WO1998046960A2 - Ensemble carter comprenant une fixation adhesive qui est insensible aux pressions de fonctionnement elevees et qui possede une capacite inherente de liberation des fortes temperatures, et ensemble moteur et ensemble fusee comprenant un tel carter - Google Patents

Ensemble carter comprenant une fixation adhesive qui est insensible aux pressions de fonctionnement elevees et qui possede une capacite inherente de liberation des fortes temperatures, et ensemble moteur et ensemble fusee comprenant un tel carter

Info

Publication number
WO1998046960A2
WO1998046960A2 PCT/US1998/003703 US9803703W WO9846960A2 WO 1998046960 A2 WO1998046960 A2 WO 1998046960A2 US 9803703 W US9803703 W US 9803703W WO 9846960 A2 WO9846960 A2 WO 9846960A2
Authority
WO
WIPO (PCT)
Prior art keywords
case
end closure
sleeve structure
case assembly
assembly
Prior art date
Application number
PCT/US1998/003703
Other languages
English (en)
Other versions
WO1998046960A3 (fr
Inventor
Roger D. Wright
Joseph J. Kliger
Russell A. Crook
Original Assignee
Wright Roger D
Kliger Joseph J
Crook Russell A
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 Wright Roger D, Kliger Joseph J, Crook Russell A filed Critical Wright Roger D
Priority to AU87553/98A priority Critical patent/AU8755398A/en
Publication of WO1998046960A2 publication Critical patent/WO1998046960A2/fr
Publication of WO1998046960A3 publication Critical patent/WO1998046960A3/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F02K9/34—Casings; Combustion chambers; Liners thereof
    • F02K9/343—Joints, connections, seals therefor

Definitions

  • This invention relates to case assemblies including a sleeve structure and at least one end closure structure, which end closure structure is bonded to an inner receptacle surface region of the sleeve structure with an adhesive material and is constructed and arranged to provide the case assembly with excellent Insensitive Munitions (IM) capability.
  • IM Insensitive Munitions
  • This invention further relates to motor assemblies comprising the above-mentioned case assemblies loaded with propellant and including a nozzle assembly, and to rocket assemblies comprising said motor assemblies and a projectile, warhead, or payload assembly.
  • FIG. 7 represents a perspective exploded view of the case assembly, which is generally designated by reference numeral 770.
  • the case assembly 770 includes a case sleeve 772, such as a resin-impregnated-filament-wound pressure vessel, a forward end closure 780, and an aft end closure 784.
  • a forward receptacle end portion 774 of the case sleeve 772 accommodates a mating portion 782 of the forward end closure 780, whereas an aft receptacle end portion 776 of the case sleeve 772 accommodates a mating portion 786 of the aft end closure 784.
  • the forward and aft end closures 780 and 784 are secured to the case ' sleeve 772 with adhesive bonds formed between opposing surfaces of the end closure mating portions 782 and 786 and their associated receptacle end portions 774 and 776.
  • conventional case assemblies 770 are usually provided with supplemental mechanical fasteners (not shown) to reinforce the adhesive bonds and account for peel loads .
  • Conventional supplemental fasteners include blind fasteners such as pop rivets, standard nuts and bolts, or bolts that extend through the tubular piece and thread into the end closure.
  • the adhesive bond thus possesses an inherent high temperature relief capability, also known as an inherent Insensitive Munitions (IM) capability.
  • IM Insensitive Munitions
  • This IM capability makes polymeric adhesives particularly advantageous for use in case assemblies.
  • the IM capability of the adhesive bond is negated by the provision of supplemental mechanical fasteners, which mechanically retain the assembly together even after the adhesive bond has undergone its inherent high temperature relief failure.
  • Another object of this invention is the provision of a case assembly in which an adhesive material bonds an end closure structure to a case sleeve structure, and which is free of mechanical fasteners or other devices that impede or destroy the IM capability of the case assembly.
  • a case assembly comprising at least one end closure structure and a case sleeve structure with an inner receptacle surface.
  • the case sleeve structure receives a mating portion of the end closure structure.
  • the mating portion comprises a tubular wall, which is coupled to the case sleeve structure via a bond comprising an adhesive material disposed between an outer surface region of the tubular wall and a region of the inner receptacle surface of the case sleeve structure.
  • the tubular wall of the end closure structure is preferably made of a metal or alloy, and more preferably is made of aluminum or an aluminum alloy.
  • the tubular wall of the mating portion has a reduced thickness portion and a transition portion, wherein the transition portion tapers in thickness.
  • the reduced thickness and transition portions are collectively constructed and arranged to deform or yield under longitudinal and radial operating loads to track variations of the inner receptacle surface due to such loads and maintain the peel load of the adhesive material below the tensile capability of the adhesive.
  • the tensile capability as referred to herein means the ultimate tensile stress that the adhesive can be subject to prior to peeling from one of the opposing surfaces.
  • the tubular wall of the end closure structure deforms to move substantially in unison with (or substantially tract) the deformation of the inner receptacle surface of the case sleeve structure, the longitudinal and radial loads are transferred away from the adhesive bond to the end closure structure so that localized tensile and shear stresses at the adhesive bond are significantly reduced and substantially eliminated.
  • structural failure occurs in the end closure structure, rather than in the adhesive bond line.
  • the tubular wall thickness can be adjusted to cause failure of the end closure structure at a desired or predetermined pressure.
  • This performance of this object is especially attainable when the average shear stress (P/A) is maintained less than 50% of the ultimate strength of the adhesive.
  • the end closure structures may be fixed to the case sleeve structure without mechanical fasteners.
  • the adhesive material may be selected so that the temperature beyond which it melts, decomposes, or otherwise becomes structurally weakened to such a point that the integrity of the case assembly becomes compromised at normal operating pressures is below the temperature at which propellant to be loaded into the case assembly ignites spontaneously. Because no mechanical fasteners are used to augment the adhesive bond at high temperatures and the adhesive possesses poor structural properties at high temperatures, the pressure vessel has inherent high temperature relief capability, which imparts IM capability in rocket motor applications.
  • It is another object of this invention to provide a motor assembly comprising the foregoing case assembly loaded with a propellant and including an igniter and an aft nozzle end assembly integrally formed with, constituted by, or otherwise secured to the end closure structure.
  • rocket assemblies unguided rocket assemblies and guided missile assemblies (collectively referred to herein as rocket assemblies) comprising the foregoing case assembly loaded with a propellant, and including a nozzle assembly, igniter, and projectile, warhead or payload assembly, in which at least one of said assemblies is integrally formed with, constituted by, or otherwise secured to the end closure structure.
  • FIG. 1 is a perspective sectional view of an end closure structure in accordance with an embodiment of the present invention
  • FIG. 2 is a sectional view of a case assembly comprising the end closure structure of FIG. 1;
  • FIG. 3 is a sectional view of an end closure structure especially suitable for securing an aft nozzle end assembly to a case assembly in accordance with another embodiment of this invention
  • FIG. 4 is a sectional view of another embodiment of an end closure structure especially suitable for securing a forward projectile end assembly to a case assembly in accordance with yet another embodiment of this invention
  • FIG. 5 is a Table comparing performance characteristics of various adhesives and surface preparation methods
  • FIG. 6 is a perspective exploded view of a rocket assembly including the forward and aft end closures of this invention.
  • FIG. 7 is a perspective exploded view of a case assembly including conventional forward and aft end closures.
  • the case assembly 100 comprises a case sleeve structure 102, such as a carbon-epoxy composite wound cylindrical vessel, with a receptacle inner surface 108, and an end closure structure 104.
  • case sleeve structure 102 such as a carbon-epoxy composite wound cylindrical vessel
  • end closure structure 104 an end closure structure
  • the end closure structure 104 has a substantially tubular configuration defined by an annular wall 106.
  • the annular wall 106 comprises a base portion 110, a reduced thickness portion 112 axially spaced from the base portion 110, and a transition portion 114 interposed between the base portion 110 and the reduced thickness portion 112.
  • the thickness of the transition portion 114 tapers from a given (or predetermined) thickness to that of the reduced thickness portion 112.
  • the outer surface of the end closure structure 104 comprises a mating outer surface region 120 associated with the reduced thickness and transition portions 112 and 114, and an enlarged outer surface region 122 associated with the base portion 110 and having a diameter larger than that of the mating outer surface region 120.
  • the sudden increase in diameter between the outer surface regions 120 and 122 defines an annular shoulder 124.
  • the end closure structure 104 has an axial slot 126 formed along a substantial portion of the reduced thickness portion 112 and a transverse bridge portion 128 partitioning an inner chamber of the end closure structure 104. This embodiment may be modified, for example, by omitting the bridge portion 128.
  • a region of the inner receptacle surface 108 of the case sleeve structure 102 opposes the mating outer surface region 120 (FIG. 1) of the end closure structure 104 to define a bond line therebetween in which adhesive material is disposed.
  • the axial positioning of the case sleeve structure 102 relative to the end closure structure 104 is determined by the annular shoulder 124, which one end of the case sleeve structure 102 abuts to inhibit axial movement of the case sleeve structure 102 towards the end closure structure 104.
  • the case sleeve structure 102 undergoes dimensional deformation due to internal operating pressure and external forces.
  • Such dimensional deformation is usually manifested by circumferential expansion of the case sleeve structure 102 and, in conventional assemblies, results in a peel load being applied to the adhesive material, which peel load promotes separation of the adhesive material from the inner receptacle surface of the case sleeve structure and/or the mating portion of the end closure structure.
  • This invention overcomes the problems associated with peel loads by the provision of the reduced thickness portion 112, which is constructed and arranged to permit the end closure structure 104 to deform or yield under normal operating pressures so that the mating outer surface region 120 moves substantially in conjunction with (i.e., tracks the movement of) the inner receptacle surface region 108 as internal pressure circumferentially expands the case sleeve structure 102.
  • an ancillary benefit of this invention is that the construction and arrangement of the reduced thickness portion 112 and the transition portion 114 permits greater axial load transfer between the case sleeve structure 102 and end closure structure 104 (which manifest as shear stresses) to be tolerated during rocket motor operation.
  • D 0 is the outer diameter of the reduced thickness portion of the end closure structure
  • the stress in the adhesive is ⁇ . 50% ⁇ ult .
  • ⁇ y and ⁇ ult can be performed by standard test specimens, or in some cases are available in the literature, such as Mill- HDBK-5F Handbook. Generally, these determinations when viewed in reference to this disclosure, would be apparent and obtainable to the skilled artisan without undue experimentation. A discussion of such tests is set forth in ASTM D3165-73.
  • axial slot 126 which may be provided in the plurality, reduce the stresses in the adhesive bond during both pressure and temperature loading; however, testing has indicated that axial slots 126 are not necessary for satisfactory performance.
  • a peripheral bevel 130 may be provided at the end of reduced thickness portion 112 to create a locally thicker bond line; however, testing has also indicated that bevel 130 is not necessary for satisfactory performance of the case assembly 100.
  • FIG. 6 A rocket motor assembly comprising the case assembly similar to that of FIG. 2 is illustrated in FIG. 6.
  • the rocket motor assembly generally designated by reference numeral 660, includes an aft end closure structure 662 and a forward end closure structure 664 designed in substantially the same manner as the end closure structure 104 discussed above.
  • the aft end closure structure 662 can constitute, be formed integrally with, or otherwise be firmly secured to at least one nozzle assembly 663
  • the forward end closure structure 664 can constitute, be formed integrally with, or otherwise be firmly secured to an assembly 665 comprising at least one aerodynamic conical portion, warhead, and/or payload assembly.
  • the rocket assembly 660 illustrated in FIG. 6 is depicted in a loaded state, meaning that the case assembly is loaded with a propellant grain 666.
  • the rocket assembly 660 further comprises an igniter 668.
  • mechanisms for securing nozzle and forward assemblies to the end closure structures are, for example and without limitation, welds, bolts, lock wires, retaining rings, adhesive joints, threaded surfaces, the like, or a combination thereof.
  • FIGS. 3 and 4 In order to facilitate an understanding of the structure and operation of these embodiments, and in the interest of brevity, the structural elements of the embodiments of FIGS. 3 and 4 corresponding in structure and/or function with elements of the embodiment in FIGS. 1 and 2 have been designated by similar reference numerals to those used to designate the corresponding elements of the embodiment of FIGS. 1 and 2, with the substitution of the prefix numeral 3 or 4 in FIGS. 3 and 4, respectively.
  • the corresponding structure of the end closure structure 104 shown in FIG. 1 is designated by reference numeral 304 in FIG. 3.
  • the end closure structure 304 shown in FIG_. 3 is especially suitable for securing a nozzle assembly to a case assembly. Although not shown in
  • the end closure structure 304 can constitute, be formed integrally with, or otherwise be firmly secured to a nozzle assembly.
  • Mechanisms useful for securing the nozzle assembly to the end closure structure 304 may include, among others, welds, bolts, adhesive joints, screw threads, a lock wire, the like, or a combination thereof.
  • the end closure structure 304 includes base portion 310, reduced thickness portion 312, and transition portion 314.
  • the reduced thickness portion 312 and a part of the transition portion 314 define a mating outer surface region 320.
  • the base portion 310 and the remainder of the transition portion 314 define an enlarged outer surface region 322, which has larger diameter than that of the mating outer surface region 320.
  • the sudden increase in diameter between the outer surface regions 320 and 322 defines an annular shoulder 324.
  • peripheral shim rings 340 and 342 Disposed on the mating outer surface region 320 are peripheral shim rings 340 and 342 extending circumferentially around the outer surface region 320 and spaced from each other in the longitudinal direction.
  • the shim rings 340 and 342 can be formed integrally with the end closure structure 304, or can be bonded or otherwise connected to the end closure structure 304 or the case sleeve structure (not shown in FIG. 3) .
  • a substantially annular cavity is thereby formed having outer and inner surfaces defined by the inner receptacle surface region (not shown in FIG. 3) and the mating outer surface region 320, respectively.
  • the ends of the annular cavity are defined by the shim rings 340 and 342.
  • the radial dimensions of the shim rings 340 and 342 and the longitudinal spacing between the shim rings 340 and 342 can be selected to give the cavity a desirable thickness and length, respectively.
  • the annular cavity contains one or more resins or adhesives, which can be introduced into the annular cavity and cured to form the adhesive bond joint.
  • the end closure structure 304 is preferably formed from an aerospace-aircraft metal alloy, such as an aluminum alloy, such as 7075 aluminum alloy with a selected temper, such as a T7351 temper, but may be formed from another metal alloy, composite or plastic.
  • the end closure structure 304 also includes portion 350 having structure adapted to permit a nozzle end assembly (not shown) to be coupled therewith.
  • the end closure structure 404 shown in FIG. 4 is especially suitable for bonding a projectile assembly to a case assembly.
  • the end closure structure 404 can constitute, be formed integrally with, or otherwise be firmly secured to a projectile assembly as noted above .
  • the end closure structure 404 includes base portion 410, reduced thickness portion 412, and transition portion 414.
  • the reduced thickness portion 412, the transition portion 414, and a part of the base portion 410 collectively define a mating outer surface region 420.
  • the remainder of the base portion 410 defines an enlarged outer surface region 422, which has larger diameter than that of the mating outer surface region 420.
  • the sudden increase in diameter between the outer surface regions 420 and 422 defines an annular shoulder 424.
  • Peripheral shim rings 440 and 442 extend circumferentially around the mating outer surface region 420 and are spaced from each other in the longitudinal direction.
  • a substantially annular cavity is defined by the inner receptacle surface region of the casing sleeve structure (not shown in FIG. 3) , and the outer surface region 420, and shim rings 440 and 442.
  • the annular cavity contains one or more resins or adhesives, which can be introduced into the annular cavity and cured to form the adhesive bond joint.
  • the end closure structure 404 can be formed from alloys, composites, and/or resins, as discussed above, yet is preferably formed from 7075-T7351 aluminum alloy.
  • the end closure structure 404 also includes portion 450 having structure adapted to permit a projectile assembly (not shown) to be coupled therewith.
  • the case assembly of this invention does not require supplemental mechanical fasteners to mate the end closure structures to the case sleeve structure, and the walls of the case sleeve structure may be configured as a simple prefabricated straight walled cylinder.
  • the preparation of the bond surfaces preferably uses environmentally friendly chemicals.
  • case assembly failure can be predicted and tailored by proper choice of end closure structure and composite case assembly parameters, such as diameters and wall thicknesses, rather than at the adhesive bond due to peel loads, where failure is much less predictable.
  • the resins and adhesives selected for the adhesive joint preferably break down at temperatures about 200°F (i.e., glass transition temperature T g ⁇ auto-ignition temperature of the rocket propellant) , so that the adhesive joint is likely to weaken well before propellant auto- ignition, thereby precluding a violent case pressure burst.
  • Suitable adhesives include, but are not limited to, epoxies, polyimides, polyesters, and polyamides . Since the adhesive bond can be provided with adequate strength without the use of mechanical fasteners at the adhesive junction, the pressure vessel is provided with inherent high temperature IM relief caused by degradation of the adhesive material.
  • Adhesive selection is also preferably based on strength and compatibility of the adhesive with the selected mating surface materials.
  • a cavity (or bondline) thickness of about 0.030 inch between the end closure structure and the case sleeve structure is preferred, although other thicknesses may be satisfactory and even preferable, depending on the application.
  • the preferred method of placing adhesive into the cavity is injection. Other placement methods such as films, troweling, or brush or spray applications are possible. Low viscosity is desired for adhesives which are injected. Adequate working potlife is highly desirable.
  • the adhesive should be selected such that the temperatures associated with cure (i.e., the heat required to cure the adhesive and the heat generated by the adhesive during cure) does not damage the case assembly or cause the propellant to auto- ignite. Generally, the temperatures associated with cure should not exceed about 180°F for these reasons.
  • peel ply unprimed Duralco 4525 is preferred although other surface preparations, such as for example, the surface preparations listed in FIG. 5, may be satisfactory, depending on the application.
  • EA9394 is manufactured by Dexter Hysol Aerospace Materials Division.
  • the primer of the surface preparations is UF 3332, available from Thiokol Corporation.
  • the case sleeve structure can be made of any structural material and be made by any method suitable for rocket motor use, but in a preferred embodiment comprises a composite material .
  • the composite case sleeve is constructed using carbon tow, such as M30S tow manufactured by Toray, pre-impregnated with a suitable resin.
  • suitable resins include, by way of example and without limitation, epoxy, polyimide, polyester, and/or polyamide formulated resins.
  • the composite fibers can be, for example and without limitation, Kevlar, glass, and/or carbon.
  • the wall thickness may vary for different applications.
  • the stiffness of the composite case sleeve which is dictated by wall thickness and laminate lay-up) should be set to substantially match the flexibility and yielding strength of the mating portion of the end closure structure so that, under internal pressure, both the composite case and the end closure structure flex substantially the same amount to prevent the adhesive joint from being subject to such peel loads that failure occurs at the adhesive joint.
  • the above-mentioned 0.030 inch preferred cavity thickness is thick enough so as to increase the compliance of the joint without sacrificing joint strength.
  • Sample case assemblies with bonded closures according to the present invention were constructed for testing as follows.
  • the case sleeve was filament wound on a mandrel to a wall thickness of 0.07". Prior to winding, the mandrel was covered with peel- ply, such as Green Release Cloth (commercially available from Airtech Bleeder-Lease "A") or non- transferring release coating on nylon fabric A888 (circumference of the forward and aft portions of the bond length of the closure.
  • the shims assured a uniform bond gap of preferably 0.030". (Shims need not be made of brass.
  • shim structures are preferably integrally formed on the outer surface of the bond length of the closure.) The closure was then inserted into the case.
  • RP6401-1 rubber urethane

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Adhesives Or Adhesive Processes (AREA)
  • Standing Axle, Rod, Or Tube Structures Coupled By Welding, Adhesion, Or Deposition (AREA)

Abstract

Cette invention se rapporte à un ensemble carter, qui comprend une structure de gaine de carter et une structure de fermeture terminale comportant une partie d'assemblage fixée à une région de surface de logement interne de la structure de gaine de carter au moyen d'un matériau adhésif. Cette partie d'assemblage est construite et disposée de façon à transférer les charges de fonctionnement longitudinales et radiales à partir du matériau adhésif jusqu'à la structure de fermeture terminale, rendant ainsi la fixation adhésive insensible aux pressions de fonctionnement internes élevées, sans qu'il soit nécessaire de recourir à des éléments de boulonnerie mécaniques supplémentaires. On peut charger cet ensemble carter de munitions muratisées ou dites à risques atténués (IM), en choisissant comme matériau adhésif un matériau ayant une température de transition vitreuse inférieure à la température d'auto-allumage de l'agent propulseur, et en excluant de cet ensemble carter tout élément de boulonnerie mécanique qui empêche la jointure entre la gaine et la fermeture de se défaire dans sa structure à une température inférieure à la température d'auto-allumage.
PCT/US1998/003703 1997-02-28 1998-02-27 Ensemble carter comprenant une fixation adhesive qui est insensible aux pressions de fonctionnement elevees et qui possede une capacite inherente de liberation des fortes temperatures, et ensemble moteur et ensemble fusee comprenant un tel carter WO1998046960A2 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU87553/98A AU8755398A (en) 1997-02-28 1998-02-27 Case assembly including adhesive bond that is insensitive to high operating pressures and exhibits inherent high temperature relief capability, and mot or assembly and rocket assembly including the same

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US3957097P 1997-02-28 1997-02-28
US60/039,570 1997-02-28
US3984297P 1997-03-04 1997-03-04
US60/039,842 1997-03-04

Publications (2)

Publication Number Publication Date
WO1998046960A2 true WO1998046960A2 (fr) 1998-10-22
WO1998046960A3 WO1998046960A3 (fr) 1999-02-18

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Family Applications (1)

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PCT/US1998/003703 WO1998046960A2 (fr) 1997-02-28 1998-02-27 Ensemble carter comprenant une fixation adhesive qui est insensible aux pressions de fonctionnement elevees et qui possede une capacite inherente de liberation des fortes temperatures, et ensemble moteur et ensemble fusee comprenant un tel carter

Country Status (2)

Country Link
AU (1) AU8755398A (fr)
WO (1) WO1998046960A2 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010007404A1 (de) * 2010-02-09 2011-08-11 INPRO Innovationsgesellschaft für fortgeschrittene Produktionssysteme in der Fahrzeugindustrie mbH, 10587 Verfahren zum Herstellen eines rohrförmigen rotationssymmetrischen Kfz-Fahrwerkbauteils wie einer Kolbenstange, und gebaute Kolbenstange
FR3011902A1 (fr) * 2013-10-16 2015-04-17 Herakles Procede de liaison d'une jupette a une enveloppe d'un corps de propulseur
CN107781062A (zh) * 2017-09-28 2018-03-09 北京理工大学 一种双脉冲固体火箭发动机级间密封结构装置
CN114199092A (zh) * 2021-12-13 2022-03-18 北京中科宇航技术有限公司 一种箭上火工品发火实验容器及其设计方法

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1203230A (en) * 1966-12-01 1970-08-26 Imp Metal Ind Kynoch Ltd Improvements in pressure vessels
DE2044170A1 (de) * 1970-09-05 1972-03-16 Bizien J Verschlußvorrichtung für eine unter Druck stehende Kammer
US3784235A (en) * 1971-10-08 1974-01-08 Us Navy Tubular adhesive joint with snap lock
US4256412A (en) * 1978-12-22 1981-03-17 Messerschmitt-Bolkow-Blohm Gesellschaft Mit Beschrankter Haftung Rod-shaped connecting element
US4602480A (en) * 1982-09-29 1986-07-29 Hercules Incorporated Threaded polar openings for composite pressure vessels
US4787202A (en) * 1986-01-22 1988-11-29 Societe Europeenne De Propulsion Combustion chamber for rocket motor and its assembling method
US5394803A (en) * 1994-02-14 1995-03-07 Bel Electronics, Inc. Joint construction between military rocket motor and warhead and releasable by melting of fusible eutectic wedging ring for operating flexible locking fingers
WO1996005440A1 (fr) * 1994-08-16 1996-02-22 Hong Kong (Link) Bicycles Ltd. Tube en deux materiaux et procede pour le fabriquer

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1203230A (en) * 1966-12-01 1970-08-26 Imp Metal Ind Kynoch Ltd Improvements in pressure vessels
DE2044170A1 (de) * 1970-09-05 1972-03-16 Bizien J Verschlußvorrichtung für eine unter Druck stehende Kammer
US3784235A (en) * 1971-10-08 1974-01-08 Us Navy Tubular adhesive joint with snap lock
US4256412A (en) * 1978-12-22 1981-03-17 Messerschmitt-Bolkow-Blohm Gesellschaft Mit Beschrankter Haftung Rod-shaped connecting element
US4602480A (en) * 1982-09-29 1986-07-29 Hercules Incorporated Threaded polar openings for composite pressure vessels
US4787202A (en) * 1986-01-22 1988-11-29 Societe Europeenne De Propulsion Combustion chamber for rocket motor and its assembling method
US5394803A (en) * 1994-02-14 1995-03-07 Bel Electronics, Inc. Joint construction between military rocket motor and warhead and releasable by melting of fusible eutectic wedging ring for operating flexible locking fingers
WO1996005440A1 (fr) * 1994-08-16 1996-02-22 Hong Kong (Link) Bicycles Ltd. Tube en deux materiaux et procede pour le fabriquer

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010007404A1 (de) * 2010-02-09 2011-08-11 INPRO Innovationsgesellschaft für fortgeschrittene Produktionssysteme in der Fahrzeugindustrie mbH, 10587 Verfahren zum Herstellen eines rohrförmigen rotationssymmetrischen Kfz-Fahrwerkbauteils wie einer Kolbenstange, und gebaute Kolbenstange
FR3011902A1 (fr) * 2013-10-16 2015-04-17 Herakles Procede de liaison d'une jupette a une enveloppe d'un corps de propulseur
WO2015055928A1 (fr) * 2013-10-16 2015-04-23 Herakles Procédé de liaison d'une jupette a une enveloppe d'un corps de propulseur
US10576671B2 (en) 2013-10-16 2020-03-03 Arianegroup Sas Method of connecting a skirt to a thruster body casing
CN107781062A (zh) * 2017-09-28 2018-03-09 北京理工大学 一种双脉冲固体火箭发动机级间密封结构装置
CN107781062B (zh) * 2017-09-28 2019-06-07 北京理工大学 一种双脉冲固体火箭发动机级间密封结构装置
CN114199092A (zh) * 2021-12-13 2022-03-18 北京中科宇航技术有限公司 一种箭上火工品发火实验容器及其设计方法
CN114199092B (zh) * 2021-12-13 2023-10-17 北京中科宇航技术有限公司 一种箭上火工品发火实验容器及其设计方法

Also Published As

Publication number Publication date
WO1998046960A3 (fr) 1999-02-18
AU8755398A (en) 1998-11-11

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