the system includes a liquid propellant, stationary combustion chamber and cavity generator and a liquid propellant, traveling combustion chamber.
  • This gun includes a breech 300 to which is secured a gun barrel 302 having a bore 304.
  • the aft end of the breech has an opening 306 which is closed by a gun bolt 308 which is locked and unlocked to the breech by suitable means such as a movable lug 310 journaled to the breech to engage an annular lug 312 integral with the bolt.
  • the forward end of the bolt 308 is formed as a truncated cone which has a channel 310 cut into it with an under cut 312 to receive the aft end of a "hold-back" or "shot-start” link 314.
  • the forward end of the link is secured to the aft end of a projectile 316 which is fitted into a sabot 318 which has an annular seal 320.
  • An annular combustion chamber 330 coaxial with the gun barrel bore 304, is provided in the breech.
  • a supply 332 of liquid propellant under pressure is coupled via an inlet valve 334 and a manifold to a pair of diametrically opposed ignition systems.
  • Each system includes a unidirectional valve 336 to an ignition chamber 338 which has a spark plug 340 and an outlet 342 coupled to the combustion chamber.
  • the combustion chamber has an annular outlet 344 having a conical shape directed into and forwardly along the gun barrel bore 304.
  • a projectile and sabot may be placed on the gun bolt by means of the link 314 and inserted through the aperture 306 into the gun barrel bore 304.
  • the link 314 permits the gun bolt to provide this function also.
  • the link may be designed to rupture when the projectile is subjected to a relatively high pressure, e.g., after ignition of the liquid propellant in the combustion chamber 330.
  • the link may be designed to rupture at a relatively low pressure, e.g., upon inletting of liquid propellant under low pressure into the gun barrel bore from the combustion chamber. In this case, after rupture of the link, the inletted propellant advances the projectile and sabot until the sabot is halted by the forcing cone 304a in the bore.
  • annular valve slide 350 is also provided.
  • This slide is coaxial with and receives the forward portion of the gun bolt and also forms the aft wall of the combustion chamber.
  • the slide is normally biased forwardly by a plurality of springs 352 so that its forwardly projecting lip 354, which forms the aft wall of an annular valve outlet 344, abuts the forward wall of the outlet to close the outlet.
  • the springs are disposed in an annular pumping chamber 356 which is coupled via a variable orifice 358 and a unidirectional valve 360 to a supply 362 of lubricant under pressure.
  • the chamber 356 is coupled, via an annular row of radial bores 364 through the slide, to an annular groove 366 in the gun bolt.
  • This initial aftward movement of the slide forces some of the lubricant from the annular groove 356 into the interface between the gun bolt and the slide to provide an initial volume of lubricant, which also serve as a seal against combustion gas, in the interface. This seal is replenished during each firing cycle of the gun.
  • the pair of spark plugs 340 are energized to ignite the liquid propellant in the ignition chambers.
  • the pair of bubbles of combustion gas respectively enlarge and ignite the liquid propellant in the combustion chamber.
  • the slide 350 is forced aftwardly to increase the volume of the combustion chamber from its initial minimum volume to its maximum volume to slow down the rate of increase in gas pressure. This final aftward movement of the slide also forces more lubricant from the annular groove 366 into the interface between the gun bolt and the slide.
  • the link 314 may be made stronger so that the projectile is thereby held to the gun bolt throughout the period of filling with propellant and after ignition until some desired pressure, such as 5,000 psi or higher is developed in the combustion system.
  • FIG. 16 shows a fifth embodiment of this invention.
  • This embodiment utilizes a technique for providing a two phase mixture of droplets of liquid propellant and a gas for the first stage propulsion. This technique is disclosed in US Patent 4,050,348, issued September 27, 1977 to A. R. Graham, the disclosure of which is hereby incorporated by reference.
  • the gun system includes a housing 400 which extends forwardly into a gun barrel having a gun bore 402 and aftwardly into a breech having an opening 404 which is closed by a gun bolt 406.
  • the gun bolt may have seals and an electrode 408 in an ignitor cavity as shown in U.S. Patent 3,783,737, issued January 8, 1974 to E. Ashley, the disclosure of which is hereby incorporated by reference.
  • a conduit 418 having a unidirectional valve 420, couples a supply 422 of gas, such as nitrogen or air, to the ignitor cavity.
  • a spring 430 loaded piston 432 operates in the housing as a fill valve to couple a liquid propellant fill system 434 via a valve 435 and a conduit 436 into the aft end 438 of the gun bore.
  • an assembly consisting of a projectile 440 carried by a sabot 442 and a cavity generator 444 fixed to the projectile by a frangible link 446, may be inserted into the aft end 438 of the bore so that the cavity generator is aft of the opening 436A of the conduit 436 into the bore and the projectile is forward thereof.
  • the gun bolt is then inserted to a first position to back up the cavity generator.
  • the spring loaded piston 432 is moved aftwardly, to open the fill valve, by applying liquid propellant under pressure from the liquid propellant supply 434. Liquid propellant then flows into the volume between the cavity generator and the projectile.
  • the ullage air contained therein is compressed and the projectile urged forwardly until the frangible link is broken.
  • the projectile moves forwardly until the full metered charge is entered and the fill valve closes. Aftward movement of the cavity generator is blocked by the gun bolt.
  • the valve 420 is now opened to admit gas under pressure from the supply 422 into the igniter cavity and this gas acts on the aft face of the cavity generator 444 to advance the train of generator, liquid propellant, and projectile and sabot forwardly until the sabot is halted by the forcing cone 450 in the gun barrel.
  • the valve 420 is closed.
  • a metered volume of liquid propellant is again applied, under pressure greater than the gas pressure, through the fill valve into the volume aft of the cavity generator. As the liquid propellant flows into the gas under pressure, it is sheared into droplets. The gun bolt is then moved forwardly to compress the two phase mixture of gas and droplets of liquid propellant, and then locked. A voltage is applied to the electrode 408 to ignite the two phase mixture in the ignition cavity and the ballistic cycle proceeds as discussed in the other embodiments.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Testing Of Engines (AREA)
  • Toys (AREA)
EP88311043A 1987-12-16 1988-11-22 Canon à charge propulsive liquide Expired - Lifetime EP0321102B1 (fr)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
US150351 1987-12-16
US150350 1987-12-16
US07/150,350 US4852459A (en) 1987-12-16 1987-12-16 Liquid propellant weapon system
US07/150,351 US4852458A (en) 1987-12-16 1987-12-16 Liquid propellant weapon system
CA000616678A CA1333669C (fr) 1987-12-16 1993-06-24 Systeme d'arme a propergol liquide

Publications (3)

Publication Number Publication Date
EP0321102A2 true EP0321102A2 (fr) 1989-06-21
EP0321102A3 EP0321102A3 (en) 1990-12-19
EP0321102B1 EP0321102B1 (fr) 1994-05-18

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EP88311043A Expired - Lifetime EP0321102B1 (fr) 1987-12-16 1988-11-22 Canon à charge propulsive liquide

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EP (1) EP0321102B1 (fr)
JP (1) JP2820702B2 (fr)
DE (1) DE3889642T2 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2664036A1 (fr) * 1990-06-29 1992-01-03 Rheinmetall Gmbh Dispositif pour la transformation compacte de propergol liquide dans des canons.
RU2488572C1 (ru) * 2012-02-21 2013-07-27 Николай Евгеньевич Староверов Пороховой заряд к легкогазовому оружию
RU2564282C2 (ru) * 2014-01-17 2015-09-27 Николай Евгеньевич Староверов Заряд к легкогазовому оружию /варианты/
RU2570011C1 (ru) * 2014-06-17 2015-12-10 Николай Евгеньевич Староверов Заряд к легкогазовому оружию - ii /варианты/
RU2576856C2 (ru) * 2014-05-13 2016-03-10 Николай Евгеньевич Староверов Заряд к легкогазовому оружию (варианты)
CN112179219A (zh) * 2020-08-24 2021-01-05 南京理工大学 一种液体发射药火炮加注系统及其工作方法
CN113687013A (zh) * 2021-07-30 2021-11-23 西北工业大学 一种用于拍摄过载条件下固体推进剂燃烧试验的装置

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4604792A (en) * 1984-12-20 1986-08-12 Lff & Associates Method for making electro-acoustic transducer apparatus
RU2488574C1 (ru) * 2012-02-21 2013-07-27 Николай Евгеньевич Староверов Пороховой заряд к легкогазовому орудию или огнестрельному оружию (варианты)
RU2490244C1 (ru) * 2012-02-21 2013-08-20 Николай Евгеньевич Староверов Пороховой заряд к легкогазовому орудию или огнестрельному оружию (варианты)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3772959A (en) 1971-09-01 1973-11-20 Gen Electric Bolt locking system
US3783737A (en) 1972-02-04 1974-01-08 Gen Electric Seal
US4011817A (en) 1975-05-07 1977-03-15 General Electric Company Liquid propellant weapon system
US4050348A (en) 1976-06-10 1977-09-27 General Electric Company Liquid propellant gun (controlled leakage regenerative piston)
US4085653A (en) 1976-09-15 1978-04-25 General Electric Company Ignition device

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4051762A (en) * 1974-05-13 1977-10-04 General Electric Company Liquid propellant weapon system
US4102269A (en) * 1977-03-17 1978-07-25 General Electric Company Liquid propellant weapon system
US4711153A (en) * 1986-12-15 1987-12-08 General Electric Company Seal

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3772959A (en) 1971-09-01 1973-11-20 Gen Electric Bolt locking system
US3783737A (en) 1972-02-04 1974-01-08 Gen Electric Seal
US4011817A (en) 1975-05-07 1977-03-15 General Electric Company Liquid propellant weapon system
US4050348A (en) 1976-06-10 1977-09-27 General Electric Company Liquid propellant gun (controlled leakage regenerative piston)
US4085653A (en) 1976-09-15 1978-04-25 General Electric Company Ignition device

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2664036A1 (fr) * 1990-06-29 1992-01-03 Rheinmetall Gmbh Dispositif pour la transformation compacte de propergol liquide dans des canons.
RU2488572C1 (ru) * 2012-02-21 2013-07-27 Николай Евгеньевич Староверов Пороховой заряд к легкогазовому оружию
RU2564282C2 (ru) * 2014-01-17 2015-09-27 Николай Евгеньевич Староверов Заряд к легкогазовому оружию /варианты/
RU2576856C2 (ru) * 2014-05-13 2016-03-10 Николай Евгеньевич Староверов Заряд к легкогазовому оружию (варианты)
RU2570011C1 (ru) * 2014-06-17 2015-12-10 Николай Евгеньевич Староверов Заряд к легкогазовому оружию - ii /варианты/
CN112179219A (zh) * 2020-08-24 2021-01-05 南京理工大学 一种液体发射药火炮加注系统及其工作方法
CN113687013A (zh) * 2021-07-30 2021-11-23 西北工业大学 一种用于拍摄过载条件下固体推进剂燃烧试验的装置

Also Published As

Publication number Publication date
DE3889642T2 (de) 1995-01-12
DE3889642D1 (de) 1994-06-23
JPH024197A (ja) 1990-01-09
JP2820702B2 (ja) 1998-11-05
EP0321102B1 (fr) 1994-05-18
EP0321102A3 (en) 1990-12-19

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