US3342104A - Guide tube magazine for carrying and launching airplane rocket-bombs - Google Patents

Guide tube magazine for carrying and launching airplane rocket-bombs Download PDF

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US3342104A
US3342104A US411817A US41181764A US3342104A US 3342104 A US3342104 A US 3342104A US 411817 A US411817 A US 411817A US 41181764 A US41181764 A US 41181764A US 3342104 A US3342104 A US 3342104A
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rocket
tube
bomb
magazine
bombs
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Robert Roger Aime
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    • 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
    • F41F3/06—Rocket or torpedo launchers for rockets from aircraft
    • F41F3/065—Rocket pods, i.e. detachable containers for launching a plurality of rockets

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  • GUIDE TUBE MAGAZINE FOR CARRYING AND LAUNCHING AIRPLANE ROCKET-BOMBS Filed Nov. 17, 1964 2 Sheets-Sheet 2 United States Patent 3,342,104 GUIDE TUBE MAGAZINE FOR CARRYING AND LAUNCHING AIRPLANE ROCKET-HOMES Roger Ann Robert, 33 Blvd. d hinder, Le Vesinet, France Filed Nov. 17, 1964, Ser. No. 411,817 Claims priority, application France, Oct. 22, 1964, 992,316, Patent 1,441,434 4 Claims. (Cl. 891.817)
  • the present invention relates to rocket-bomb carrying airplanes and, more particularly, to an arrangement of a guide-tube magazine for carrying and launching airplane rocket-bombs.
  • Fitting a high-speed airplane for carrying rocket-bombs raises many delicate and even unexpected problems.
  • Rocket-bombs are generally contained in tubes adapted to ensure the guidance thereof along the first portion of their trajectory, such tubes being assembled in a bunch or array located in a magazine arranged in the plane. It has been however established, for 'a long time, that in a tube-containing magazine of a fast-flying airplane, streamlined at the front where the guide tubes emerge, excessive heating is produced, during the high speeds of the plane, at the front end of the rocket-bomb, with the risk of a premature bursting of certain of the rocket-bombs.
  • the invention is intended to avoid, in a highly reliable manner, the bursting of a rocket-bomb contained in a guide-tube, without sealing the opening of the latter, but be only restricting the same peripherally by means of an annular diaphragm, transverse to the axis of the tube.
  • the annular diaphragm provided inside the tube is such that it does not offer any substantial resistance to the passage of the rocket-bomb at the instant 'of its launching.
  • the restriction peripheral rings or annular diaphragms are of a single piece which is adapted as a whole to the various guide-tubes of a magazine, so that the fitting of this single piece is sulficient to assure the improvement for all the guide tubes forming part of said magazine.
  • the central opening formed by the peripheral diaphragm is shaped as a polygon, thus facilitating at the passage of the rocket, the deformation of the diaphragm and reduces its resistance thereto.
  • FIGURE 1 is a general perspective view of an improved rocket-bomb magazine according to the invention, the various pieces of which are spaced apart for a better understanding of the drawing.
  • FIGURE 2 is a longitudinal cross-sectional view of part of a guide-tube for a rocket-bomb, comprising the restriction means according to the invention, in the position before the launching of the rocket-bomb.
  • FIGURE 3 is a view similar to that of FIGURE 2 at the instant of passage of the front portion of the launched rocket-bomb.
  • FIGURE 4 is a view similar to those in FIGURES 2 and 3, but after the passage of the rocket-bomb.
  • FIGURE 5 is a front view of the piece constituting the diaphragms of the various tubes.
  • the magazine 20 comprises a cylindrical body 21 containing a nest of guide tubes 22 for rocket-bombs 23.
  • the body 21 is extended, at the front portion thereof, by a stream-lined nose portion or cowl 24 of a conical, cylindroconical or ogival shape, tipped as at 25.
  • the tubes 22 emerge at the front wall 26 of body 21 along circular openings 27 the diameter of which is the same as that of the inner surface 28 of said tubes 22.
  • the nose 24 comprises channels 29 extending in corresponding relationship with the tubes 22, the outlets of said channels at the external surface 30 of nose 24 being constituted by more or less elliptical elongated curves 31.
  • partition 32 there is inserted between body 21 and nose 24 a partition 32 presenting holes 33 of the same number and the same arrangement as openings 27, but of a smaller diameter than the latter.
  • partition 32 When partition 32 is in position, there exists, in front of each one of the openings 27 of tube 22, a peripheral ring or annulus member 34 formed with a central opening 35 of a smaller diameter than opening 27; the insertion of said annular ring or diaphragm 34 between space 36 located in front of tube 22 and space 37 inside the latter, has proved of utmost importance for the nonheating of space 37 or, at least, for a substantially lesser degree of heating as compared to the case where there is a non-restricted communication between space 37 and channels 29.
  • each diaphragm 34 is of such material and/or of such shape that it offers little resistance to the passage of the rocket-bomb 23.
  • each diaphragm 34 has a slightly curved contour, with a portion 38, linked with the flat portion 39 of the partition, forming a smaler angle with the axis of the tube than the main internal portion 40 of said diaphragm.
  • FIGURE 3 illustrates the deforming of diaphragm 34 under the action of tip 41 of the rocket-bomb 23
  • FIGURE 4 shows the condition of said diaphragm after the passage of the rocket-bomb, the various parts thereof being applied against wall 42 limiting channel 29.
  • Partition 32 is simply made of a sheet of thin metal having a low mechanical resistance. Satisfactory results have been obtained, in the use of a magazine the guide tubes of which had an internal diameter of 70* mm., with diaphragms providing a central opening of a diameter of about 30 mm.
  • each diaphragm a central opening of a polygonal contour, for instance hexagonal or octagonal, facilitating in this way the breaking of the closure upon passage of the rocket-bomb.
  • FIGURE 5 there is shown a thin sheet piece 40, in the shape of a disk, wherein eighteen annular diaphragms 34 have been stamped out for the protection of eighteen tubes of a rocket-bomb magazine, the inner edge 41 of each one of said diaphragm been cut out in the form of an octagon.
  • Peripheral slots such as 42 and a central opening 43 assure the positioning of piece 49 and cooperate with the same being secured between body 21 and nose 24.
  • the rocket-bombs of certain magazines get overheated and may reach temperatures up to 200 C., i.e. a multiple of the temperature at rest, the temperatures found on rocket-bombs contained in the improved magazine according to the invention did not exceed 50 to 60 C.
  • a guide-tube magazine for carrying and launching airplane rocket-bombs, comprising a magazine body, a tapered nose portion mounted on the forward end of said magazine body, a plurality of guide tubes mounted in said magazine body, said tapered nose portion having channels with outlets on the external surface of the tapered nose, said channels being longitudinal aligned with each of said guide tubes, a transversal partition inserted between said body and said nose portion and formed with a plurality of openings coaxial, respectively, withsaid tubes and of a diameter smaller than the inner diameter thereof.
  • transversal partition comprises means for its angular positioning relative to said body and to said nose portion.
  • a guide-tube magazine for carrying and launching airplane rocket-bombs, comprising a magazine body, a tapered nose portion mounted on the forward end of said magazine body, a plurality of guide tubes mounted in said magazine body, said tapered nose portion having channels with outlets on the external surface of the tapered nose, said channels being longitudinally aligned with each of said guide tubes, an annular wall in each tube secured to the latter along its outer edge, saidannular Wall being positioned in the tube forwardly of the rocket-bomb located therein and spaced from the forward end of the rocket-bomb, said wall having a central opening smaller in diameter than that of the tube, and being operative to restrict heating of the rocket-bomb due to penetration of air at high speed within the channels of the tapered nose portion, said annular wall being deformable upon passage therethrough of the corresponding rocket-bomb in the tube.
  • annular wall has a domed shape with its convex side facing forwardly.

Description

Sept. 19, 1967 R. A. ROBERT GUIDE TUBE MAGAZINE FOR CARRYING AND LAUNCHIN AIRPLANE ROCKET-BOMBS 2 Sheets-Sheet 1 Filed Nov. 17, 1964 vsl Sept. 19, 1967 R. A. ROBERT 3,342,104
GUIDE TUBE MAGAZINE FOR CARRYING AND LAUNCHING AIRPLANE ROCKET-BOMBS Filed Nov. 17, 1964 2 Sheets-Sheet 2 United States Patent 3,342,104 GUIDE TUBE MAGAZINE FOR CARRYING AND LAUNCHING AIRPLANE ROCKET-HOMES Roger Ann Robert, 33 Blvd. dAngleterre, Le Vesinet, France Filed Nov. 17, 1964, Ser. No. 411,817 Claims priority, application France, Oct. 22, 1964, 992,316, Patent 1,441,434 4 Claims. (Cl. 891.817)
The present invention relates to rocket-bomb carrying airplanes and, more particularly, to an arrangement of a guide-tube magazine for carrying and launching airplane rocket-bombs.
Fitting a high-speed airplane for carrying rocket-bombs raises many delicate and even unexpected problems.
Rocket-bombs are generally contained in tubes adapted to ensure the guidance thereof along the first portion of their trajectory, such tubes being assembled in a bunch or array located in a magazine arranged in the plane. It has been however established, for 'a long time, that in a tube-containing magazine of a fast-flying airplane, streamlined at the front where the guide tubes emerge, excessive heating is produced, during the high speeds of the plane, at the front end of the rocket-bomb, with the risk of a premature bursting of certain of the rocket-bombs.
In order to obviate such a drawback, it was proposed to seal, by means of plugs, the front end of the guide tubes, so as to avoid the admission of the air at a high speed into said tubes during the flight of the airplane, a plug being thereafter ejected by the rocket itself when launched.
While some satisfactory devices have been constructed and utilized, the opinion prevails among technicians that, at least for certain forms of plugs, the possibility is not entirely excluded that, under certain particular circumstances, a plug might offer an excessive resistance to its being ejected, resulting in possible serious damage, and also that during the arming procedure of a rocket-launching apparatus, the operator in charge is liable to forget to seal one of the tubes of the apparatus, which would cause the corresponding rocket to be subjected to the action of the air penetrating at a great speed.
The invention is intended to avoid, in a highly reliable manner, the bursting of a rocket-bomb contained in a guide-tube, without sealing the opening of the latter, but be only restricting the same peripherally by means of an annular diaphragm, transverse to the axis of the tube.
Experience has shown that, surprisingly, while there still exists a free pneumatic communication between the inside of the tube and the outside space, the temperature of the front end of the rocket-bomb remains at a substantially lower value than that which was previously found in tubes not provided with such a restriction.
The following analysis of this phenomenon, which does not appear to have been formulated up to the present, but of which no advantage was taken, provides an explanation of this fact.
When a guide-tube of a rocket-bomb emerges at the slanted surface of the stream-lined profile, there is produced in the tube, in front of the rocket head, a vortex motion of the air due to a dissymmetry in the distribution of the pressures at the outlet of the tube, such as dissymmetry occurring always when the axis of the tube forms an angle-dilferent from zero-with the direction of the air stream. Such a phenomenon is similar to that occurring in the so-called vortex-tube, wherein the vortex is produced by a jet perpendicular to the axis of the tube.
Now, many research Works and tests have shown that in such a vortex motion, a thermal separation will take place between a peripheral flux of a high temperature and a central flux of a low temperature.
3,342,104 Patented Sept. 19, 1967 'ice By placing, according to the invention, a peripheral annular diaphragm in front of each rocket-bomb, the hot air of the peripheral flux is unable to come in contact with the rocket-bomb; only comparatively cool air from the center is able to pass.
This explanation is confirmed by the fact that, in a magazine with no stream-lined profile, with the tubes thereof opening therefore onto a front face perpendicular to their axes, the temperature elevation of the front ends of the rocket-bombs is found to be much lower.
The annular diaphragm provided inside the tube is such that it does not offer any substantial resistance to the passage of the rocket-bomb at the instant 'of its launching.
According to the invention, the restriction peripheral rings or annular diaphragms are of a single piece which is adapted as a whole to the various guide-tubes of a magazine, so that the fitting of this single piece is sulficient to assure the improvement for all the guide tubes forming part of said magazine.
According to an embodiment, the central opening formed by the peripheral diaphragm is shaped as a polygon, thus facilitating at the passage of the rocket, the deformation of the diaphragm and reduces its resistance thereto.
The invention will be best understood from the following description and appended drawings, wherein:
FIGURE 1 is a general perspective view of an improved rocket-bomb magazine according to the invention, the various pieces of which are spaced apart for a better understanding of the drawing.
FIGURE 2 is a longitudinal cross-sectional view of part of a guide-tube for a rocket-bomb, comprising the restriction means according to the invention, in the position before the launching of the rocket-bomb.
FIGURE 3 is a view similar to that of FIGURE 2 at the instant of passage of the front portion of the launched rocket-bomb.
FIGURE 4 is a view similar to those in FIGURES 2 and 3, but after the passage of the rocket-bomb.
FIGURE 5 is a front view of the piece constituting the diaphragms of the various tubes.
The magazine 20 comprises a cylindrical body 21 containing a nest of guide tubes 22 for rocket-bombs 23. The body 21 is extended, at the front portion thereof, by a stream-lined nose portion or cowl 24 of a conical, cylindroconical or ogival shape, tipped as at 25. The tubes 22 emerge at the front wall 26 of body 21 along circular openings 27 the diameter of which is the same as that of the inner surface 28 of said tubes 22. The nose 24 comprises channels 29 extending in corresponding relationship with the tubes 22, the outlets of said channels at the external surface 30 of nose 24 being constituted by more or less elliptical elongated curves 31.
In the illustrated embodiment described, there is inserted between body 21 and nose 24 a partition 32 presenting holes 33 of the same number and the same arrangement as openings 27, but of a smaller diameter than the latter. When partition 32 is in position, there exists, in front of each one of the openings 27 of tube 22, a peripheral ring or annulus member 34 formed with a central opening 35 of a smaller diameter than opening 27; the insertion of said annular ring or diaphragm 34 between space 36 located in front of tube 22 and space 37 inside the latter, has proved of utmost importance for the nonheating of space 37 or, at least, for a substantially lesser degree of heating as compared to the case where there is a non-restricted communication between space 37 and channels 29. Said ring or diaphragm 34 is of such material and/or of such shape that it offers little resistance to the passage of the rocket-bomb 23. In the illustrated embodiment, each diaphragm 34 has a slightly curved contour, with a portion 38, linked with the flat portion 39 of the partition, forming a smaler angle with the axis of the tube than the main internal portion 40 of said diaphragm.
FIGURE 3 illustrates the deforming of diaphragm 34 under the action of tip 41 of the rocket-bomb 23, and FIGURE 4 shows the condition of said diaphragm after the passage of the rocket-bomb, the various parts thereof being applied against wall 42 limiting channel 29.
Partition 32 is simply made of a sheet of thin metal having a low mechanical resistance. Satisfactory results have been obtained, in the use of a magazine the guide tubes of which had an internal diameter of 70* mm., with diaphragms providing a central opening of a diameter of about 30 mm.
The invention provides for each diaphragm a central opening of a polygonal contour, for instance hexagonal or octagonal, facilitating in this way the breaking of the closure upon passage of the rocket-bomb. In FIGURE 5, there is shown a thin sheet piece 40, in the shape of a disk, wherein eighteen annular diaphragms 34 have been stamped out for the protection of eighteen tubes of a rocket-bomb magazine, the inner edge 41 of each one of said diaphragm been cut out in the form of an octagon. Peripheral slots such as 42 and a central opening 43 assure the positioning of piece 49 and cooperate with the same being secured between body 21 and nose 24.
Whereas at the high subsonic speeds .8 M 1), the rocket-bombs of certain magazines get overheated and may reach temperatures up to 200 C., i.e. a multiple of the temperature at rest, the temperatures found on rocket-bombs contained in the improved magazine according to the invention did not exceed 50 to 60 C.
I claim:
1. In a guide-tube magazine for carrying and launching airplane rocket-bombs, comprising a magazine body, a tapered nose portion mounted on the forward end of said magazine body, a plurality of guide tubes mounted in said magazine body, said tapered nose portion having channels with outlets on the external surface of the tapered nose, said channels being longitudinal aligned with each of said guide tubes, a transversal partition inserted between said body and said nose portion and formed with a plurality of openings coaxial, respectively, withsaid tubes and of a diameter smaller than the inner diameter thereof.
2. A magazine according to claim 1, wherein said transversal partition comprises means for its angular positioning relative to said body and to said nose portion.
3. In a guide-tube magazine for carrying and launching airplane rocket-bombs, comprising a magazine body, a tapered nose portion mounted on the forward end of said magazine body, a plurality of guide tubes mounted in said magazine body, said tapered nose portion having channels with outlets on the external surface of the tapered nose, said channels being longitudinally aligned with each of said guide tubes, an annular wall in each tube secured to the latter along its outer edge, saidannular Wall being positioned in the tube forwardly of the rocket-bomb located therein and spaced from the forward end of the rocket-bomb, said wall having a central opening smaller in diameter than that of the tube, and being operative to restrict heating of the rocket-bomb due to penetration of air at high speed within the channels of the tapered nose portion, said annular wall being deformable upon passage therethrough of the corresponding rocket-bomb in the tube.
4. In a magazine as claimed in claim 3 wherein said annular wall has a domed shape with its convex side facing forwardly.
References Cited UNITED STATES PATENTS 245,363 8/1881 Ericsson 8931 3,137,231 6/ 196 4- I ohnson 102-34.4 3,199,40'6 8/1965 Gould 89--1.7
FOREIGN PATENTS 1,196,091 5/1959 France.
972,555 10 /1964 Great Britain.
SAMUEL W. ENGLE, Primary Examiner.
BENJAMIN A. BORCHELT, Examiner.

Claims (1)

  1. 3. IN A GUIDE-TUBE MAGAZINE FOR CARRYING AND LAUNCHING AIRPLANE ROCKET-BOMBS, COMPRISING A MAGAZINE BODY, A TAPERED NOSE PORTION MOUNTED ON THE FORWARD END OF SAID MAGAZINE BODY, A PLURALITY OF GUIDE TUBES MOUNTED IN SAID MAGAZINE BODY, SAID TAPERED NOSE POSITION HAVING CHANNELS WITH OUTLETS ON THE EXTERNAL SURFACE OF THE TAPERED NOSE, SAID CHANNELS BEING LONGITUDINALLY ALIGNED WITH EACH OF SAID GUIDE TUBES, AN ANNULAR WALL IN EACH TUBE SECURED TO THE LATTER ALONG ITS OUTER EDGE, SAID ANNULAR WALL BEING POSITIONED IN THE TUBE FORWARDLY OF THE ROCKET-BOMB LOCATED THEREIN AND SPACED FROM THE FORWARD END OF THE ROCKET-BOMB, SAID WALL HAVING A CENTRAL OPENING SMALLER IN DIAMETER THAN THAT OF THE TUBE, AND BEING OPERATIVE TO RESTRICT HETING OF THE ROCKET-BOMB DUE TO PENETRATION OF AIR AT HIGH SPEED WITHIN THE CHANNELS OF THE TAPERED NOSE PORTION, SAID ANNULAR WALL BEING DEFORMABLE UPON PASSAGE THERETHROUGH OF THE CORRESPONDING ROCKET-BOMB IN THE TUBE.
US411817A 1964-10-22 1964-11-17 Guide tube magazine for carrying and launching airplane rocket-bombs Expired - Lifetime US3342104A (en)

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FR992316A FR1441434A (en) 1964-10-22 1964-10-22 Advanced training in tube magazines for carrying and launching rocket bombs

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Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3456552A (en) * 1967-04-20 1969-07-22 Alsco Inc Rocket launcher fairings
US3500717A (en) * 1968-06-25 1970-03-17 Matra Engins Rocket-bomb magazine
US3719120A (en) * 1970-06-29 1973-03-06 Us Navy Rocket launching system
US3841197A (en) * 1972-12-13 1974-10-15 Us Air Force Foam structured rocket dispenser
US4635527A (en) * 1984-07-09 1987-01-13 Minister Of National Defence Of Her Majesty's Canadian Government Compact molded bulkhead for a tube-cluster rocket launcher
US5058481A (en) * 1990-10-15 1991-10-22 The United States Of America As Represented By The Secretary Of The Navy Dual modular rocket launcher
US20050204910A1 (en) * 2002-05-21 2005-09-22 Nir Padan System and method for enhancing the payload capacity, carriage efficiency, and adaptive flexibility of external stores mounted on an aerial vehicle
US20120055323A1 (en) * 2010-09-03 2012-03-08 Raytheon Company Systems and Methods for Launching Munitions
US8302524B2 (en) * 2008-12-02 2012-11-06 American Dynamics Flight Systems, Inc. Aerodynamic rotating launcher
US8635937B2 (en) 2010-09-03 2014-01-28 Raytheon Company Systems and methods for launching munitions
US9488438B1 (en) * 2014-11-17 2016-11-08 The United States Of America As Represented By The Secretary Of The Navy Small vehicle encapsulation for torpedo tube vehicle launch
US10240896B2 (en) 2015-03-12 2019-03-26 Raytheon Company Tube to bulkhead bonded joint design
USD956416S1 (en) * 2019-09-19 2022-07-05 Glenn Yench Projectile container

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3523443C1 (en) * 1985-06-29 1987-02-05 Messerschmitt Boelkow Blohm Cover for ammunition and firing containers for aircraft

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US245363A (en) * 1881-08-09 Nelius e
FR1196091A (en) * 1958-05-09 1959-11-20 Gen Aeronautique Marcel Dassau Rocket launcher device
US3137231A (en) * 1956-06-08 1964-06-16 Francis M Johnson Chaff dispenser system
GB972555A (en) * 1961-05-18 1964-10-14 French & Sons Thomas Improvements in or relating to rocket launchers
US3199406A (en) * 1961-06-21 1965-08-10 Mb Assoc In-line launching

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US245363A (en) * 1881-08-09 Nelius e
US3137231A (en) * 1956-06-08 1964-06-16 Francis M Johnson Chaff dispenser system
FR1196091A (en) * 1958-05-09 1959-11-20 Gen Aeronautique Marcel Dassau Rocket launcher device
GB972555A (en) * 1961-05-18 1964-10-14 French & Sons Thomas Improvements in or relating to rocket launchers
US3199406A (en) * 1961-06-21 1965-08-10 Mb Assoc In-line launching

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3456552A (en) * 1967-04-20 1969-07-22 Alsco Inc Rocket launcher fairings
US3500717A (en) * 1968-06-25 1970-03-17 Matra Engins Rocket-bomb magazine
US3719120A (en) * 1970-06-29 1973-03-06 Us Navy Rocket launching system
US3841197A (en) * 1972-12-13 1974-10-15 Us Air Force Foam structured rocket dispenser
US4635527A (en) * 1984-07-09 1987-01-13 Minister Of National Defence Of Her Majesty's Canadian Government Compact molded bulkhead for a tube-cluster rocket launcher
US5058481A (en) * 1990-10-15 1991-10-22 The United States Of America As Represented By The Secretary Of The Navy Dual modular rocket launcher
US20050204910A1 (en) * 2002-05-21 2005-09-22 Nir Padan System and method for enhancing the payload capacity, carriage efficiency, and adaptive flexibility of external stores mounted on an aerial vehicle
US7610841B2 (en) * 2002-05-21 2009-11-03 Nir Padan System and method for enhancing the payload capacity, carriage efficiency, and adaptive flexibility of external stores mounted on an aerial vehicle
US8302524B2 (en) * 2008-12-02 2012-11-06 American Dynamics Flight Systems, Inc. Aerodynamic rotating launcher
US20120055323A1 (en) * 2010-09-03 2012-03-08 Raytheon Company Systems and Methods for Launching Munitions
US8424439B2 (en) * 2010-09-03 2013-04-23 Raytheon Company Systems and methods for launching munitions
US8635937B2 (en) 2010-09-03 2014-01-28 Raytheon Company Systems and methods for launching munitions
US9488438B1 (en) * 2014-11-17 2016-11-08 The United States Of America As Represented By The Secretary Of The Navy Small vehicle encapsulation for torpedo tube vehicle launch
US10240896B2 (en) 2015-03-12 2019-03-26 Raytheon Company Tube to bulkhead bonded joint design
USD956416S1 (en) * 2019-09-19 2022-07-05 Glenn Yench Projectile container

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BE671128A (en) 1966-04-20
FR1441434A (en) 1966-06-10
DE1428641A1 (en) 1968-11-28
GB1028379A (en) 1966-05-04

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