US3266373A - Compact hold-down and vertical shock mount - Google Patents

Compact hold-down and vertical shock mount Download PDF

Info

Publication number
US3266373A
US3266373A US406951A US40695164A US3266373A US 3266373 A US3266373 A US 3266373A US 406951 A US406951 A US 406951A US 40695164 A US40695164 A US 40695164A US 3266373 A US3266373 A US 3266373A
Authority
US
United States
Prior art keywords
missile
support ring
ring
hold
wall
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.)
Expired - Lifetime
Application number
US406951A
Inventor
Charles R Brown
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to US406951A priority Critical patent/US3266373A/en
Application granted granted Critical
Publication of US3266373A publication Critical patent/US3266373A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/07—Underwater launching-apparatus

Definitions

  • This invention relates to a missile launching system of the type having an outer and an inner launching tube and a vertically supported missile and to the mechanism for holding down the missile and serving as a vertical shock absorber.
  • the vertical shock absorber was a separate mechanism which was larger than necessary and consisted of an arrangement of springs and hydraulic support. The necessity for eliminating some of the weight and conserving space made it impossible to use the established assemblies. A compact support and hold-down mechanism which would also absorb the vertical shocks and eliminate vibration from reaching the missile was desirable.
  • the object of this invention is to provide a hold-down mechanism and a vertical shock absorber in a single assembly which will utilize little space and add little to the weight of the launching system.
  • Another object of the present invention is to provide a hold-down mechanism and a shock absorber for vertical shocks in a single piece of apparatus which will occupy little space in the launcher tube which will fit the existing missile and which will not be complicated or be diflicult to install.
  • FIG. 1 is a vertical sectional view of the missile and launching tube
  • FIG. 2 is a vertical section of that portion of the missile and launching tube showing the particular hold-down mechanism and shock absorber.
  • the invention shows the invention as applied to a missile launching system as designed for application to a submarine.
  • the same structure, slightly modified, could be used for a missile launching system either land based or for application to larger surface ships.
  • a small section of the hull 11 of a submarine is shown supporting a missile launching system comprising an outer tube 12 and inner tube 13 and a spacing means consisting of a ring 14 and a filler 15 between the two tubes.
  • the missile 16 is housed within the inner tube and spaced therefrom by a seal facing 17 which separates the missile from the inner side of the tube and provides a packing which gives the missile some rigidity in a radial direction.
  • the missile is of the usual type having exhaust nozzles 18 and a bottom rim 19 which is inturned.
  • the mechanism forming this invention comprises a bottom support ring 21 having lower ears to which supporting turnbuckles or hydraulic springs are attached.
  • This supporting structure for the bottom support ring forms no part of this invention and is here shown only diagrammatically.
  • the support ring 21 is formed with a comparatively small radial wall 22 and a substantially extended vertical wall 23.
  • An inner or upper support ring 24 is formed with an upper section having a diameter slightly larger than the diameter of the missile and slightly below the upper edge an internal collar or ledge 25 extends under the bottom rim 19 of the missile.
  • This annular collar 25 is tapered on its underside as at 26 which taper conforms to a similar taper 27 formed on the missile rim 19.
  • the diameter of the upper support ring 24 is decreased in a lower section below the clamping ring to provide an annular shoulder 29 formed with an inner upturned lip 31.
  • This lip has an upper rim 32 projecting outward to form a catch for a downwardly projecting foot 33 of the clamping ring 24.
  • the smaller diameter section of the upper support ring 24 extends downward within the confines of the bottom support ring and is attached to the bottom support ring by a resilient collar 34 to provide a shear mount for the inner support ring.
  • the resilient or rubber collar 34 is firmly attached to the inner wall of the bottom support ring and to the outer wall of the inner support ring to provide both support and a shock absorber for vibration in a vertical direction.
  • the height of this rubber collar may 'be controlled by the rigidity desired and the weight to be supported. It may be formed of one piece or of several sections spaced slightly from each other.
  • the bottom support ring has an outer wall covering of a :soft foam rubber which may be covered with Teflon. This serves as a packing between the tube Wall and the bottom support ring and centers the bottom support ring.
  • the radial wall of the bottom support ring has a plurality of integral ears for engaging supporting brackets which are attached to the tube.
  • the clamping ring holds the missile firmly attached to the inner support ring which is supported by the bottom support ring through the rubber collar in a vibration absorbing manner.
  • the clamping ring Upon release of the missile by contracting the clamping ring through any desired mechanism such as a hydraulic piston, the clamping ring is retained by the lip 31 and prevented from entangling with the exhaust nozzles.
  • Such a support serves as both a shock absorber and a hold-down mechanism and is not bulky or unnecessarily heavy. It is comparatively easy to install and functions successfully.
  • a missile launching system having an outer and an inner launching tube and a vertically supported missile, a missile. hold-down mechanism and a vertical shock absorber comprising:
  • a bottom support ring located within the outer tube and secured thereto;
  • resilient means connecting the bottom support ring with the upper support ring and supporting the upper ring; means integral with the upper support ring supporting the missile;
  • a missile hold-down mechanism and a vertical shock absorber according to claim 1 wherein the means securing the upper support ring to the missile comprises an inwardly contracting clamping ring operable to release the missile from the upper support ring.
  • a missile hold-down mechanism and a vertical shock absorber according to claim 1 wherein the resilient means connecting the upper support ring with the bottom support ring comprises a rubber collar secured to the outer wall of the upper support ring and to the inner wall of the bottom support ring and serving as a substantially rigid brace in a radial direction and as a vibration absorber in a vertical direction.
  • a missile hold-down mechanism and a vertical shock absorber according to claim 2 and including means integral with the upper support ring for engaging the clamping ring upon release of the missile from the upper support ring by retraction of the clamping ring, said means retaining the clamping ring and preventing interference with the passage of the missile.
  • a missile launching system having a launching tube and a vertically positioned missile, a missile holddown mechanism and a vertical shock absorber comprising:
  • a bottom support ring securely fastened to the side wall of the launching tube, said ring being formed with a comparatively tall vertical wall;
  • an upper support ring having a lower diameter section and an upper diameter section, the lower section being of less diameter than the upper section, the larger part of the lower section extending downward within the confines of the bottom support ring, the upper section being formed with an annular internal collar engaging the bottom rim of the missile, said upper section being further formed with an internal shoulder having an upstanding lip;
  • clamping ring engaging the annular internal collar and the rim of the bottom of the missile and clamping them together, said clamping ring being formed with a depending foot, which upon disengagement of the clamping ring with the internal collar and rim said foot will engage the lip of the shoulder and retain the clamping ring from interference with the missile;
  • a rubber collar extending between the outer wall of the lower section of the upper support ring and the inner wall of the bottom support ring, said rubber collar being firmly secured to each of said support rings to provide hold-down mechanism and shock absorption for the missile.

Landscapes

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

Description

Aug-y 6, 1966 c. R. BROWN 3,266,373
COMPACT HOLD-DOWN AND VERTICAL SHOCK MOUNT Filed Oct. 27, 1964 2 Sheets-Sheet l FIG.
r. 28 C /4 l "I RN /9 25-" 25'- I II' /8 24 :w I I I 22 2/ y INVENTOR GHARLES R BROWN m MM BY ATTORNEY AGENT Aug. 16, 1966 c. R. BROWN 3,266,373
COMPACT HOLD-DOWN AND VERTICAL SHOCK MOUNT Filed on 27, 1964 2 Sheets-Sheet 2 l mm - I mug g I Z3 I II I MW llm' Hill llliiii;
United States atent 3,266,373 COMPACT HOLD-DOWN AND VERTICAL SHOCK MOUNT Charles R. Brown, Sunnyvale, Calif., assignor, by mesne assignments, to the United States of America as represented by the Secretary of the Navy Filed Oct. 27, 1964, Ser. No. 406,951 Claims. (Cl. 891.7)
This invention relates to a missile launching system of the type having an outer and an inner launching tube and a vertically supported missile and to the mechanism for holding down the missile and serving as a vertical shock absorber.
In the past missiles supported in a vertical position, in either a ground supported missile installation or one carried in a submarine, have been held down by a separate, complicated and space consuming assembly. The vertical shock absorber was a separate mechanism which was larger than necessary and consisted of an arrangement of springs and hydraulic support. The necessity for eliminating some of the weight and conserving space made it impossible to use the established assemblies. A compact support and hold-down mechanism which would also absorb the vertical shocks and eliminate vibration from reaching the missile was desirable.
The object of this invention is to provide a hold-down mechanism and a vertical shock absorber in a single assembly which will utilize little space and add little to the weight of the launching system.
Another object of the present invention is to provide a hold-down mechanism and a shock absorber for vertical shocks in a single piece of apparatus which will occupy little space in the launcher tube which will fit the existing missile and which will not be complicated or be diflicult to install.
It is a further object of the present invention to provide a pair of metallic support rings, a lower or bottom ring and an upper or inner support ring and to so join the two rings that they will support the missile resiliently to absorb the vertical vibrations.
It is a still further object of the present invention to provide a pair of ring supports, one partially nested within the other and to join these two support rings with a resilient collar which will give a substantially rigid support in a lateral or radial direction while furnishing a resilient support which will absorb vibration in a vertical direction.
It is a still further object of the present invention to provide a means similar to previously used means for attaching the upper support ring to the missile so that the support for the missile also holds the missile down in the tube and to provide an anchorage for the lower ring so that the missile is held down by the upper support ring and the lower support ring through the resilient connection between the two rings.
It is a still further object of the present invention to provide means for clamping the bottom of the missile to the upper end of the upper support ring, such clamping means being usually in the form of a clamping ring which is collapsible towards the center and to provide means associated with the upper support ring and formed integral therewith for receiving this collapsed ring and retaining it from intreference with the exhaust nozzles of the missile.
Other objects, advantages and novel features of the invention will become apparent from the following detailed description of the invention when considered in conjunction with the accompanying drawings wherein:
FIG. 1 is a vertical sectional view of the missile and launching tube;
FIG. 2 is a vertical section of that portion of the missile and launching tube showing the particular hold-down mechanism and shock absorber.
The invention, as illustrated, shows the invention as applied to a missile launching system as designed for application to a submarine. The same structure, slightly modified, could be used for a missile launching system either land based or for application to larger surface ships.
Referring to the drawings where like parts are indicated by similar numerals, a small section of the hull 11 of a submarine is shown supporting a missile launching system comprising an outer tube 12 and inner tube 13 and a spacing means consisting of a ring 14 and a filler 15 between the two tubes.
The missile 16 is housed within the inner tube and spaced therefrom by a seal facing 17 which separates the missile from the inner side of the tube and provides a packing which gives the missile some rigidity in a radial direction. The missile is of the usual type having exhaust nozzles 18 and a bottom rim 19 which is inturned.
The mechanism forming this invention comprises a bottom support ring 21 having lower ears to which supporting turnbuckles or hydraulic springs are attached. This supporting structure for the bottom support ring forms no part of this invention and is here shown only diagrammatically. The support ring 21 is formed with a comparatively small radial wall 22 and a substantially extended vertical wall 23.
An inner or upper support ring 24 is formed with an upper section having a diameter slightly larger than the diameter of the missile and slightly below the upper edge an internal collar or ledge 25 extends under the bottom rim 19 of the missile. This annular collar 25 is tapered on its underside as at 26 which taper conforms to a similar taper 27 formed on the missile rim 19. These two engaging rims of frusto-conical shape in cross section are engaged by the outer surface of a clamping ring 28 which firmly clamps the rim 19 to the collar 25 and provides the hold-down connection as well as a support.
The diameter of the upper support ring 24 is decreased in a lower section below the clamping ring to provide an annular shoulder 29 formed with an inner upturned lip 31. This lip has an upper rim 32 projecting outward to form a catch for a downwardly projecting foot 33 of the clamping ring 24. Upon contraction of the clamping ring at the time of release of the missile from the holddown mechanism, the clamping ring will be caught and held by the lip 31 and prevented from interferring with the exhaust nozzles.
The smaller diameter section of the upper support ring 24 extends downward within the confines of the bottom support ring and is attached to the bottom support ring by a resilient collar 34 to provide a shear mount for the inner support ring. The resilient or rubber collar 34 is firmly attached to the inner wall of the bottom support ring and to the outer wall of the inner support ring to provide both support and a shock absorber for vibration in a vertical direction. The height of this rubber collar may 'be controlled by the rigidity desired and the weight to be supported. It may be formed of one piece or of several sections spaced slightly from each other.
The bottom support ring has an outer wall covering of a :soft foam rubber which may be covered with Teflon. This serves as a packing between the tube Wall and the bottom support ring and centers the bottom support ring. The radial wall of the bottom support ring has a plurality of integral ears for engaging supporting brackets which are attached to the tube.
The function of the supporting ring is clearly seen, as the clamping ring holds the missile firmly attached to the inner support ring which is supported by the bottom support ring through the rubber collar in a vibration absorbing manner. Upon release of the missile by contracting the clamping ring through any desired mechanism such as a hydraulic piston, the clamping ring is retained by the lip 31 and prevented from entangling with the exhaust nozzles.
Such a support serves as both a shock absorber and a hold-down mechanism and is not bulky or unnecessarily heavy. It is comparatively easy to install and functions successfully.
Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.
What is claimed is:
1. In a missile launching system having an outer and an inner launching tube and a vertically supported missile, a missile. hold-down mechanism and a vertical shock absorber comprising:
a bottom support ring located Within the outer tube and secured thereto;
means attached to the outer wall of the bottom support ring and engaging the wall of the outer tube to serve as a packing unit;
an upper support ring located above and extending within the bottom support ring;
resilient means connecting the bottom support ring with the upper support ring and supporting the upper ring; means integral with the upper support ring supporting the missile; and
means securing the upper support ring to the missile.
2. A missile hold-down mechanism and a vertical shock absorber according to claim 1 wherein the means securing the upper support ring to the missile comprises an inwardly contracting clamping ring operable to release the missile from the upper support ring.
3. A missile hold-down mechanism and a vertical shock absorber according to claim 1 wherein the resilient means connecting the upper support ring with the bottom support ring comprises a rubber collar secured to the outer wall of the upper support ring and to the inner wall of the bottom support ring and serving as a substantially rigid brace in a radial direction and as a vibration absorber in a vertical direction.
4. A missile hold-down mechanism and a vertical shock absorber according to claim 2 and including means integral with the upper support ring for engaging the clamping ring upon release of the missile from the upper support ring by retraction of the clamping ring, said means retaining the clamping ring and preventing interference with the passage of the missile.
5. In a missile launching system having a launching tube and a vertically positioned missile, a missile holddown mechanism and a vertical shock absorber comprising:
a bottom support ring securely fastened to the side wall of the launching tube, said ring being formed with a comparatively tall vertical wall;
a foam rubber covering on the outer wall of said bottom ring contacting the inner Wall of the tube, said covering acting to center the bottom ring in the tube and serving as a packing member;
an upper support ring having a lower diameter section and an upper diameter section, the lower section being of less diameter than the upper section, the larger part of the lower section extending downward within the confines of the bottom support ring, the upper section being formed with an annular internal collar engaging the bottom rim of the missile, said upper section being further formed with an internal shoulder having an upstanding lip;
a clamping ring engaging the annular internal collar and the rim of the bottom of the missile and clamping them together, said clamping ring being formed with a depending foot, which upon disengagement of the clamping ring with the internal collar and rim said foot will engage the lip of the shoulder and retain the clamping ring from interference with the missile;
a rubber collar extending between the outer wall of the lower section of the upper support ring and the inner wall of the bottom support ring, said rubber collar being firmly secured to each of said support rings to provide hold-down mechanism and shock absorption for the missile.
No references cited.
BENJAMIN A. BORCHELT, Primary Examiner.
S. W. ENGLE, Assistant Examiner.

Claims (1)

1. IN A MISSILE LAUNCHING SYSTEM HAVING AN OUTER AND AN INNER LAUNCHING TUBE AND A VERTICALLY SUPPORTED MISSILE, A MISSILE HOLD-DOWN MECHANISM AND A VERTICAL SHOCK ABSORBER COMPRISING: A BOTTOM SUPPORT RING LOCATED WITHIN THE OUTER TUBE AND SECURED THERETO; MEANS ATTACHED TO THE OUTER WALL OF THE BOTTOM SUPPORT RING AND ENGAGING THE WALL OF THE OUTER TUBE TO SERVE AS A PACKING UNIT; AN UPPER SUPPORT RING LOCATED ABOVE AND EXTENDING WITHIN THE BOTTOM SUPPORT RING; RESILIENT MEANS CONNECTING THE BOTTOM SUPPORT RING WITH THE UPPER SUPPORT RING AND SUPPORTING THE UPPER RING; MEANS INTEGRAL WITH THE UPPER SUPPORT RING SUPPORTING THE MISSILE; AND MEANS SECURING THE UPPER SUPPORT RING TO THE MISSILE.
US406951A 1964-10-27 1964-10-27 Compact hold-down and vertical shock mount Expired - Lifetime US3266373A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US406951A US3266373A (en) 1964-10-27 1964-10-27 Compact hold-down and vertical shock mount

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US406951A US3266373A (en) 1964-10-27 1964-10-27 Compact hold-down and vertical shock mount

Publications (1)

Publication Number Publication Date
US3266373A true US3266373A (en) 1966-08-16

Family

ID=23610017

Family Applications (1)

Application Number Title Priority Date Filing Date
US406951A Expired - Lifetime US3266373A (en) 1964-10-27 1964-10-27 Compact hold-down and vertical shock mount

Country Status (1)

Country Link
US (1) US3266373A (en)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3516628A (en) * 1967-04-21 1970-06-23 Menasco Mfg Co Suspension system
US3731898A (en) * 1971-07-27 1973-05-08 Pneumo Dynamics Corp Missile suspension system
US4464972A (en) * 1983-03-15 1984-08-14 The United States Of America As Represented By The Secretary Of The Air Force Lateral support system for canister-launched missile
US4492143A (en) * 1983-05-31 1985-01-08 Westinghouse Electric Corp. Anti-rotation mass support system particularly for missile support
US4602552A (en) * 1984-06-25 1986-07-29 The United States Of America As Represented By The Secretary Of The Air Force Zero adhesion system
EP0284777A1 (en) * 1987-04-02 1988-10-05 Howaldtswerke-Deutsche Werft Ag Arrangement of launching and firing tubes or containers in submarines
US5115711A (en) * 1991-03-25 1992-05-26 Fmc Corporation Missile canister and method of fabrication
US5327809A (en) * 1993-03-24 1994-07-12 Fmc Corporation Dual pack canister
US5438905A (en) * 1984-06-19 1995-08-08 Westinghouse Electric Corporation Method and apparatus for stabilizing the in-tube trajectory of a missile
FR2781771A1 (en) * 1998-08-03 2000-02-04 Mediterranee Const Ind METHOD OF SETTING A TUBE IN A TUBULAR HOUSING, PARTICULARLY A MISSILE LAUNCH TUBE
US20050066800A1 (en) * 2003-09-09 2005-03-31 Hagan James Dennis Pressure-released brake assembly for restraining projectile in launch tube
US11065910B2 (en) * 2017-07-14 2021-07-20 Illinois Tool Works Inc. Color shifting heat transfer label

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3516628A (en) * 1967-04-21 1970-06-23 Menasco Mfg Co Suspension system
US3731898A (en) * 1971-07-27 1973-05-08 Pneumo Dynamics Corp Missile suspension system
US4464972A (en) * 1983-03-15 1984-08-14 The United States Of America As Represented By The Secretary Of The Air Force Lateral support system for canister-launched missile
US4492143A (en) * 1983-05-31 1985-01-08 Westinghouse Electric Corp. Anti-rotation mass support system particularly for missile support
US5438905A (en) * 1984-06-19 1995-08-08 Westinghouse Electric Corporation Method and apparatus for stabilizing the in-tube trajectory of a missile
US4602552A (en) * 1984-06-25 1986-07-29 The United States Of America As Represented By The Secretary Of The Air Force Zero adhesion system
EP0284777A1 (en) * 1987-04-02 1988-10-05 Howaldtswerke-Deutsche Werft Ag Arrangement of launching and firing tubes or containers in submarines
US5115711A (en) * 1991-03-25 1992-05-26 Fmc Corporation Missile canister and method of fabrication
US5327809A (en) * 1993-03-24 1994-07-12 Fmc Corporation Dual pack canister
FR2781771A1 (en) * 1998-08-03 2000-02-04 Mediterranee Const Ind METHOD OF SETTING A TUBE IN A TUBULAR HOUSING, PARTICULARLY A MISSILE LAUNCH TUBE
EP0978676A1 (en) * 1998-08-03 2000-02-09 Constructions Industrielles de la Mediterranee C.N.I.M. Method for wedging a tube, particularly a missile launch tube, in a tubular support
US20050066800A1 (en) * 2003-09-09 2005-03-31 Hagan James Dennis Pressure-released brake assembly for restraining projectile in launch tube
US6895850B2 (en) * 2003-09-09 2005-05-24 The United States Of America As Represented By The Secretary Of The Navy Pressure-released brake assembly for restraining projectile in launch tube
US11065910B2 (en) * 2017-07-14 2021-07-20 Illinois Tool Works Inc. Color shifting heat transfer label

Similar Documents

Publication Publication Date Title
US3266373A (en) Compact hold-down and vertical shock mount
US2660387A (en) Vibration and shock isolator
JPS583134B2 (en) Shindougeki Oyobi Shindozetsuentritsukedai
US20140260941A1 (en) Mountable Fixture for Absorbing Recoil
US3243956A (en) Flexible support
US4854260A (en) Configuration of discharge tubes, ejection tubes or receptacles in submarines
US3124040A (en) Support system for tube launched
GB2219651A (en) A stand device for a mine.
US3089389A (en) Missile launcher
MX167187B (en) FRICTIONALLY CUSHIONED SUSPENSION SUPPORT
GB1447666A (en) Shock absorbers and suspension struts for vehicles
CA2504928A1 (en) Blast protection seat
US3167294A (en) Missile launcher shock absorber
US20130000477A1 (en) Vibration dampening firearm mount for vehicles
US3160061A (en) Tsoy k
US2415340A (en) Gun mount
US3438304A (en) Device for mounting a gun beneath the wing of an airplane
US3561679A (en) Collapsible nozzle for aircraft rocket motors
US3088374A (en) Inching and centering system
US6588707B1 (en) Device for suspending a payload in a launch vehicle
US4492143A (en) Anti-rotation mass support system particularly for missile support
US2728295A (en) Multiple grain rocket
US3433436A (en) Ball release mechanism
US2493788A (en) Resilient support for the firing control mechanism of a marine mine
US2404403A (en) Radio mounting structure