EP0114901A1 - Vorrichtung für Geschosszerstreuung - Google Patents

Vorrichtung für Geschosszerstreuung Download PDF

Info

Publication number
EP0114901A1
EP0114901A1 EP83100604A EP83100604A EP0114901A1 EP 0114901 A1 EP0114901 A1 EP 0114901A1 EP 83100604 A EP83100604 A EP 83100604A EP 83100604 A EP83100604 A EP 83100604A EP 0114901 A1 EP0114901 A1 EP 0114901A1
Authority
EP
European Patent Office
Prior art keywords
submissile
support member
ejected
exterior surface
displaceable panel
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.)
Withdrawn
Application number
EP83100604A
Other languages
English (en)
French (fr)
Inventor
George T. Pinson
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.)
Boeing Co
Original Assignee
Boeing 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
Application filed by Boeing Co filed Critical Boeing Co
Priority to EP83100604A priority Critical patent/EP0114901A1/de
Publication of EP0114901A1 publication Critical patent/EP0114901A1/de
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
    • F42B12/60—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected radially
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B15/00—Fluid-actuated devices for displacing a member from one position to another; Gearing associated therewith
    • F15B15/19—Pyrotechnical actuators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B3/00—Blasting cartridges, i.e. case and explosive
    • F42B3/006—Explosive bolts; Explosive actuators

Definitions

  • This invention relates to the deployment of a body from another body moving in a fluid stream. More particularly this invention relates to a system for ejecting a submissile from a carrier missile.
  • the aerodynamic forces surrounding the carrier missile can cause a deployed submissile to perform large amplitude oscillations. Even if the submissile is provided with internal flight controls, these oscillations may cause the submissile to depart from the desired flight path. In a worst case, the unpredictable flight path of the submissile may lead to an in-flight collision with the carrier missile possibly leading to mutual destruction.
  • Other factors including, e.g., the size of the submissile, speed of the carrier missile and whether the submissile is provided with its own guidance and control system must be considered.
  • the present invention provides an apparatus for deploying a body from a stowed position within a moving carrier vehicle to an operative position initially parallel to a fluid stream contiguous the carrier vehicle.
  • the apparatus comprises a deployment assembly attached to the vehicle and a plurality of body ejection mechanisms housed within the deployment assembly. Each of the ejection mechanisms has a body support member having an axis oriented substantially parallel to the fluid stream.
  • the present apparatus comprises means attached to the body support member capable of imparting a motion to the body substantially perpendicular to the vehicle fluid stream.
  • FIG. 1 a carrier vehicle or missile 10 having a plurality of fins 12 is shown as having ejected (by a means not shown) a body or a submissile 15 into the fluid stream 20 contiguous to the carrier missile 10. Also shown is a shock wave 22 having a downstream turbulent high-pressure zone.
  • the submissile deployment apparatus of the present invention avoids ejecting submissiles into the turbulent high-pressure fluid stream proximate the shock wave 22 because of the extreme difficulty of deploying submissiles into stable trajectories in such an environment.
  • a submissile 15 if not initially deployed into a predefined and carefully controlled predictable trajectory after it leaves the carrier missile, may suffer oscillations such as is shown in FIG. 1 leading to probable impact between the submissile and the carrier missile.
  • these impacts in a worst case, may cause mutual destruction of the carrier missile and submissile or may prevent the submissile from reaching its preselected target.
  • the magnitude of the aerodynamic forces operating upon the submissile may prevent the establishment of a stable flight path in the vicinity of the carrier missile. Consequently, it has been found to be very important to place the submissile in an initial flight path substantially parallel to the streamlines of the fluid stream contiguous the carrier missile 10.
  • the present invention provides an apparatus for deploying one or more submissiles 15, by a carrier missile 25, in a safe and predictable manner wherein a submissile 15 is ejected from the carrier missile 25 and deployed in a fluid stream parallel to the local fluid streamlines adjacent the carrier missile.
  • the carrier missile 25 is shown as having a plurality of deployment assemblies 30, 35 and 40 whereby one (FIG. 3) or more (FIG. 4) submissiles may be given an initial flight path parallel to a streamline of the fluid stream contiguous the carrier missile 10.
  • each deployment assembly Disposed about the longitudinal axis of each deployment assembly (e.g. assembly 35) is a plurality of identical submissile ejection mechanisms 45 (only one of which is shown in FIG. 5).
  • Each mechanism 45 comprises a pair of partition walls 50 attached at one end to an ejection mechanism support 55 connected by a means (not shown) to the main body of the carrier missile 25.
  • the other end of each of the walls 50 is attached to the covering or aerodynamic skin 60 of the deployment assembly 35 by means of a pair of brackets 190.
  • a cavity or an expansion chamber 65 is defined within the support 55 by means of a chamber sleeve or a cylinder 67. Positioned within the cavity 65 is a piston head 70 having seals (not shown) whereby an expansible chamber 75 may be defined.
  • the expansible chamber 75 is provided with a source of motive fluid, e.g., an explosive or high speed gas generating charge 80.
  • the charge 80 may, for example, be ignited by an ignition initiator or a squib 85.
  • a suitable controller 90 may, for example, be electrically connected to the squib 85 using electrical leads 92.
  • the controller 90 sends a signal along the leads 92 to a preselected squib 85 whereby a submissile 15 is ejected and thereby deployed as illustrated in FIG. 3.
  • a plurality of submissiles 15 may be simultaneously deployed, as is illustrated in FIG. 4, using the controller 90.
  • a piston rod 95 connected at one end to the piston head 70, is constrained for vertical translation substantially perpendicular to the fluid stream contiguous the carrier missile 25 by means of a piston rod guide and stop 100.
  • the stop 100 may, for example, be threadedly connected to the cylinder 67 and performs a function which will be described hereinafter.
  • the other end of the piston rod 95 is connected to a submissile support member or a saddle 105.
  • the saddle 105 supports a submissile 15 in its stowed position and is fixed thereto by means of any conventional application oriented constraint, such as, for example a plurality of shear pins 110.
  • the saddle 105 is oriented substantially parallel to the fluid stream contiguous to the carrier missile 25, as will be better understood hereinafter.
  • the saddle may be provided with a means (not shown) whereby the carrier missile may provide (electrically, e.g.) the submissile with any desired information, e.g. control, guidance and target information, prior to and during ejection of the submissile.
  • the carrier missile may provide (electrically, e.g.) the submissile with any desired information, e.g. control, guidance and target information, prior to and during ejection of the submissile.
  • An aerodynamic panel 115 is positioned within a porthole or a body ejection passageway 120 formed in the skin 60 of the assembly 35.
  • a pair of lips 125 fit between the brackets 190 and the undersurface of the skin 60 whereby the panel 115 may be affixed to the assembly 35 when the submissile 15 is in its stowed position.
  • a compressible material or a foam 130 is juxtaposed between the skin 115 and the submissile 15 whereby the submissile 15 may be further secured in its stowed position. Any conventional attachment means (not shown) affixes the foam 130 to the panel 115.
  • the controller 90 sends a signal along the leads 92 to the squib 85 whereby the explosive charge 80 is ignited.
  • the motive fluid resulting from the rapid combustion of the charge forces the piston head 70 upwardly causing the piston rod 95 to translate vertically to its fullest upward stroke (not shown).
  • the saddle 105 moves vertically causing the submissile 15 to compress the foam material 130 and force the lips 125 out of their engagement with the undersurface of the skin 60.
  • the aerodynamic panel 115 is quickly removed allowing the submissile 15 to be ejected and deployed into a position which is substantially parallel to the local fluid stream 20.
  • FIGS. 6 and 7 The deployment of a submissile is shown more clearly in FIGS. 6 and 7 wherein a cross-sectional view of the deployment assemblies 35 and 40 is shown.
  • FIGS. 6 and 7 A submissile 15 in the stowed position is illustrated in FIG. 6 while FIG. 7 shows a deployed submissile.
  • the saddle 105 should preferably be parallel or substantially parallel to the local fluid stream at the full upward stroke of the piston rod 95, i.e., at the point where the submissile 15 is separated from the saddle 105.
  • the local flow pattern around the carrier missile 10 will change as the velocity of the carrier missile 10 varies, it is difficult to insure that a saddle 105 will deploy a submissile 15 into an initial flight path that is perfectly parallel with the local fluid flow. Consequently, it is important to understand that there may be-a misalignment of the submissile 15 relative to the local fluid stream defined herein in terms of an angle A (see FIG. 7).
  • the angle A can be minimized. If deployment is desired over a wide range of speeds, the angle A can be minimized by designing the deployment angle based on dynamic pressure considerations.
  • the worst case dynamic pressure condition occurs at a mach number (M) of about 1.5.
  • Another factor to consider that aids in insuring that a submissile 15 is deployed into an initial flight path that is substantially parallel with the fluid stream contiguous the carrier missile 25 is the provision of a minimum radial or side velocity related to the worst case velocity of the carrier missile as defined above.
  • the minimum side velocity is given a direction which is substantially perpendicular to the streamline proximate the carrier missile 25 and is provided by the ejection mechanism 45.
  • the minimuim side velocity is ascertained through the consideration of one or more of the following two primary factors, i.e.
  • a carrier missile structure avoidance requirement and the requirement to eject uncontrolled submissiles (i.e., a submissile having no internal guidance and control system) to a given distance away from the carrier missile allowing the submissile 15 to impact a given target or point.
  • uncontrolled submissiles i.e., a submissile having no internal guidance and control system
  • a minimum side velocity is imposed on a submissile 15 as it is being ejected from the carrier missile 25
  • the piston head 70 will strike the stop 100 and momentum will cause the shear pins 110 to break thereby releasing the submissile 15 from its associated saddle 105.
  • the saddle 105 will be substantially unconstained possibly resulting in an undesirable change in the aerodynamic performance of the carrier missile 25.
  • a stop 100 there is illustrated in FIG. 10 a means to not only control the maximum upward movement of the saddle 105 but also fix the saddle in a position proximate the passageway 120 as shown generally in FIGS. 3 and 4. With the saddle fixed proximate the passageway 120 after deployment of a submissile 15, any change in the aerodynamic characteristics of the carrier missile 10 may be substantially reduced.
  • the piston head 70 is provided with a plurality of seals 140 and is shown as being disposed within the cylinder 67 thereby forming the expansible chamber 75.
  • a piston rod 145 fixed at one end to the piston head 70 and at its other end to a saddle 105 (not shown), is provided with a piston rod ramp surface 150.
  • the surface 150 may be a tapered collar which has been shrunk fit to the rod 145.
  • the piston rod 145 is guided by a bushing 155 which is fastened within a cylinder cap 160 threadably attached to the cylinder 67.
  • the cylinder cap 160 is provided with an integral cap extension 165 to which is attached a piston stop damping section 170.
  • the section 170 is shown in FIG. 10 as having a guiding section 172 and a ramp section 174.
  • the section 174 wedgingly cooperates with the ramp 150 as the rod 145 is forced upwardly (as viewed in FIG. 10) when motive fluid fills the expansion chamber 75.
  • the piston rod 145 moves upwardly. Concomitantly, the ramp 150 is guided by the section 172 to the ramp section 174 whereby the motion of the piston rod 145 is slowed and subsequently stopped. As can be understood the ramp 150 will be tightly wedged within the section 174 whereby the saddle 105 may be fixedly disposed proximate the passageway 120. The deceleration of the saddle 105 will be sufficient to break the shear pins 110 allowing the separation of the submissile 15 from its associated saddle.
  • FIGS. 11 to 15 Another mechanism that may be used to fix a saddle in an upward position proximate the passageway 120 is shown in FIGS. 11 to 15.
  • a saddle 175 is provided with expanded distal portions mounting a plurality of pins 180.
  • One of the pins 180 is shown in FIG. 14 as comprising a truncated cone.
  • the pins 180 act as male members cooperating with a corresponding number of female portions or pin locks 185 (see FIG. 12).
  • the pin locks 185 are attachable to the brackets 190 by means of a threaded bumper head or stop 195 and an internally threaded retainer 200.
  • the retainer 200 is secured within a groove of a flexible latch member 205.
  • the latch member 205 is a substantially cylindrical member provided at its pin- receiving portion with a ramp surface 210 formed by a plurality of flexible fingers 215 (see FIG. 13). Each of the fingers 215 terminate forming an orifice 220 leading to a receptacle 225.
  • the pins 180 are forced into contact with the ramp surfaces 210 eventually passing through the orifices 220 into the receptacles 225 (see FIG. 15) whereby the pins are held within the receptacles 225. Consequently, the saddle 175 may be fixed proximate the passageway 120 whereby any changes in the aerodynamic characteristics of the carrier missile 10 may be reduced.
  • the stop 195 acts as a bumper coacting with the upper surface 182 of the pin 180 as the pin 180 is forced into the receptacle 225 thereby aiding in the provision of the shear force necessary to break the shear pins 110 and cause separation of a submissile 15 from its associated saddle 175.
  • an integral threaded insert 230 may be provided (see FIG. 16).
  • the insert 230 is provided with threads 235 on its exterior surface and a ramp surface 240 comparable to the surface 210.
  • the integral insert 230 is also provided with a receptacle 245 and a bumper stop 250.
  • the threaded insert 230 may be received in a cavity 255 formed in the brackets 190.
  • FIG. 17 shows one of a plurality of pin receiving cavities 260 that may be formed in the brackets 190.
  • Each cavity 260 is provided with a groove 265 forming a support for a rolled edge 270 of a metal spring 275 disposable within each cavity 260.
  • the metal spring 275 has the general shape of a hollow truncated cone.
  • the spring 275 is provided with an orifice 282 and a plurality of flexible fingers or tines 280.
  • the interior surface 285 of the spring 275 acts as a ramp surface whereby when any pin 180 is forced into contact with the ramp surface 285, the tines 280 are forced outwardly allowing the pin 180 to enter the orifice 282 and pass into the cavity 260. Once the pin 180 passes through the orifice 282 the tines 280 return to their unflexed, original position and lock the pin 180 in the closed position shown in FIG. 19.
  • the inner surface 262 of the cavity 260 performs the same function as the stops 195, 250.
  • FIGS. 20 and 21 illustrate a more preferred embodiment wherein changes in the aerodynamic characteristics of a carrier missile are substantially minimized.
  • FIG. 2 0 shows a submissile 15 attached to a saddle 105 by means of a plurality of shear pins 110.
  • a piston rod 95 forms part of an ejection mechanism 45.
  • an aerodynamic panel comprises a first aerodynamic panel 290 and a second aerodynamic panel 295 bounded by a central separation plane 300.
  • Each aerodynamic panel 290, 295 is attached to the skin of a deployment assembly by means of a hinge plate 305 and a hinge 310.
  • the panels 295 and 300 are maintained in an abutting contact with each other and with the submissile 15 by means of a plurality of springs 315.
  • the springs 315 are fixed at their distal ends at 320 on the partitions 50 and at 325 on the panels 290 and 295.
  • the saddle 105 forceable contacts bumper stops (not shown but which may be positioned proximate the brackets 190) thereby aiding in breaking the shear pins 110 (see FIG. 21).
  • the panels 290 and 295 are forced outwardly along the hinge axis of the hinge 310.
  • the springs 315 force the panels 290 and 295 back into a closed position, illustrated in FIG. 20. Consequently, after the panels.290, 295 return to their original position the aerodynamic characteristics of the carrier missile 25 are maintained.
  • the pins 180 may be fixed to the brackets 190 and the pin locks 185 or 230 may be affixed to the saddle 175. It is also obvious that the deployment apparatus of the present invention is useful not only with carrier missiles but may also be useful with any moving carrier vehicle, such as, for example, aircraft, etc.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Analytical Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP83100604A 1983-01-24 1983-01-24 Vorrichtung für Geschosszerstreuung Withdrawn EP0114901A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP83100604A EP0114901A1 (de) 1983-01-24 1983-01-24 Vorrichtung für Geschosszerstreuung

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP83100604A EP0114901A1 (de) 1983-01-24 1983-01-24 Vorrichtung für Geschosszerstreuung

Publications (1)

Publication Number Publication Date
EP0114901A1 true EP0114901A1 (de) 1984-08-08

Family

ID=8190255

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83100604A Withdrawn EP0114901A1 (de) 1983-01-24 1983-01-24 Vorrichtung für Geschosszerstreuung

Country Status (1)

Country Link
EP (1) EP0114901A1 (de)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2557286A1 (fr) * 1983-12-27 1985-06-28 Brandt Armements Charge militaire a tetes multiples
FR2594219A1 (fr) * 1986-02-13 1987-08-14 Rafaut & Cie Dispositif d'ejection, en particulier pour munitions
GB2226624A (en) * 1987-12-12 1990-07-04 Thorn Emi Electronics Ltd Projectile.
EP0412774A1 (de) * 1989-08-10 1991-02-13 British Aerospace Public Limited Company Waffensystem
FR2654822A1 (fr) * 1987-03-17 1991-05-24 Thomson Brandt Armements Dispenseur de sous-projectiles.
US5431106A (en) * 1985-06-05 1995-07-11 Shorts Missile Systems Limited Release of daughter missiles
EP1502075A2 (de) * 2001-06-04 2005-02-02 Raytheon Company Gefechtskopf mit ausgerichteten geschossen
WO2010047861A1 (en) * 2008-10-22 2010-04-29 Raytheon Company Missile with system for separating subvehicles
DE202012103084U1 (de) 2012-08-15 2012-09-07 W. Döllken & Co. GmbH Kernsockelleiste
CN113959276A (zh) * 2021-10-15 2022-01-21 上海机电工程研究所 能防止炸膛的燃气弹射多弹分离装置
CN114087929A (zh) * 2021-09-01 2022-02-25 重庆零壹空间科技集团有限公司 一种内置旋转舱门子母弹随域抛撒机构

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2972946A (en) * 1950-07-07 1961-02-28 Thomas C Poulter Bomb cluster
US3114962A (en) * 1961-12-21 1963-12-24 Hi Shear Corp Separable fastener and parts catcher therefor
US3295444A (en) * 1956-08-02 1967-01-03 Vincent J Cushing Dispersal type cluster warhead
US3386380A (en) * 1967-01-04 1968-06-04 Francis Gus Method and apparatus for propelling projectiles for space and other applications
US3461801A (en) * 1968-01-25 1969-08-19 Us Navy Multi-canister ejecting device
FR2135411A1 (de) * 1971-05-04 1972-12-22 Serat
DE2920347A1 (de) * 1979-05-19 1980-11-20 Messerschmitt Boelkow Blohm Gefechtskopf mit ausstossbaren wirkkoerpern

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2972946A (en) * 1950-07-07 1961-02-28 Thomas C Poulter Bomb cluster
US3295444A (en) * 1956-08-02 1967-01-03 Vincent J Cushing Dispersal type cluster warhead
US3114962A (en) * 1961-12-21 1963-12-24 Hi Shear Corp Separable fastener and parts catcher therefor
US3386380A (en) * 1967-01-04 1968-06-04 Francis Gus Method and apparatus for propelling projectiles for space and other applications
US3461801A (en) * 1968-01-25 1969-08-19 Us Navy Multi-canister ejecting device
FR2135411A1 (de) * 1971-05-04 1972-12-22 Serat
DE2920347A1 (de) * 1979-05-19 1980-11-20 Messerschmitt Boelkow Blohm Gefechtskopf mit ausstossbaren wirkkoerpern

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2557286A1 (fr) * 1983-12-27 1985-06-28 Brandt Armements Charge militaire a tetes multiples
EP0169956A1 (de) * 1983-12-27 1986-02-05 Thomson-Brandt Armements Trägergeschoss mit mehreren Innengeschossen
US5431106A (en) * 1985-06-05 1995-07-11 Shorts Missile Systems Limited Release of daughter missiles
FR2594219A1 (fr) * 1986-02-13 1987-08-14 Rafaut & Cie Dispositif d'ejection, en particulier pour munitions
FR2654822A1 (fr) * 1987-03-17 1991-05-24 Thomson Brandt Armements Dispenseur de sous-projectiles.
US4957046A (en) * 1987-12-12 1990-09-18 Thorn Emi Electronics Limited Projectile
FR2642830A1 (fr) * 1987-12-12 1990-08-10 Thorn Emi Electronics Ltd Projectile notamment projectile anti-missile
GB2226624B (en) * 1987-12-12 1991-07-03 Thorn Emi Electronics Ltd Projectile
GB2226624A (en) * 1987-12-12 1990-07-04 Thorn Emi Electronics Ltd Projectile.
EP0412774A1 (de) * 1989-08-10 1991-02-13 British Aerospace Public Limited Company Waffensystem
US5067411A (en) * 1989-08-10 1991-11-26 British Aerospace Public Limited Company Weapon systems
EP1502075A4 (de) * 2001-06-04 2008-11-12 Raytheon Co Gefechtskopf mit ausgerichteten geschossen
EP1502075A2 (de) * 2001-06-04 2005-02-02 Raytheon Company Gefechtskopf mit ausgerichteten geschossen
WO2010047861A1 (en) * 2008-10-22 2010-04-29 Raytheon Company Missile with system for separating subvehicles
US8082848B2 (en) 2008-10-22 2011-12-27 Raytheon Company Missile with system for separating subvehicles
DE202012103084U1 (de) 2012-08-15 2012-09-07 W. Döllken & Co. GmbH Kernsockelleiste
CN114087929A (zh) * 2021-09-01 2022-02-25 重庆零壹空间科技集团有限公司 一种内置旋转舱门子母弹随域抛撒机构
CN114087929B (zh) * 2021-09-01 2023-04-11 重庆零壹空间科技集团有限公司 一种内置旋转舱门子母弹随域抛撒机构
CN113959276A (zh) * 2021-10-15 2022-01-21 上海机电工程研究所 能防止炸膛的燃气弹射多弹分离装置
CN113959276B (zh) * 2021-10-15 2023-02-24 上海机电工程研究所 能防止炸膛的燃气弹射多弹分离装置

Similar Documents

Publication Publication Date Title
US4455943A (en) Missile deployment apparatus
EP0114901A1 (de) Vorrichtung für Geschosszerstreuung
US5760330A (en) Method and apparatus for conveying a large-calibre payload over an operational terrain
US3903804A (en) Rocket-propelled cluster weapon
KR20080059148A (ko) 파이로테크닉 액추에이터
US3430533A (en) Aircraft dispenser pod having self-sealing ejection tubes
JP2795537B2 (ja) ミサイルの横方向スラスト集合体
US3943854A (en) Ejection head with active elements for rockets
US5029776A (en) Variable explosive source for an ejector system
US3517584A (en) Stores ejection means
US3070018A (en) Nose cone ejection system
US5218165A (en) Pneumatic separation device
US3749317A (en) Thrust vector control system
US5104067A (en) Detonating cord powered canopy breakers
US3112906A (en) Flying body construction
CN112361898B (zh) 一种航天飞行器分离系统
DE2608961C3 (de) Schleudervorrichtung
US6492632B1 (en) Lock and slide mechanism for tube launched projectiles
US5750917A (en) Warhead
US9605935B1 (en) Multi-charge munitions, incorporating hole-boring charge assemblies
US3079111A (en) Rockets and seat ejecting apparatus
GB2024920A (en) Ejectable coupling
US4499829A (en) Explosively separable casing
US4784350A (en) Passive step trimmer for a maneuvering re-entry body (U)
US3115320A (en) Ejection seat catapult

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Designated state(s): AT BE CH DE FR GB IT LI LU NL SE

17P Request for examination filed

Effective date: 19841127

17Q First examination report despatched

Effective date: 19860404

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 19860815

RIN1 Information on inventor provided before grant (corrected)

Inventor name: PINSON, GEORGE T.